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

Claim 8:
9. A gas turbine engine comprising:
a fan delivering air into a bypass duct defined by an outer fan housing and an outer core engine panel, the fan also delivering air into a core engine inward of an inner core engine panel; and a compressor section receiving air from said fan, 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 into the bypass duct, with the air exiting the core engine at an exit location radially inward of the outer core panel; wherein 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 anon-bleed air portion not receiving the bleed air, and having a first portion extending from the inner core panel and along a direction with a greater component in a radial direction than in an axial direction; and
a fan exit guide vane on the outer core engine panel, and the bleed valve and the conduit are aft relative to the axis of the gas turbine engine relative to a root of the fan exit guide vane as connected to the outer core panel.