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A Test Fixture For Measuring High Temperature Hypersonic Engine Seal Performance
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781725054509 Total Pages :36 pages Book Rating :4.0/5 (545 download)
Book Synopsis A Test Fixture for Measuring High-Temperature Hypersonic-Engine Seal Performance by : National Aeronautics and Space Administration (NASA)
Download or read book A Test Fixture for Measuring High-Temperature Hypersonic-Engine Seal Performance written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-10 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test fixture for measuring the performance of several high temperature engine seal concepts was installed at the NASA Lewis Research Center. The test fixture was developed to evaluate seal concepts under development for advanced hypersonic engines such as those being considered for the National Aerospace Plane. The fixture can measure static seal leakage performance from room temperature up to 1500 F and air pressure differentials up to 100 psi. Performance of the seals can be measured while sealing against flat or engine simulated distorted walls, where distortions can be as large as 0.150 in. in only an 18 in. span. The fixture is designed to evaluate seals 3 feet long, a typical engine panel length. The seal channel can be configured to test square, circular, or rectangular seals that are nominally 0.5 in. high. The sensitivity of leakage performance to lateral or axial loading can also be measured using specially designed high temperature lateral and axial bellows preload systems. Leakage data for a candidate ceramic wafer engine seal is provided by way of example to demonstrate the test fixture's capabilities. Steinetz, Bruce M. Glenn Research Center NASA-TM-103658, E-5780, NAS 1.15:103658 RTOP 505-63-1B...
Book Synopsis A Test Fixture for Measuring High-temperature Hypersonic-engine Seal Performance by :
Download or read book A Test Fixture for Measuring High-temperature Hypersonic-engine Seal Performance written by and published by . This book was released on 1990 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
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Book Synopsis Hot Dynamic Test Rig for Measuring Hypersonic Engine Seal Flow and Durability by :
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Download or read book NASA Technical Memorandum written by and published by . This book was released on 1994 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722273729 Total Pages :24 pages Book Rating :4.2/5 (737 download)
Book Synopsis High Temperature Performance Evaluation of a Hypersonic Engine Ceramic Wafer Seal by : National Aeronautics and Space Administration (NASA)
Download or read book High Temperature Performance Evaluation of a Hypersonic Engine Ceramic Wafer Seal written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-05 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Leakage rates of an innovative hypersonic engine seal were measured using a specially developed static high temperature seal test fixture at NASA Lewis Research Center. The three foot long structural panel-edge seal is designed to minimize leakage of high temperature, high pressure gases past the movable panels of advanced ramjet/scramjet engines. The seal is made of a stack of precision machined ceramic wafer pieces that are inserted into a closely conforming seal channel in the movable engine panel. The wafer seal accommodates the significant distortions in the adjacent engine walls through relative sliding between adjacent wafers. Seal leakage rates are presented for engine simulated air temperatures up to 1350 F and for engine pressures up to 100 psi. Leakage rates are also presented for the seal, sealing both a flat wall condition, and an engine simulated distorted wall condition in which the distortion was 0.15 in. in only an 18 in. span. Seal leakage rates were low, meeting an industry-established tentative leakage limit for all combinations of temperature, pressure, and wall conditions considered. Comparisons are made between the measured leakage rates and leakage rates predicted using a seal leakage model developed from externally-pressurized gas film bearing theory. Steinetz, Bruce M. Glenn Research Center RTOP 505-63-5B...
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Book Synopsis High Temperature Performance Evaluation of a Hypersonic Engine Ceramic Wafer Seal by :
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Book Synopsis Bibliography of Lewis Research Center Technical Publications Announced in 1993 by :
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Book Synopsis Government Reports Announcements & Index by :
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