Methods and system for cooling integral turbine nozzle and shroud assemblies
US7740442B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 30, 2006 |
| Grant date | Jun 22, 2010 |
| Priority date | — |
| Expiry date | Oct 15, 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 includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. 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, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip to facilitate film cooling the shroud segment.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.