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Dynamic gas temperature measurement systemA gas temperature measurement system with compensated frequency response of 1 KHz and capability to operate in the exhaust of a gas turbine combustor was developed. Environmental guidelines for this measurement are presented, followed by a preliminary design of the selected measurement method. Transient thermal conduction effects were identified as important; a preliminary finite-element conduction model quantified the errors expected by neglecting conduction. A compensation method was developed to account for effects of conduction and convection. This method was verified in analog electrical simulations, and used to compensate dynamic temperature data from a laboratory combustor and a gas turbine engine. Detailed data compensations are presented. Analysis of error sources in the method were done to derive confidence levels for the compensated data.
Document ID
19860002032
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Elmore, D. L.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Robinson, W. W.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Watkins, W. B.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1983
Publication Information
Publication: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST)
Subject Category
Instrumentation And Photography
Accession Number
86N11499
Funding Number(s)
CONTRACT_GRANT: NAS3-23154
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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