Non-intrusive measurement of hot gas temperature in a gas turbine engine
US9453784B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 4, 2013 |
| Grant date | Sep 27, 2016 |
| Priority date | — |
| Expiry date | Jan 24, 2035 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01K13/024
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.