Turbine combustion system liner
US8955330B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 18, 2011 |
| Grant date | Feb 17, 2015 |
| Priority date | — |
| Expiry date | Sep 28, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03043
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion chamber liner (41) with a forward section (44) and an aft section (46). The aft section has an array of aft axial cooling fins (62) covered by a tubular support ring (52), thus forming an array of aft axial grooves (66) between the aft axial fins. Inlet holes (54) in the front end of the support ring may admit coolant (37) into an upstream end of the aft axial cooling fins. An impingement plenum (61) may receive the coolant just before the aft axial cooling fins. Each aft axial fin may include a plurality of axially spaced bumpers (64) that contact the support ring. Spaces or grooves (68) between the bumpers provide circumferential cross flow of coolant between the grooves. The aft axial grooves may discharge the coolant as film cooling along the inner wall (76) of a transition duct (28).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.