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  • Aircraft Propulsion and Power
  • Limnology
  • General Chemistry
  • Cell & Developmental Biology
  • 2010-2014  (49)
  • 1945-1949  (95)
  • 2011  (49)
  • 1946  (95)
  • 1
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    Late Pleistocene-Holocene chemical stratigraphy and paleolimnology of the Rift Valley lakes of central Africa (2011)
    Woods Hole Oceanographic Institution
    Details
    Publication Date: 2022-05-26
    Description: The interaction of climate and geology in Central Africa during Late Pleistocene and Holocene is examined. The study is based on sedimentological and limnological work on the main lakes of the Western Branch of the East African Rift Valley, particularly Lake Kivu, Changes in sediment chemistry, mineralogy and diatom assemblage provide a detailed histogram of lake level oscillations. Calculations indicate that the drop in lake level could be as high as 600 m for Tanganyika and 400 m for Kivu, Fluctuations in water levels.are the means for reconstruction of climatic events in tropical Africa of the last 15,000 years. Paleoclimatic comparison between tropical and temperate zones reveals that pluvial times coincide with the prominent interstadials in Europe, e.g. Bølling, Allerød, Climatic Optimum, and reversely, cool and dry periods in equatorial Africa with ice ages in the Northern Hemisphere. The African climatic sequence of pluvials and interpluvials is accompanied by corresponding periods of hydrothermal activity and quiescence. This may suggest that rain water exercises control on hydrothermal. activities.
    Description: Prepared for the National Science Foundation under Grants GA-30641 and GA-35334.
    Keywords: Paleoclimatology ; Limnology
    Repository Name: Woods Hole Open Access Server
    Type: Technical Report
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  • 2
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    A Risk Management Architecture for Emergency Integrated Aircraft Control (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: Enhanced engine operation--operation that is beyond normal limits--has the potential to improve the adaptability and safety of aircraft in emergency situations. Intelligent use of enhanced engine operation to improve the handling qualities of the aircraft requires sophisticated risk estimation techniques and a risk management system that spans the flight and propulsion controllers. In this paper, an architecture that weighs the risks of the emergency and of possible engine performance enhancements to reduce overall risk to the aircraft is described. Two examples of emergency situations are presented to demonstrate the interaction between the flight and propulsion controllers to facilitate the enhanced operation.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217143 , AIAA Paper 2011-1568 , E-17880 , Infotech at Aerospace 2011 Conference; 29-31 Mr. 2011; St. Louis, MO; United States
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  • 3
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    Development of an Open Rotor Cycle Model in NPSS Using a Multi-Design Point Approach (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA's Environmentally Responsible Aviation Project and Subsonic Fixed Wing Project are focused on developing concepts and technologies which may enable dramatic reductions to the environmental impact of future generation subsonic aircraft (Refs. 1 and 2). The open rotor concept (also referred to as the Unducted Fan or advanced turboprop) may allow the achievement of this objective by reducing engine emissions and fuel consumption. To evaluate its potential impact, an open rotor cycle modeling capability is needed. This paper presents the initial development of an open rotor cycle model in the Numerical Propulsion System Simulation (NPSS) computer program which can then be used to evaluate the potential benefit of this engine. The development of this open rotor model necessitated addressing two modeling needs within NPSS. First, a method for evaluating the performance of counter-rotating propellers was needed. Therefore, a new counter-rotating propeller NPSS component was created. This component uses propeller performance maps developed from historic counter-rotating propeller experiments to determine the thrust delivered and power required. Second, several methods for modeling a counter-rotating power turbine within NPSS were explored. These techniques used several combinations of turbine components within NPSS to provide the necessary power to the propellers. Ultimately, a single turbine component with a conventional turbine map was selected. Using these modeling enhancements, an open rotor cycle model was developed in NPSS using a multi-design point approach. The multi-design point (MDP) approach improves the engine cycle analysis process by making it easier to properly size the engine to meet a variety of thrust targets throughout the flight envelope. A number of design points are considered including an aerodynamic design point, sea-level static, takeoff and top of climb. The development of this MDP model was also enabled by the selection of a simple power management scheme which schedules propeller blade angles with the freestream Mach number. Finally, sample open rotor performance results and areas for further model improvements are presented.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217225 , GT2011-46694 , E-17908 , Turbo Expo 2011; Jun 06, 2011 - Jun 10, 2011; Vancouver, BC; Canada
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  • 4
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    Assessment of Some Atomization Models Used in Spray Calculations (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The paper presents the results from a validation study undertaken as a part of the NASA s fundamental aeronautics initiative on high altitude emissions in order to assess the accuracy of several atomization models used in both non-superheat and superheat spray calculations. As a part of this investigation we have undertaken the validation based on four different cases to investigate the spray characteristics of (1) a flashing jet generated by the sudden release of pressurized R134A from cylindrical nozzle, (2) a liquid jet atomizing in a subsonic cross flow, (3) a Parker-Hannifin pressure swirl atomizer, and (4) a single-element Lean Direct Injector (LDI) combustor experiment. These cases were chosen because of their importance in some aerospace applications. The validation is based on some 3D and axisymmetric calculations involving both reacting and non-reacting sprays. In general, the predicted results provide reasonable agreement for both mean droplet sizes (D32) and average droplet velocities but mostly underestimate the droplets sizes in the inner radial region of a cylindrical jet.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217029 , E-17694 , International Conference on Computational and Experimental Engineering and Sciences (ICCES 2011); Apr 18, 2011 - Apr 21, 2011; Nanjing; China
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  • 5
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    Rotating Arc Jet Test Model: Time-Accurate Trajectory Heat Flux Replication in a Ground Test Environment (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Though arc jet testing has been the proven method employed for development testing and certification of TPS and TPS instrumentation, the operational aspects of arc jets limit testing to selected, but constant, conditions. Flight, on the other hand, produces timevarying entry conditions in which the heat flux increases, peaks, and recedes as a vehicle descends through an atmosphere. As a result, we are unable to "test as we fly." Attempts to replicate the time-dependent aerothermal environment of atmospheric entry by varying the arc jet facility operating conditions during a test have proven to be difficult, expensive, and only partially successful. A promising alternative is to rotate the test model exposed to a constant-condition arc jet flow to yield a time-varying test condition at a point on a test article (Fig. 1). The model shape and rotation rate can be engineered so that the heat flux at a point on the model replicates the predicted profile for a particular point on a flight vehicle. This simple concept will enable, for example, calibration of the TPS sensors on the Mars Science Laboratory (MSL) aeroshell for anticipated flight environments.
