Dimensioning of the skeleton angle of the trailing edge of the arms crossing the by-pass flow of a turbofan

Patent metadata

Field	Value
Publication number	US-11221020-B2
Application number	US-201615756387-A
Country	US
Kind code	B2
Filing date	Sep 2, 2016
Priority date	Sep 2, 2015
Publication date	Jan 11, 2022
Grant date	Jan 11, 2022

Abstract

A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3° and 15°.

First claim

The invention claimed is:

1. A bypass flow guide vane stage of a turbine engine of a turbofan type, comprising:
a plurality of obstacles including
a blade,
a pylon, and
an arm which is not said pylon; and

a platform from which said plurality of obstacles extend,
wherein said pylon and the arm are both wider and longer than the blade, the arm is more massive than the blade, and said pylon is more massive than the arm,
wherein said pylon is defined by a pylon skeleton angle having, at a trailing edge of said pylon, a trailing value between 5° and 13° with respect to a longitudinal axis of the turbine engine, said pylon skeleton angle at the trailing edge of said pylon being oriented so as to cause an orientation of a suction side of said pylon to tend forward the longitudinal axis of the turbine engine, and
wherein the trailing edge of said pylon is disposed downstream of a trailing edge of the arm and downstream of a trailing edge of the blade, and the trailing edge of the arm is disposed downstream of the trailing edge of the blade.

2. The guide vane stage according to claim 1 , wherein said trailing value is between 7° and 11°.

3. The guide vane stage according to claim 1 , wherein said pylon has an inclination start position situated at between 40% and 80% of a relative length of a chord extending from a leading edge to the trailing edge of said pylon, said pylon skeleton angle having said trailing value between a curvature start position and the trailing edge of said pylon.

4. The guide vane stage according to claim 3 , wherein the inclination start position is situated at between 50% and 70% of the relative length of the chord.

5. The guide vane stage according to claim 1 , wherein the suction side or a pressure side of said pylon is rectilinear between the inclination start position and a beginning of a closure of the trailing edge of said pylon.

6. The guide vane stage according to claim 1 , wherein said arm is defined by an arm skeleton angle having, at the trailing edge of said arm, said trailing value.

7. The guide vane stage according to claim 6 , wherein said arm is situated at the suction side of said pylon, said arm skeleton angle at the trailing edge of said arm being oriented so as to cause an orientation of a suction side of said arm to tend forward the longitudinal axis of the turbine engine.

8. The guide vane stage according to claim 6 , wherein said arm is situated at a pressure side of said pylon, said arm skeleton angle at the trailing edge of said arm being oriented so as to cause an orientation of a pressure side of said arm to tend forward the longitudinal axis of the turbine engine.

9. The guide vane stage according to claim 6 , wherein said trailing value increases in absolute value with proximity of said arm to said pylon.

10. A turbine engine comprising the bypass flow guide vane stage according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Madiot Ghislain Maxime Romuald
• Bertucchi Jean
• Cellier Damien Joseph
• Kernemp Irwin Pierre Robert
• Mazzella Aurelien

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F01D25/162

  Bearing supports · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title