Invention Grant
- Patent Title: Gas turbine compressor radial door bleed valve
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Application No.: US16869847Application Date: 2020-05-08
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Publication No.: US11428234B2Publication Date: 2022-08-30
- Inventor: Jonathan D. Little
- Applicant: Raytheon Technologies Corporation
- Applicant Address: US CT Farmington
- Assignee: Raytheon Technologies Corporation
- Current Assignee: Raytheon Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: Cantor Colburn LLP
- Main IPC: F04D27/02
- IPC: F04D27/02 ; F02K3/075

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.
Public/Granted literature
- US20210348618A1 GAS TURBINE COMPRESSOR RADIAL DOOR BLEED VALVE Public/Granted day:2021-11-11
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