Gas turbine compressor radial door bleed valve
US11428234B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | May 8, 2020 |
| Grant date | Aug 30, 2022 |
| Priority date | — |
| Expiry date | Nov 20, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/101
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A bleed system of a gas turbine engine includes a bleed duct having a duct inlet located at a flowpath of a gas turbine engine, and a bleed outlet located outside of the flowpath, and extending circumferentially around a central longitudinal axis. A plurality of bleed doors are located at the bleed outlet and are arrayed along a circumferential length on the bleed duct. Each bleed door includes a first circumferential end, and a second circumferential end. The bleed doors are arrayed such that when the bleed doors are in a closed position the first circumferential end is located at the second circumferential end of an adjacent bleed door of the bleed doors. Each bleed door includes a pivot, such that each bleed door rotates about the pivot from the closed position covering the duct outlet to an opened position allowing a bleed airflow to pass through the duct outlet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.