System and method of measuring turbine vane cooling air consumption during engine operation
US10684149B2 · kind B2 · utility
4Cited by
6References
18Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Mar 9, 2018 |
| Grant date | Jun 16, 2020 |
| Priority date | — |
| Expiry date | Jul 16, 2038 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01F1/40
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Vanes for use in gas turbine engines and methods of measuring cooling air flow through vanes are disclosed herein. Each vane includes an airfoil and an end wall. The airfoil is shaped to interact with hot gasses moving along a primary gas path during operation of the gas turbine engine. The end wall is coupled to the airfoil and shaped to define a boundary of the primary gas path near a radial end of the airfoil. The end wall includes a platform that is exposed to the primary gas path and a projection that extends away from the platform and is located outside the primary gas path.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.