Active Compressor Stability Management Via a Stall Margin Control Mode

2010 ◽  
Vol 132 (5) ◽  
Author(s):  
Yuan Liu ◽  
Manuj Dhingra ◽  
J. V. R. Prasad
Keyword(s):  
Pressure Fluctuations ◽  
Aircraft Engine ◽  
Rotating Stall ◽  
Control Mode ◽  
Engine Control ◽  
Correlation Measure ◽  
Stall Margin ◽  
Engine Control System ◽  
Compressor Rotor ◽  
Margin Control

An active engine control scheme for protection against compressor instabilities such as rotating stall and surge is presented. Compressor stability detection is accomplished via a parameter known as the correlation measure, which quantifies the repeatability of the pressure fluctuations in the tip region of a compressor rotor. This work investigates the integration of the correlation measure with an aircraft engine control system through the use of a stall margin control mode. The development and implementation of the stall margin mode are described. The effectiveness of the overall active control framework—an active compressor stability management system—is assessed using a computer simulation of a high-bypass, dual-spool, commercial-type turbofan engine.

Active Compressor Stability Management via a Stall Margin Control Mode

2009 ◽  
Author(s):  
Yuan Liu ◽  
Manuj Dhingra ◽  
J. V. R. Prasad
Keyword(s):  
Pressure Fluctuations ◽  
Aircraft Engine ◽  
Rotating Stall ◽  
Control Mode ◽  
Engine Control ◽  
Correlation Measure ◽  
Stall Margin ◽  
Engine Control System ◽  
Compressor Rotor ◽  
Margin Control

An active engine control scheme for protection against compressor instabilities such as rotating stall and surge is presented. Compressor stability detection is accomplished via a parameter known as the correlation measure, which quantifies the repeatability of the pressure fluctuations in the tip region of a compressor rotor. This work investigates the integration of the correlation measure with an aircraft engine control system through the use of a stall margin control mode. The development and implementation of the stall margin mode is described. The effectiveness of the overall active control framework—an active compressor stability management system—is assessed using a computer simulation of a high-bypass, dual-spool, commercial-type turbofan engine.

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.

DIGATEC (Digital Gas Turbine Engine Control)

1968 ◽  
Author(s):  
J. E. Bayati ◽  
R. M. Frazzini
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Control Mode ◽  
Engine Control ◽  
Analog Simulation ◽  
Turbine Engine ◽  
Engine Control System ◽  
Discharge Temperature ◽  
Basic Operating ◽  
Experimental Runs

The basic operating principles of an electronic digital computer gas turbine engine control system are presented. Closed loop turbine discharge temperature and speed controls have been implemented; their feasibility was demonstrated through hybrid digital/analog simulation and actual tests of a GE J85 turbojet engine through the start mode to maximum afterburner. Control mode description and results of the analysis and experimental runs are given in this paper.

Development of HIDEC Adaptive Engine Control Systems

1987 ◽  
Vol 109 (2) ◽  
pp. 146-151
Author(s):  
R. J. Landy ◽  
W. A. Yonke ◽  
J. F. Stewart
Keyword(s):  
Integrated Control ◽  
Engine Performance ◽  
Control Mode ◽  
Engine Control ◽  
Engine Model ◽  
Engine Control System ◽  
Fuel Flow ◽  
Expected Performance ◽  
Propulsion Control ◽  
And Performance

The NASA Ames/Dryden Flight Research Facility is sponsoring a flight research program designated Highly Integrated Digital Electronic Control (HIDEC), whose purpose is to develop integrated flight-propulsion control modes and evaluate their benefits in flight on NASA F-15 test aircraft. The Adaptive Engine Control System (ADECS I) is one phase of the HIDEC program. ADECS I involves uptrimming the P&W Engine Model Derivative (EMD) PW1128 engines to operate at higher engine pressure ratios (EPR) and produce more thrust. In a follow-on phase, called ADECS II, a constant thrust mode will be developed which will significantly reduce turbine operating temperatures and improve thrust specific fuel consumption. A performance seeking control mode is scheduled to be developed. This mode features an onboard model of the engine that will be updated to reflect actual engine performance, accounting for deterioration and manufacturing differences. The onboard engine model, together with inlet and nozzle models, are used to determine optimum control settings for the engine, inlet, and nozzle that will maximize thrust at power settings of intermediate and above and minimize fuel flow at cruise. The HIDEC program phases are described in this paper with particular emphasis on the ADECS I system and its expected performance benefits. The ADECS II and performance seeking control concepts and the plans for implementing these modes in a flight demonstration test aircraft are also described. The potential payoffs for these HIDEC modes as well as other integrated control modes are also discussed.

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.

