Patent ID: 11927140
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A gas turbine engine comprising:
a propulsor delivering air into a core engine inward of an outer core panel; the core engine having a compressor section, a combustor and a turbine section the compressor and turbine sections having rotors for rotating on an axis;
a compressor bleed system comprising a bleed valve on a conduit communicating with compressed air from the compressor section, the bleed valve configured to deliver air into a chamber where the air can flow outwardly of the core engine at an exit location radially inward of the outer core panel;
an inner core housing surrounds the compressor section and defines the chamber between the inner core housing and the outer core panel;
a flow guide member is positioned within said chamber to guide the bleed airflow from the valve to the exit location, and the flow guide member received in the chamber, and separating the chamber into a bleed air portion and a non-bleed air portion not receiving the bleed air; and the flow guide member having a first portion extending from the inner core housing and along a direction with a greater component in a radial direction than in an axial direction, and the flow guide member then including a turn which turns the air in a more axial direction and then along an inner surface of the outer core panel to guide the air to the exit location.