Taking air away from the tips of the rotor wheels of a high pressure compressor in a turbojet
US7549838B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Feb 8, 2006 |
| Grant date | Jun 23, 2009 |
| Priority date | — |
| Expiry date | Jan 4, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S415/914
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbomachine compressor comprises at least one plurality of moving blades and spaced apart therefrom in an axial direction relative to a central longitudinal axis of the turbomachine, a plurality of stationary vanes, and a stationary casing surrounding said plurality of moving blades and including a plurality of bleed holes centered in the range 5% to 50% of the blade chord length and having a diameter less than or equal to 30% of the blade chord length, each bleed hole sloping at two angles of inclination relative to the central longitudinal axis. Advantageously, each bleed hole has a first axis of inclination presenting an angle φ relative to the central longitudinal axis lying in the range 30° to 90°, and a second axis of inclination perpendicular to the first and presenting an angle θ relative to the central longitudinal axis lying in the range 30° to 90°.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.