Gas turbine engine combustor
US5271219A · kind A · utility
64Cited by
2References
7Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jul 29, 1991 |
| Grant date | Dec 21, 1993 |
| Priority date | — |
| Expiry date | Jul 29, 2011 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine annular combustor (16) has a bulkhead (19) at its upstream end which is protected by an annular array of heatshields (32). Each of the heatshields (32) is spaced apart from the bulkhead (19) by flanges (37, 38,39,40) on the upstream heatshield face. Cooling air entry apertures (47) provided in the bulkhead (19) direct cooling air into the space (36) between the bulkhead (19) and each heatshield (32). The flanges (37,38,39,40) direct the cooling air so that some flows towards a fuel burner aperture (35) in the center of each heatshield (32) while the remainder flows towards the heatshield (32) edges.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.