Propulsion assembly for an aircraft comprising a stator vane integrated into an upstream part of a mounting pylon of reduced height

Patent metadata

Field	Value
Publication number	US-12570404-B2
Application number	US-202218261124-A
Country	US
Kind code	B2
Filing date	Jan 5, 2022
Priority date	Jan 12, 2021
Publication date	Mar 10, 2026
Grant date	Mar 10, 2026

Abstract

A propulsion assembly for an aircraft comprising a dual-flow turbine engine equipped with a fan, an aerodynamic outer shroud acting as a nacelle as well as a mounting pylon, the propulsion assembly having a secondary flow path defined by an outer radial defining surface formed by the shroud, the turbine engine including stator vanes, and the mounting pylon comprising a part housed in the secondary flow path, referred to as upstream part. According to the invention, the upstream part of the pylon extends radially from the inner radial defining surface, along a radial pylon height strictly less than a total radial height of the secondary flow path, and the upstream part of the pylon extends in the downstream direction from a root part of one of the stator vanes.

First claim

The invention claimed is:

1 . A propulsion assembly for an aircraft comprising a dual-flow turbine engine comprising a fan; an aerodynamic outer shroud acting as a nacelle arranged around the fan; a mounting pylon for fastening the turbine engine to a wing element of the aircraft, the propulsion assembly having a primary gas flow path; and a secondary gas flow path defined by an inner radial defining surface as well by an outer radial defining surface formed by the aerodynamic outer shroud, the turbine engine further including an annular row of stator vanes arranged in the secondary flow path downstream from the fan, each stator vane extending through the secondary flow path while having a tip end connected to the aerodynamic outer shroud and a root end connected to the inner radial defining surface of the secondary flow path, the mounting pylon comprising an upstream part housed in the secondary flow path and a downstream part arranged downstream from a trailing edge of the aerodynamic outer shroud, the trailing edge of the aerodynamic outer shroud is arranged entirely upstream from a leading edge of the wing element,
wherein the upstream part of the mounting pylon housed in the secondary flow path extends radially from the inner radial defining surface, along a radial pylon height strictly less than a total radial height of the secondary flow path, and in that the upstream part of the mounting pylon extends in the downstream direction from a root part of one of the stator vanes, wherein the upstream part of the mounting pylon is radially surrounded by the secondary flow path and the downstream part of the mounting pylon is not surrounded by the secondary flow path, and wherein the one stator vane includes, radially outwards from the upstream part of the mounting pylon, a free trailing edge of the stator vane extending to the aerodynamic outer shroud.

2 . The propulsion assembly according to claim 1 , wherein the radial pylon height locally represents 20 to 70% of the total radial height of the secondary flow path.

3 . The propulsion assembly according to claim 1 , wherein the one stator vane includes the following parts, in radial succession from the inside outwards:
the root part integrated in the upstream part of the mounting pylon; a transition part; and a tip part.

4 . The propulsion assembly according to claim 3 , wherein a trailing edge of the transition part has a transverse thickness which increases moving radially towards the root part of the one stator vane.

5 . The propulsion assembly according to claim 3 , wherein the transition part has a chord of greater length than that of the tip part or wherein said transition part comprises a truncated trailing edge such that the chord of the transition part has an increasing length moving from the root part to the tip part.

6 . The propulsion assembly according to claim 1 , wherein the ratio between the total axial length of the aerodynamic outer shroud and the diameter of the fan is less than 1.25.

7 . The propulsion assembly according to claim 1 , wherein the fan includes variable-pitch rotary vanes and wherein the aerodynamic outer shroud acting as a nacelle is devoid of a thrust reversal system.

8 . An aircraft part comprising a propulsion assembly according to claim 1 and the wing element.

9 . An aircraft comprising at least one part according to claim 8 .

10 . The propulsion assembly according to claim 1 , wherein an upper part of the shroud is arranged axially upstream of the leading edge of the wing element and wherein an apex of the outside of the aerodynamic outer shroud extends higher than the wing element.

Assignees

• Safran Aircraft Engines

Inventors

• Lebeault Eva Julie
• Binder Anthony
• Soulat Laurent

Classifications

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title

• B64C7/02

  Nacelles · CPC title

• F02K3/068

  being characterised by a short axial length relative to the diameter · CPC title

• F02K1/66

  using reversing fan blades · CPC title

• B64D27/402

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