Apparatus for reducing thermal stress in turbine airfoils
US6398501B1 · kind B1 · utility
20Cited by
10References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 17, 1999 |
| Grant date | Jun 4, 2002 |
| Priority date | — |
| Expiry date | Sep 17, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/603
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine airfoil includes at least one spar arrangement having a length less than an associated turbine airfoil length. During operation, the turbine airfoil has an outer skin surface which operates at a substantially higher temperature than that of an internal supporting parted spar arrangement. The parted spar arrangement permits the turbine airfoil outer skin surface to thermally expand between spar arrangements, thus preventing self-constraining thermal stresses from forming within the spar arrangement or the airfoil skin surfaces.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.