Frame junction cooling holes

Patent metadata

Field	Value
Publication number	US-10240532-B2
Application number	US-201314655656-A
Country	US
Kind code	B2
Filing date	Dec 20, 2013
Priority date	Dec 29, 2012
Publication date	Mar 26, 2019
Grant date	Mar 26, 2019

Abstract

A module for a gas turbine engine comprises a frame and a frame cooling system. The frame includes a circumferentially distributed plurality of radially extending struts. Each strut is joined to an outer frame section at an outer frame junction, and joined to an inner frame section at an inner frame junction. The frame cooling system comprises an inlet, a plurality of cooling air passages extending from the inlet radially through each of the plurality of frame struts; and an outlet. The outlet is in fluid communication with at least one of the cooling air passages and includes a film cooling hole formed through the frame proximate the outer frame junction.

First claim

The invention claimed is:

1. A module for a gas turbine engine comprising:
a frame including a circumferentially distributed plurality of radially extending struts, each strut integrally joined to an outer frame section at an outer frame junction, and integrally joined to an inner frame section at an inner frame junction; and
a frame cooling system comprising:
an inlet;
a cooling air passage extending from the inlet radially through one of the plurality of frame radially extending struts;
a first outlet in fluid communication with the cooling air passage, the first outlet including at least one film cooling hole formed through the frame proximate the outer frame junction, an exit portion of the at least one film cooling hole directed into an outer cooling air cavity toward at least one of an inner surface of the outer frame section, and an outer surface of each strut; and
a second outlet in fluid communication with the cooling air passage, the second outlet including at least one second outlet film cooling hole formed through the frame proximate the inner frame junction, an exit portion of the at least one second outlet film cooling hole directed into an inner cooling air cavity toward at least one of an inner surface of the inner frame section, and an inner side of each strut;
wherein the cooling air passage is sized to direct more than 50% of cooling air flow in the cooling air passage toward the outer frame section and the outer cooling air cavity.

2. The module of claim 1 , further comprising:
a fairing assembly disposed over and spaced apart from an annular frame surface.

3. The module of claim 2 , wherein the fairing assembly comprises at least one of a fairing platform and a strut liner disposed over and spaced apart from the at least one film cooling hole, the film cooling hole including an exit portion angled to direct a volume of cooling air from the cooling air passage into at least one fairing cavity defined between the fairing assembly and the annular frame surface.

4. The module of claim 2 , further comprising:
a heat shield assembly including at least one heat shield element with a reflective portion disposed within the at least one fairing cavity.

5. The module of claim 1 , wherein the first outlet includes a plurality of film cooling holes formed through each strut proximate the outer frame junction.

6. The module of claim 5 , wherein at least one of the plurality of film cooling holes is directed radially inboard toward a circumferentially facing strut outer wall.

7. The module of claim 5 , wherein the plurality of film cooling holes are arranged linearly along the outer frame junction.

8. The module of claim 1 , wherein the frame cooling system includes a plurality of cooling air inlets providing fluid communication between each cooling air passage and the inner cooling air cavity disposed radially inward of the inner frame section, each inlet circumferentially aligned relative to each cooling air passage.

9. The module of claim 1 , further comprising:
a first turbine section operable to rotate a first shaft;
a second turbine section operable to rotate a second shaft independent of the first shaft;
wherein the outer frame section interconnects an outer case of the first turbine section with an outer case of the second turbine section.

10. The module of claim 1 , wherein the module comprises a turbine exhaust case assembly.

11. The module of claim 10 , wherein the turbine exhaust case assembly is adapted to interconnect a low-pressure turbine assembly to a power turbine assembly.

12. The module of claim 1 , wherein the frame cooling system comprises at least one cooling air passage extending radially through each of the plurality of circumferentially distributed radially extending struts.

13. A gas turbine engine frame comprising:
an outer case;
an inner hub;
a first strut extending radially between the inner hub and the outer case, the first strut integrally joined to the outer case at an outer frame junction, and integrally joined to the inner hub at an inner frame junction; and
a frame cooling system including an inlet, a cooling air passage extending from the inlet radially through the strut, a first outlet in fluid communication with the cooling air passage, the first outlet including at least one film cooling hole formed through at least one circumferential side of the outer frame junction, an exit portion of the at least one film cooling hole directed toward at least one of an inner surface of an outer frame section, and an outer surface of the first strut, and a second outlet in fluid communication with the cooling air passage, the second outlet including at least one second outlet film cooling hole formed through the frame proximate the inner frame junction, an exit portion of the at least one second outlet film cooling hole directed into an inner cooling air cavity toward at least one of an inner surface of the inner frame section, and an inner side of the first strut;
wherein the cooling air passage is sized to direct more than 50% of cooling air flow in the cooling air passage toward the outer case and the outer cooling air cavity.

14. The frame of claim 13 , wherein the at least one film cooling hole comprises a second exit portion directed toward a circumferentially facing first strut wall.

15. The frame of claim 13 , further comprising:
a circumferentially distributed plurality of struts including the first strut, each strut integrally extending radially between the inner hub and the outer case, and each strut integrally joined to the outer case at the outer frame junction, and joined to the inner case at the inner frame junction;
wherein each strut includes at least one cooling air passage extending radially therethrough.

16. The frame of claim 13 , wherein the first outlet comprises a plurality of film cooling holes, including the at least one film cooling hole, arranged linearly along the outer frame junction.

17. The frame of claim 13 , wherein the second outlet comprises a second plurality of second outlet film cooling holes, including the at least one second outlet film cooling hole, linearly along a line parallel to an engine centerline.

18. The frame of claim 13 , wherein at least one of the first outlet and the second outlet comprises a plurality of film cooling holes, including the at least one film cooling hole, arranged in an axially staggered manner relative to a line parallel to an engine center line.

19. The frame of claim 13 , wherein a plurality of film cooling holes, including the at least one film cooling hole comprises a second exit portion extending normal to a circumferentially facing strut wall.

20. The frame of claim 13 , wherein a plurality of film cooling holes, including the at least one film cooling hole comprises a second exit portion angled in a radial outboard direction relative to a circumferentially facing strut wall.

21. The frame of claim 20 , wherein the at least one film cooling hole comprises a third exit portion angled in a radial inboard direction relative to the circumferentially facing strut wall.

22. The frame of claim 20 , wherein the at least one film cooling hole comprises an exit portion angled in an axial forward direction relative to the circumferentially facing strut wall.

23. The frame of claim 20 , wherein the at least one film cooling hole comprises a third exit portion angled in an axial aft direction relative to the circumferentially facing strut wall.

Assignees

• United Technologies Corp

Inventors

• Scott Jonathan Ariel
• Yeager William

Classifications

• F01D9/065 Primary

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F05D2250/38

  angled, e.g. sweep angle · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F01D25/162

  Bearing supports · CPC title

• F02C7/20 Primary

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title