Swirl nozzle for a cooling system in gas turbine engines
US4666368A · kind A · utility
27Cited by
12References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 1, 1986 |
| Grant date | May 19, 1987 |
| Priority date | — |
| Expiry date | May 1, 2006 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/082
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Cooling air from turbine nozzle vanes of a hot gas turbine engine is collected from the vanes by an air connector. A conduit connects to the connector and terminates adjacent a turbine wheel so that air flows through the vanes and through the conduit to be emitted from the end thereof in a jet stream directed against the turbine wheel. A vaned swirl nozzle is inserted in the conduit and adjacent a turbine wheel to impart a turning impetus to the air flow stream being emitted from the nipple. The emitted air stream is then directed tangentially against or adjacent the turbine wheel in the direction of rotation thereof.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.