Improved aerothermodynamic measurements of the T63-A-700 gas turbine engine

Approved for public release, distribution unlimited--Cover. === This thesis contains an analysis of the failure of the instrumentation ring for measuring the combustor exit temperature and total pressure in the T63-A-700 gas turbine engine. An improved ring design has been constructed and installed....

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Main Author:	Garrott, Kristin B.
Other Authors:	Millsaps, Knox T.
Published:	Monterey, California. Naval Postgraduate School 2012
Online Access:	http://hdl.handle.net/10945/10045

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spelling	ndltd-nps.edu-oai-calhoun.nps.edu-10945-100452014-11-27T16:08:45Z Improved aerothermodynamic measurements of the T63-A-700 gas turbine engine Garrott, Kristin B. Millsaps, Knox T. Hobson, Garth V. Department of Mechanical Engineering. Approved for public release, distribution unlimited--Cover. This thesis contains an analysis of the failure of the instrumentation ring for measuring the combustor exit temperature and total pressure in the T63-A-700 gas turbine engine. An improved ring design has been constructed and installed. Extensions to the exhaust stacks have been installed to keep the cell temperature reasonable. A water-cooled heat exchanger was installed in place of an air-cooled heat exchanger that was not adequately cooling the oil temperature while running the engine. In the program GASTURB, a compressor map with data from the manufacturer was created and an operating line from three separate speeds was plotted. 2012-08-22T15:31:01Z 2012-08-22T15:31:01Z 2005-09 http://hdl.handle.net/10945/10045 Approved for public release, distribution unlimited--Cover. This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, it may not be copyrighted. Monterey, California. Naval Postgraduate School
collection	NDLTD
sources	NDLTD
description	Approved for public release, distribution unlimited--Cover. === This thesis contains an analysis of the failure of the instrumentation ring for measuring the combustor exit temperature and total pressure in the T63-A-700 gas turbine engine. An improved ring design has been constructed and installed. Extensions to the exhaust stacks have been installed to keep the cell temperature reasonable. A water-cooled heat exchanger was installed in place of an air-cooled heat exchanger that was not adequately cooling the oil temperature while running the engine. In the program GASTURB, a compressor map with data from the manufacturer was created and an operating line from three separate speeds was plotted.
author2	Millsaps, Knox T.
author_facet	Millsaps, Knox T. Garrott, Kristin B.
author	Garrott, Kristin B.
spellingShingle	Garrott, Kristin B. Improved aerothermodynamic measurements of the T63-A-700 gas turbine engine
author_sort	Garrott, Kristin B.
title	Improved aerothermodynamic measurements of the T63-A-700 gas turbine engine
title_short	Improved aerothermodynamic measurements of the T63-A-700 gas turbine engine
title_full	Improved aerothermodynamic measurements of the T63-A-700 gas turbine engine
title_fullStr	Improved aerothermodynamic measurements of the T63-A-700 gas turbine engine
title_full_unstemmed	Improved aerothermodynamic measurements of the T63-A-700 gas turbine engine
title_sort	improved aerothermodynamic measurements of the t63-a-700 gas turbine engine
publisher	Monterey, California. Naval Postgraduate School
publishDate	2012
url	http://hdl.handle.net/10945/10045
work_keys_str_mv	AT garrottkristinb improvedaerothermodynamicmeasurementsofthet63a700gasturbineengine
_version_	1716721429987196928

Improved aerothermodynamic measurements of the T63-A-700 gas turbine engine

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