Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies
US7665953B2 · kind B2 · utility
8Cited by
15References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 30, 2006 |
| Grant date | Feb 23, 2010 |
| Priority date | — |
| Expiry date | Jun 12, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, and directing the cooling air in the gap through at least one cooling hole extending between the leading edge and the inner surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.