Gas turbine engine compressor rotor vaporization cooling
US10364679B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 2, 2014 |
| Grant date | Jul 30, 2019 |
| Priority date | — |
| Expiry date | Feb 20, 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 rotor includes a rotor that provides a cooling cavity. The cooling cavity has a first chamber and a second chamber that are fluidly connected to one another by a passageway. At least one of the first and second rotor portions is configured to support a blade that is fluidly isolated from the cavity. A phase change material is arranged in the cavity. The phase change material is configured to be arranged in the first chamber in a first state and in the second chamber in the second state. The passageway is configured to carry the phase change material between the second and first chambers once changed between the first and second states.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.