Vortex spoiler for delivery of cooling airflow in a turbine engine
US7708519B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Mar 26, 2007 |
| Grant date | May 4, 2010 |
| Priority date | — |
| Expiry date | Nov 17, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A vortex spoiler (180) for delivery of a cooling airflow (192) in a turbine (108) engine (100) including a plurality of inlet ports (182) formed circumferentially about a radial exterior sidewall (188), and a plurality of outlet ports (184) formed circumferentially about a radial interior sidewall (190). The plurality of inlet ports (182) are coupled to the plurality of outlet ports (184) via a plurality of ducts (186). Each of the ducts is formed having an interior diameter at the inlet port and the outlet port formed at a preselected angle normal to the surface of the each of the radial sidewalls to form a radially curved profile such that a cooling airflow (192) may pass radially inwardly through each of the plurality of ducts (186) with minimal tangential stress and minimal static pressure loss.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.