Speed-controlled conditioning valve for high pressure compressor
Number of patents in Portfolio can not be more than 2000
United States of America
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-
Apr 5, 2022
Grant Date -
Nov 25, 2021
app pub date -
May 22, 2020
filing date -
May 22, 2020
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A rotor for a gas turbine engine has: a first rotor disk; an interstage flange that extends from the first rotor disk to a flange end portion that has an axial end surface and first radial outer and inner surfaces; a circumferential groove, formed in the flange end portion and extending from the axial end surface toward the first rotor disk; radial outer and inner slots formed in the first radial outer and inner surfaces along the circumferential groove and extend through the first radial outer and inner surfaces; and a valve member disposed within the circumferential groove and is secured within the circumferential groove when the flange end portion is connected to a second rotor disk, wherein the valve member deflects from rotor rotational speeds to seal or unseal the radial outer slot.
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