Removable combustor liner for gas turbine engine combustor
US5435139A · kind A · utility
81Cited by
9References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 6, 1995 |
| Grant date | Jul 25, 1995 |
| Priority date | — |
| Expiry date | Jan 6, 2015 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03044
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine combustor 20 has a wall structure 22 including an outer wall 24 having a plurality of wall elements 26 attached thereto. Each wall element 26 has a flange 27 around its periphery which defines a chamber 28 between each wall element and the outer wall 24. Holes 30 in the outer wall 24 permit the flow of cooing air into each chamber 28 to provide impingement cooling of the wall elements 26. Holes 30 in the wall elements 26 permit the exhaustion of cooling air from the chambers to provide film cooling of the wall elements 26.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.