Channeling furrow upstream of a blade

Patent metadata

Field	Value
Publication number	US-11519274-B2
Application number	US-201917269742-A
Country	US
Kind code	B2
Filing date	Aug 19, 2019
Priority date	Aug 20, 2018
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

The invention relates to an assembly for a turbomachine ( 1 ) extending about an axis (X) comprising: —an inner annular platform ( 13 ) and an outer annular platform ( 14 ) delimiting a flow channel ( 3 ) for a flow flowing from upstream to downstream, and —at least one fixed blade ( 12 ) extending radially between the inner annular platform ( 13 ) and the outer annular platform ( 14 ), said fixed blade ( 12 ) being profiled with a leading edge ( 15 ), characterized in that the inner annular platform ( 13 ) and/or the outer annular platform ( 14 ) comprises, upstream of the leading edge ( 15 ) of the fixed blade ( 12 ), a furrow ( 21 ) for channeling the fluid flowing in the channel ( 3 ), having a segment forming an upstream limit ( 22 ) and a segment forming a downstream limit ( 23 ), the length of the upstream limit ( 22 ) being greater than the length of the downstream limit ( 23 ).

First claim

The invention claimed is:

1. An assembly for a turbomachine,
the assembly extending around an axis,
the assembly including:
an inner annular platform and an outer annular platform, the inner annular platform and the outer annular platform delimiting a flow channel for a fluid circulating from upstream to downstream; and
at least one fixed blade extending radially between the inner annular platform and the outer annular platform, the fixed blade being profiled with a leading edge,
wherein the inner annular platform and/or the outer annular platform includes, upstream of the leading edge of the fixed blade, a furrow for channeling fluid circulating in the flow channel,
the furrow having a segment forming an upstream limit and a segment forming a downstream limit,
a length of the upstream limit being greater than a length of the downstream limit, and
wherein the furrow has a profile including a first cross section of parabolic shape and a second cross section of sinusoidal shape.

2. The assembly for a turbomachine according to claim 1 ,
wherein the blade includes a camber line, and
wherein the furrow includes a median line,
the median line of the furrow extending in a continuation of the camber line of the blade.

3. The assembly for a turbomachine according to claim 2 , wherein the downstream limit of the furrow is located downstream of the leading edge of the blade.

4. The assembly for a turbomachine according to claim 1 ,
wherein the blade comprises a maximum thickness in a direction,
transverse with respect to a chord line of the blade,
the length of the upstream limit being comprised between 150% and 400% of the maximum thickness of the blade, and
the length of the downstream limit being comprised between 80% and 120% of the maximum thickness of the blade.

5. The assembly for a turbomachine claim 1 ,
wherein the first cross section has a depth which is a maximum depth of the furrow,
the furrow having a depth that decreases downstream of the first cross section,
the second cross section being located in proximity to the leading edge of the blade and having a smaller depth than the depth of the first cross section.

6. The assembly according to claim 1 , wherein the furrow includes a median longitudinal guide curve having an arc length comprised between 40% and 200% of a length of a chord of the blade.

7. The assembly according to claim 1 , wherein the furrow has, at the upstream limit, an angular opening greater than a range of variation of an angle of attack relative to the blades of the flow flowing in the flow channel.

8. The assembly according to claim 1 ,
wherein each blade has a pressure side and a suction side; and
wherein the furrow has at the downstream limit an angular opening corresponding to a relative inclination of the pressure side and of the suction side at the downstream limit.

9. A turbomachine including the assembly according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Maniere Vianney Christophe Marie

Classifications

• F01D9/041

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

• F01D5/143 Primary

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• Y02T50/60

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

• F05D2250/184

  sinusoidal · CPC title

• F05D2220/323

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