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Title: Temperature measurement in a gas turbine engine combustor

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