Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions
US7870739B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Feb 2, 2006 |
| Grant date | Jan 18, 2011 |
| Priority date | — |
| Expiry date | May 28, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A curved diffuser (210) in a gas turbine engine (201) directs a primary portion of air flow from a compressor (202) through a curved discharge opening (213) into a plenum (220). The curved diffuser (210) also comprises ports (217) through which a secondary portion of air passes into confined space (225) that is defined in part by a pressure boundary element that may be comprised of at least one plate (222) or at least one conduit (306). The at least one plate (222) and the at least one conduit (306) respectively comprise apertures (246, 312) through which pass the secondary portion of air to provide impingement-type cooling to transitions (230, 320). In various embodiments the velocity of the air between adjacent transitions (230, 320) may flow at relatively uniform velocity along the longitudinal distance of the respective transitions (230, 320).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.