Radial pre-swirl assembly and cooling fluid metering structure for a gas turbine engine
US8677766B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 20, 2010 |
| Grant date | Mar 25, 2014 |
| Priority date | — |
| Expiry date | Jan 23, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine comprises a pre-swirl structure coupled to a shaft cover structure and located radially between a supply of cooling fluid and a flow path. The pre-swirl structure defines a flow passage and includes a plurality of swirl members in the flow passage. A flow direction of cooling fluid passing through the flow passage is altered by the swirl members such that the cooling fluid has a velocity component in a direction tangential to the circumferential direction. The bypass passages provide cooling fluid into a turbine rim cavity associated with a first row vane assembly to prevent hot gas ingestion into the turbine rim cavity from a hot gas flow path associated with a turbine section of the engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.