Patent ID: 8565999
Filing Date: 2013-10-22
Classification: F02C,F05D,G01K

Abstract:
1. A method operating a gas turbine engine, including determining a temperature of a working gas passing through a flow path within the gas turbine engine, the method comprising the steps of: transmitting acoustic signals from a plurality of acoustic transmitters located at a predetermined axial location adjacent to and downstream from a last stage of a turbine section of the gas turbine engine; receiving the acoustic signals from the acoustic transmitters at a plurality of acoustic receivers located at the predetermined axial location; each acoustic signal comprising a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path; determining, using a processor, a time-of-flight for the signals traveling along each of the line-of-sound paths; and processing, via a processor, the time-of-flight for the signals traveling along the line-of-sound paths to determine a temperature in a region of the predetermined axial location.