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Forced Mixer Nozzle OptimizationComputational fluid dynamic (CFD) and computational acoustic analyses (CAA) were performed for a TFE731-40 compound nozzle, a TFE731-60 mixer nozzle and an Energy Efficient Engine (E(sup 3)) mixer nozzle for comparison with available data. The CFD analyses were performed with a three dimensional, Navier-Stokes solution of the flowfield on an unstructured grid using the RAMPANT program. The CAA analyses were performed with the NASA Glenn MGB program using a structured grid. A successful aerodynamic solution for the TFE731-40 compound nozzle operating statically was obtained, simulating an engine operating on a test stand. Analysis of the CFD results of the TFE731-40 with the MGB program produced predicted sound power levels that agree quite well with the measured data front full-scale static engine tests. Comparison of the predicted sound pressure with the data show good agreement near the jet axis, but the noise levels are overpredicted at angles closer to the inlet. The predicted sound power level for the TFE731-60 did not agree as well with measured static engine data as the TFE731-40. Although a reduction in the predicted noise level due to the mixed flow was observed, the reduction was not as significant as the measured data. The analysis of the V2 mixer from the E(sup 3) study showed that peak temperatures predicted in the mixer exit flowfield were within 5 percent of the values measured by the exit probes. The noise predictions of the V2 mixer nozzle tended to be 3-5 dB higher in peak noise level than the measurements. In addition, the maximum frequency of the noise was also overpredicted. An analysis of the 3 candidate mixer nozzle configurations demonstrated the feasibility of using centerbody lobes and porosity to improve mixing efficiency. A final configuration was designed with a predicted thermal mixing efficiency that was 5 percent higher than the 3 candidate mixers. The results of the MGB noise calculations show that the final design will exceed the design goal of a 3 dB reduction in noise as compared to the baseline TFE731-40.
Document ID
19990097978
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Sheoran, Yogi
(Allied-Signal Engines Phoenix, AZ United States)
Hoover, Robert
(Allied-Signal Engines Phoenix, AZ United States)
Schuster, William
(Allied-Signal Engines Phoenix, AZ United States)
Anderson, Morris
(Allied-Signal Engines Phoenix, AZ United States)
Weir, Donald S.
(Allied-Signal Engines Phoenix, AZ United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1999
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.26:209160
NASA/CR-1999-209160
E-11723
Report Number: NAS 1.26:209160
Report Number: NASA/CR-1999-209160
Report Number: E-11723
Funding Number(s)
PROJECT: RTOP 538-03-11
CONTRACT_GRANT: NAS3-27483
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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