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:
- Issue Date:
- Research Org.:
- National Energy Technology Laboratory (NETL), Pittsburgh, PA, Morgantown, WV (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1444108
- Patent Number(s):
- 9976915
- Application Number:
- 13/804,132
- Assignee:
- SIEMENS ENERGY, INC. (Orlando, FL)
- Patent Classifications (CPCs):
-
G - PHYSICS G01 - MEASURING G01K - MEASURING TEMPERATURE
- 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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