scholarly journals Flight Research Using F100 Engine P680063 in the NASA F-15 Airplane

1995 ◽  
Author(s):  
Frank W. Burcham ◽  
Timothy R. Conners ◽  
Michael D. Maxwell
Keyword(s):  
Control System ◽  
Flight Control ◽  
Flight Test ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Stall Margin ◽  
Engine Control System ◽  
Engine Thrust ◽  
Research Activities ◽  
Margin Control

The value of flight research in developing and evaluating gas turbine engines is high. NASA Dryden Flight Research Center has been conducting flight research on propulsion systems for many years. The F100 engine has been tested in the NASA F-15 research airplane in the last three decades. One engine in particular, S/N P680063, has been used for the entire program and has been flown in many pioneering propulsion flight research activities. Included are detailed flight-to-ground facility tests; tests of the first production digital engine control system, the first active stall margin control system, the first performance-seeking control system; and the first use of computer-controlled engine thrust for emergency flight control. The flight research has been supplemented with altitude facility tests at key times. This paper presents a review of the tests of engine P680063, the F-15 airplanes in which it flew, and the role of the flight test in maturing propulsion technology.

The Electronic Control of Gas Turbine Engines

1965 ◽  
Vol 69 (655) ◽  
pp. 429-447 ◽  
Author(s):  
A. Sadler ◽  
S. Tweedy ◽  
P. J. Colburn
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Engine Fuel ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Engine Control System ◽  
Pumping System ◽  
Prime Movers ◽  
General Aspects

The advances made in the development of gas turbine engines during the past two decades have been remarkable. The engines have been improved tremendously in terms of power, weight, efficiency and cost. They are now being applied successfully as the prime movers for helicopters, VTOL aircraft, ground power units and for many other diverse purposes, besides the more conventional military and civil aircraft.There have been parallel advances in the development of gas turbine engine fuel systems (which for convenience may be subdivided into the “control” and the “pumping arrangement”). These systems were originally wholly hydro-mechanical in nature. Sixteen or so years ago, the first supplementary electronic devices were introduced into fuel control systems. Since then, progressively more complex hybrid electronic/hydro-mechanical systems have been employed, with a corresponding easement of the demands on the hydro-mechanical portion. In 1957 Sturrock described to this Society what is now the classic Proteus engine control system used in Britannia aircraft. The satisfactory experience gained with the Proteus system led to the adoption of a comprehensive electronic fuel control system, coupled to a relatively simple fuel pumping system, for the supersonic Olympus engine. This system has been described by Hunt and by Colburn, Tweedy and Dent in papers presented at the joint RAeS/IEE conference “The Importance of Electricity in Aircraft” in 1962. Further papers by Rush presented at the same conference and by Airey in 1963, were devoted to the more general aspects of control.

scholarly journals HIDEC Adaptive Engine Control System Flight Evaluation Results

1987 ◽  
Author(s):  
W. A. Yonke ◽  
R. J. Landy ◽  
J. F. Stewart
Keyword(s):  
Control System ◽  
Pressure Ratio ◽  
Engine Performance ◽  
Control Mode ◽  
Engine Control ◽  
Sideslip Angle ◽  
Stall Margin ◽  
Engine Control System ◽  
Engine Thrust ◽  
Unique Predictor

An integrated flight propulsion control mode called Adaptive Engine Control System (ADECS) has been developed and flight demonstrated on an F-15 test aircraft in the Highly Integrated Digital Electronic Control (HIDEC) Program, sponsored by the NASA Ames/Dryden Flight Research Center. The ADECS system provides additional engine thrust by increasing engine pressure ratio (EPR) at intermediate and afterburning power. The amount of EPR uptrim is modulated based on a unique predictor scheme for angle-of-attack and sideslip angle thus ensuring adequate fan stall margin for the engine. These predicted angles are derived from fight control and inertial navigation information. The ADECS mode demonstrated substantial improvements in aircraft and engine performance in the flight evaluation program, even with only one engine incorporating EPR uptrim. Highlights were a 16% rate of climb increase, a 14% reduction in time to climb, and a 15% reduction in time to accelerate. Significant EPR uptrim capability was demonstrated with angles-of-attack up to 20 degrees.

Real Time Simulators for Use in Design of Integrated Flight and Propulsion Control Systems

1988 ◽  
Author(s):  
William J. Davies ◽  
Charlie L. Jones ◽  
Robert A. Noonan
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
Integrated Control ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Flight Control System ◽  
Simulation Tools ◽  
Military Applications ◽  
Propulsion Control

The introduction of Full Authority Digital Electronic Controls (FADEC) to both commercial and military aircraft gas turbine engines provides significant operational benefits. FADEC’s are reliable and more maintainable than the hydromechanical controls they have replaced. The next significant change in their use will be integration with the flight control, particularly in military applications, to provide reduced fuel consumption in cruise and rapid, accurate engine transients for increased maneuverability. Integration with the flight control system requires another level of control system testing beyond verification that the FADEC will perform it’s principle functions-control and protection of the engine. This new testing requires that the FADEC be tested in unison with the flight control to verify total control system capability and safety throughout the flight envelope. These testing requirements have been addressed at Pratt & Whitney and various airframers through application of the same simulation tools which have been in use to verify FADEC hardware and software capability prior to engine test. These test systems and their application to advanced integrated control systems are described herein to provide insight into both their operation and application.

