NTRS - NASA Technical Reports Server

Back to Results
A hot dynamic seal rig for measuring hypersonic engine seal durability and flow performanceA test fixture for measuring the dynamic performance of candidate high-temperature engine seal concepts has been installed at NASA Lewis Research Center. The test fixture has been designed to evaluate seal concepts under development for advanced hypersonic engines, such as those being considered for the National Aerospace Plane (NASP). The fixture can measure dynamic seal leakage performance from room temperature up to 840 C (1550 F) and air pressure differentials up to 690 kPa (100 psi). Performance of the seals can be measured while sealing against flat or distorted walls. In the fixture two seals are preloaded against the sides of a 30 cm (1 ft) long saber that slides transverse to the axis of the seals, simulating the scrubbing motion anticipated in these engines. This report covers the capabilities of this test fixture along with preliminary data showing the dependence of seal leakage performance on high temperature cycling.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Miller, Jeffrey H.
(Sverdrup Technology, Inc. Brook Park, OH, United States)
Steinetz, Bruce M.
(NASA Lewis Research Center Cleveland, OH, United States)
Sirocky, Paul J.
(Sverdrup Technology, Inc. Brook Park, OH, United States)
Kren, Lawrence A.
(Case Western Reserve Univ. Cleveland, OH, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 1 (A93-33876 1
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Mechanical Engineering
Report/Patent Number
AIAA PAPER 93-1346
Accession Number
Distribution Limits

Available Downloads

There are no available downloads for this record.
No Preview Available