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| Title: |
Innovative Adaptive Control Method Demonstrated for Active Suppression of Instabilities in Engine Combustors
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| Author(s): |
Kopasakis, George
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| Abstract: |
This year, an improved adaptive-feedback control method was demonstrated that suppresses thermoacoustic instabilities in a liquid-fueled combustor of a type used in aircraft engines. Extensive research has been done to develop lean-burning (low fuel-to-air ratio) combustors that can reduce emissions throughout the mission cycle to reduce the environmental impact of aerospace propulsion systems. However, these lean-burning combustors are susceptible to thermoacoustic instabilities (high-frequency pressure waves), which can fatigue combustor components and even downstream turbine blades. This can significantly decrease the safe operating life of the combustor and turbine. Thus, suppressing the thermoacoustic combustor instabilities is an enabling technology for meeting the low-emission goals of the NASA Ultra-Efficient Engine Technology (UEET) Project.
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| NASA Center: |
Glenn Research Center
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| Publication Date: |
June 2005
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| Document Source: |
CASI |
| Online Source: |
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| Document ID: |
20050215693
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| Publication Information: |
Research and Technology 2004, Number of Pages = 4 |
| Price Code: |
A01 |
| Keywords: |
ADAPTIVE CONTROL; COMBUSTION CHAMBERS; FEEDBACK CONTROL; FUEL-AIR RATIO; PROPULSION SYSTEM PERFORMANCE; ENVIRONMENTAL SURVEYS; ELASTIC WAVES; PROPULSION SYSTEM CONFIGURATIONS; SPACECRAFT PROPULSION; STABILITY; TURBINE BLADES;
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| Accessibility: |
Unclassified; No Copyright; Unlimited; Publicly available; |
| Updated/Added to NTRS: |
2008-06-02 |
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