Patent ID: 9540109
Date: 2017-01-10
CPC Classifications: B64C,B64D,F02C,F02K,F05D,Y02T

Claim:
1. A turbomachine comprising: a nozzle extending along an axial direction, said nozzle being configured to convey a hot gas stream; a mounting pylon for mounting the turbomachine, said pylon extending radially from a base arranged in the vicinity of the nozzle; and a pylon cooler device having an auxiliary gas duct having a gas inlet configured to take cold gas from outside the nozzle, and a gas outlet opening out in the vicinity of the base of the pylon, wherein the pylon includes a front mount for mounting an intermediate casing, located axially between a fan and a low pressure compressor of the turbomachine, to the pylon, and a rear mount for mounting a turbine casing to the pylon, the rear mount including a plurality of links distributed in azimuth and being fastened to a flange provided on the turbine casing housing a low pressure turbine of the turbomachine, wherein the auxiliary duct is arranged inside a rear mount fairing which protects the rear mount and provides aerodynamic continuity for a stream of the cold gas, wherein the gas inlet is arranged in an upstream end of the rear mount fairing , and wherein the gas outlet is arranged radially between an exhaust outlet of the nozzle and the base of the pylon, and is arranged axially at a same axial position as the exhaust outlet of the nozzle.