Injection cooled cooling air system for a gas turbine engine
US10961911B2 · kind B2 · utility
1Cited by
63References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 17, 2017 |
| Grant date | Mar 30, 2021 |
| Priority date | — |
| Expiry date | Jun 3, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes an engine core having a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. At least one compressor bleed connects a compressor flowpath with a first cooled cooling air path. The first cooled cooling air path includes a supplementary coolant injector connected to a supplementary coolant supply. The cooled cooling air path including a portion exterior to the engine core.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.