Gas turbine engine combustor
US5396759A · kind A · utility
71Cited by
4References
2Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Feb 1, 1994 |
| Grant date | Mar 14, 1995 |
| Priority date | — |
| Expiry date | Feb 1, 2014 |
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 having a bulkhead at its upstream end which is thermally protected by an annular array of heat shields. Each heat shield is provided with integral flanges which space apart the heat shields and bulkhead to define chambers therebetween. Apertures in the bulkhead direct cooling air into the chambers. Further apertures in the heat shields exhaust the cooling air in a common circumferential direction so that the air flows merge to define a substantially continuous annular flow of cooling air about the longitudinal axis of the combustor and across the downstream heat shield faces.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.