Gas turbine engine anti-ice formation device and system
US7874137B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 18, 2007 |
| Grant date | Jan 25, 2011 |
| Priority date | — |
| Expiry date | Jun 6, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/584
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An anti-ice formation device for a gas turbine engine is configured to be mounted within an inlet duct of the engine, and adjacent the gas turbine engine compressor inlet. The device is configured to selectively receive a flow of compressed air that is discharged from the compressor. Because the compressed air is relatively hot, the anti-ice formation device temperature increases to a temperature sufficient to prevent ice accumulation and formation in the engine inlet duct. The anti-ice formation device is also configured such that heat is not transferred to the compressor inlet housing. As a result, the anti-ice formation device does not cause impeller clearance variations, which would adversely affect engine performance.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.