    Keywords: Aircraft Propulsion and Power
    Type: ARC-E-DAA-TN3214 , 8th International Planetary Probe Workshop (IPPW-8); Jun 06, 2011 - Jun 10, 2011; Portsmouth, VA; United States
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  • 6
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    Engine Icing Modeling and Simulation (Part 2): Performance Simulation of Engine Rollback Phenomena (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Ice buildup in the compressor section of a commercial aircraft gas turbine engine can cause a number of engine failures. One of these failure modes is known as engine rollback: an uncommanded decrease in thrust accompanied by a decrease in fan speed and an increase in turbine temperature. This paper describes the development of a model which simulates the system level impact of engine icing using the Commercial Modular Aero-Propulsion System Simulation 40k (C-MAPSS40k). When an ice blockage is added to C-MAPSS40k, the control system responds in a manner similar to that of an actual engine, and, in cases with severe blockage, an engine rollback is observed. Using this capability to simulate engine rollback, a proof-of-concept detection scheme is developed and tested using only typical engine sensors. This paper concludes that the engine control system s limit protection is the proximate cause of iced engine rollback and that the controller can detect the buildup of ice particles in the compressor section. This work serves as a feasibility study for continued research into the detection and mitigation of engine rollback using the propulsion control system.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217200 , 11ICE-0081/2011-38-0026 , E-17885 , International Conference on Aircraft and Engine Icing and Ground Deicing; Jun 13, 2011 - Jun 17, 2011; Chicago, IL; United States
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  • 7
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    Exhaust Nozzle Plume Effects on Sonic Boom Test Results for Isolated Nozzles (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Reducing or eliminating the operational restrictions of supersonic aircraft over populated areas has led to extensive research at NASA. Restrictions were due to the disturbance of the sonic boom, caused by the coalescence of shock waves formed off the aircraft. Recent work has been performed to reduce the magnitude of the sonic boom N-wave generated by airplane components with focus on shock waves caused by the exhaust nozzle plume. Previous Computational Fluid Dynamics (CFD) analysis showed how the shock wave formed at the nozzle lip interacts with the nozzle boat-tail expansion wave. An experiment was conducted in the 1- by 1-ft Supersonic Wind Tunnel at the NASA Glenn Research Center to validate the computational study. Results demonstrated how the nozzle lip shock moved with increasing nozzle pressure ratio (NPR) and reduced the nozzle boat-tail expansion, causing a favorable change in the observed pressure signature. Experimental results were presented for comparison to the CFD results. The strong nozzle lip shock at high values of NPR intersected the nozzle boat-tail expansion and suppressed the expansion wave. Based on these results, it may be feasible to reduce the boat-tail expansion for a future supersonic aircraft with under-expanded nozzle exhaust flow by modifying nozzle pressure or nozzle divergent section geometry.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217137 , AIAA Paper 2010-4936 , E-17430 , 28th Applied Aerodynamics Conference; Jun 28, 2010 - Jul 01, 2010; Chicago, IL; United States
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  • 8
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    Full-Scale Turbofan-Engine Turbine-Transfer Function Determination Using Three Internal Sensors (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Existing NASA/Honeywell EVNERT full-scale static engine test data is analyzed by using source-separation techniques in order to determine the turbine transfer of the currently sub-dominant combustor noise. The results are used to assess the combustor-noise prediction capability of the Aircraft Noise Prediction Program (ANOPP). Time-series data from three sensors internal to the Honeywell TECH977 research engine is used in the analysis. The true combustor-noise turbine-transfer function is educed by utilizing a new three-signal approach. The resulting narrowband gain factors are compared with the corresponding constant values obtained from two empirical acoustic-turbine-loss formulas. It is found that a simplified Pratt & Whitney formula agrees better with the experimental results for frequencies of practical importance. The 130 deg downstream-direction far-field 1/3-octave sound-pressure levels (SPL) results of Hultgren & Miles are reexamined using a post-correction of their ANOPP predictions for both the total noise signature and the combustion-noise component. It is found that replacing the standard ANOPP turbine-attenuation function for combustion noise with the simplified Pratt & Whitney formula clearly improves the predictions. It is recommended that the GECOR combustion-noise module in ANOPP be updated to allow for a user-selectable switch between the current transmission-loss model and the simplified Pratt & Whitney formula. The NASA Fundamental Aeronautics Program has the principal objective of overcoming today's national challenges in air transportation. The Subsonic Fixed Wing Project's Reduce-Perceived-Noise Technical Challenge aims to develop concepts and technologies to dramatically reduce the perceived aircraft noise outside of airport boundaries. The reduction of aircraft noise is critical to enabling the anticipated large increase in future air traffic.
    Keywords: Aircraft Propulsion and Power
    Type: AIAA Paper-2011-2912 , E-18007-1 , 17th AIAA/CEAS Aeroacoustics Conferences; Jun 05, 2011 - Jun 08, 2011; Portland, OR; United States
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  • 9
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    Annular MHD Physics for Turbojet Energy Bypass (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The use of annular Hall type MHD generator/accelerator ducts for turbojet energy bypass is evaluated assuming weakly ionized flows obtained from pulsed nanosecond discharges. The equations for a 1-D, axisymmetric MHD generator/accelerator are derived and numerically integrated to determine the generator/accelerator performance characteristics. The concept offers a shockless means of interacting with high speed inlet flows and potentially offers variable inlet geometry performance without the complexity of moving parts simply by varying the generator loading parameter. The cycle analysis conducted iteratively with a spike inlet and turbojet flying at M = 7 at 30 km altitude is estimated to have a positive thrust per unit mass flow of 185 N-s/kg. The turbojet allowable combustor temperature is set at an aggressive 2200 deg K. The annular MHD Hall generator/accelerator is L = 3 m in length with a B(sub r) = 5 Tesla magnetic field and a conductivity of sigma = 5 mho/m for the generator and sigma= 1.0 mho/m for the accelerator. The calculated isentropic efficiency for the generator is eta(sub sg) = 84 percent at an enthalpy extraction ratio, eta(sub Ng) = 0.63. The calculated isentropic efficiency for the accelerator is eta(sub sa) = 81 percent at an enthalpy addition ratio, eta(sub Na) = 0.62. An assessment of the ionization fraction necessary to achieve a conductivity of sigma = 1.0 mho/m is n(sub e)/n = 1.90 X 10(exp -6), and for sigma = 5.0 mho/m is n(sub e)/n = 9.52 X 10(exp -6).
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217210 , AIAA Paper-2011-2230 , E-17889 , 17th AIAA International Space Planes and Hypersonics Systems Conference; Apr 11, 2011 - Apr 14, 2011; San Francisco, CA; United States
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  • 10
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    Can Water-Injected Turbomachines Provide Cost-Effective Emissions and Maintenance Reductions? (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An investigation has been performed to evaluate the effect of water injection on the performance of the Air Force Research Laboratory (AFRL, Wright-Patterson Air Force Base (WPAFB)) experimental trapped vortex combustor (TVC) over a range of fuel-to-air and water-to-fuel ratios. Performance is characterized by combustor exit quantities: temperature and emissions measurements using rakes, and overall pressure drop, from upstream plenum to combustor exit. Combustor visualization is performed using gray-scale and color still photographs and high-frame-rate videos. A parallel investigation evaluated the performance of a computational fluid dynamics (CFD) tool for the prediction of the reacting flow in a liquid fueled combustor (e.g., TVC) that uses water injection for control of pollutant emissions and turbine inlet temperature. Generally, reasonable agreement is found between data and NO(x) computations. Based on a study assessing the feasibility and performance impact of using water injection on a Boeing 747-400 aircraft to reduce NO(x) emissions during takeoff, retrofitting does not appear to be cost effective; however, an operator of a newly designed engine and airframe might be able to save up to 1.0 percent in operating costs. Other challenges of water injection will be discussed.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-214039 , 141-ISROMAC-11 , E-15396-2 , 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery; Feb 26, 2006 - Mar 02, 2006; Honolulu, HI; United States
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  • 11
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    Compliant Turbomachine Sealing (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Sealing interface materials and coatings are sacrificial, giving up their integrity for the benefit of the component. Seals that are compliant while still controlling leakage, dynamics, and coolant flows are sought to enhance turbomachine performance. Herein we investigate the leaf-seal configuration. While the leaf seal is classified as contacting, a ready modification using the leaf-housing arrangement in conjunction with an interface film rider (a bore seal, for example) provides for a film-riding noncontact seal. The leaf housing and leaf elements can be made from a variety of materials from plastic to ceramic. Four simplistic models are used to identify the physics essential to controlling leakage. Corroborated by CFD, these results provide design parameters for applications to within reasonable engineering certainty. Some potential improvements are proposed.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-214040 , 54-ISROMAC-11 , E-15397-2 , 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery; Feb 26, 2006 - Mar 02, 2006; Honolulu, HI; United States
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  • 12
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    Improving Engine Efficiency Through Core Developments (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASA Environmentally Responsible Aviation (ERA) Project and Fundamental Aeronautics Projects are supporting compressor and turbine research with the goal of reducing aircraft engine fuel burn and greenhouse gas emissions. The primary goals of this work are to increase aircraft propulsion system fuel efficiency for a given mission by increasing the overall pressure ratio (OPR) of the engine while maintaining or improving aerodynamic efficiency of these components. An additional area of work involves reducing the amount of cooling air required to cool the turbine blades while increasing the turbine inlet temperature. This is complicated by the fact that the cooling air is becoming hotter due to the increases in OPR. Various methods are being investigated to achieve these goals, ranging from improved compressor three-dimensional blade designs to improved turbine cooling hole shapes and methods. Finally, a complementary effort in improving the accuracy, range, and speed of computational fluid mechanics (CFD) methods is proceeding to better capture the physical mechanisms underlying all these problems, for the purpose of improving understanding and future designs.
