Gas turbine engine cooling systems having hub-bleed impellers and methods for the production thereof
US8920128B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 19, 2011 |
| Grant date | Dec 30, 2014 |
| Priority date | — |
| Expiry date | Apr 18, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/4932
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Embodiments of a gas turbine engine cooling system for deployment within a gas turbine engine are provided, as are embodiment of a method for producing a gas turbine engine cooling system. In one embodiment, the gas turbine engine cooling system includes an impeller having a hub, a plurality of hub bleed air passages, and a central bleed air conduit. The plurality of hub bleed air passages each have an inlet formed in an outer circumferential surface of the hub and an outlet formed in an inner circumferential surface of the hub. The central bleed air conduit is fluidly coupled to the outlets of the plurality of hub bleed air passages and is configured to conduct bleed air discharged by the plurality of hub bleed air passages to a section of the gas turbine engine downstream of the impeller to provide cooling air thereto.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.