Active clearance control system for gas turbine engines
US7491029B2 · kind B2 · utility
18Cited by
6References
7Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 14, 2005 |
| Grant date | Feb 17, 2009 |
| Priority date | — |
| Expiry date | Jan 31, 2026 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine generally includes a compressor, a combustor, and a turbine. The turbine can include an integrated manifold comprising a plenum defined by a manifold disposed in connection with a divider plate and opposite a shielding plate comprising a plurality of apertures. During operation of the gas turbine engine, a quantity of working fluid enters the integrated manifold and circulates throughout the plenum and shielding plate, and enters the turbine through the apertures to actively control clearances between turbine engine components.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.