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  • 1
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    Comparisons Between Unsteady Aerodynamic Events in a Gas Turbine Generator and an Identical Compressor Rig (1996)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: Extensive testing done on a T55-L-712 turboshaft engine compressor in a compressor test rig is being followed by engine tests in progress as part of the Army Non-Recoverable Stall Program. Goals include a greater understanding of the gas turbine engine start cycle and compressor/engine operation in the regions 'beyond' the normal compressor stall line (rotating stall/surge). Rig steady state instrumentation consisted of 497 steady state pressure sensors and 153 temperature sensors. Engine instrumentation was placed in similar radial/axial locations and consists of 122 steady state pressure sensors and 65 temperature sensors. High response rig instrumentation consisted of 34 wall static pressure transducers. Rig and engine high response pressure transducers were located in the same axial/radial/circumferential locations in front of the first three stages. Additional engine high response instrumentation was placed in mach probes in front of the engine and on the compressor hub. This instrumentation allows for the generation of detailed stage characteristics, overall compressor mapping, and detailed analysis of dynamic compressor events.
    Keywords: Aircraft Propulsion and Power
    Type: Loss Mechanisms and Unsteady Flows in Turbomachines; AGARD-CP-571
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Space Transportation Propulsion Systems (2001)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This report outlines the Space Transportation Propulsion Systems for the NPSS (Numerical Propulsion System Simulation) program. Topics include: 1) a review of Engine/Inlet Coupling Work; 2) Background/Organization of Space Transportation Initiative; 3) Synergy between High Performance Computing and Communications Program (HPCCP) and Advanced Space Transportation Program (ASTP); 4) Status of Space Transportation Effort, including planned deliverables for FY01-FY06, FY00 accomplishments (HPCCP Funded) and FY01 Major Milestones (HPCCP and ASTP); and 5) a review current technical efforts, including a review of the Rocket-Based Combined-Cycle (RBCC), Scope of Work, RBCC Concept Aerodynamic Analysis and RBCC Concept Multidisciplinary Analysis.
    Keywords: Aircraft Propulsion and Power
    Type: 2000 Numerical Propulsion System Simulation Review; 59-69; NASA/CP-2001-210673
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Validation of an Integrated Airframe and Turbofan Engine Simulation for Evaluation of Propulsion Control Modes (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The National Aeronautics and Space Administration (NASA) has developed independent airframe and engine models that have been integrated into a single real-time aircraft simulation for piloted evaluation of propulsion control algorithms. In order to have confidence in the results of these evaluations, the integrated simulation must be validated to demonstrate that its behavior is realistic and that it meets the appropriate Federal Aviation Administration (FAA) certification requirements for aircraft. The paper describes the test procedures and results, demonstrating that the integrated simulation generally meets the FAA requirements and is thus a valid testbed for evaluation of propulsion control modes.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN19726 , SciTech 2015; Jan 05, 2015 - Jan 09, 2015; Kissimmee, FL; United States
    Format: application/pdf
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  • 4
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    Flight Simulator Evaluation of Enhanced Propulsion Control Modes for Emergency Operation (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes piloted evaluation of enhanced propulsion control modes for emergency operation of aircraft. Fast Response and Overthrust modes were implemented to assess their ability to help avoid or mitigate potentially catastrophic situations, both on the ground and in flight. Tests were conducted to determine the reduction in takeoff distance achievable using the Overthrust mode. Also, improvements in Dutch roll damping, enabled by using yaw rate feedback to the engines to replace the function of a stuck rudder, were investigated. Finally, pilot workload and ability to handle the impaired aircraft on approach and landing were studied. The results showed that improvement in all aspects is possible with these enhanced propulsion control modes, but the way in which they are initiated and incorporated is important for pilot comfort and perceived benefit.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2012-217698 , AIAA Paper 2012-2604 , E-18385 , AIAA Infotech@Aerospace Conference; Jun 19, 2012 - Jun 21, 2012; Garden Grove, CA; United States
    Format: application/pdf
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  • 5
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    An Intelligent Propulsion Control Architecture to Enable More Autonomous Vehicle Operation (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes an intelligent propulsion control architecture that coordinates with the flight control to reduce the amount of pilot intervention required to operate the vehicle. Objectives of the architecture include the ability to: automatically recognize the aircraft operating state and flight phase; configure engine control to optimize performance with knowledge of engine condition and capability; enhance aircraft performance by coordinating propulsion control with flight control; and recognize off-nominal propulsion situations and to respond to them autonomously. The hierarchical intelligent propulsion system control can be decomposed into a propulsion system level and an individual engine level. The architecture is designed to be flexible to accommodate evolving requirements, adapt to technology improvements, and maintain safety.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN50405 , SciTech 2018; Jan 08, 2018 - Jan 12, 2018; Kissimmee, FL; United States
    Format: application/pdf
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  • 6