More Electric Engine Architecture for Aircraft Engine Application

2011 ◽  
Author(s):  
Noriko Morioka ◽  
Hitoshi Oyori ◽  
Daiki Kakiuchi ◽  
Kanji Ozawa
Keyword(s):  
Fault Tolerant ◽  
Fuel Efficiency ◽  
Reducing Power ◽  
Aircraft Engine ◽  
Engine Control ◽  
Pump System ◽  
Power Extraction ◽  
Engine Control System ◽  
Fuel Burn ◽  
Electric Engine

This paper describes the system design and evaluation of a noble MEE (More Electric Engine) system. The results show that the proposed MEE system can significantly reduce the fuel burn of engines and CO2 emissions from aircraft and also improve the safety, reliability and maintainability of engines. The MEE is advanced engine control technology utilizing recent innovations in electrical motors, motor controllers and power electronics. It replaces conventional engine accessories, such as AGB (Accessory Gear Box)-driven pumps, hydraulic actuators with electrical pumps and EMAs (Electro-Mechanical Actuators), which are powered by generators. The first step of the MEE is supposed to be the motor-driven fuel pump system, which can improve engine efficiency by reducing power extraction from the engine and eliminating ACOCs (Air-Cooled Oil Coolers) which worsen fuel efficiency by wasting fan discharge air. The goal of the MEE consists of eliminating the heavy AGB via electrical accessories and an engine-embedded starter/generator. The incorporation of a unique redundant Active-Active control architecture and a fault-tolerant design for the dual motor system successfully achieves a highly reliable and complete one fail operational/two fail safe engine control system.

Aeroelastic aspects of Axial Compressor Stage with Self-Recirculating Casing Treatment

2021 ◽  
pp. 1-34
Author(s):  
S Satish Kumar ◽  
Dilipkumar Bhanudasji Alone ◽  
Shobhavathy Thimmaiah ◽  
J Rami Reddy Mudipalli ◽  
Lakshya Kumar ◽  
...  
Keyword(s):  
Flow Condition ◽  
Axial Compressor ◽  
Rotating Stall ◽  
Successful Implementation ◽  
Compressor Stage ◽  
Stall Margin ◽  
Casing Treatment ◽  
Compressor Rotor ◽  
Forcing Function ◽  
Treatment Designs

Abstract For successful implementation of casing treatment designs in axial compressors, apart from the stall margin improvement benefits, aeroelasticity also plays a major role. This manuscript addresses the not often discussed aeroelastic aspects of a new discrete type of passive Self-Recirculating Casing Treatment (RCT) designed for a transonic axial compressor stage. Experiments are carefully designed for synchronized measurement of the unsteady fluidic disturbances and vibrations during rotating stall for compressor with baseline solid casing and Self-RCT. The modal characteristics of the axial compressor rotor-disk assembly are studied experimentally and numerically. Experimentally it is observed that the rotating stall cells excite the blades in their fundamental mode in a compressor with baseline solid casing at the stall flow condition. In contrast, there is no excitation of the blades in the compressor with self-recirculating casing treatment at the same solid casing stall flow condition. Also, the self-recirculating casing treatment compared to the solid casing can significantly reduce the overall vibration levels of the blades that are excited at the stall flow condition. The casing treatment is able to alter the flow field near the tip region of the rotor blade, and hence influencing the forcing function of the rotating cantilever blades to have the aeroelastic benefit.

The Effect of Speed Ratio on the First Rotating Stall Stage in Contra-Rotating Compressor

2012 ◽  
Author(s):  
Limin Gao ◽  
Xiaojun Li ◽  
Jian Xie ◽  
Bo Liu
Keyword(s):  
Weight Ratio ◽  
Aircraft Engine ◽  
Work Conditions ◽  
Rotating Stall ◽  
Speed Ratio ◽  
Stall Margin ◽  
Rotating Speed ◽  
Tip Leakage ◽  
Important Approach ◽  
The Impact

Since the structure and aerodynamic advantages of contra-rotating technology, it has been considered as an important approach to further improve the thrust-weight ratio of aircraft engine. In the present work, the impact of rotating speed ratio on the first rotating stall stage of a CRAC which consist of two counter-rotating rotors is investigated numerically. To detect the stall margin of CRAC exactly, the back pressure dichotomy method is developed, the grid indepence is verified and the performance is measured. A large number computation is carried out to explore the influence of rotating speed ratio on the performance of contra-rotating compressor. Finally the flow filed near blade tip is analyzed to find the relation between the rotating speed ratio and the first stall rotor. The result shows: (1) The work conditions of ROT1 have a significant impact on the aerodynamic performance of ROT2, while ROT2 play a little impact on the performance of ROT1. (2) At the condition of rotating speed ratio R2:R1≥0.9, the second rotor will be the first stall stage as the mass flow is decreased. (3) When the ROT2 rotating speed is slower than the ROT1, the intensity of tip leakage in ROT2 declines obviously with decreasing the rotating speed ratio, but the intensity of tip leakage in ROT1 has little changes. At the condition of R2:R1<0.9, the first rotor will be the first stall stage.

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