Gas turbine engine wall assembly with support shell contour regions
US10655855B2 · kind B2 · utility
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18References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 29, 2014 |
| Grant date | May 19, 2020 |
| Priority date | — |
| Expiry date | Apr 4, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.