Turbomachine part with a non-axisymmetric surface

Patent metadata

Field	Value
Publication number	US-10352330-B2
Application number	US-201415028059-A
Country	US
Kind code	B2
Filing date	Oct 10, 2014
Priority date	Oct 11, 2013
Publication date	Jul 16, 2019
Grant date	Jul 16, 2019

Abstract

A turbomachine part including at least first and second blades, and a platform from which the blades extend, wherein the platform has a non-axisymmetric surface limited by first and second end planes, and defined by at least three construction curves of class CI each representing the value of a radius of the surface on the basis of a position between the lower surface of the first blade and the upper surface of the second blade according to a plane substantially parallel to the end planes, including a first curve that increases in the vicinity of the second blade; a second curve that decreases in the vicinity of the second blade; a third curve having a minimum at the second blade.

First claim

The invention claimed is:

1. A part of a turbine engine, the part comprising:
at least first and second blades; and
a platform from which the blades extend,
wherein the platform has a non-axisymmetrical surface limited by a first and a second end plane, and defined by at least three construction curves of class C 1 each representing the value of a radius of said surface as a function of a position from an intrados of the first blade to an extrados of the second blade according to a plane parallel to the end planes, whereof:
a first curve increasing at the second blade;
a second curve arranged between the first curve and a trailing edge of the first and second blades, and decreasing at the second blade;
a third curve arranged between the first curve and a leading edge of the first and second blades, and having a minimum at the first blade.

2. The part according to claim 1 , wherein the third curve is strictly increasing from the intrados of the first blade to the extrados of the second blade.

3. The part according to claim 1 , wherein the third curve is less than the first curve at the second blade.

4. The part according to claim 1 , wherein the first curve is strictly increasing from the intrados of the first blade to the extrados of the second blade.

5. The part according to claim 1 , wherein the second curve has a local maximum between the intrados of the first blade and the extrados of the second blade.

6. The part according to claim 1 , wherein the first curve is associated to a position along a blade chord extending from the leading edge to the trailing edge of the first and second blades located between 0% and 60% of relative length of blade chord, and the second curve is associated to a position along the blade chord located between 65% and 100% of relative length of blade chord.

7. The part according to claim 6 , wherein the third curve is associated to a position along the blade chord located between 0% and 25% in relative length of blade chord, and the first curve is associated to a position along the blade chord located between 30% and 60% of relative length of blade chord.

8. The part according to claim 1 , wherein the platform has an annular form along which the at least first and second blades is uniformly arranged.

9. The part according to claim 8 , wherein the platform has said non-axisymmetrical surface between each consecutive pair of blades of the at least first and second blades.

10. The part according to claim 9 , being a compressor part of the turbine engine.

11. The part according to claim 10 , being a rotor or stator stage of the compressor.

12. The part according to claim 1 , for which each construction curve is modelled by a data-processor performing steps of:
parametrization of the construction curve as curve of class C 1 representing the value of the radius of said surface as a function of a position between the intrados of the first blade and the extrados of the second blade, the curve being defined by:
two end control points, respectively on each of the first and second blades between which said surface extends; and
at least one spline;

parametrization being performed according to at least one parameter defining at least one of the end control points;
determination of optimized values of said at least one parameter.

13. A turbine engine comprising a part according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Cellier Damien Joseph

Classifications

• F04D29/329

  Details of the hub · CPC title

• F05B2240/80

  Platforms for stationary or moving blades · CPC title

• F04D29/324

  Blades · CPC title

• F05D2250/71

  curved · CPC title

• F04D29/544

  Blade shapes · CPC title