Gas turbine engine component arrangement
US9879601B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 31, 2013 |
| Grant date | Jan 30, 2018 |
| Priority date | — |
| Expiry date | Feb 27, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.