Turbomachine guide vanes with improved vane profile

Patent metadata

Field	Value
Publication number	US-10844735-B2
Application number	US-201715618904-A
Country	US
Kind code	B2
Filing date	Jun 9, 2017
Priority date	Jul 6, 2012
Publication date	Nov 24, 2020
Grant date	Nov 24, 2020

Abstract

A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the suction face side, the curve of tangential stacking, of the position, in the direction tangential to the annulus, of centers of gravity of successive vane cross sections along the vane height, is a curve that increases constantly towards the suction face side. The curve, near the vane tip end, has an accentuated gradient towards the suction face side compared with the rest of the curve, and has a mean gradient near the vane tip end that is greater than at least 1.2 times the mean gradient of the curve over the portion between 30% and 90% of the vane height.

First claim

The invention claimed is:

1. A straightener of a turbomachine, comprising:
a plurality of vanes arranged around a ring centered on an axis of the turbomachine, each vane including a leading edge and extending between a root end and a tip end,
the leading edge at the root end of each vane being situated upstream of the leading edge at the tip end of each vane, relative to an air flow direction, an offset of the leading edge between the root end and the tip end being greater than 10% of a height of each vane, measured in a direction of the axis of the turbomachine,
a tangential stacking curve, of a position, in a tangential direction of the ring, of centers of gravity of consecutive vane sections of each vane along the height of each vane from the root end to the tip end of each vane, is a monotonic function increasing toward an extrados of each vane,
the curve has, in proximity to the tip end of each vane, a first portion with an increased slope toward the extrados compared to a rest of the curve, and the curve has an average slope in proximity to the tip end of each vane greater than at least 1.2 times the average slope of the curve on a second portion of the curve between 30% and 90% of the vane height.

2. The turbomachine straightener according to claim 1 , wherein the first portion of the curve in proximity to the tip end is between 90% and 100% of the vane height.

3. The turbomachine straightener according to claim 1 , wherein the leading edge of each vane includes at least one portion located downstream of a position of the leading edge at the tip end of the vane with respect to the direction of the air flow.

4. The turbomachine straightener according to claim 3 , wherein the at least one portion of the leading edge located downstream of the position of the leading edge at the tip end of the vane with respect to the direction of the air flow is included in a region of the leading edge situated between 60% and 100% of the height of the vane.

5. The turbomachine straightener according to claim 3 , wherein a point of the leading edge positioned in line with a position of the leading edge at the tip end of the vane is situated between 60% and 80% of the vane height.

6. The turbomachine straightener according to claim 1 , wherein the leading edge at the root end of each vane is situated upstream of the leading edge at the tip end of the vane with respect to the air flow direction by a distance between 10% and 20% of the vane height, or between 12% and 20% of the vane height, the distance being measured in the direction of the axis of the turbomachine.

7. A turbomachine comprising at least one straightener according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Cojande Pradeep
• Reiss Hanna

Classifications

• F01D5/141 Primary

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

• F05D2240/121

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

• F04D29/544 Primary

  Blade shapes · CPC title