Aircraft propulsion unit comprising an unducted-fan turbine engine and an attachment pylon

Patent metadata

Field	Value
Publication number	US-2018065727-A1
Application number	US-201615551921-A
Country	US
Kind code	A1
Filing date	Feb 18, 2016
Priority date	Feb 19, 2015
Publication date	Mar 8, 2018
Grant date	—

Abstract

A propulsion assembly for aircraft, the assembly including a turbojet having at least one unducted propulsion 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 an airfoil extending transversely between a leading edge and a trailing edge, the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, the cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection.

First claim

1 . A propulsion assembly for aircraft, the assembly comprising:
a turbojet having at least one unducted propulsion propeller; and an attachment pylon for attaching the turbojet to a structural element of the aircraft, said pylon being positioned on the turbojet upstream from the propeller and having an airfoil extending transversely between a leading edge and a trailing edge; wherein the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, said cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection.

2 . The propulsion assembly according to claim 1 , wherein the trailing edge of the airfoil of the pylon presents a geometrical profile that is curved.

3 . The propulsion assembly according to claim 1 , wherein the cutout of the trailing edge of the airfoil of the pylon extends longitudinally over the trailing edge between a point of the trailing edge situated at less than 80% of the height of the propeller and a point of the trailing edge situated at more than 110% of the height of the propeller.

4 . The propulsion assembly according to claim 1 , wherein the cutout in the trailing edge of the airfoil of the pylon presents a geometrical profile made up of a central segment and of two junction curves, said junction curves each presenting a point of inflection and being tangential at their ends to the central segment and to the trailing edge.

5 . The propulsion assembly according to claim 1 , wherein the cutout in the trailing edge of the airfoil of the pylon presents a geometrical profile comprising a circular arc.

6 . The propulsion assembly according to claim 1 , wherein the cutout in the trailing edge of the airfoil of the pylon presents a geometrical profile describing a polynomial curve or a spline curve.

7 . The propulsion assembly according to claim 1 , wherein the cutout in the trailing edge of the airfoil of the pylon presents a geometrical profile made up of two junction curves, each junction curve being tangential at one end to the trailing edge and at another end to the other junction curve.

Assignees

• Safran Aircraft Engines

Inventors

• Gruber Mathieu Simon Paul
• Jodet Norman Bruno Andre

Classifications

• B64D2027/005

  Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR] · CPC title

• B64C1/40

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title

• B64D27/14

  within, or attached to, fuselages · CPC title

• B64D27/00

  Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants · CPC title

• B64C2230/14

  achieving noise reductions · CPC title