Airfoils for reducing secondary flow losses in gas turbine engines

Patent metadata

Field	Value
Publication number	US-10107104-B2
Application number	US-201615011081-A
Country	US
Kind code	B2
Filing date	Jan 29, 2016
Priority date	Jan 29, 2016
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

Airfoils for gas turbine engines are disclosed herein. The airfoils each include a pressure side and a suction side. Vortex-reduction passageways extend from the pressure side to the suction side.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, the airfoil comprising
a pressure side that extends radially from a radially-outer point to a radially-inner point arranged opposite the radially-outer point,
a suction side arranged opposite the pressure side that extends radially from the radially-outer point to the radially-inner point,
a first vortex-reduction passageway arranged to extend directly from the pressure side to the suction side to provide fluid communication from the pressure side to the suction side and located near one of the radially-outer point of the airfoil and the radially-inner point of the airfoil such that the first vortex-reduction passageway is configured to conduct gas from the pressure side to the suction side during use of the airfoil in a gas turbine engine in order to inhibit radial migration of a secondary-flow vortex that may form along a radially-outer portion or a radially-inner portion of the suction side,
an inlet slot formed in the pressure side separately from the first vortex-reduction passageway that is fluidly coupled to the first vortex-reduction passageway to direct gas passing along the pressure side during use of the airfoil in the gas turbine engine into the first vortex-reduction passageway, and
an outlet slot formed in the suction side separately from the first vortex-reduction passageway that is fluidly coupled to the first vortex-reduction passageway to direct gas passing through the first vortex-reduction passageway during use of the airfoil in the gas turbine engine along the suction side,
wherein the first vortex-reduction passageway is spaced apart from a radially-middle portion of the airfoil located between the radially-outer portion of the airfoil and the radially-inner portion of the airfoil, the radially-middle portion sized to make up at least a third of a distance between the radially-outer point and the radially inner point of the airfoil, and the radially-middle portion is devoid of passageways that provide fluid communication directly from the pressure side to the suction side of the airfoil, and wherein the inlet slot extends partway through the airfoil from one of the radially-outer point and the radially-inner point toward the other of the radially-outer point and the radially-inner point.

2. The airfoil of claim 1 , wherein the pressure side and the suction side interconnect with one another at a leading edge of the airfoil and at a trailing edge of the airfoil positioned aft of the leading edge and the first vortex-reduction passageway is located closer to the leading edge than the trailing edge.

3. The airfoil of claim 1 , wherein the airfoil has an aspect ratio of less than 1.0.

4. The airfoil of claim 1 , wherein the first vortex-reduction passageway extends radially partway through the airfoil from one of the radially-outer point and the radially-inner point toward the other of the radially-outer point and the radially-inner point.

5. The airfoil of claim 4 , further comprising a second vortex-reduction passageway arranged to extend directly from the pressure side to the suction side to provide fluid communication from the pressure side to the suction side and located between the first vortex-reduction passageway and the radially-middle portion such that the second vortex-reduction passageway is spaced apart from the first vortex-reduction passageway and the radially-middle portion.

6. The airfoil of claim 1 , wherein the outlet slot extends partway through the airfoil from the one of the radially-outer point and the radially-inner point toward the other of the radially-outer point and the radially-inner point.

7. An airfoil for a gas turbine engine, the airfoil comprising
a pressure side,
a suction side,
a first vortex-reduction passageway arranged to extend directly from the pressure side to the suction side to provide fluid communication from the pressure side to the suction side, wherein the first vortex-reduction passageway is spaced apart from a middle portion of the airfoil that is located about midway along a height of the airfoil, sized to make up at least a third of the height of the airfoil, and devoid of any passageways that provide fluid communication directly from the pressure side to the suction side of the airfoil,
an inlet slot separate from the first vortex-reduction passageway that is fluidly coupled to the first vortex-reduction passageway to direct gas passing along the pressure side during use of the airfoil in the gas turbine engine into the first vortex-reduction passageway, and
an outlet slot separate from the first vortex-reduction passageway that is fluidly coupled to the first vortex-reduction passageway to direct gas passing through the first vortex-reduction passageway during use of the airfoil in the gas turbine engine along the suction side,
wherein the pressure side and the suction side interconnect with one another at a leading edge of the airfoil and at a trailing edge of the airfoil positioned aft of the leading edge and the first vortex-reduction passageway is located closer to the leading edge than the trailing edge.

8. The airfoil of claim 7 , wherein the first vortex-reduction passageway is configured to conduct gas from the pressure side to the suction side during use of the airfoil in a gas turbine engine in order to inhibit radial migration of a secondary-flow vortex that may form along a radially-outer portion or a radially-inner portion of the suction side.

9. The airfoil of claim 8 , wherein the airfoil has an aspect ratio of less than 1.0.

10. A vane adapted for use in a gas turbine engine, the vane comprising
an outer end wall,
an inner end wall spaced from the outer end wall, and
an airfoil that extends from the outer end wall to the inner end wall, the airfoil having a pressure side, a suction side, a first vortex-reduction passageway arranged to extend from the pressure side to the suction side to provide fluid communication from the pressure side to the suction side, an inlet slot formed in the pressure side separately from the first vortex-reduction passageway that is fluidly coupled to the first vortex-reduction passageway, and an outlet slot formed in the suction side separately from the first vortex-reduction passageway that is fluidly coupled to the first vortex-reduction passageway, wherein the inlet slot extends partway through the airfoil from one of the outer end wall and the inner end wall toward the other of the outer end wall and the inner end wall.

11. The vane of claim 10 , wherein the first vortex-reduction passageway is configured to conduct gas from the pressure side to the suction side during use of the vane in a gas turbine engine in order to inhibit radial migration of a secondary-flow vortex that may form along a radially-outer portion or a radially-inner portion of the suction side.

12. The vane of claim 10 , wherein the first vortex-reduction passageway is spaced apart from a middle portion of the vane that is located about midway along a height of the vane, sized to make up at least a third of the height of the vane, and devoid of any passageways that provide fluid communication directly from the pressure side to the suction side of the vane.

13. The vane of claim 10 , wherein the airfoil has an aspect ratio of less than 1.0.

Assignees

• Rolls Royce Corp

Inventors

• Bloxham Matthew J

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/124

  related to the suction side of a stator vane · CPC title

• F05D2240/123

  related to the pressure side of a stator vane · CPC title

• F01D5/145 Primary

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

• F05D2240/306

  related to the suction side of a rotor blade · CPC title