Methods and apparatus for minimizing gas turbine engine thermal stress
US6511284B2 · kind B2 · utility
38Cited by
4References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 1, 2001 |
| Grant date | Jan 28, 2003 |
| Priority date | — |
| Expiry date | Jun 1, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49323
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A heat shield for a gas turbine engine hub which facilitates reducing thermal stress in an exhaust frame of a gas turbine engine. The exhaust frame includes the hub mounted within the engine with a plurality of supports. The supports extend radially outward from the hub through a primary flow cavity and facilitate flow to a secondary flow cavity. The heat shield defines the secondary flow cavity such that the secondary flow cavity is radially inward and axially adjacent the hub. The heat shield includes a plurality of thermal stress relieving corrugations.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.