Vane for variable area turbine

Patent metadata

Field	Value
Publication number	US-10480326-B2
Application number	US-201715701008-A
Country	US
Kind code	B2
Filing date	Sep 11, 2017
Priority date	Sep 11, 2017
Publication date	Nov 19, 2019
Grant date	Nov 19, 2019

Abstract

Disclosed is a vane stage for a variable area turbine, comprising vane platforms comprising a first vane platform and a second vane platform, one of the vane platforms being a radial inner vane platform and another of the vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath; a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, a secondary vane body movably secured at the first vane platform, the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension.

First claim

What is claimed is:

1. A vane stage for a variable area turbine, comprising:
a plurality of vane platforms comprising a first vane platform and a second vane platform, one of the plurality of vane platforms being a radial inner vane platform and another of the plurality of vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath;
a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, the primary vane body having a primary leading edge, a primary trailing edge, a primary pressure side and a primary suction side,
a secondary vane body movably secured at the first vane platform, the secondary vane body having secondary leading edge, a secondary trailing edge, a secondary pressure side and a secondary suction side, and
the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path and a first radial end surface of the secondary vane body is flush with the first vane platform, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension, and
the secondary vane body includes a plurality of radially spaced tabs that support the secondary pressure side and secondary suction side of the secondary body, the plurality of tabs defining the leading edge of the secondary vane body and the tabs forming a first boss for positioning the secondary vane body at the trailing edge of the primary vane body.

2. The vane stage of claim 1 wherein the radial end of surface of the secondary vane body includes a plurality of protrusions forming a second boss for positioning secondary vane body against the second vane platform.

3. The vane stage of claim 2 wherein the trailing edge of the primary body includes a cooling air slot.

4. The vane stage of claim 3 wherein a trailing edge of the plurality of tabs is tapered to form an air convergence cavity within the secondary vane body, the wherein the air convergence cavity receives air flowing from the trailing edge of the primary vane body when the secondary vane body is in the deployed position.

5. The vane stage of claim 4 wherein the secondary vane body includes a plurality of cooling holes in one or both of the secondary pressure side surface and secondary suction side surface proximate the air convergence cavity.

6. The vane stage of claim 3 wherein the secondary vane body includes a cooling slot extending from the leading edge to the trailing edge of the secondary body.

7. The vane stage of claim 3 wherein the trailing edge of the primary vane body includes a radially extending cutback slot along which the secondary leading edge of the secondary vane body is positioned in the deployed position.

8. A gas turbine engine comprising:
a variable area turbine that includes a vane stage, the vane stage comprising:
a plurality of vane platforms comprising a first vane platform and a second vane platform, one of the plurality of vane platforms being a radial inner vane platform and another of the plurality of vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath;
a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, the primary vane body having a primary leading edge, a primary trailing edge, a primary pressure side and a primary suction side,
a secondary vane body movably secured at the first vane platform, the secondary vane body having secondary leading edge, a secondary trailing edge, a secondary pressure side and a secondary suction side,
the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path and a first radial end surface of the secondary vane body is flush with the first vane platform, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension, and
the secondary vane body includes a plurality of radially spaced tabs that support the secondary pressure side and secondary suction side of the secondary body, the plurality of tabs defining the leading edge of the secondary vane body and the tabs forming a first boss for positioning the secondary vane body at the trailing edge of the primary vane body.

9. The engine of claim 8 wherein the radial end of surface of the secondary vane body includes a plurality of protrusions forming a second boss for positioning secondary vane body against the second vane platform.

10. The engine of claim 9 wherein the trailing edge of the primary body includes a cooling air slot.

11. The engine of claim 10 wherein a trailing edge of the plurality of tabs is tapered to form an air convergence cavity within the trailing edge of the secondary vane body, the wherein the air convergence cavity receives air flowing from the first plurality of film cooling holes when the secondary vane body is in the deployed position.

12. The engine of claim 11 wherein the secondary vane body includes a plurality of cooling holes in one or both of the secondary pressure side surface and secondary suction side surface proximate the air convergence cavity.

13. The engine of claim 10 wherein the secondary vane body includes a cooling slot extending from the leading edge to the trailing edge of the secondary body.

14. The engine of claim 10 wherein the trailing edge of the primary vane body includes a radially extending cutback slot along which the secondary leading edge of the secondary vane body is positioned in the deployed position.

15. A method for decreasing a gage distance between at least two vanes in a plurality of vanes on a first vane stage of a variable area turbine, the first vane stage comprising:
a plurality of vane platforms comprising a first vane platform and a second vane platform, one of the plurality of vane platforms being a radial inner vane platform and another of the plurality of vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath;
a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, the primary vane body having a primary leading edge, a primary trailing edge, a primary pressure side and a primary suction side,
a secondary vane body movably secured at the first vane platform, the secondary vane body having secondary leading edge, a secondary trailing edge, a secondary pressure side and a secondary suction side, and
the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path and a first radial end surface of the secondary vane body is flush with the first vane platform, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension, and
the secondary vane body includes a plurality of radially spaced tabs that support the secondary pressure side and secondary suction side of the secondary body, the plurality of tabs defining the leading edge of the secondary vane body and the tabs forming a first boss for positioning the secondary vane body at the trailing edge of the primary vane body;
the method comprising extending the secondary vane body from the stowed position to the deployed position.

16. The method of claim 15 wherein each of the plurality of vanes includes a primary vane body fixedly disposed on the first stage of the variable area turbine.

Assignees

• United Technologies Corp

Inventors

• Candelori David J
• Blair Michael F

Classifications

• F04D29/544

  Blade shapes · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F01D17/16

  by means of nozzle vanes · CPC title

• F01D5/145 Primary

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

• F01D5/142

  of the blades of successive rotor or stator blade-rows · CPC title