Propulsion assembly for an aircraft having a turbojet with a non-ducted fan and an attachment pylon

Patent metadata

Field	Value
Publication number	US-10737796-B2
Application number	US-201615182860-A
Country	US
Kind code	B2
Filing date	Jun 15, 2016
Priority date	Jun 15, 2015
Publication date	Aug 11, 2020
Grant date	Aug 11, 2020

Abstract

A propulsion assembly for an aircraft, the assembly including a turbojet having at least one unducted propulsive propeller, and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having a streamlined profile defined by two opposite side faces extending transversely between a leading edge and a trailing edge. The pylon includes a plurality of blow nozzles situated in the vicinity of its trailing edge and configured to blow air taken from a pressurized portion of the turbojet, the blow nozzles being positioned over at least a fraction of the trailing edge of the pylon that extends longitudinally facing at least a portion of the propeller. A method of reducing the noise generated by a pylon attaching a turbojet to an aircraft is presented.

First claim

The invention claimed is:

1. A propulsion assembly for an aircraft, the assembly comprising:
a turbojet having at least one unducted propulsive propeller; and
an attachment pylon for attaching the turbojet to a structural element of the aircraft, said attachment pylon being positioned on the turbojet upstream from the unducted propulsive propeller and having a streamlined profile defined by two opposite side faces extending transversely between a leading edge and a trailing edge;
wherein the attachment pylon has a plurality of blow nozzles situated in the vicinity of its trailing edge and configured to blow air taken from a pressurized portion of the turbojet, said blow nozzles being positioned over at least a fraction of the trailing edge of the attachment pylon that extends longitudinally facing at least a portion of the unducted propulsive propeller,
wherein each of the plurality of blow nozzles has a circular or elliptical outlet section,
wherein the plurality of blow nozzles project out from the trailing edge of the attachment pylon,
wherein the blow nozzles open out in line with the trailing edge of the attachment pylon, and
wherein the blow nozzles are retractable into the inside of the attachment pylon.

2. A propulsion assembly according to claim 1 , further comprising at least one valve configured to control an arrival of air at least one blow nozzle.

3. A method of reducing noise generated by an attachment pylon for attaching a turbojet to a structural element of an aircraft, the turbojet having at least one unducted propulsive propeller, the attachment pylon being positioned on the turbojet upstream from the unducted propulsive propeller and having a streamlined profile extending transversely between a leading edge and a trailing edge, the method comprising blowing air taken from a pressurized portion of the turbojet from the trailing edge of the attachment pylon via a plurality of blow nozzles positioned over at least a fraction of the trailing edge of the attachment pylon extending longitudinally facing at least a portion of the unducted propulsive propeller, wherein each of the plurality of blow nozzles has a circular or elliptical outlet section, wherein the plurality of blow nozzles project out from the trailing edge of the attachment pylon wherein the blow nozzles open out in line with the trailing edge of the attachment pylon, and wherein the blow nozzles are retractable into the inside of the attachment pylon.

4. A method according to claim 3 , further comprising controlling the air blown by the blow nozzles as a function of a stage of flight of the aircraft.

5. A method according to claim 3 , wherein the air blown by the blow nozzles is pulsed at a predefined frequency that is less than a passing frequency of a blade of the unducted propulsive propeller facing the attachment pylon.

6. A method according to claim 3 , wherein the air blown by the blow nozzles is pulsed sequentially at different random frequencies that are less than a passing frequency of blades of a propeller facing the attachment pylon.

Assignees

• Snecma
• Safran Aircraft Engines

Inventors

• Gruber Mathieu Simon Paul
• Delteil Mcwilliams Timothy

Classifications

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64D29/04

  associated with fuselages · CPC title

• B64C2230/14

  achieving noise reductions · CPC title

• F05D2220/323

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