System and method for providing cooling in a compressor section of a gas turbine engine
US12078105B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 14, 2022 |
| Grant date | Sep 3, 2024 |
| Priority date | — |
| Expiry date | Dec 14, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/232
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.