    Keywords: Aircraft Propulsion and Power
    Type: E-17721 , 49th AIAA Aero Sciences Meeting; Jan 04, 2011 - Jan 07, 2011; Orlando, FL; United States
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  • 13
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    Overview of CMC Research at NASA Glenn Research Center (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: CMC technology development in the Ceramics Branch at NASA Glenn Research Center addresses Aeronautics propulsion goals across subsonic, supersonic and hypersonic flight regimes. Combustor, turbine and exhaust nozzle applications of CMC materials will enable NASA to demonstrate reduced fuel consumption, emissions, and noise in advanced gas turbine engines. Applications ranging from basic Fundamental Aeronautics research activities to technology demonstrations in the new Integrated Systems Research Program will be discussed.
    Keywords: Aircraft Propulsion and Power
    Type: E-17719 , 35th Annual Conference on Composites, Materials and Structures; Jan 24, 2011 - Jan 27, 2011; Cape Canaveral, FL; United States
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  • 14
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    Turboelectric Distributed Propulsion in a Hybrid Wing Body Aircraft (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The performance of the N3-X, a 300 passenger hybrid wing body (HWB) aircraft with turboelectric distributed propulsion (TeDP), has been analyzed to see if it can meet the 70% fuel burn reduction goal of the NASA Subsonic Fixed Wing project for N+3 generation aircraft. The TeDP system utilizes superconducting electric generators, motors and transmission lines to allow the power producing and thrust producing portions of the system to be widely separated. It also allows a small number of large turboshaft engines to drive any number of propulsors. On the N3-X these new degrees of freedom were used to (1) place two large turboshaft engines driving generators in freestream conditions to maximize thermal efficiency and (2) to embed a broad continuous array of 15 motor driven propulsors on the upper surface of the aircraft near the trailing edge. That location maximizes the amount of the boundary layer ingested and thus maximizes propulsive efficiency. The Boeing B777-200LR flying 7500 nm (13890 km) with a cruise speed of Mach 0.84 and an 118100 lb payload was selected as the reference aircraft and mission for this study. In order to distinguish between improvements due to technology and aircraft configuration changes from those due to the propulsion configuration changes, an intermediate configuration was included in this study. In this configuration a pylon mounted, ultra high bypass (UHB) geared turbofan engine with identical propulsion technology was integrated into the same hybrid wing body airframe. That aircraft achieved a 52% reduction in mission fuel burn relative to the reference aircraft. The N3-X was able to achieve a reduction of 70% and 72% (depending on the cooling system) relative to the reference aircraft. The additional 18% - 20% reduction in the mission fuel burn can therefore be attributed to the additional degrees of freedom in the propulsion system configuration afforded by the TeDP system that eliminates nacelle and pylon drag, maximizes boundary layer ingestion (BLI) to reduce inlet drag on the propulsion system, and reduces the wake drag of the vehicle.
    Keywords: Aircraft Propulsion and Power
    Type: ISABE-2011-1340 , E-18064 , 20th International Society for Airbreathing Engines (ISABE 2011); Sep 12, 2011 - Sep 16, 2011; Gothenburg; Sweden
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  • 15
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    Overview of ERA Ultra High Bypass Propulsor Technology Development (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A review of the current research being conducted under the Environmentally Responsible Aviation (ERA) Ultra High Bypass (UHB) Testing subelement is presented. The four exiting tasks under the subelement, a description of each task, and the current status of each are given. The four tasks are: 1. Collaborate with P&W to design, fabricate and test a second generation of Geared Turbofan 2. Design, fabricate and test advanced Over the Rotor acoustic treatment and acoustically treated Soft Vanes 3. Develop a Shape Memory Alloy Variable Area Nozzle concept and demonstrate prototype 4. Refurbish and update the GRC Ultra High Bypass Drive Rig Following the current task updates, an overview of three proposed additional tasks to support the existing tasks is presented. The additional tasks would allow noise reduction and noise diagnostic testing technologies to be demonstrated at TRL 4 as part of existing planned fan model testing in the NASA Glenn 9 x15 Low Speed Wind Tunnel under the ERA UHB Testing subelement.
    Keywords: Aircraft Propulsion and Power
    Type: E-17844 , Acoustics Technical Working Group Meeting; Apr 21, 2011 - Apr 22, 2011; Cleveland, OH; United States
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  • 16
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    A Plan for Revolutionary Change in Gas Turbine Engine Control System Architecture (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The implementation of Distributed Engine Control technology on the gas turbine engine has been a vexing challenge for the controls community. A successful implementation requires the resolution of multiple technical issues in areas such as network communications, power distribution, and system integration, but especially in the area of high temperature electronics. Impeding the achievement has been the lack of a clearly articulated message about the importance of the distributed control technology to future turbine engine system goals and objectives. To resolve these issues and bring the technology to fruition has, and will continue to require, a broad coalition of resources from government, industry, and academia. This presentation will describe the broad challenges facing the next generation of advanced control systems and the plan which is being put into action to successfully implement the technology on the next generation of gas turbine engine systems.
    Keywords: Aircraft Propulsion and Power
    Type: E-17833 , A Plan for Revolutionary Change in Gas Turbine Engine Control System Architecture; Apr 18, 2011; Columbus, OH; United States
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  • 17
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    Laser-Based Diagnostic Measurements of Low Emissions Combustor Concepts (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This presentation provides a summary of primarily laser-based measurement techniques we use at NASA Glenn Research Center to characterize fuel injection, fuel/air mixing, and combustion. The report highlights using Planar Laser-Induced Fluorescence, Particle Image Velocimetry, and Phase Doppler Interferometry to obtain fuel injector patternation, fuel and air velocities, and fuel drop sizes and turbulence intensities during combustion. We also present a brief comparison between combustors burning standard JP-8 Jet fuel and an alternative fuels. For this comparison, we used flame chemiluminescence and high speed imaging.
