Guide assembly with optimised aerodynamic performance

Patent metadata

Field	Value
Publication number	US-10385708-B2
Application number	US-201615549647-A
Country	US
Kind code	B2
Filing date	Feb 9, 2016
Priority date	Feb 9, 2015
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

The invention relates to a turbine engine air flow guide assembly including: a structural arm ( 30 ); and a guide vane ( 21 ) on the lower surface of the structural arm, comprising a leading edge ( 22 ), a trailing edge ( 23 ), and a camber line ( 24 ), said vane and arm extending radially about an axis (X-X) of the turbine engine and defining therebetween an air flow channel. The structural arm ( 30 ) comprises: an upstream end ( 31 ) having a guide vane profile ( 21 ) and comprising a leading edge ( 32 ) aligned with that of the vane; and a shoulder ( 35 ) located on the lower surface of the arm, defining a neck in the channel. The assembly is characterized in that the area (A neck ) of the section of the channel at the neck is between 0.7 and 0.9 times the area (A inlet ) of the section of the channel at the leading edges.

First claim

The invention claimed is:

1. A turbine engine air flow guide assembly comprising:
a structural arm and
at least one guide vane, situated at a lower surface of the structural arm and comprising a leading edge, a trailing edge and a camber line extending between the leading edge and the trailing edge,

wherein the vane and the arm extend radially between an annular inner wall and an annular outer wall around an axis (X-X) of the turbine engine and define an air flow channel between them, and the structural arm comprises:
an upstream end, with respect to the air flow direction in the channel, having a guide vane profile and comprising a leading edge aligned with the leading edge of the vane, and
a shoulder situated at the lower surface of the arm, defining a throat in the channel upstream of which the channel is convergent and downstream of which it is divergent,

wherein the area (A throat ) of the section of the channel at the throat is comprised between 0.7 and 0.9 times the area (A inlet ) of the section of the channel at the leading edges of the vane and of the arm.

2. The turbine engine air flow guide assembly according to claim 1 , wherein the area (A throat ) of the section of the channel at the throat is comprised between 0.75 and 0.85 times the area (A inlet ) of the section of the channel at the leading edges of the vane and of the arm.

3. The turbine engine air flow guide assembly according to claim 2 , wherein the area (A throat ) of the section of the channel at the throat is comprised between 0.79 and 0.81 times the area (A inlet ) of the section of the channel at the leading edges of the vane and of the arm.

4. The turbine engine air flow guide assembly according to claim 1 , wherein the throat of the channel has an axial position x throat defined by:
x throat =x 1/2emax ±0.05 c

where x 1/2emax is the axial position of the maximum thickness section of the arm on the lower surface side and c is the length of the axial chord of the guide vane,
and the axial position of the maximum thickness section of the arm on the lower surface side is comprised between the axial position of the leading edge and that of the trailing edge of the vane.

5. A bypass type turbine engine, comprising a secondary flow guide comprising a plurality of vanes arranged radially around an axis (X-X) of the turbine engine, and at least one structural arm, wherein at least one structural arm and a vane of the guide form a guide assembly according to claim 1 .

Assignees

• Safran Aircraft Engines
• Snecma

Inventors

• Damevin Henri-Marie
• Fessou Philippe Jacques Pierre
• Maniere Vianney Christophe Marie
• Schvallinger Michael Franck Antoine

Classifications

• F01D25/162

  Bearing supports · CPC title

• F01D9/041 Primary

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

• F01D5/141

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

• F04D29/544 Primary

  Blade shapes · CPC title

• F04D29/667

  by influencing the flow pattern, e.g. suppression of turbulence · CPC title