Gas turbine engine combustion liner float wall cooling arrangement
US5461866A · kind A · utility
34Cited by
9References
4Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 15, 1994 |
| Grant date | Oct 31, 1995 |
| Priority date | — |
| Expiry date | Dec 15, 2014 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05B2260/2241
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
When second shell section 18 diverges with respect to first shell section 16, the second liner panel 50 is located with a changing spacing from the shell. The liner is close to the shell at the upstream edge 68, and farther from the liner at the downstream end 57. The downstream end of the first liner panel 64 overlaps the second liner panel 50 on the gas side.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.