Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines
US9963996B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 22, 2014 |
| Grant date | May 8, 2018 |
| Priority date | — |
| Expiry date | Aug 22, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/232
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A shroud cooling system configured to cool a shroud adjacent to an airfoil within a gas turbine engine is disclosed. The turbine engine shroud may be formed from shroud segments that include a plurality of cooling air supply channels extending through a forward shroud support for impingement of cooling air onto an outer radial surface of the shroud segment with respect to the inner turbine section of the turbine engine. The channels may extend at various angles to increase cooling efficiency. The backside surface may also include various cooling enhancement components configured to assist in directing, dispersing, concentrating, or distributing cooling air impinged thereon from the channels to provide enhanced cooling at the backside surface. The shroud cooling system may be used to slow down the thermal response by isolating a turbine vane carrier from the cooling fluids while still providing efficient cooling to the shroud.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.