    Keywords: Aircraft Propulsion and Power
    Type: E-17841 , NASA Fundamental Aeronautics Program 2011 Technical Conference; Mar 15, 2011 - Mar 17, 2011; Cleveland, OH; United States
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  • 18
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    Implementation of Enhanced Propulsion Control Modes for Emergency Flight Operation (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Aircraft engines can be effective actuators to help pilots avert or recover from emergency situations. Emergency control modes are being developed to enhance the engines performance to increase the probability of recovery under these circumstances. This paper discusses a proposed implementation of an architecture that requests emergency propulsion control modes, allowing the engines to deliver additional performance in emergency situations while still ensuring a specified safety level. In order to determine the appropriate level of engine performance enhancement, information regarding the current emergency scenario (including severity) and current engine health must be known. This enables the engine to operate beyond its nominal range while minimizing overall risk to the aircraft. In this architecture, the flight controller is responsible for determining the severity of the event and the level of engine risk that is acceptable, while the engine controller is responsible for delivering the desired performance within the specified risk range. A control mode selector specifies an appropriate situation-specific enhanced mode, which the engine controller then implements. The enhanced control modes described in this paper provide additional engine thrust or response capabilities through the modification of gains, limits, and the control algorithm, but increase the risk of engine failure. The modifications made to the engine controller to enable the use of the enhanced control modes are described, as are the interaction between the various subsystems and importantly, the interaction between the flight controller/pilot and the propulsion control system. Simulation results demonstrate how the system responds to requests for enhanced operation and the corresponding increase in performance.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217038 , AIAA Paper 2011-1590 , E-17744 , Infotech@Aerospace 2011 Conference; Mar 29, 2011 - Mar 31, 2011; Saint Louis, MO; United States
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  • 19
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    A Technology Pathway for Airbreathing, Combined-Cycle, Horizontal Space Launch Through SR-71 Based Trajectory Modeling (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Access to space is in the early stages of commercialization. Private enterprises, mainly under direct or indirect subsidy by the government, have been making headway into the LEO launch systems infrastructure, of small-weight-class payloads of approximately 1000 lbs. These moderate gains have emboldened the launch industry and they are poised to move into the middle-weight class (roughly 5000 lbs). These commercially successful systems are based on relatively straightforward LOX-RP, two-stage, bi-propellant rocket technology developed by the government 40 years ago, accompanied by many technology improvements. In this paper we examine a known generic LOX-RP system with the focus on the booster stage (1st stage). The booster stage is then compared to modeled Rocket-Based and Turbine-Based Combined Cycle booster stages. The air-breathing propulsion stages are based on/or extrapolated from known performance parameters of ground tested RBCC (the Marquardt Ejector Ramjet) and TBCC (the SR-71/J-58 engine) data. Validated engine models using GECAT and SCCREAM are coupled with trajectory optimization and analysis in POST-II to explore viable launch scenarios using hypothetical aerospaceplane platform obeying the aerodynamic model of the SR-71. Finally, and assessment is made of the requisite research technology advances necessary for successful commercial and government adoption of combined-cycle engine systems for space access.
    Keywords: Aircraft Propulsion and Power
    Type: DFRC-E-DAA-TN3255 , DFRC-E-DAA-TN3352 , DFRC-E-DAA-TN3351 , 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference; Apr 11, 2011 - Apr 14, 2011; San Francisco, CA; United States
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  • 20
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    Combustion Dynamics and Control for Ultra Low Emissions in Aircraft Gas-Turbine Engines (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Future aircraft engines must provide ultra-low emissions and high efficiency at low cost while maintaining the reliability and operability of present day engines. The demands for increased performance and decreased emissions have resulted in advanced combustor designs that are critically dependent on efficient fuel/air mixing and lean operation. However, all combustors, but most notably lean-burning low-emissions combustors, are susceptible to combustion instabilities. These instabilities are typically caused by the interaction of the fluctuating heat release of the combustion process with naturally occurring acoustic resonances. These interactions can produce large pressure oscillations within the combustor and can reduce component life and potentially lead to premature mechanical failures. Active Combustion Control which consists of feedback-based control of the fuel-air mixing process can provide an approach to achieving acceptable combustor dynamic behavior while minimizing emissions, and thus can provide flexibility during the combustor design process. The NASA Glenn Active Combustion Control Technology activity aims to demonstrate active control in a realistic environment relevant to aircraft engines by providing experiments tied to aircraft gas turbine combustors. The intent is to allow the technology maturity of active combustion control to advance to eventual demonstration in an engine environment. Work at NASA Glenn has shown that active combustion control, utilizing advanced algorithms working through high frequency fuel actuation, can effectively suppress instabilities in a combustor which emulates the instabilities found in an aircraft gas turbine engine. Current efforts are aimed at extending these active control technologies to advanced ultra-low-emissions combustors such as those employing multi-point lean direct injection.
    Keywords: Aircraft Propulsion and Power
    Type: E-17835
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    Review of Propulsion Technologies for N+3 Subsonic Vehicle Concepts (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: NASA has set aggressive fuel burn, noise, and emission reduction goals for a new generation (N+3) of aircraft targeting concepts that could be viable in the 2035 timeframe. Several N+3 concepts have been formulated, where the term "N+3" indicate aircraft three generations later than current state-of-the-art aircraft, "N". Dramatic improvements need to be made in the airframe, propulsion systems, mission design, and the air transportation system in order to meet these N+3 goals. The propulsion system is a key element to achieving these goals due to its major role with reducing emissions, fuel burn, and noise. This report provides an in-depth description and assessment of propulsion systems and technologies considered in the N+3 subsonic vehicle concepts. Recommendations for technologies that merit further research and development are presented based upon their impact on the N+3 goals and likelihood of being operational by 2035.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217239 , E-17995
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    The NASA Subsonic Jet Particle Image Velocimetry (PIV) Dataset (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Many tasks in fluids engineering require prediction of turbulence of jet flows. The present document documents the single-point statistics of velocity, mean and variance, of cold and hot jet flows. The jet velocities ranged from 0.5 to 1.4 times the ambient speed of sound, and temperatures ranged from unheated to static temperature ratio 2.7. Further, the report assesses the accuracies of the data, e.g., establish uncertainties for the data. This paper covers the following five tasks: (1) Document acquisition and processing procedures used to create the particle image velocimetry (PIV) datasets. (2) Compare PIV data with hotwire and laser Doppler velocimetry (LDV) data published in the open literature. (3) Compare different datasets acquired at the same flow conditions in multiple tests to establish uncertainties. (4) Create a consensus dataset for a range of hot jet flows, including uncertainty bands. (5) Analyze this consensus dataset for self-consistency and compare jet characteristics to those of the open literature. The final objective was fulfilled by using the potential core length and the spread rate of the half-velocity radius to collapse of the mean and turbulent velocity fields over the first 20 jet diameters.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-216807 , E-17439
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    Reduction of Altitude Diffuser Jet Noise Using Water Injection (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A feasibility study on the effects of injecting water into the exhaust plume of an altitude rocket diffuser for the purpose of reducing the far-field acoustic noise has been performed. Water injection design parameters such as axial placement, angle of injection, diameter of injectors, and mass flow rate of water have been systematically varied during the operation of a subscale altitude test facility. The changes in acoustic far-field noise were measured with an array of free-field microphones in order to quantify the effects of the water injection on overall sound pressure level spectra and directivity. The results showed significant reductions in noise levels were possible with optimum conditions corresponding to water injection at or just upstream of the exit plane of the diffuser. Increasing the angle and mass flow rate of water injection also showed improvements in noise reduction. However, a limit on the maximum water flow rate existed as too large of flow rate could result in un-starting the supersonic diffuser.
    Keywords: Aircraft Propulsion and Power
    Type: SSTI-8080-0056
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    Commercial Modular Aero-Propulsion System Simulation 40k (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The Commercial Modular Aero-Propulsion System Simulation 40k (CMAPSS40k) software package is a nonlinear dynamic simulation of a 40,000-pound (approximately equals 178-kN) thrust class commercial turbofan engine, written in the MATLAB/Simulink environment. The model has been tuned to capture the behavior of flight test data, and is capable of running at any point in the flight envelope [up to 40,000 ft (approximately equals 12,200 m) and Mach 0.8]. In addition to the open-loop engine, the simulation includes a controller whose architecture is representative of that found in industry. C-MAPSS40k fills the need for an easy-to-use, realistic, transient simulation of a medium-size commercial turbofan engine with a representative controller. It is a detailed component level model (CLM) written in the industry-standard graphical MATLAB/Simulink environment to allow for easy modification and portability. At the time of this reporting, no other such model exists in the public domain.
