Oil cooler integrated into the pylon

Patent metadata

Field	Value
Publication number	US-2017066540-A1
Application number	US-201615255043-A
Country	US
Kind code	A1
Filing date	Sep 1, 2016
Priority date	Sep 4, 2015
Publication date	Mar 9, 2017
Grant date	—

Abstract

The invention relates to a suspension pylon comprising:
at least one arm ( 3 ) for suspending a propulsion unit ( 4 ) from the fuselage ( 2 ) of an airplane ( 1 ), an oil exchange circuit ( 70 ) configured to be connected, on the one hand, to an oil pump ( 5 ) in the fuselage ( 2 ) and on the other hand, to the propulsion unit ( 4 ) the arm ( 3 ) whereof provides for suspension, said circuit ( 70 ) comprising a feed line ( 72 ) and a return line ( 74 ), which both extend inside said arm ( 3 ), an intermediate shaft ( 6 ) which extends in said arm ( 3 ), said shaft being configured, on the one hand, to be driven by the propulsion unit ( 4 ) the arm ( 3 ) whereof provides for suspension and, on the other hand, to drive the oil pump ( 5 ) in the fuselage ( 2 ),

wherein the arm ( 3 ) has a structure adapted for cooling the oil exchange circuit at the arm ( 3 ).

First claim

1 . A suspension pylon comprising:
at least one arm for suspending a propulsion unit from the fuselage of an airplane, an oil exchange circuit-configured to be connected, on the one hand, to an oil pump in the fuselage and on the other hand, to the propulsion unit the arm whereof provides for suspension, said circuit-comprising a feed line and a return line, which both extend inside said arm, an intermediate shaft-which extends in said arm, said shaft being configured, on the one hand, to be driven by the propulsion unit the arm whereof provides for suspension and, on the other hand, to drive the oil pump in the fuselage,
wherein the arm has a structure adapted for cooling the oil exchange circuit at the arm.

2 . The pylon according to claim 1 , wherein the arm comprises a leading edge, and wherein the return line is located at the leading edge to favour cooling of the oil and to favour de-icing of said leading edge.

3 . The pylon according to claim 1 , wherein the arm comprises a plurality of cooling compartments through which the return line circulates.

4 . The pylon according to claim 3 , wherein the compartments are filled with oil.

5 . The pylon according to claim 4 , wherein the compartments are fed with oil from the feed line.

6 . The pylon according to claim 3 , wherein the compartments comprise valves for allowing or preventing fluid communication between the different compartments.

7 . The pylon according to claim 1 , further comprising an intermediate bearing located in the arm and supporting the intermediate shaft, wherein the intermediate bearing is lubricated from the oil exchange circuit.

8 . An assembly comprising a pylon according to claim 1 and an accessory gearbox, said box being located in the fuselage, said box being driven by the intermediate shaft and the oil pump being driven by the gearbox.

9 . The assembly according to claim 8 , also comprising a propulsion unit.

10 . An airplane comprising an assembly according to claim 9 , wherein the propulsion unit is attached to the rear fuselage and the propulsion unit comprises a turbine engine.

Assignees

• Safran Aircraft Engines

Inventors

• Lemarchand Kevin Morgane

Classifications

• B64D33/08

  of power plant cooling systems · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• B64D27/20

  within, or attached to, fuselages · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F01D25/20

  using lubrication pumps · CPC title