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    A Demonstration of a Retrofit Architecture for Intelligent Control and Diagnostics of a Turbofan Engine (2005)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A retrofit architecture for intelligent turbofan engine control and diagnostics that changes the fan speed command to maintain thrust is proposed and its demonstration in a piloted flight simulator is described. The objective of the implementation is to increase the level of autonomy of the propulsion system, thereby reducing pilot workload in the presence of anomalies and engine degradation due to wear. The main functions of the architecture are to diagnose the cause of changes in the engine s operation, warning the pilot if necessary, and to adjust the outer loop control reference signal in response to the changes. This requires that the retrofit control architecture contain the capability to determine the changed relationship between fan speed and thrust, and the intelligence to recognize the cause of the change in order to correct it or warn the pilot. The proposed retrofit architecture is able to determine the fan speed setting through recognition of the degradation level of the engine, and it is able to identify specific faults and warn the pilot. In the flight simulator it was demonstrated that when degradation is introduced into an engine with standard fan speed control, the pilot needs to take corrective action to maintain heading. Utilizing the intelligent retrofit control architecture, the engine thrust is automatically adjusted to its expected value, eliminating yaw without pilot intervention.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2005-214019 , ARL-TR-3667 , AIAA Paper 2005-6905 , E-15334 , Infotech; Sep 26, 2005 - Sep 29, 2005; Arlington, VA; United States
    Format: application/pdf
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  • 7
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    Multidisciplinary Analysis of a Hypersonic Engine (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes implementation of a technique used to obtain a high fidelity fluid-thermal-structural solution of a combined cycle engine at its scram design point. Single-discipline simulations are insufficient here since interactions from other disciplines are significant. Using off-the-shelf, validated solvers for the fluid, chemistry, thermal, and structural solutions, this approach couples together their results to obtain consistent solutions.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2002-211971 , NAS 1.15:211971 , E-13614 , AIAA Paper 2002-5127 , 11th International Conference on Space Planes and Hypersonic Systems and Technologies; Sep 29, 2002 - Oct 04, 2002; Orleans; France
    Format: application/pdf
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  • 8
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    Dynamic Modeling of Starting Aerodynamics and Stage Matching in an Axi-Centrifugal Compressor (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A DYNamic Turbine Engine Compressor Code (DYNTECC) has been modified to model speed transients from 0-100% of compressor design speed. The impetus for this enhancement was to investigate stage matching and stalling behavior during a start sequence as compared to rotating stall events above ground idle. The model can simulate speed and throttle excursions simultaneously as well as time varying bleed flow schedules. Results of a start simulation are presented and compared to experimental data obtained from an axi-centrifugal turboshaft engine and companion compressor rig. Stage by stage comparisons reveal the front stages to be operating in or near rotating stall through most of the start sequence. The model matches the starting operating line quite well in the forward stages with deviations appearing in the rearward stages near the start bleed. Overall, the performance of the model is very promising and adds significantly to the dynamic simulation capabilities of DYNTECC.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-107338 , E-10477 , NAS 1.15:107338 , ARL-TR-1107 , Gas Turbine and Aeroengine Congress; Jun 10, 1996 - Jun 13, 1996; Birmingham; United Kingdom
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Forced response testing of an axi-centrifugal turboshaft engine (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Dynamic data from tests of a T55-L-712 engine are presented. Engine stall/surge data were analyzed using digital signal processing techniques. In addition, forced response testing (system identification studies) was done at various engine speeds. Forced response testing was done using eight jet ejectors approximately equally circumferentially spaced about the compressor front face. This paper presents some preliminary results for the ground idle (approximately 60% of design speed) point. Brief descriptions of the jet injection system, the test matrix, and analysis techniques used are presented. Results of these analyses indicate a substantial transfer of energy across the compressor first stage at some frequencies and that the ejectors are effective in modifying the local flow conditions in front of the first compressor stage.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-107282 , NAS 1.15:107282 , AIAA Paper 96-2573 , E-10357 , ARL-TR-1151 , Joint Propulsion Conference; Jul 01, 1996 - Jul 03, 1996; Lake Buena Vista, FL; United States
    Format: application/pdf
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  • 10
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    Validation of an Integrated Airframe and Turbofan Engine Simulation for Evaluation of Propulsion Control Modes (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The National Aeronautics and Space Administration (NASA) has developed independent airframe and engine models that have been integrated into a single real-time aircraft simulation for piloted evaluation of propulsion control algorithms. In order to have confidence in the results of these evaluations, the integrated simulation must be validated to demonstrate that its behavior is realistic and that it meets the appropriate Federal Aviation Administration (FAA) certification requirements for aircraft. The paper describes the test procedures and results, demonstrating that the integrated simulation generally meets the FAA requirements and is thus a valid testbed for evaluation of propulsion control modes.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2015-218715 , AIAA Paper 2015-1476 , E-19049 , GRC-E-DAA-TN21120 , SciTech 2015; Jan 05, 2015 - Jan 09, 2015; Kissimmee, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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