Method and system to facilitate preferentially distributed recuperated film cooling of turbine shroud assembly
US7722315B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 30, 2006 |
| Grant date | May 25, 2010 |
| Priority date | — |
| Expiry date | Feb 12, 2029 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49236
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of assembling a gas turbine engine includes coupling a turbine shroud assembly within the gas turbine engine. The turbine shroud assembly includes a shroud segment having a leading edge defining a forward face and a radial inner surface. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face. A plurality of recuperated cooling openings are defined through the leading edge at an oblique inlet angle with respect to a centerline of the gap and between the forward face and the radial inner surface to direct cooling fluid through the leading edge to facilitate preferential cooling of the leading edge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.