    Keywords: Aircraft Propulsion and Power
    Type: LEW-18624-1 , NASA Tech Briefs, September 2011; 36-37
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    Levitated Duct Fan (LDF) Aircraft Auxiliary Generator (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This generator concept includes a novel stator and rotor architecture made from composite material with blades attached to the outer rotating shell of a ducted fan drum rotor, a non-contact support system between the stator and rotor using magnetic fields to provide levitation, and an integrated electromagnetic generation system. The magnetic suspension between the rotor and the stator suspends and supports the rotor within the stator housing using permanent magnets attached to the outer circumference of the drum rotor and passive levitation coils in the stator shell. The magnets are arranged in a Halbach array configuration.
    Keywords: Aircraft Propulsion and Power
    Type: LEW-18658-1 , NASA Tech Briefs, September 2011; 21-22
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    Radiation-Spray Coupling for Realistic Flow Configurations (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Three Large Eddy Simulations (LES) for a lean-direct injection (LDI) combustor are performed and compared. In addition to the cold flow simulation, the effect of radiation coupling with the multi-physics reactive flow is analyzed. The flame let progress variable approach is used as a subgrid combustion model combined with a stochastic subgrid model for spray atomization and an optically thin radiation model. For accurate chemistry modeling, a detailed Jet-A surrogate mechanism is utilized. To achieve realistic inflow, a simple recycling technique is performed at the inflow section upstream of the swirler. Good comparison is shown with the experimental data mean and root mean square profiles. The effect of combustion is found to change the shape and size of the central recirculation zone. Radiation is found to change the spray dynamics and atomization by changing the heat release distribution and the local temperature values impacting the evaporation process. The simulation with radiation modeling shows wider range of droplet size distribution by altering the evaporation rate. The current study proves the importance of radiation modeling for accurate prediction in realistic spray combustion configurations, even for low pressure systems.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217111 , E-17787
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    Factors Influencing Dwell Fatigue Cracking in Notches of Powder Metallurgy Superalloys (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The influences of heat treatment and cyclic dwells on the notch fatigue resistance of powder metallurgy disk superalloys were investigated for low solvus high refractory (LSHR) and ME3 disk alloys. Disks were processed to produce material conditions with varied microstructures and associated mechanical properties. Notched specimens were first subjected to baseline dwell fatigue cycles having a dwell at maximum load, as well as tensile, stress relaxation, creep rupture, and dwell fatigue crack growth tests at 704 C. Several material heat treatments displayed a bimodal distribution of fatigue life with the lives varying by two orders-of-magnitude, while others had more consistent fatigue lives. This response was compared to other mechanical properties, in search of correlations. The wide scatter in baseline dwell fatigue life was observed only for material conditions resistant to stress relaxation. For selected materials and conditions, additional tests were then performed with the dwells shifted in part or in total to minimum tensile load. The tests performed with dwells at minimum load exhibited lower fatigue lives than max dwell tests, and also exhibited early crack initiation and a substantial increase in the number of initiation sites. These results could be explained in part by modeling evolution of peak stresses in the notch with continued dwell fatigue cycling. Fatigue-environment interactions were determined to limit life for the fatigue cycles with dwells.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217118 , E-17805
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    Enhanced Core Noise Modeling for Turbofan Engines (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This report describes work performed by MTC Technologies (MTCT) for NASA Glenn Research Center (GRC) under Contract NAS3-00178, Task Order No. 15. MTCT previously developed a first-generation empirical model that correlates the core/combustion noise of four GE engines, the CF6, CF34, CFM56, and GE90 for General Electric (GE) under Contract No. 200-1X-14W53048, in support of GRC Contract NAS3-01135. MTCT has demonstrated in earlier noise modeling efforts that the improvement of predictive modeling is greatly enhanced by an iterative approach, so in support of NASA's Quiet Aircraft Technology Project, GRC sponsored this effort to improve the model. Since the noise data available for correlation are total engine noise spectra, it is total engine noise that must be predicted. Since the scope of this effort was not sufficient to explore fan and turbine noise, the most meaningful comparisons must be restricted to frequencies below the blade passage frequency. Below the blade passage frequency and at relatively high power settings jet noise is expected to be the dominant source, and comparisons are shown that demonstrate the accuracy of the jet noise model recently developed by MTCT for NASA under Contract NAS3-00178, Task Order No. 10. At lower power settings the core noise became most apparent, and these data corrected for the contribution of jet noise were then used to establish the characteristics of core noise. There is clearly more than one spectral range where core noise is evident, so the spectral approach developed by von Glahn and Krejsa in 1982 wherein four spectral regions overlap, was used in the GE effort. Further analysis indicates that the two higher frequency components, which are often somewhat masked by turbomachinery noise, can be treated as one component, and it is on that basis that the current model is formulated. The frequency scaling relationships are improved and are now based on combustor and core nozzle geometries. In conjunction with the Task Order No. 10 jet noise model, this core noise model is shown to provide statistical accuracy comparable to the jet noise model for frequencies below blade passage. This model is incorporated in the NASA FOOTPR code and a user s guide is provided.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/CR-2011-217026 , E-17691
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    Gas turbine combustor (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes a radially inner liner, a radially outer liner that circumscribes the inner liner, and a bulkhead, having a height, H1, which extends between the respective forward ends of the inner liner and the outer liner. The combustor has an exit height, H3, at the respective aft ends of the inner liner and the outer liner interior. The annular combustor has a ratio H1/H3 having a value less than or equal to 1.7. The annular combustor may also have a ration L/H3 having a value less than or equal to 6.0.
    Keywords: Aircraft Propulsion and Power
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    Jet engine nozzle exit configurations and associated systems and methods (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter.
    Keywords: Aircraft Propulsion and Power
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    Apparatus and method for gas turbine active combustion control system (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An Active Combustion Control System and method provides for monitoring combustor pressure and modulating fuel to a gas turbine combustor to prevent combustion dynamics and/or flame extinguishments. The system includes an actuator, wherein the actuator periodically injects pulsed fuel into the combustor. The apparatus also includes a sensor connected to the combustion chamber down stream from an inlet, where the sensor generates a signal detecting the pressure oscillations in the combustor. The apparatus controls the actuator in response to the sensor. The apparatus prompts the actuator to periodically inject pulsed fuel into the combustor at a predetermined sympathetic frequency and magnitude, thereby controlling the amplitude of the pressure oscillations in the combustor by modulating the natural oscillations.
    Keywords: Aircraft Propulsion and Power
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    Fluctuating Pressure Environments and Hydrodynamic Radial Force Mitigation for a Two Blade Unshrouded Inducer (2011)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Fluctuating pressure data from water flow testing of an unshrouded two blade inducer revealed a cavitation induced oscillation with the potential to induce a radial load on the turbopump shaft in addition to other more traditionally analyzed radial loads. Subsequent water flow testing of the inducer with a rotating force measurement system confirmed that the cavitation induced oscillation did impart a radial load to the inducer. After quantifying the load in a baseline configuration, two inducer shroud treatments were selected and tested to reduce the cavitation induced load. The first treatment was to increase the tip clearance, and the second was to introduce a circumferential groove near the inducer leading edge. Increasing the clearance resulted in a small decrease in radial load along with some steady performance degradation. The groove greatly reduced the hydrodynamic load with little to no steady performance loss. The groove did however generate some new, relatively high frequency, spatially complex oscillations to the flow environment.
