NON-INTRUSIVE MEASURMENT OF HOT GAS TEMPERATURE IN A GAS TURBINE ENGINE

摘要

A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. An acoustic signal is encoded with a distinct signature defined by a set of predetermined frequencies transmitted as a non-broadband signal. Acoustic signals are transmitted from an acoustic transmitter located at a predetermined axial location along the flow path of the gas turbine engine. A received signal is compared to one or more transmitted signals to identify a similarity of the received signal to a transmitted signal to identify a transmission time for the received signal. A time-of-flight is determined for the signal and the time-of-flight for the signal is processed to determine a temperature in a region of the predetermined axial location.

主权项

1. A method of 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 an acoustic signal from an acoustic transmitter located at a predetermined axial location along the flow path of the gas turbine engine; receiving the acoustic signal from the acoustic transmitter at an acoustic receiver located at the predetermined axial location; the acoustic signal being encoded with a distinct signature defined by a set of predetermined frequencies transmitted as a non-broadband acoustic signal; wherein receiving the acoustic signal includes comparing a received signal to one or more transmitted signals to identify a similarity of the received signal to a transmitted signal to identify a transmission time for the received signal; determining a time-of-flight for the signal from the acoustic transmitter to the acoustic receiver; and processing the time-of-flight for the signal to determine a temperature in a region of the predetermined axial location.