Stator vane with platform having sloped face

Patent metadata

Field	Value
Publication number	US-9938840-B2
Application number	US-201514618035-A
Country	US
Kind code	B2
Filing date	Feb 10, 2015
Priority date	Feb 10, 2015
Publication date	Apr 10, 2018
Grant date	Apr 10, 2018

Abstract

An airfoil includes a stator vane that has a platform with a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end. An airfoil portion extends radially outwardly from the first side. The platform axial trailing end includes a rear axial face that extends from the first radial side and a radially sloped face that extends from the rear axial face to the second radial side.

First claim

What is claimed is:

1. A stator vane comprising:
a platform having a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end, and
an airfoil portion extending radially outwardly from the first radial side,
the platform axial trailing end including a rear axial face extending from the first radial side and a radially sloped face extending from the rear face to the second side, wherein the radially sloped face has a first section proximate the rear axial face and a second section proximate the second radial side, the first section having a first curvature and the second section having a second curvature that is less than the first curvature.

2. The airfoil as recited in claim 1 , wherein the radially sloped face is parabolic.

3. A gas turbine engine comprising:
forward and aft rotors rotatable about an axis, the aft rotor including,
a rotor hub rotatable about an axis and including a bore portion and a rim, and
an arm extending axially and radially inwardly from the rim, the arm having a radially inner side and a radially outer side;

a row of stator vanes axially between the forward and aft rotors, each of the stator vanes including,
a platform having a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end, and
an airfoil portion extending from the first radial side,

a cavity extending from an inlet, between the arm and the platform along the second radial side, to an outlet, the inlet being between the row of stator vanes and the aft rotor and the outlet being between the row of stator vanes and the forward rotor,
the platform axial trailing end of the platform including a rear axial face extending from the first radial side and a radially sloped face extending from the rear axial face to the second radial side, wherein the arm includes a protruding ramp on the radially outer side, and the protruding ramp terminates at a corner and is angled in a direction toward the radially sloped face.

4. The gas turbine engine as recited in claim 3 , wherein the platform axial leading end includes a forward axial face extending from the first radial side and another radially sloped face extending from the forward axial face to the second radial side.

5. The gas turbine engine as recited in claim 3 , wherein the radially sloped face is substantially flat.

6. The gas turbine engine as recited in claim 3 , wherein the radially sloped face has an angle, relative to an axis around which the stator vane is situated, or is to be situated, of approximately 15° to approximately 60°.

7. The gas turbine engine as recited in claim 3 , wherein the radially sloped face is parabolic.

8. The gas turbine engine as recited in claim 3 , wherein the radially sloped face has a first section proximate the rear axial face and a second section proximate the second radial side, the first section having a first curvature and the second section having a second curvature that is less than the first curvature.

9. The gas turbine engine as recited in claim 3 , wherein the radially sloped face has a curvature.

10. The gas turbine engine as recited in claim 9 , wherein the curvature has multiple radii of curvature.

11. The gas turbine engine as recited in claim 3 , wherein the protruding ramp includes a first section proximate the rim and a second section that extends from the first section and also slopes radially outwards from the first section.

12. The gas turbine engine as recited in claim 11 , wherein the first section is curved and the second section is flat and terminates at the corner.

13. The gas turbine engine as recited in claim 3 , wherein the radially sloped face is substantially flat and has an angle, relative to an axis around which the stator vane is situated, or is to be situated, of approximately 15° to approximately 60°.

14. The gas turbine engine as recited in claim 13 , wherein the platform axial leading end includes a forward axial face extending from the first radial side and another radially sloped face extending from the forward axial face to the second radial side.

15. The gas turbine engine as recited in claim 13 , wherein the radially sloped face is angled with regard to the angle of the protruding ramp, to receive at least a portion of a directed stream of gas off of the protruding ramp.

16. The gas turbine engine as recited in claim 13 , wherein the protruding ramp includes a first section proximate the rim and a second section that extends from the first section and also slopes radially outwards from the first section.

17. The gas turbine engine as recited in claim 16 , wherein the first section is curved and the second section is flat and also terminates at a corner.

18. A method for use with an airfoil, the method comprising:
providing a stator vane that includes,
a platform that has a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end, wherein the platform axial trailing end includes a rear axial face that extends from the first radial side and a radially sloped face that extends from the rear axial face to the second radial side, and
an airfoil portion that extends radially outwardly from the first radial side;

using the radially sloped face to receive at least a portion of a directed stream of gas and deflect at least the portion of the directed stream of gas along the second radial side of the platform;
providing a rotor that includes,
a rotor hub that is rotatable about an axis and that has a bore portion and a rim, and
an arm that extends axially and radially inwardly from the rim, wherein the arms has a radially inner side, a radially outer side, and a protruding ramp on the radially outer side; and

using the protruding ramp to vault gas that is flowing along the radially outer side off of the radially outer side as the directed stream of gas.

Assignees

• United Technologies Corp

Inventors

• Forcier Matthew P
• Schuler Brian J
• Wall Jordan T

Classifications

• F01D5/02

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

• F01D11/02

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F05D2250/16

  parabolic · CPC title

• F05D2250/712

  concave · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title