Methods and system for shielding cooling air to facilitate cooling integral turbine nozzle and shroud assemblies
US7690885B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 30, 2006 |
| Grant date | Apr 6, 2010 |
| Priority date | — |
| Expiry date | Nov 28, 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. Post impingement cooling air is directed at the forward face to facilitate forming a film cooling layer on the shroud segment. The film cooling layer is shielded from combustion gases flowing through the gas turbine engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.