Aircraft Turbine Engine Control Research at NASA Glenn Research Center

Garg, Sanjay

doi:10.1061/(asce)as.1943-5525.0000296

Cited by 65 publications

(45 citation statements)

References 37 publications

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“…-Single-input single-output (SISO) control algorithm -Min-Max or cascade control algorithm -Advanced control algorithm -More electric and electronic control algorithm A. Single-input single-output (SISO) control algorithm During this period much research was carried out at scientific centers, two of them being General Electric and NASA. 112 They are the first type of time controller and are briefly discussed below in A-1 and, subsequently, the most important developments from this era are dwelt upon in sections A-2 to A-7.…”

Section: A Historical Review Of Gas Turbine Engine Controlmentioning

confidence: 99%

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A scientometric analysis and critical review of gas turbine aero-engines control: From Whittle engine to more-electric propulsion

Mohammadi

Fashandi

Jafari

et al. 2020

Measurement and Control

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The gas turbine aero-engine control systems over the past eight decades have been thoroughly investigated. This review purposes are to present a comprehensive reference for aero-engine control design and development based on a systematic scientometric analysis and to categorize different methods, algorithms, and approaches taken into account to improve the performance and operability of aircraft engines from the first days to present to enable this challenging technology to be adopted by aero-engine manufacturers. Initially, the benefits of the control systems are restated in terms of improved engine efficiency, reduced carbon dioxide emissions, and improved fuel economy. This is followed by a historical coverage of the proposed concepts dating back to 1936. A comprehensive scientometric analysis is then presented to introduce the main milestones in aero-engines control. Possible control strategies and concepts are classified into four distinct phases, including Single input- single output control algorithms, MIN-MAX or Cascade control algorithms, advanced control algorithms, More-electric and electronic control algorithms and critically reviewed. The advantages and disadvantages of milestones are discussed to cover all practical aspects of the review to enable the researchers to identify the current challenges in aircraft engine control systems.

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Section: A Historical Review Of Gas Turbine Engine Controlmentioning

confidence: 99%

“…Engine altitude testing performed at the Global Research Center. 112 The main controller achievements were:…”

Section: A Historical Review Of Gas Turbine Engine Controlmentioning

confidence: 99%

A scientometric analysis and critical review of gas turbine aero-engines control: From Whittle engine to more-electric propulsion

Mohammadi

Fashandi

Jafari

et al. 2020

Measurement and Control

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“…Digital control systems therefore exhibited predictable product systemic interdependencies, since such interdependencies were managed by the interface software [4]. DEEC was initially tested and evaluated by the NASA Dryden Flight Research Center from 1981 to 1983 in a joint endeavor with engine manufacturer Pratt and Whitney, the U.S. Air Force, and NASA's Lewis Research Center (now the NASA Glenn Research Center) [11].The DEEC was developed for the Pratt and Whitney F100 turbofan engine, but its technology is now incorporated on other engine models. The DEEC replaced the F100 test engine's standard control system and had full control authority over a variety of engine functions.…”

Section: Digital Electronic Engine Control (Deec)mentioning

confidence: 99%

“…The DEEC replaced the F100 test engine's standard control system and had full control authority over a variety of engine functions. Development of the DEEC is looked upon asa milestone in propulsion control, and a major transition from hydro mechanical to digital control.Benefits of the system are substantial and include reduced operating and maintenance costs, plus major boosts in engine performance and extended engine life [11].…”

Section: Digital Electronic Engine Control (Deec)mentioning

confidence: 99%

Aircraft turbine engine control systems development: Historical perspective

Lutambo

Wang

Yue

et al. 2015

2015 34th Chinese Control Conference (CCC)

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This paper describes the development of aircraft turbine engine control systems from the historical point of view to the present. With the increasing emphasis on aircraft safety, enhanced performance, and affordability, as well as the need to reduce the environmental effect caused by aircraft, there are many new challenges being faced by the designers of aircraft propulsion systems. The paper provides an overview of the various technological development activities in aircraft engine control and diagnostics, both current and some accomplished in the recent past. The motivations for each of the research efforts, the research approach, technical challenges, and the key progress to date are summarized.

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“…3 Under the Small Business Innovative Research (SBIR) program, Sporian Microsystems has developed high-temperature operable, corrosion-resistant pressure/temperature sensor suites and electronics packaging for in situ measurement in propulsion and power generation applications. 4…”

Section: Introductionmentioning

confidence: 99%

Demonstration of Smart, High-Temperature Pressure Sensors in an Engine Harsh EnvironmentDemonstration of Smart, High-Temperature Pressure Sensors in an Engine Harsh Environment

Usrey¹,

Knowles²,

Brand³

et al. 2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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Gas turbine engine efficiency, safety, and life cycle cost are directly influenced by the durability and performance of the turbine hot section. Numerous advances have been applied to improve the capabilities of turbines including new structural materials, innovative thermal barrier coatings, and advanced heat transfer techniques; however, improved designs are still dependent on accurate knowledge of true turbine environmental conditions during operation. In conjunction with ongoing advances in physics-based modeling, physical measurement of actual turbine conditions remains a necessity. The Small CAESAR project supports the demonstration and maturation of advanced components, including sensors, under the VAATE program. Sporian Microsystems provided smart pressure/temperature sensor suite probes for testing under Small CAESAR. These probes survived in situ conditions in three engine locations: compressor discharge, high pressure turbine inlet and low pressure turbine inlet, in a test designed to demonstrate TRL 6. Nomenclature% = Percent °C = Degree Celsius °F = Degree Fahrenheit A = Amp BNC = Bayonet Neill-Concelman CAESAR = Component and Engine Structural Assessment Research CAD = Computer Aided Design DC = Direct Current DEC = Distributed Engine Control DECWG = Distributed Engine Controls Working Group DIRCT = Distributed Intelligent Robust Controls Technologies EGT = Exhaust Gas Temperature ERA = Environmentally Responsible Aviation FADEC = Full Authority Digital Engine Control

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Aircraft Turbine Engine Control Research at NASA Glenn Research Center

Cited by 65 publications

References 37 publications

A scientometric analysis and critical review of gas turbine aero-engines control: From Whittle engine to more-electric propulsion

A scientometric analysis and critical review of gas turbine aero-engines control: From Whittle engine to more-electric propulsion

Aircraft turbine engine control systems development: Historical perspective

Demonstration of Smart, High-Temperature Pressure Sensors in an Engine Harsh EnvironmentDemonstration of Smart, High-Temperature Pressure Sensors in an Engine Harsh Environment

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