Flow discourager for vane sealing area of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10107118-B2
Application number	US-201414900737-A
Country	US
Kind code	B2
Filing date	Jun 27, 2014
Priority date	Jun 28, 2013
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.

First claim

What is claimed is:

1. An interface within a gas turbine engine comprising:
a sealing surface defined by an axial flange that extends from a platform parallel to an engine central longitudinal axis;
a seal in contact with said sealing surface to seal from a secondary airflow; and
a barrier that extends transverse and beyond said sealing surface with respect to the engine central longitudinal axis, said barrier located between said seal and the secondary airflow that recirculates in a recirculating air cavity.

2. The interface as recited in claim 1 , wherein said barrier extends from a low pressure turbine seal.

3. The interface as recited in claim 1 , wherein said barrier is transverse to said sealing surface and extends radially inboard with respect to engine central longitudinal axis and toward said vane platform.

4. The interface as recited in claim 1 , wherein said seal surface is parallel to said engine central longitudinal axis.

5. The interface as recited in claim 1 , wherein said barrier is angled with respect to said seal to align with a trailing edge of a vane that extends from said vane platform.

6. The interface as recited in claim 1 , wherein said barrier is L-shaped in cross-section.

7. The interface as recited in claim 6 , wherein said seal is in contact with said axial flange.

8. The interface as recited in claim 1 , wherein said barrier is step-shaped in cross-section, said step-shape located radially beyond said sealing surface with respect to the engine central longitudinal axis.

9. The interface as recited in claim 1 , wherein said barrier extends with respect to the engine central longitudinal axis toward said platform to permit an increase in temperature of a section of said vane platform and reduce a structural thermal conflict of said vane platform.

10. A mid turbine frame module for a gas turbine engine comprising:
an outer turbine case about an axis;
an inner case about said axis;
a mid-turbine frame radially between said outer turbine case and said inner case, said mid turbine frame includes an inner vane platform, an outer vane platform and a plurality of vanes between said inner vane platform and said outer vane platform;
a seal in contact with said mid-turbine frame at a sealing surface to seal from a secondary airflow; and
a barrier that extends transverse and beyond said sealing surface with respect to the engine central longitudinal axis, said barrier located between said seal and the secondary airflow that recirculates in a recirculating air cavity.

11. The mid turbine frame module as recited in claim 10 , wherein said barrier extends toward but is not in contact with said inner vane platform, said barrier axially aligned with an edge of a vane that extends from said vane platform.

12. The mid turbine frame module as recited in claim 10 , wherein said barrier extends toward but is not in contact with said outer vane platform, said barrier axially aligned with an edge of a vane that extends from said vane platform.

13. The mid turbine frame module as recited in claim 10 , further comprising a plurality of tie-rods through said mid turbine frame.

14. The mid turbine frame module as recited in claim 10 , wherein said seal is mounted to said inner case, said barrier extends from said inner case toward but not in contact with, said inner vane platform.

15. A method of reducing a temperature gradient within a portion of a wall defining a core gas passage in a gas turbine engine, the method comprising:
orienting a barrier to extend transverse and beyond a sealing surface with respect to the engine central longitudinal axis to seal from a secondary airflow to at least partially shield the sealing surface from recirculating air, said barrier located between a seal in contact with said sealing surface and the secondary airflow that recirculates in a recirculating air cavity, said barrier extending with respect to the engine central longitudinal axis toward the vane platform to permit an increase in temperature of a section of a vane platform thereby reducing a structural thermal conflict with the vane platform.

16. The method as recited in claim 15 , further comprising extending the barrier toward but not into contact with the wall.

17. The method as recited in claim 15 , wherein the barrier is located between the recirculating air cavity and a seal in contact with the wall.

18. The method as recited in claim 15 , wherein the vane platform supports a plurality of vanes.

19. The method as recited in claim 18 , wherein a core airflow flows through the core gas passage, and the recirculating air cavity is configured to recirculate the secondary airflow.

20. A mid turbine frame module for a gas turbine engine comprising:
an outer turbine case about an axis;
an inner case about said axis;
a mid-turbine frame radially between said outer turbine case and said inner case, said mid turbine frame includes an inner vane platform, an outer vane platform and a plurality of vanes between said inner vane platform and said outer vane platform;
a seal in contact with said mid-turbine frame at a sealing surface; and
a barrier transverse to said vane platform to at least partially shield said sealing surface from recirculating air within a recirculating air cavity adjacent to said inner platform, wherein said barrier extends toward but is not in contact with said outer vane platform, said barrier axially aligned with an edge of a vane that extends from said vane platform.

Assignees

• United Technologies Corp

Inventors

• Ols John T
• Allen Richard N
• Sanchez Paul K
• Porter Steven D
• Lemoine Jonathan

Classifications

• F01D9/041 Primary

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

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title

• F01D11/003

  by packing rings; Mechanical seals · 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