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  • Aircraft Propulsion and Power
  • General Chemistry
  • 2010-2014  (5)
  • 1950-1954  (5)
  • 1945-1949
  • 1935-1939
  • 1930-1934
  • 2011  (5)
  • 1950  (5)
  • 1
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Zeitschrift für die chemische Industrie 62 (1950), S. 430-430 
    ISSN: 0044-8249
    Keywords: Chemistry ; General Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
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  • 2
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Zeitschrift für die chemische Industrie 62 (1950), S. 475-480 
    ISSN: 0044-8249
    Keywords: Chemistry ; General Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Bei künstlich konjugierten Ölen und Fettsäuren ergibt die Dienzahlbestimmung bedeutend kleinere Werte als die UV-Methode. Offensichtlich werden einige Isomere nicht erfaßt. Es wurde daher eine abgewandelte Untersuchungsmethode entwickelt, welche es ermöglicht, quantitativ die konjugiert-ungesättigten Bestandteile als „Pandienzahl“ zu erfassen, und mit deren Hilfe es u.a. möglich ist, in die Verteilung der Isomeren Einblick zu erhalten.
    Additional Material: 1 Tab.
    Type of Medium: Electronic Resource
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  • 3
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Zeitschrift für die chemische Industrie 62 (1950), S. 82-83 
    ISSN: 0044-8249
    Keywords: Chemistry ; General Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
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  • 4
    ISSN: 0044-8249
    Keywords: Chemistry ; General Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
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  • 5
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Zeitschrift für die chemische Industrie 62 (1950), S. 471-473 
    ISSN: 0044-8249
    Keywords: Chemistry ; General Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Entwicklung der neuen Insektizide „HETP“ und „TEPP“ und das innertherapeutisch an lebenden Pflanzen wirksame „Pestox“ wird beschrieben. Ferner wird über die Darstellung des Mioticums „Mintacol“ und die Entwicklung der Pflanzenschutzmittel „E 605“ und „E838“ berichtet. Alle Entwicklungsgeschichte neuer Insektizide auf Grundlage organischer Fluor- und Phosphorverbindungen“, die als Beiheft zu dieser Zeitschrift erscheint.
    Type of Medium: Electronic Resource
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  • 6
    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
    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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  • 8
    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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  • 9
    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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  • 10
    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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