    Keywords: Aircraft Propulsion and Power
    Type: M11-1243 , M11-1350 , JANNAF 8th Modeling and Simulation Subcommittee Meeting; Dec 05, 2011 - Dec 09, 2011; Huntsville, AL; United States|JANNAF 6th Liquid Propulsion Subcommittee Meeting; Dec 05, 2011 - Dec 09, 2011; Huntsville, AL; United States|JANNAF 5th Spacecraft Propulsion Subcommittee Meeting; Dec 05, 2011 - Dec 09, 2011; Huntsville, AL; United States
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    Integrated Turbine-Based Combined Cycle Dynamic Simulation Model (2011)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A Turbine-Based Combined Cycle (TBCC) dynamic simulation model has been developed to demonstrate all modes of operation, including mode transition, for a turbine-based combined cycle propulsion system. The High Mach Transient Engine Cycle Code (HiTECC) is a highly integrated tool comprised of modules for modeling each of the TBCC systems whose interactions and controllability affect the TBCC propulsion system thrust and operability during its modes of operation. By structuring the simulation modeling tools around the major TBCC functional modes of operation (Dry Turbojet, Afterburning Turbojet, Transition, and Dual Mode Scramjet) the TBCC mode transition and all necessary intermediate events over its entire mission may be developed, modeled, and validated. The reported work details the use of the completed model to simulate a TBCC propulsion system as it accelerates from Mach 2.5, through mode transition, to Mach 7. The completion of this model and its subsequent use to simulate TBCC mode transition significantly extends the state-of-the-art for all TBCC modes of operation by providing a numerical simulation of the systems, interactions, and transient responses affecting the ability of the propulsion system to transition from turbine-based to ramjet/scramjet-based propulsion while maintaining constant thrust.
    Keywords: Aircraft Propulsion and Power
    Type: E-17775P , 58th JANNAF (JPM/CS/APS/EPSS/PHHS) Propulsion meeting; Apr 18, 2011 - Apr 22, 2011; Arlington, VA; United States
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    The Promise and Challenges of Ultra High Bypass Ratio Engine Technology and Integration (2011)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: In this presentation, an overview of the research being conducted by the ERA Project in Ultra High Bypass aircraft propulsion and in partnership with Pratt & Whitney with their Geared TurboFan (GTF) is given. The ERA goals are shown followed by a discussion of what areas need to be addressed on the engine to achieve the goals and how the GTF is uniquely qualified to meet the goals through a discussion of what benefits the cycle provides. The first generation GTF architecture is then shown highlighting the areas of collaboration with NASA, and the fuel burn, noise and emissions reductions possible based on initial static ground test and flight test data of the first GTF engine. Finally, a 5 year technology roadmap is presented focusing on Ultra High Bypass propulsion technology research areas that are being pursued and being planned by ERA and P&W under their GTF program.
    Keywords: Aircraft Propulsion and Power
    Type: HQ-STI-11-012 , E-17843 , 49th AIAA Aero Sciences Meeting; Jan 04, 2011 - Jan 07, 2011; Orlando, FL; United States
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    Wet active chevron nozzle for controllable jet noise reduction (2011)
    In:  CASI
    Details
    Publication Date: 2019-08-24
    Description: Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fashion as mechanically disposed chevrons have done in the known art. Unlike mechanically disposed chevrons of the known art, the fluid flow may be secured thereby increasing the engine efficiency. Various flow patterns, water pressures, orifice designs or other factors can be made operative to provide desired performance characteristics.
    Keywords: Aircraft Propulsion and Power
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    Jet Engine Exhaust Nozzle Flow Effector (2011)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A jet engine exhaust nozzle flow effector is a chevron formed with a radius of curvature with surfaces of the flow effector being defined and opposing one another. At least one shape memory alloy (SMA) member is embedded in the chevron closer to one of the chevron's opposing surfaces and substantially spanning from at least a portion of the chevron's root to the chevron's tip.
    Keywords: Aircraft Propulsion and Power
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    Reestablishing Open Rotor as an Option for Significant Fuel Burn Improvements (2011)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A low-noise open rotor system is being tested in collaboration with General Electric and CFM International, a 50/50 joint company between Snecma and GE. Candidate technologies for lower noise will be investigated as well as installation effects such as pylon integration. Current test status is presented as well as future scheduled testing which includes the FAA/CLEEN test entry. Pre-test predictions show that Open Rotors have the potential for revolutionary fuel burn savings.
    Keywords: Aircraft Propulsion and Power
    Type: E-17663 , HQ-STI-11-013 , AIAA 2010 Aero Sciences Meeting; Jan 04, 2011 - Jan 07, 2011; Orlando, FL; United States
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    Assessment of Turbulence-Chemistry Interaction Models in the National Combustion Code (NCC) - Part I (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the implementations of the linear-eddy model (LEM) and an Eulerian FDF/PDF model in the National Combustion Code (NCC) for the simulation of turbulent combustion. The impacts of these two models, along with the so called laminar chemistry model, are then illustrated via the preliminary results from two combustion systems: a nine-element gas fueled combustor and a single-element liquid fueled combustor.
    Keywords: Aircraft Propulsion and Power
    Type: E-17966 , 48th AIAA Aerospace Sciences Meering (ASM); Jan 04, 2010 - Jan 07, 2010; Orlando, FL; United States
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    Axisymmetric Calculations of a Low-Boom Inlet in a Supersonic Wind Tunnel (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes axisymmetric CFD predictions made of a supersonic low-boom inlet with a facility diffuser, cold pipe, and mass flow plug within wind tunnel walls, and compares the CFD calculations with the experimental data. The inlet was designed for use on a small supersonic aircraft that would cruise at Mach 1.6, with a Mach number over the wing of 1.7. The inlet was tested in the 8-ft by 6-ft Supersonic Wind Tunnel at NASA Glenn Research Center in the fall of 2010 to demonstrate the performance and stability of a practical flight design that included a novel bypass duct. The inlet design is discussed here briefly. Prior to the test, CFD calculations were made to predict the performance of the inlet and its associated wind tunnel hardware, and to estimate flow areas needed to throttle the inlet. The calculations were done with the Wind-US CFD code and are described in detail. After the test, comparisons were made between computed and measured shock patterns, total pressure recoveries, and centerline pressures. The results showed that the dual-stream inlet had excellent performance, with capture ratios near one, a peak core total pressure recovery of 96 percent, and a large stable operating range. Predicted core recovery agreed well with the experiment but predicted bypass recovery and maximum capture ratio were high. Calculations of offdesign performance of the inlet along a flight profile agreed well with measurements and previous calculations.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217224 , AIAA Paper 2011-3800 , E-17907 , 29th Applied Aerodynamics Conference; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
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    Computational Analysis of a Low-Boom Supersonic Inlet (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A low-boom supersonic inlet was designed for use on a conceptual small supersonic aircraft that would cruise with an over-wing Mach number of 1.7. The inlet was designed to minimize external overpressures, and used a novel bypass duct to divert the highest shock losses around the engine. The Wind-US CFD code was used to predict the effects of capture ratio, struts, bypass design, and angles of attack on inlet performance. The inlet was tested in the 8-ft by 6-ft Supersonic Wind Tunnel at NASA Glenn Research Center. Test results showed that the inlet had excellent performance, with capture ratios near one, a peak core total pressure recovery of 96 percent, and a stable operating range much larger than that of an engine. Predictions generally compared very well with the experimental data, and were used to help interpret some of the experimental results.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217223 , AIAA Paper 2011-3801 , E-17906 , 29th Applied Aerodynamics Conference; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
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    Experimental and Modeling Studies of the Combustion Characteristics of Conventional and Alternative Jet Fuels. Final Report (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objectives of this project have been to develop a comprehensive set of fundamental data regarding the combustion behavior of jet fuels and appropriately associated model fuels. Based on the fundamental study results, an auxiliary objective was to identify differentiating characteristics of molecular fuel components that can be used to explain different fuel behavior and that may ultimately be used in the planning and design of optimal fuel-production processes. The fuels studied in this project were Fischer-Tropsch (F-T) fuels and biomass-derived jet fuels that meet certain specifications of currently used jet propulsion applications. Prior to this project, there were no systematic experimental flame data available for such fuels. One of the key goals has been to generate such data, and to use this data in developing and verifying effective kinetic models. The models have then been reduced through automated means to enable multidimensional simulation of the combustion characteristics of such fuels in real combustors. Such reliable kinetic models, validated against fundamental data derived from laminar flames using idealized flow models, are key to the development and design of optimal combustors and fuels. The models provide direct information about the relative contribution of different molecular constituents to the fuel performance and can be used to assess both combustion and emissions characteristics.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/CR-2011-216356 , E-17292 , Turbo Expo 2010; Jun 14, 2010 - Jun 18, 2010; Glasgow, Scotland; United Kingdom
