Active-control Technologies for Aircraft Engines PDF Download
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Author: Stephen J. Przybylko
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Stephen J. Przybylko
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN: 9789283700180
Category : Vehicles, Military
Languages : en
Pages :
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Author: Link C. Jaw
Publisher: AIAA Education
ISBN: 9781600867057
Category : Technology & Engineering
Languages : en
Pages : 0
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Overview of engine control systems -- Engine modeling and simulation -- Model reduction and dynamic analysis -- Design of set-point controllers -- Design of transient and limit controllers -- Control system integration -- Advanced control concepts -- Engine monitoring and health management -- Integrated control and health monitoring -- Appendix A. Fundamentals of automatic control systems -- Appendix B. Gas turbine engine performance and operability.
Author:
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Category :
Languages : en
Pages : 0
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The Symposium analyzed the potential of active control technology for the performance demands of future vehicles and engines. in particular high maneuverability, lower specific fuel consumption, higher power-to-weight ratios and lower life-cycle cost. Performance, stability, control, fluid dynamics, structural and engine layout questions were dealt with in 5 keynotes and 77 papers. The following sessions were held: Boundary Layer Control, Active Flow Control of Nozzle/jet, Drag and Buffet Control, Noise Control, Vortex Control, Flight Vehicle Active Control, Smart Structures Applications, Active Control Technology For Load Alleviation, Active Elements for Structural Design, Active Materials and Applications, Applications Overview, Compressor Stall/ Surge - Measurements, Compressor Stall/Surge - Control, Combustion Instabilities - Measurements and Predictions, Combustion Instabilities - Control Fundamentals, Combustion Instabilities - Control Applications. The Symposium was organized by the Applied Vehicle Technology Panel (AVT).
Author: John C. Delaat
Publisher: BiblioGov
ISBN: 9781289111984
Category :
Languages : en
Pages : 24
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Book Description
Future aircraft engines must provide ultra-low emissions and high efficiency at low cost while maintaining the reliability and operability of present day engines. The demands for increased performance and decreased emissions have resulted in advanced combustor designs that are critically dependent on efficient fuel/air mixing and lean operation. However, all combustors, but most notably lean-burning low-emissions combustors, are susceptible to combustion instabilities. These instabilities are typically caused by the interaction of the fluctuating heat release of the combustion process with naturally occurring acoustic resonances. These interactions can produce large pressure oscillations within the combustor and can reduce component life and potentially lead to premature mechanical failures. Active Combustion Control which consists of feedback-based control of the fuel-air mixing process can provide an approach to achieving acceptable combustor dynamic behavior while minimizing emissions, and thus can provide flexibility during the combustor design process. The NASA Glenn Active Combustion Control Technology activity aims to demonstrate active control in a realistic environment relevant to aircraft engines by providing experiments tied to aircraft gas turbine combustors. The intent is to allow the technology maturity of active combustion control to advance to eventual demonstration in an engine environment. Work at NASA Glenn has shown that active combustion control, utilizing advanced algorithms working through high frequency fuel actuation, can effectively suppress instabilities in a combustor which emulates the instabilities found in an aircraft gas turbine engine. Current efforts are aimed at extending these active control technologies to advanced ultra-low-emissions combustors such as those employing multi-point lean direct injection.
Author:
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ISBN:
Category :
Languages : en
Pages : 16
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Author: National Research Council (U.S.). Committee on Aeronautical Technologies
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 21
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Author: Marcus H. Richman
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
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The U.S. Navy, as a participant in the United States' Integrated High Performance Turbine Engine Technology (IHPTET) initiative, is dedicated to increasing aircraft engine performance to satisfy the propulsion requirements of future Navy aircraft. This is accomplished by identifying the propulsion requirements, in terms of performance and total cost, for specific Navy aircraft. The required engine technology advances are then broken down into specific engine component technology objectives. Advanced technology is then developed on the component level. Once an appropriate level of readiness is reached, the components are then assembled into an engine for overall advanced propulsion system demonstration. Technologies from this demonstrator engine are then made available to development engine programs, such as the Joint Strike Fighter (JSF), for further development and eventual transition to production engine programs.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721588237
Category :
Languages : en
Pages : 30
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Active control of high-frequency (greater than 500 Hz) combustion instability has been demonstrated in the NASA single-nozzle combustor rig at United Technologies Research Center. The combustor rig emulates an actual engine instability and has many of the complexities of a real engine combustor (i.e. actual fuel nozzle and swirler, dilution cooling, etc.) In order to demonstrate control, a high-frequency fuel valve capable of modulating the fuel flow at up to 1kHz was developed. Characterization of the fuel delivery system was accomplished in a custom dynamic flow rig developed for that purpose. Two instability control methods, one model-based and one based on adaptive phase-shifting, were developed and evaluated against reduced order models and a Sectored-1-dimensional model of the combustor rig. Open-loop fuel modulation testing in the rig demonstrated sufficient fuel modulation authority to proceed with closed-loop testing. During closed-loop testing, both control methods were able to identify the instability from the background noise and were shown to reduce the pressure oscillations at the instability frequency by 30%. This is the first known successful demonstration of high-frequency combustion instability suppression in a realistic aero-engine environment. Future plans are to carry these technologies forward to demonstration on an advanced low-emission combustor. Corrigan, Bob (Technical Monitor) and DeLaat, John C. and Chang, Clarence T. Glenn Research Center NASA/TM-2003-212611, E-14169, NAS 1.15:212611, ISABE-2003-1054
