Cooling features for a gas turbine engine transition duct
US10801341B2 · kind B2 · utility
0Cited by
1References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 15, 2015 |
| Grant date | Oct 13, 2020 |
| Priority date | — |
| Expiry date | Jun 4, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas engine turbine has a transition duct (100) that has improved cooling features and a method for forming the cooling features. A continuous exit section cooling channel (130) is formed through the transition duct panel (112), the exit frame (114) and the connection (116). The continuous exit section cooling channel (130) reduces the need for effusion channels in the transition duct. The continuous exit section cooling channel (130) further reduces costs and improves the emissions associated with the transition duct (100) of the gas engine turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.