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    Control of Fan Blade Vibrations Using Piezoelectrics and Bi-Directional Telemetry (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A novel wireless device which transfers supply power through induction to rotating operational amplifiers and transmits low voltage AC signals to and from a rotating body by way of radio telemetry has been successfully demonstrated in the NASA Glenn Research Center (GRC) Dynamic Spin Test Facility. In the demonstration described herein, a rotating operational amplifier provides controllable AC power to a piezoelectric patch epoxied to the surface of a rotating Ti plate. The amplitude and phase of the sinusoidal voltage command signal, transmitted wirelessly to the amplifier, was tuned to completely suppress the 3rd bending resonant vibration of the plate. The plate's 3rd bending resonance was excited using rotating magnetic bearing excitation while it spun at slow speed in a vacuum chamber. A second patch on the opposite side of the plate was used as a sensor. This paper discusses the characteristics of this novel device, the details of a spin test, results from a preliminary demonstration, and future plans.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-217093 , GT2011-46714 , E-17747 , Turbo Expo 2011; Jun 06, 2011 - Jun 10, 2011; Vancouver, BC; Canada
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    Fundamental Aeronautics Program: Overview of Project Work in Supersonic Cruise Efficiency (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Supersonics Project, part of NASA?s Fundamental Aeronautics Program, contains a number of technical challenge areas which include sonic boom community response, airport noise, high altitude emissions, cruise efficiency, light weight durable engines/airframes, and integrated multi-discipline system design. This presentation provides an overview of the current (2011) activities in the supersonic cruise efficiency technical challenge, and is focused specifically on propulsion technologies. The intent is to develop and validate high-performance supersonic inlet and nozzle technologies. Additional work is planned for design and analysis tools for highly-integrated low-noise, low-boom applications. If successful, the payoffs include improved technologies and tools for optimized propulsion systems, propulsion technologies for a minimized sonic boom signature, and a balanced approach to meeting efficiency and community noise goals. In this propulsion area, the work is divided into advanced supersonic inlet concepts, advanced supersonic nozzle concepts, low fidelity computational tool development, high fidelity computational tools, and improved sensors and measurement capability. The current work in each area is summarized.
    Keywords: Aircraft Propulsion and Power
    Type: E-17750 , 2011 Technical Conference; Mar 15, 2011 - Mar 17, 2011; Cleveland, OH; United States
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    Previous Open Rotor Research in the US (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Previous Open Rotor noise experience in the United States, current Open Rotor noise research in the United States and current NASA prediction methods activities were presented at a European Union (EU) X-Noise seminar. The invited attendees from EU industries, research establishments and universities discussed prospects for reducing Open Rotor noise and reviewed all technology programs, past and present, dedicated to Open Rotor engine concepts. This workshop was particularly timely because the Committee on Aviation Environmental Protection (CAEP) plans to involve Independent Experts in late 2011 in assessing the noise of future low-carbon technologies including the open rotor.
    Keywords: Aircraft Propulsion and Power
    Type: E-17780 , X-Noise Workshop; Mar 18, 2011; Lausanne; Switzerland
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    Exhaust System Experiments at NASA's AeroAcoustic Propulsion Lab (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This presentation gives an overview of the planned testing in the AeroAcoustic Propulsion Lab (AAPL) in the coming 15 months. It was stressed in the presentation that these are plans that are subject to change due to changes in funding and/or programmatic direction. The first chart shows a simplified schedule of test entries with funding sponsor and dates for each. In subsequent charts are pages devoted to the Objectives and Issues with each test entry, along with a graphic intended to represent the test activity. The chart for each test entry also indicates sponsorship of the activity, and a contact person.!
    Keywords: Aircraft Propulsion and Power
    Type: E-17795 , Presented to Acoustics Technical Working Group; Apr 21, 2011 - Apr 22, 2011; Cleveland, OH; United States
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    Intake Noise Generation: Source Mechanisms (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Propulsion and Power
    Type: E-664221 , Engine Intake Aerothermal Design: Subsonic to High Speed Application; Nov 14, 2011 - Nov 16, 2011; Rhode-St-Genýse; Belgium
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    Advanced Concepts for Aircraft LTO NOx Reduction: A NASA Perspective (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Propulsion and Power
    Type: E-663266 , Aircraft Noise and Emissions Reduction Symposium (ANERS); Oct 25, 2011 - Oct 27, 2011; Marseille; France
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    Propulsion Technologies for Future Aircraft Generations: Clean, Lean, Quiet, and Green (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Propulsion and Power
    Type: E-663265 , ISABE Conference; Sep 12, 2011 - Sep 16, 2011; Gothenberg; Sweden
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    Excitation/Detection Strategies for OH Planar Laser-Induced Fluorescence Measurements in the Presence of Interfering Fuel Signal and Absorption Effects (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Planar laser-induced fluorescence (PLIF) excitation/detection methods have been applied to obtain spatial distributions of the hydroxyl [OH] reacting intermediary and hydrocarbon [HC] primary species in laminar and turbulent combustion reactions. In this report, broadband and narrowband excitation/filtering techniques are explored to identify an optimal experimental configuration yielding significant fluorescent signal with low absorption losses. The combustion environments analyzed include 1) a laminar non-premixed methane/air flame and 2) a turbulent, non-premixed Jet-A/air fueled flame within a lean flame tube combustor. Hydrocarbon-based fuel and OH were excited via the R1 (1), R1(10) and R2(7) transitions of the A(sup 2)Epsilon(+) X(sup 2)pi(1,0) band using a broadband Nd:YAG pumped optical parametric oscillator (OPO) and narrowband Nd:YAG/dye laser with ultraviolet frequency extension (UVX) package. Variables tested for influence on fluorescent signal and absorption characteristics were excitation line, laser energy, exciting linewidth, combustion reactants, and test flow conditions. Results are intended to guide the transition from a dye/UVX laser to an OPO system for performing advanced diagnostics of low-emission combustion concepts.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2011-216947 , AIAA Paper 2010-6667 , E-17551 , 46th Joint Propulsion Conference and Exhibit; Jul 25, 2010 - Jul 28, 2010; Nashville, TN; United States
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    Masthead (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946) 
    Details
    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jmor.1050780101
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    A study of adrenal cortical tissue in rana pipiens with special reference to metamorphosis (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 27-41 
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    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    Morphogentic studies of the rabbit II. Evidence of regionally specific hereditary factors influencing the extent of the lumbar regionThis study is part of a research program being partially supported by a grant from the Rockefeller Foundation. (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 1-26 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    A new type of spermiogenesis in iceryine coccids  -  with linear alignment of chromosomes in the sperm (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 43-83 
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    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    A resurgent population of the California bay-mussel (Mytilus edulis diegensis)Contributions from the Scripps Institution of Oceanography of the University of California, New Series no. 284. (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 85-103 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    The anatomy and histology of the alimentary tract of the bottom-feeder, Mulloides auriflamma (Forsk.) (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 121-153 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    The relationship of skeletal type and body size in an inbred strain of mice (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 113-120 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    The effect of uterine environment on the skeleton of the mouse (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 105-112 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Cephalogenesis in relation to the integration center of the beetle callosobruchus maculatus fabr.On the authority of J. L. Bottimer, I have used the synonomy of Bridwell ('29). Callosobruchus maculatus Fabr. rather than Bruchus quadrimaculatus (Geoffroy, 1762). (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 155-179 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Masthead (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946) 
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    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    History of the nuclei of tillina magna during division and encystment (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 181-200 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    The cytology of the cecidomyidae (Diptera) I. Polyploidy and polyteny in salivary gland cells of Lestodiplosis spp (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 201-219 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    A technique for counting numerous chromosomes (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 221-230 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    The development of the vascular pattern within the walls of the central nervous system of the chick embryo (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 231-303 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Masthead (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946) 
