Bleed system driven in simplified manner for a turbojet or turboprop engine
US6622475B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 12, 2002 |
| Grant date | Sep 23, 2003 |
| Priority date | — |
| Expiry date | Apr 13, 2022 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A bypass gas turbine engine having an intermediate structural casing positioned between a primary flow path and a bypass flow path, and configured between a low pressure compressor and a high pressure compressor. The engine further having a bleed device arranged to deflect a portion of a gas flow from the low pressure compressor toward the bypass flow path. The bleed device includes an annular cavity defining a manifold situated upstream the intermediate casing and opening along the outer wall of the primary flow path, a plurality of conduits positioned along the intermediate casing, a plurality of tubes configured around the high pressure compressor and connecting the conduits to the bypass flow path, and at least one flow regulating valve disposed along the interior of each of the plurality of tubes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.