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Development of hypersonic engine seals - Flow effects of preload and engine pressuresA new type of engine seal is being developed to meet the needs of advanced hypersonic engines. A seal braided of emerging high temperature ceramic fibers comprised of a sheath-core construction has been selected for study based on its low leakage rates. Flexible, low-leakage, high-temperature seals are required to seal the movable engine panels of advanced ramjet-scramjet engines either preventing potentially dangerous leakage into backside engine cavities or limiting the purge coolant flow rates through the seals. To predict the leakage through these flexible, porous seal structures as a function of preload and engine pressures, new analytical flow models are required. An empirical leakage resistance/preload model is proposed to characterize the observed decrease in leakage with increasing preload. Empirically determined compression modulus and preload factor are used to correlate experimental leakage data for a wide range of seal architectures. Good agreement between measured and predicted values are observed over a range of engine pressures and seal preload.
Document ID
19930065844
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cai, Zhong
(NASA Lewis Research Center Cleveland, OH, United States)
Mutharasan, Rajakkannu
(NASA Lewis Research Center Cleveland, OH, United States)
Ko, Frank K.
(Drexel Univ. Philadelphia, PA, United States)
Steinetz, Bruce M.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Mechanical Engineering
Report/Patent Number
AIAA PAPER 93-1998
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: June 28, 1993
End Date: June 30, 1993
Sponsors: AIAA, SAE, ASME, ASEE
Accession Number
93A49841
Distribution Limits
Public
Copyright
Other

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