Uniform cooling film replenishment thermal liner assembly
US5265409A · kind A · utility
46Cited by
10References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 18, 1992 |
| Grant date | Nov 30, 1993 |
| Priority date | — |
| Expiry date | Dec 18, 2012 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49234
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine liner assembly is disclosed having uniformly spaced rows of cooling orifices oriented perpendicular to the combustion gas flow of the engine. The orifices within each row are spaced equidistant from adjacent orifices within the same row, thereby providing a uniform, uninterrupted pattern of cooling orifices over the hot side of the liner. The liner is secured to a component of the gas turbine engine by a plurality of fasteners which are secured to the liner without affecting the uniform pattern of the cooling orifices.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.