Impingement cooling arrangement for a gas turbine engine
US8414255B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 18, 2010 |
| Grant date | Apr 9, 2013 |
| Priority date | — |
| Expiry date | Oct 16, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/187
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
There is disclosed an impingement cooling arrangement for a gas turbine engine (6), and an engine provided with such an arrangement. The cooling arrangement comprises at least part of a casing (21) configured to define a flowpath for the passage of hot gases through the engine, and a manifold (22) configured to direct cooling air against an outer surface (23) of the casing for impingement cooling thereof. The arrangement is characterized by said manifold (22) being configured to direct a primary flow of cooling air (65) against a first area (64) of the casing outer surface (23) for impingement cooling of said first area, and to recirculate (66) at least a portion of said primary flow of cooling air after impingement against said first area (64) and to direct at least a portion of the recirculated flow against a second area (67) of the casing outer surface (23) for impingement cooling of said second area (67). In a preferred arrangement, the manifold (22) is spaced from said casing (21) so as to define a space (41) between the manifold and the outer surface (23) of the casing, and the manifold (22) further comprises a baffle (46) extending at least partially across said space, subst…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.