Turbine blade tip clearance control
US9644490B2 · kind B2 · utility
8Cited by
9References
24Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 9, 2016 |
| Grant date | May 9, 2017 |
| Priority date | — |
| Expiry date | Feb 9, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An aircraft engine according to an example of the present disclosure includes, among other things, a high pressure turbine having a blade, an engine casing disposed about the blade, a shield disposed around the casing adjacent to the blade and creating an area between the shield and the casing, and a gate disposed along the shield. The gate is rotatable about the engine casing between an opened position and a closed position for selectively controlling entry of cooling air into the area. A method of cooling an engine is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.