Intelligent Life-Extending Controls for Aircraft Engines

Guo, Ten-Huei; Chen, Philip; Jaw, Link C.

doi:10.2514/6.2004-6468

Cited by 15 publications

(9 citation statements)

References 8 publications

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“…Then NASA Glenn Research Center used the Thermo-Mechanical Fatigue (TMF) of a critical component to demonstrate how a LEC can drastically reduce the engine life usage with minimum sacrifice in performance. Simulation results showed that LEC could ensure that the engine basic I performance does not lose or lose a small amount, while the selected component life increases by nearly 30% [8,9] . While Daniel T, Jensen used model predictive control to extend the life of the gas turbine system [10] .…”

Section: Instructionmentioning

confidence: 99%

Adaptive Life Extending Control of Aircraft Engine

Guo¹,

Chen²,

Du³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Current Life Extending Control (LEC) aims to extend engine life with minimum sacrifice in performance. However, it does not take the engine-performance degradation into account. When engine-performance degrades, its acceleration performance reduces. Keeping on using the current LEC designed for no-degradation engine may extend the engine life with substantial sacrifice in performance, and then make the engine not meet the normal needs when the engine degrades. In order to solve the problem, this paper analyzes the effect of current LEC on the engine acceleration and the life of selected engine component firstly. On this basis, the adaptive life extending control of aircraft engine is proposed. It could adjust the LEC law according to the engine-performance degradation. Moreover, the adaptive LEC system structure is built, which could evaluate engine-performance degradation in real time and provide proper LEC law for various engine-performance degradations through interpolation. The simulation results show that adaptive life extending control system could choose appropriate LEC limit line according to current engine-performance status, which could extend component life and maintain the engine acceleration performance in the whole life. Nomenclature N l =Fan speed N l Design ， =Fan speed at design point 41,max T =Highest temperature of turbine inlet max T  =Maximum temperature difference before and after the high-pressure turbine vane   t =Total strain ' N f =Thermo-Mechanical Fatigue (TMF) life of the high-pressure turbine vane T stable =Settling time of low-pressure rotor T rise =Rise time of low-pressure rotor I. Instructionn recent years, with the upgrading of aircraft engine electronic controller, intelligent control was incorporated into the study of aircraft engine control systems, where life extending control was one of them [1,2] . Lorenzo et al. first introduced LEC in the early 1990s [3][4][5] , which was applied to the Space Shuttle Main Engine (SSME).Guo Ten-huei elaborated several common LEC methods of the aircraft engine, and described the basic structure and key technologies of LEC [6,7] . Then NASA Glenn Research Center used the Thermo-Mechanical Fatigue (TMF) of a critical component to demonstrate how a LEC can drastically reduce the engine life usage with minimum sacrifice in performance. Simulation results showed that LEC could ensure that the engine basic I Downloaded by KUNGLIGA TEKNISKA HOGSKOLEN KTH on August 11, 2015 | http://arc.aiaa.org |

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Section: Instructionmentioning

confidence: 99%

Adaptive Life Extending Control of Aircraft Engine

Guo¹,

Chen²,

Du³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…The controller used in this simulation effort is an extension the controller described in [9] based on the NASA's Modular Aerospace Propulsion System Simulation (MAPSS). The simulated controller has been extended to implement and validate LEC concepts suggested by Guo, et.al in [6] to optimize engine spool acceleration schedules in order to mitigate damage due to TMF. A block diagram of the simulation setup is shown in Figure 1.…”

Section: Simulation Setupmentioning

confidence: 99%

“…3) Optimization of the acceleration schedules was performed using an ad hoc iterative approach. The optimization accomplished by Guo [6] requires not only a rise time input, but also a damage model. The acceleration schedule selected for the Air Force model meets the form and function of Guo's [6] and is shown in Figure 2.…”

Section: )mentioning

confidence: 99%

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A Feasibility Study of Life-Extending Controls for Aircraft Turbine Engines Using a Generic Air Force Model

Behbahani

Jordan

Millar

2006

Volume 2: Aircraft Engine; Ceramics; Coal, Biomass and Alternative Fuels; Controls, Diagnostics and Instrumentation; Environmen

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Turbine engine controllers are typically designed and operated to meet required or desired performance criterion within stability margins, while maximizing fuel efficiency. The U.S. Air Force turbine engine research program is seeking to incorporate sustainable cost reduction into this approach, by considering a life-cycle design objective if the life of the engine is considered as an objective during the design of the engine controller. Specifically during aircraft takeoff, the turbine engines are subject to high temperature variations that aggravate the stress of the material used in their construction and thus a negative effect in their life spans. Therefore, the control strategy needs to be re-evaluated to include operating cost, and extending the life of the engine is one way to reduce that. Life-Extending Control (LEC) is an area that deals with control action, engine component life usage, and designing an intelligent control algorithm embedded in the FADEC. This paper evaluates the LEC, based on critical components research, to demonstrate how an intelligent engine control algorithm can drastically reduce the engine life usage, with minimum sacrifice in performance. Finally, a generic turbine engine is extensively simulated using a sophisticated non-linear model of the turbine engine. The paper concludes that LEC is worth consideration and further research should include development of the damage models for turbine engines, and experimental research that could correlate the damage models to actual damage for turbine engines. This could lead to implementation of online damage models in real-time that will allow for more robust damage prevention.

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“…With the software development, the object-oriented modeling and simulation is more close to physical skeleton of the component and also makes the simulation more efficient. In reference [8], AMESim, a modeling and simulation platform of the physical meaning of components especially in hydraulic or mechanical system, has been used to simulate anti surge and oil switching, guide vane control in the field of aero-engine. But little research on control characteristics of hydraulic components of the afterburner fuel and spout control system has been carried out [9]- [15].…”

Section: Introductionmentioning

confidence: 99%

Object-oriented simulation research on components of inner fuel main pipe in aero-engine

Wang

Zhou

Yang

et al. 2010

2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics

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In order to find the control characteristics of fuel flow rate of inner fuel main pipe in aero-engines, the influences of parameters on the flow rate need to be studied systematically. This paper uses object-oriented AMESim to investigate modelling and simulation of the main control components. Modeling methods of components such as electrohydraulic servo valve, pressure difference valve and flow metering valve are obtained, and then the steady, dynamic properties of fuel flow rate influenced by the main designing parameters are studied. The results show that AMESim is an excellent platform for modeling and simulation of the actuating and controlling mechanism in aero-engine fuel control system. Generally, control performance of the flow metering valve with a constant pressure difference satisfies the requirements. It is also shown that for pressure difference valve, the diameter of restrictor in spring chamber has a great influence on the dynamics of outlet pressure. AMESim research results can provide theoretical foundation for the design of either control systems or relating components.

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Intelligent Life-Extending Controls for Aircraft Engines

Cited by 15 publications

References 8 publications

Adaptive Life Extending Control of Aircraft Engine

Adaptive Life Extending Control of Aircraft Engine

A Feasibility Study of Life-Extending Controls for Aircraft Turbine Engines Using a Generic Air Force Model

Object-oriented simulation research on components of inner fuel main pipe in aero-engine

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