Method and apparatus for the cooling of jet-engine turbine casings
US6625989B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Apr 18, 2001 |
| Grant date | Sep 30, 2003 |
| Priority date | — |
| Expiry date | Apr 18, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
This invention relates to a method and an apparatus for the cooling of the casing (1) of the turbines (2, 3) of jet engines, in which cooling air is diverted from a bypass flow and supplied to the outer side of the casing via an inlet duct (8) provided with a shut-off element (5). According to the present invention, the cooling air is supplied to a first chamber (6) in which it is divided by volume. One portion of the cooling air is issued to the casing (1) via orifice holes (10), while another portion is ducted via several tubes (9) to a second chamber (7) which annularly encloses the casing (1) in the area of a low-pressure turbine (3).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.