Sealed combustor liner panel for a gas turbine engine
US10816201B2 · kind B2 · utility
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39References
9Claims
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Assignee
Inventor
Key dates
| Filing date | Jul 11, 2014 |
| Grant date | Oct 27, 2020 |
| Priority date | — |
| Expiry date | Mar 13, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A liner panel for a combustor of a gas turbine engine includes a rail which at least partially defines an impingement cavity. The rail includes a notch which faces toward the impingement cavity. A method of cooling a wall assembly within a combustor for of a gas turbine engine includes directing air through a support shell and a liner panel to form a pressure drop across the support shell that is less than about 80% of a pressure drop across the combustor and to also form a pressure drop across the liner panel greater than about 20% of the pressure drop across the combustor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.