Airfoil and platform assembly for supersonic flow

Patent metadata

Field	Value
Publication number	US-9458720-B2
Application number	US-201213984722-A
Country	US
Kind code	B2
Filing date	Feb 6, 2012
Priority date	Feb 10, 2011
Publication date	Oct 4, 2016
Grant date	Oct 4, 2016

Abstract

An assembly including an airfoil and a platform on which the airfoil may be mounted, the surface of the platform presenting a circumferential depression between a leading edge and trailing edge of the airfoil, a deepest section of the depression being situated in an upstream half of the airfoil. A skeleton curve designates a curve of variations of a skeleton angle of the airfoil as a function of position along the axis of the wheel, and a linearized skeleton curve designates a curve of variations of an angle as a function of position along the axis of the wheel, the curve being a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge. In a vicinity of the platform, the skeleton curve presents a raised portion that lies above the linearized skeleton curve.

First claim

The invention claimed is:

1. An assembly comprising:
an airfoil for a turbine engine bladed wheel and a platform on which the airfoil is configured to be mounted:
a plurality of the airfoils configured to be fastened to the platform or to a plurality of the platforms assembled together so as to form a bladed wheel including a wheel axis and defining upstream and downstream directions along the wheel axis, the airfoils being arranged radially in the wheel;
in the wheel, the platform or the assembled-together platforms present a platform surface between the airfoils and that radially defines an inside of gas-passing passages formed between the airfoils; and
the platform surface presenting a circumferential depression extending axially substantially between a leading edge and a trailing edge of an airfoil, a deepest section of the depression being situated axially in an upstream half of the airfoil;
wherein:
a skeleton curve is a curve representing variations of a skeleton angle of the airfoil in a section plane substantially parallel to the platform surface, as a function of position along the wheel axis;
a linearized skeleton curve is a curve representing variations of an angle as a function of position along the wheel axis, which linearized skeleton curve is a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge,
in a vicinity of the platform, the skeleton curve presents a raised portion lying above the linearized skeleton curve, and
a plane in which an offset between the skeleton curve and the linearized skeleton curve is at a maximum is situated axially between a position at 0.5×N % of the deepest section and 1.5×N %, the value N being a percentage expressed relative to axial extent of the airfoil from the leading edge.

2. An assembly according to claim 1 , wherein a plane in which an offset between the skeleton curve and the linearized skeleton curve is at a maximum substantially coincides with the plane of the deepest section.

3. An assembly according to claim 1 , wherein the deepest section is situated axially in a range of 15% to 40% of the axial extent of the airfoil from the leading edge.

4. A blade for a turbine engine, comprising:
an assembly according to claim 1 , the blade comprising a platform formed integrally with at least one airfoil.

5. A turbine engine bladed wheel comprising blades according to claim 4 .

6. A turbine engine bladed wheel comprising at least one assembly according to claim 1 .

7. A turbine engine comprising at least one bladed wheel according to claim 5 .

8. A turbine engine comprising at least one bladed wheel according to claim 6 .

9. An assembly comprising:
an airfoil for a turbine engine bladed wheel and a platform on which the airfoil is configured to be mounted:
a plurality of the airfoils configured to be fastened to the platform or to a plurality of the platforms assembled together so as to form a bladed wheel including a wheel axis and defining upstream and downstream directions along the wheel axis, the airfoils being arranged radially in the wheel;
in the wheel, the platform or the assembled-together platforms present a platform surface between the airfoils and that radially defines an inside of gas-passing passages formed between the airfoils; and
the platform surface presenting a circumferential depression extending axially substantially between a leading edge and a trailing edge of an airfoil, a deepest section of the depression being situated axially in an upstream half of the airfoil;
wherein:
a skeleton curve is a curve representing variations of a skeleton angle of the airfoil in a section plane substantially parallel to the platform surface, as a function of position along the wheel axis;
a linearized skeleton curve is a curve representing variations of an angle as a function of position along the wheel axis, which linearized skeleton curve is a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge,
in a vicinity of the platform, the skeleton curve presents a raised portion lying above the linearized skeleton curve, and a lowered portion lying under the linearized skeleton curve and situated axially downstream from the raised portion.

10. An assembly according to claim 9 , wherein the skeleton curve and the linearized skeleton curve intersect at a point situated in a range of 50% to 75% of the axial extent of the airfoil from the leading edge.

Assignees

• Cellier Damien
• Perrot Vincent Paul Gabriel
• Rios Jean-Francois
• Snecma

Inventors

• Cellier Damien
• Perrot Vincent Paul Gabriel
• Rios Jean-Francois

Classifications

• F05D2240/301

  Cross-sectional characteristics · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F01D5/02 Primary

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F01D5/143 Primary

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

• F05D2250/713

  inflexed · CPC title