Double pass air impingement and air film cooling for gas turbine combustor walls
US6079199A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jun 3, 1998 |
| Grant date | Jun 27, 2000 |
| Priority date | — |
| Expiry date | Jun 3, 2018 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03044
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A one piece cold combustor wall for lining the reverse flow hot combustor wall of a gas turbine engine, disposed at a distance from the outer surface of the hot combustor wall. Improved cooling of the hot combustor wall results from the addition of impingement cooling air injected through orifices in the cold combustion wall directed at the hot combustion wall together with film cooling by air conducted between the hot and cold combustor walls. The cold combustor wall is perforated with a pattern of air impingement inlet orifices through the cold combustor wall conducting compressed air from the outer surface of the cold combustor wall in compressed air jets directed at the outer surface of the hot combustor wall. The provision of a cold combustor wall also improves conventional air film cooling by adding impingement cooling and reusing the air after impingement to form a contained air film between the hot and cold walls. An air cooled thermal expansion joint joins the hot and cold walls at a downstream end with interlocking flanges, with sliding seal surfaces disposed on parallel adjacent sides.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.