Turbine cooling system
US10633996B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 17, 2016 |
| Grant date | Apr 28, 2020 |
| Priority date | — |
| Expiry date | Mar 22, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine assembly for a gas turbine engine is disclosed herein. The turbine assembly includes a turbine vane and an annular turbine shroud. The turbine vane has an airfoil extending through a primary gas path and is formed to include cooling passages sized to conduct cooling air from an inlet aperture to a discharge aperture. The turbine shroud is adapted to extend around a bladed turbine wheel to resist gasses from passing over turbine blades without interacting with the turbine blades. The turbine shroud includes a ceramic matrix composite blade track having a radially-inwardly facing inner surface arranged in confronting relation with the primary gas path.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.