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Title: Temperature measurement in a gas turbine engine combustor

Abstract

A method and system for determining a temperature of a working gas passing through a passage to a turbine section of a gas turbine engine. The method includes identifying an acoustic frequency at a first location in the engine upstream from the turbine section, and using the acoustic frequency for determining a first temperature value at the first location that is directly proportional to the acoustic frequency and a calculated constant value. A second temperature of the working gas is determined at a second location in the engine and, using the second temperature, a back calculation is performed to determine a temperature value for the working gas at the first location. The first temperature value is compared to the back calculated temperature value to change the calculated constant value to a recalculated constant value. Subsequent first temperature values at the first location may be determined based on the recalculated constant value.

Inventors:
Publication Date:
Research Org.:
National Energy Technology Laboratory, Pittsburgh, PA, and Morgantown, WV (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1444108
Patent Number(s):
9,976,915
Application Number:
13/804,132
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2013 Mar 14
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

DeSilva, Upul. Temperature measurement in a gas turbine engine combustor. United States: N. p., 2018. Web.
DeSilva, Upul. Temperature measurement in a gas turbine engine combustor. United States.
DeSilva, Upul. Tue . "Temperature measurement in a gas turbine engine combustor". United States. https://www.osti.gov/servlets/purl/1444108.
@article{osti_1444108,
title = {Temperature measurement in a gas turbine engine combustor},
author = {DeSilva, Upul},
abstractNote = {A method and system for determining a temperature of a working gas passing through a passage to a turbine section of a gas turbine engine. The method includes identifying an acoustic frequency at a first location in the engine upstream from the turbine section, and using the acoustic frequency for determining a first temperature value at the first location that is directly proportional to the acoustic frequency and a calculated constant value. A second temperature of the working gas is determined at a second location in the engine and, using the second temperature, a back calculation is performed to determine a temperature value for the working gas at the first location. The first temperature value is compared to the back calculated temperature value to change the calculated constant value to a recalculated constant value. Subsequent first temperature values at the first location may be determined based on the recalculated constant value.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2018},
month = {5}
}

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Works referenced in this record:

The Measurement of Performance of Combustors Using Passive Acoustic Methods
conference, June 2012

  • Kleppe, John; Norris, W.; McPherson, D.
  • 42nd AIAA Aerospace Sciences Meeting and Exhibit
  • DOI: 10.2514/6.2004-1046