Patent ID: 9534640
Date: 2017-01-03
CPC Classifications: F02C,F05D,F16D,Y02T

Claim:
1. A gas turbine engine power transmission assembly comprising a stack of axially aligned annular shape power transmission disks capable of selectively transmitting power from a drive shaft of a gas turbine engine to a driven aircraft component, the annular shape power transmission disks together defining a dry clutch assembly having an axially extending central passage; a transmission shaft that extends through the axially extending central passage of the annular shape power transmission disks and that defines an axially extending fluid transfer passage that extends through the transmission shaft at least the length of the axially extending central passage, the transmission shaft comprising a central shaft portion that extends at least the length of the axially extending central passage, and a diverging shaft portion upstream of the central shaft portion in which a wide end of the diverging shaft portion is joined to the central shaft portion; and means for transferring a heat conducting fluid through the axially extending fluid transfer passage of the transmission shaft, wherein the axially aligned annular shape power transmission disks are disposed between the gas turbine engine and the driven aircraft component, and wherein the means for transferring a heat conducting fluid comprises a liquid fluid transfer mechanism configured to transfer a heat convecting liquid fluid through the fluid transfer passage of the transmission shaft.