Advanced Control Program for Army Gas Turbine Engines

1973 ◽  
Author(s):  
A. H. White ◽  
D. F. Wills
Keyword(s):  
Control System ◽  
Control Systems ◽  
Gas Turbine ◽  
Control Program ◽  
Turbine Engines ◽  
Engine Control ◽  
Gas Turbine Engines ◽  
System Technology ◽  
Engine Control System ◽  
Advanced Control

This paper summarizes the results of a 30-month program of design, fabrication, and test of an advanced electronic engine control system for small (2 to 5-lb/sec airflow) turboshaft engines. The objective of the program was to develop engine control system technology which would be implemented in future systems to meet advanced engine requirements and to alleviate many of the problems experienced with past and present control systems.

scholarly journals Automated Virtual Testing Rig Incorporating Multi-level Models of Gas Turbine Engines

2018 ◽  
Vol 220 ◽  
pp. 03001
Author(s):  
Andrey Tkachenko ◽  
Ilia Krupenich ◽  
Evgeny Filinov ◽  
Yaroslav Ostapyuk
Keyword(s):  
Gas Turbine ◽  
Power Plants ◽  
Educational Process ◽  
Turbine Engines ◽  
Experimental Investigations ◽  
Gas Turbine Engines ◽  
Engine Operation ◽  
Virtual Testing ◽  
Research Activities ◽  
Multi Level

This article describes the multi-level approach to developing the virtual testing rig of gas turbine engines and power plants. The described virtual rig is developed on the basis of computer-aided system of thermogasdynamic calculations and analysis ASTRA, developed at Samara National Research University. Existing testing rig is widely used in educational process to supply the students’ research activities with the information on engine operation in a variety of ambient and flight conditions during transients. An approach to upgrading the virtual testing rig is proposed. The described modifications would provide the capabilities to solve more complex research tasks, including investigation of influence of geometry of engine elements on the engine characteristics, multidisciplinary investigations, identification of engine models using the results of experimental investigations and identification of sources of engine deficiencies during the development phase of engine designing.

Development of Gas Turbine Performance Seeking Logic

1978 ◽  
Vol 100 (4) ◽  
pp. 571-575
Author(s):  
D. Jordan ◽  
G. J. Michael
Keyword(s):  
Gas Turbine ◽  
Performance Optimization ◽  
Flight Test ◽  
Test Stand ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Control Logic ◽  
Algorithm Performance ◽  
Static Performance ◽  
Performance Results

Adaptive control logic has been defined for static performance optimization of variable geometry gas turbine engines. The control logic is directed toward (1) in-flight minimization of thrust specific fuel consumption, (2) test-stand automatic trimming, and (3) generation of optimum control schedules. The algorithm was evaluated by application to a nonlinear digital dynamic simulation of the F100/F401 turbofan engine throughout a range of representative flight conditions. Engine component degradations as well as mistrimmed control schedules were introduced to assess algorithm performance. Results indicate that the performance seeking algorithm offers promise for steady state performance optimization for in-flight, test-stand, and set point design optimization applications.

Engine Test and Post Engine Test Characterization of Self-Sealing Ceramic Matrix Composites for Nozzle Applications in Gas Turbine Engines

2004 ◽  
Author(s):  
Eric P. Bouillon ◽  
Patrick C. Spriet ◽  
Georges Habarou ◽  
Caroline Louchet ◽  
Thibault Arnold ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Flight Test ◽  
Turbine Engines ◽  
Internal Cooling ◽  
Matrix Composites ◽  
Gas Turbine Engines ◽  
Engine Test ◽  
Residual Properties

The advancement of self-sealing ceramic matrix composites offers durability improvements in hot section components of gas turbine engines. These durability improvements come with no need for internal cooling and with reduced weight. Building on past material efforts, ceramic matrix composites based on either a carbon fiber or a SiC fiber with a sequenced self-sealing matrix have been developed for gas turbine applications. The specific application being pursued on this effort is an F100-PW-229 nozzle seal. Full design life ground engine testing has been accomplished with both material systems. The ground testing has demonstrated a significant durability improvement from the baseline metal design. Residual properties are being determined for both systems by extracting tensile and microstructural coupons from the ceramic matrix composite seal. Nondestructive interrogation showed no material degradation and was used as a guide in setting cutting diagrams. The results from this effort will be presented along with documentation from flight test efforts.

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