Gas turbine engine
US12404773B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 26, 2024 |
| Grant date | Sep 2, 2025 |
| Priority date | — |
| Expiry date | Jun 26, 2044 |
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 a cooling air supply passage that feeds air from a compressor, as a cooling medium, to a turbine by swirling the air in a circumferential direction. The cooling air supply passage includes an entry zone to which the air enters, and a swirl zone in which the air flowing past the entry zone is circumferentially redirected. The gas turbine engine also includes a chamber branching from the swirl zone to capture foreign particles in the air. The chamber is formed to meet the relation: α≥β where, when viewed in a radial direction, α is an angle defined by the swirl zone relative to a horizontal direction and β is an angle defined between the chamber and the swirl zone.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.