High recovery multi-use bleed
US6325595A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Mar 24, 2000 |
| Grant date | Dec 4, 2001 |
| Priority date | — |
| Expiry date | Mar 24, 2020 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/545
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compressor air bleed assembly for a gas turbine engine includes a compressor casing surrounding a row of circumferentially spaced compressor blades and defining a flowpath for receiving compressor air flow compressed by the blades. The casing includes a bleed port disposed down stream of at least a row of the blades for receiving a portion of compressed air as bleed airflow. A bleed port, preferably in the form of an annular slot, extends away from the bleed port and has a first throat downstream of the port and a second throat downstream of the first throat. A first duct outlet in the duct leads to a first bleed air circuit, receives a first portion of the bleed airflow, and is disposed between the first and second throats. A second duct outlet in the duct leads to a second bleed air circuit, receives a second portion of the bleed circuit.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.