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 Development of HIDEC Adaptive Engine Control Systems

1986 ◽  
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 the 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 pay-offs for these HIDEC modes as well as other integrated control modes are also discussed.

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.

Design and Performance of a Controlled Turbocharging System on Marine Diesel Engines

2006 ◽  
Author(s):  
Ioannis Vlaskos ◽  
Ennio Codan ◽  
Nikolaos Alexandrakis ◽  
George Papalambrou ◽  
Marios Ioannou ◽  
...  
Keyword(s):  
Steady State ◽  
Engine Performance ◽  
Operating Conditions ◽  
Electric Actuator ◽  
Engine Simulation ◽  
Engine Control System ◽  
Turbocharging System ◽  
Compressor Impeller ◽  
Marine Diesel ◽  
And Performance

The paper describes the design process for a controlled pulse turbocharging system (CPT) on a 5 cylinder 4-stroke marine engine and highlights the potential for improved engine performance as well as reduced smoke emissions under steady state and transient operating conditions, as offered by the following technologies: • controlled pulse turbocharging, • high pressure air injection onto the compressor impeller as well as into the air receiver, and • an electronic engine control system, including a hydraulic powered electric actuator. Calibrated engine simulation computer models based on the results of tests performed on the engine in its baseline configuration were used to design the CPT components. Various engine tests with CPT under steady state and transient operating conditions show the engine optimization process and how the above-mentioned technologies benefit engine behavior in both generator and propeller law operation.

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.

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.

Generic Airplane and Aero-Engine Simulation Procedures for Exhaust Emission Studies

2007 ◽  
Author(s):  
Savad A. Shakariyants ◽  
Jos P. van Buijtenen ◽  
Wilfried P. J. Visser ◽  
Alexander Tarasov
Keyword(s):  
Engine Performance ◽  
Exhaust Emission ◽  
Validation Data ◽  
Emission Analysis ◽  
Engine Simulation ◽  
Fuel Flow ◽  
And Performance ◽  
Aero Engines ◽  
Emission Studies

The paper presents generic simulation procedures for air-planes and aero-engines to support in-flight exhaust emission studies. They take a detailed account of the vehicle aerodynamics and performance as well as engine performance during typical flight missions. The procedures are coupled via lookup tables containing engine data for standard thrust settings. The models and their applicability to emission analysis were tested in a case study for a long-haul airliner with two large turbofans. The Boeing Method 2 fuel flow methodology [1] was selected as a test pollutants model. CO2 and H2O were found by directly linking them to the fuel flow via constant emission indexes. The case study first proved the accuracy of the airplane and engine models by matching available validation data. Secondly, it demonstrated the possibilities of evaluating exhaust emissions at different segments of a flight mission. Both emission profiles and the cumulative environmental footprint of the mission were estimated. The paper concludes by applying the models for the analysis of engine exhaust under varying flight conditions and engine deterioration. This can be used as a tool for optimizing operational procedures for emission reduction and assessing the environmental performance of an aging fleet.

Model Based Control Concepts for Jet Engines

2001 ◽  
Author(s):  
Klaus Lietzau ◽  
Andreas Kreiner
Keyword(s):  
Turbine Blades ◽  
Engine Performance ◽  
Current Control ◽  
Engine Control ◽  
Jet Engines ◽  
Jet Engine ◽  
Engine Model ◽  
Model Based ◽  
Safety Margins ◽  
Engine Life

Many jet engine variables cannot be measured in-flight or can only be measured with a complex, and hence unreliable, instrumentation system. This includes variables that are of imminent importance for the safe operation of the engine or for engine life, such as the temperature of the high pressure turbine blades or the surge margins of the turbo compressors, for instance. Current control systems therefore transform limits on these variables into limits on other variables measured by the engine’s sensors. This leads to increased safety margins and thus to non-optimal engine performance. An onboard engine model incorporated into the engine control system could provide information about all engine variables. This could enable further control and monitoring system optimisations leading to improved engine performance, reduced fuel consumption, increased safety and engine life. This paper explains the principle of model based engine control and gives an overview about possible applications for conventional and also thrust vectored jet engines. Modeling methods for real-time simulation as well as methods for online model adaptation are presented. The potential of model based jet engine control is analyzed and fortified by some prototype realizations.

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.

scholarly journals Marine Dual Fuel Engine Control System Modelling and Safety Implications Analysis

2018 ◽  
Author(s):  
G Theotokatos ◽  
S Stoumpos ◽  
B Bolbot ◽  
E Boulougouris ◽  
D Vassalos
Keyword(s):  
Control System ◽  
Operating Mode ◽  
Dual Fuel ◽  
Published Data ◽  
System Modelling ◽  
Engine Control ◽  
Engine Model ◽  
Engine Control System ◽  
Compressor Surge ◽  
Gate Control

The present study focuses on the modelling of a marine dual fuel engine and its control system with an aim to study the engine response at transient conditions and identify and discuss potential safety implications. This investigation is based on an integrated engine model developed in GT-ISE™ software, capable of predicting the steady state performance as well as the transient response of the engine. This model includes the appropriate modules for realising the functional modelling of the engine control system to implement the ordered engine load changes as well as switching the engine operating mode. The developed model is validated against available published data. Subsequently, two test cases with fuel changes, from gas to diesel and diesel to gas were simulated and the derived results were analysed for investigating the safety implications that may arise during operation. The results showed that the matching of the engine and the turbocharger as well as the exhaust gas waste gate control are critical factors for ensuring compressor surge free operation during fuel changes. 

A Step Further on the Control of Acceleration of Gas Turbines With Controlled Variable Geometry and Combustion Emissions

2014 ◽  
Author(s):  
João Roberto Barbosa ◽  
Cleverson Bringhenti ◽  
Jesuíno Takachi Tomita
Keyword(s):  
Control System ◽  
Gas Turbines ◽  
Time Interval ◽  
Variable Geometry ◽  
Engine Control ◽  
Control Logic ◽  
Convergent Nozzle ◽  
Fuel Flow ◽  
Combustion Emissions ◽  
And Performance

The paper aim is to study the transient performance using fuel flow schedule, variable geometry compressor control and combustion emissions for a simple turbojet engine in a thrust class of 5kN. This engine is under development, it was designed, manufactured and are being tested in test bench, it is composed by a 5-stage axial flow compressor, an annular combustor, an uncooled turbine and a convergent nozzle. The engine was originally designed to run on kerosene but other types of fuels, as biofuels, are intended to be used, having in mind a turboshaft in a class of 1.2 MW for power generation purpose. PID control is being studied to determine the appropriate setting of the VIGV in conjunction with a prescribed fuel flow injection necessary to accelerate, or decelerate, the engine from 80% to full thrust in a prescribed time interval. The engine control system is being studied during this engine design phase, so that all the components characteristics needed are being synthesized using in-house developed computer codes: compressor design and performance; combustion chamber design and performance; turbine design and performance; whole engine performance. The engine is required to accelerate from 80% to full thrust in a short time interval, which is also a limitation imposed to the control system. Compressor surge margin is controlled during accelerations using controlled positioning of the VIGV at each engine speed. The engine running lines, for accelerations and decelerations are shown and commented. They served as basis for the design of the engine control logic and hardware. The combustor was designed for kerosene, but other types of fuels can be burned, with the lower heating value and all the necessary parameters recalculated using reaction mechanisms, reactor network and stability loops approach.

Sign in / Sign up

Export Citation Format

Share Document