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    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Cleavage and attachment stages of the pigPaper no. 2263, Scientific Journal Series of the Minnesota Agricultural Station. This study was conducted with animals produced in cooperation with the Regional Swine Breeding Laboratory, Ames, Iowa, Bureau of Animal Industry, U. S. Department of Agriculture, and supported in part by a Grant in Aid of Research of the Graduate School, University of Minnesota. (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 305-316 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    Pelomyxa carolinensis Wilson. I. General observation on the illinois stockA contribution from the Zoological Laboratory of the University of Illinois. (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 317-351 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    The slime glands and thread cells of the hagfish, Polistrotrema stouti (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 397-409 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Conjugation in paramecium bursaria I. Conjugation of three animalsThis work was aided by grants from the Committee for Research in Problems of Sex of the National Reasearch Council and from the Penrose Fund of the American Philosophical Society. Part of the expense of publishing the plates was defrayed by grants from the University of California and from Brook's Fund of the Johns Hopkins University. (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 78 (1946), S. 353-395 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    Masthead (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946) 
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    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Situs inversus viscerum in conjoined twins of the brook trout (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 1-25 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    Structure, motility and locomotion in isolated embryonic amphibian cellsExecuted with the support of a Fellowship from the John Simon Guggenheim Memorial Foundation and a grant from the American Philosophical Society. (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 27-62 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    Hermaphroditism in the largemouth bass (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 93-96 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    The gustatory papillae and the stomach of Hyracoidea, with a discussion of the evolution of the mammalian tongue papillae (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 97-111 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    Histology of gonadal changes in the bluegill, Lepomis macrochirus Rafinesque, and the largemouth bass, Huro salmoides (Lacépède)Submitted from thesis written in partial fulfillment of the requirements for the degree of Doctor of Philosophy in the Graduate School of the University of Illinois. The writer is now an assistant professor at MacMurray College, Jacksonville, Illinois. (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 63-91 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    Masthead (1946)
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    Journal of Morphology 79 (1946) 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Cytological studies on Acrididae. IV. The structure of the X-chromosome in the meiosis of Phlaeoba infumata (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 113-123 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    Oral breathing valves in fishes (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 263-285 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    Conjugation in Paramecium bursaria. II. Nuclear phenomena in lethal conjugation between varietiesThis work was aided by grants from the Committee for Research in Problems of Sex of the National Research Council, from the Joseph Henry Fund of the National Academy of Sciences, and from the Permanent Science Fund of the American Academy of Arts and Sciences. Part of the expense of publishing the plates was defrayed by a grant from the University of California. (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 125-261 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    The histology of anuran limb regenerationPresented to the faculty of Princeton University in partial fulfillment of the requirements for the degree of Doctor of Philosophy. (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 287-321 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
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    Masthead (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946) 
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    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
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    The cytology of the Cecidomyidae (Diptera). II. The chromosome cycle and anomalous spermatogenesis of Miastor (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 323-369 
    Details
    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 21 Ill.
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    URL: http://dx.doi.org/10.1002/jmor.1050790302
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    Observations on the morphology of the face in insects (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 371-417 
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    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    Ingestion organs in folliculinids and in stentors (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 419-444 
    Details
    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 2 Ill.
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    URL: http://dx.doi.org/10.1002/jmor.1050790304
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    The morphology and systematic position of a holotrichous ciliate parasitizing Deroceras agreste (L.) (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 445-465 
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    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 1 Tab.
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    URL: http://dx.doi.org/10.1002/jmor.1050790305
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    The development, structure and functional capacity of the ovaries in triploid Ambystomid salamanders (1946)
    New York, NY : Wiley-Blackwell
    Journal of Morphology 79 (1946), S. 467-509 
    Details
    ISSN: 0362-2525
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/jmor.1050790306
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    Temperature regulation in three central American mammalsThese observations were made, incidental to a study of mammals in Northern Panama during the summer of 1941, and were supported in part by a grant from the American Philosophical Society to Dr. R. K. Enders. (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 27 (1946), S. 125-137 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 6 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030270302
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    In vitro control of growing check nerve fibers by applied electric currentsAided by a grant from the Rockefeller Foundation for work in cellular physiology. (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 27 (1946), S. 139-157 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 5 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030270303
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    Acetylcholine and related substances in the cockroach, fly and crayfish and the effect of DDTDDT, 2,2-bis (p-chlorophenyl)-1,1,1-trichloroethane. (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 28 (1946), S. 159-182 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    URL: http://dx.doi.org/10.1002/jcp.1030280202
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    A study of the enzymatic and other properties of the crystalline style of clams: Evidence for the presence of a cellulaseAided by a grant in memory of Miss Susanne Dercum. (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 28 (1946), S. 183-195 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    URL: http://dx.doi.org/10.1002/jcp.1030280203
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    Alkaline and acid phosphomonoesterase activity in chick embryosAided by a grant from the Rockefeller Foundation. (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 28 (1946), S. 197-208 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 2 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030280204
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    Localization of acid and alkaline phosphomonoesterases in cytoplasmic granulesAided by a grant from the Rockefeller Foundation. (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 28 (1946), S. 209-220 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    Phosphorylation in living yeast cells (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 28 (1946), S. 221-230 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 1 Tab.
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    Masthead (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 28 (1946) 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    URL: http://dx.doi.org/10.1002/jcp.1030280301
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    The relationship of potassium to carbohydrate metabolism in Baker's yeast (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 28 (1946), S. 231-252 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 13 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030280207
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    Biochemical and physiological differentiation during morphogenesis. VI. Succinic dehydrogenase and succinoxidase in the cerebral cortex of the fetal pigPrevious papers of this series are listed in the bibliography as follows: I, Flexner and Gersh. '37; II, Flexner, '38; III, Flexner and Stiehler, '38; IV, Flexner, '39; V, Flexner, Flexner and Straus, '41.Aided by a grant from The National Foundation for Infantile Paralysis, Inc. (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 27 (1946), S. 35-42 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 2 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030270106
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    The influence of temperature upon the oxygen consumption of several arthropods (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 27 (1946), S. 53-64 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 4 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030270108
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    Effect of a respiratory enzyme system and creatine upon the growth of cells in vitroPresented before Division of Biochemistry  -  American Chemical Society, Fall Meeting, 1944. (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 27 (1946), S. 43-51 
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    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
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    The excretion of estrogens by the aglomerular kidneyThis work was made possible through the cooperation of the staff of the Chesapeake Biological Laboratory at Solomon's Island, Maryland. (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 27 (1946), S. 65-67 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 1 Tab.
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    Masthead (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 27 (1946) 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030270201
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    True cholinesterases with pronounced resistance to eserine (1946)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 27 (1946), S. 69-85 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 2 Ill.
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    URL: http://dx.doi.org/10.1002/jcp.1030270202
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