Secondary flow, high pressure turbine module cooling air system for recuperated gas turbine engines
US7383686B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 13, 2004 |
| Grant date | Jun 10, 2008 |
| Priority date | — |
| Expiry date | Jan 19, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/18
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A secondary flow, turbine cooling air system for the uniform cooling of high pressure turbine module components such as the turbine shroud, turbine blade tips, turbine nozzle, transion liner, and turbine bearing support housing in a recuperated gas turbine engine is provided. The secondary flow turbine cooling system provides uniform cooling air having a similar pressure and temperature in a recuperated gas turbine engine as the compressor discharge air of a non-recuperated gas turbine engine. A method for uniform cooling of high pressure turbine module components using the secondary flow turbine cooling air system is also provided.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.