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High Temperature Propulsion System Structural Seals for Future Space Launch VehiclesHigh temperature, dynamic structural seals are required in advanced hypersonic engines to seal the perimeters of movable engine ramps for efficient, safe operation in high heat flux environments at temperatures from 2000 to 2500 F. NASA GRC became involved in the development of high temperature structural seals in the late 1980 s and early 1990 s during the National Aerospace Plane (NASP) program. Researchers at GRC carried out an in-house program to develop seals for the NASP hypersonic engine and oversaw industry efforts for airframe and propulsion system seal development for this vehicle. The figure shows one of the seal locations in the NASP engine. Seals were needed along the edges of movable panels in the engine to seal gaps between the panels and adjacent engine sidewalls. Seals developed during the NASP program met many requirements but fell short of leakage, durability, and resiliency goals. Due to program termination the seals could not be adequately matured. To overcome these shortfalls, GRC is currently developing advanced seals and seal preloading devices for the hypersonic engines of future space vehicles as part of NASA s Next Generation Launch Technology (NGLT) program.
Document ID
20040182410
Document Type
Conference Paper
Authors
Dunlap, Patrick H., Jr. (NASA Glenn Research Center Cleveland, OH, United States)
Steinetz, Bruce M. (NASA Glenn Research Center Cleveland, OH, United States)
DeMange, Jeffrey J. (Toledo Univ. OH, United States)
Date Acquired
September 7, 2013
Publication Date
September 1, 2004
Publication Information
Publication: 2003 NASA Seal/Secondary Air System Workshop, Volume 1
Subject Category
Spacecraft Propulsion and Power
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle20040182396Analytic Primary2003 NASA Seal/Secondary Air System Workshop