Methods and apparatuses for cooling gas turbine engine rotor assemblies
US7341429B2 · kind B2 · utility
19Cited by
11References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 16, 2005 |
| Grant date | Mar 11, 2008 |
| Priority date | — |
| Expiry date | Jun 3, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/201
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine mid-frame such that a cavity is defined between the rotor disk and the turbine mid-frame, and forming at least one opening extending through the turbine mid-frame to facilitate channeling cooling air into the gap, the opening configured to impart a high relative tangential velocity into the cooling air discharged from the opening.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.