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Combustion Dynamics Characteristics and Fuel Pressure Modulation Responses of a Three-Cup Third-Generation Swirl-Venturi Lean Direct Injection Combustion ConceptThis paper presents the combustion dynamic data and fuel modulation response of a three-cup Lean Direct Injection combustor developed by Woodward, FST. The test was conducted at the NASA Glenn Research Center CE-5 flame tube test facility. The facility provided inlet air up to 922 K and pressure up to 19.0 bar. At the low-power configuration, the combustion noise was quiet. Large combustion pressure oscillations were observed with the High-power configuration at an off design condition, with low inlet air temperature and pressure conditions and a high equivalence ratio (about T3=600 K, P3 = 800 kPa, and ER =0.46). The noise amplitude was as high as 1.5 psi at around 220 Hz. As inlet air pressure and temperature increased, this combustion instability decreased. Fuel modulated signals were produced with the WASK fuel modulator located in the fuel line upstream of the center cup pilot fuel-air mixer. The amplitudes of the modulated signals detected in the combustor were low. Only less than 0.13% (0.06 psi) of the input energy was detected, and the signal amplitudes decreased as the modulated frequencies increased. Interaction between the modulated signals and the combustion noise varied with operating conditions. At a condition with low combustion noise around 150 hz, modulating a signal at around the same frequency would increase the combustion noise from 0.2 psi to as high as 0.6 psi, whereas at a condition with a high combustion instability around 250 hz, the modulated signal did not seem to have much effect on the combustion noise.
Document ID
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
He, Zhuohui J.
(NASA Glenn Research Center Cleveland, OH, United States)
Saus, Joseph R.
(NASA Glenn Research Center Cleveland, OH, United States)
Thomas, Randy
(NASA Glenn Research Center Cleveland, OH, United States)
Kopasakis, George
(NASA Glenn Research Center Cleveland, OH, United States)
Lee, F. P.
(Woodward FST, Inc. Zeeland, MI, United States)
Dam, B.
(Woodward FST, Inc. Zeeland, MI, United States)
Date Acquired
April 8, 2020
Publication Date
April 1, 2020
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Funding Number(s)
WBS: 081876.
Distribution Limits
Public Use Permitted.
Technical Review
Single Expert
Fuel flexible combustor
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