Engine mid-turbine frame transfer tube for low pressure turbine case cooling

Patent metadata

Field	Value
Publication number	US-10087782-B2
Application number	US-201414773876-A
Country	US
Kind code	B2
Filing date	Mar 12, 2014
Priority date	Mar 13, 2013
Publication date	Oct 2, 2018
Grant date	Oct 2, 2018

Abstract

A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.

First claim

What is claimed is:

1. A turbine engine, comprising:
a turbine section including a low pressure turbine and a turbine case disposed about an engine axis, wherein the turbine case includes a turbine cavity;
a frame assembly defining an outer cavity and an inner cavity, wherein the outer cavity includes at least one opening configured and adapted to communicate cooling air to the turbine cavity within the turbine case; and
a transfer tube including an axial portion that transitions into a bend portion and that is disposed within the outer cavity and is configured to receive cooling air from a supply tube, the axial portion extending aft towards the turbine section from the supply tube to the bend portion, wherein the bend portion is disposed at an angle relative to a line parallel with the engine axis to impart a circumferential velocity to the cooling air within the outer cavity.

2. The turbine engine as recited in claim 1 , wherein the axial portion extends aft from the supply tube in a direction near parallel to the axis.

3. The turbine engine as recited in claim 2 , wherein the angle of the bend portion relative to the a line parallel to the engine axis is between 30° and 89°.

4. The turbine engine as recited in claim 1 , wherein the transfer tube includes an opening disposed within a distal end of the bend portion.

5. The turbine engine as recited in claim 1 , further comprising a compressor section in communication with the supply tube for supplying cooling air to the frame assembly.

6. The turbine engine as recited in claim 5 , wherein the compressor section comprises a high pressure compressor and the cooling air is obtained from a front stage of the high pressure compressor.

7. The turbine engine as recited in claim 1 , wherein the turbine section includes a high pressure turbine and the frame is a mid-turbine frame which defines a flow path between the high pressure turbine and the low pressure turbine.

8. A frame assembly for a turbine engine, the frame assembly comprising:
a plurality of vane struts extending radially outward relative to an axis;
an outer cavity which includes an opening for communicating cooling air to a turbine cavity disposed within a turbine section aft of the plurality of vane struts; and
a transfer tube including an axial portion that transitions into a bend portion and extends within the outer cavity and is configured and adapted to receive cooling air, the axial portion extending aft from a supply tube toward the turbine section to the bend portion, wherein the bend portion is angled relative to the engine axis to impart circumferential velocity into cooling air within the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.

9. The frame assembly as recited in claim 8 , wherein the supply tube delivers cooling air to the transfer tube.

10. The frame assembly as recited in claim 9 , wherein the axial portion extends aft from the supply tube in a direction near parallel to the engine axis.

11. The frame assembly as recited in claim 9 , wherein the transfer tube includes an opening disposed within a distal end of the bend.

12. The frame assembly as recited in claim 9 , wherein the bend is disposed at an angle within a range of between 30° and 89° degrees relative to the engine axis.

13. The frame assembly as recited in claim 9 , including an inner cavity radially inward of the plurality of vane struts, wherein the inner cavity is in communication with the outer cavity.

14. The frame assembly as recited in claim 9 , wherein the opening for communicating cooling air to the turbine section comprise a plurality of openings disposed circumferentially within the outer cavity.

15. The frame assembly as recited in claim 9 , including a feather seal leak path defined between the outer cavity and the turbine section for supplying cooling air to the turbine section.

16. The frame assembly as recited in claim 9 , wherein the supply tube comprises at least two supply tubes communicating cooling air to the outer cavity and the transfer tube comprises at least two transfer tubes in communication with a corresponding supply tube.

Assignees

• United Technologies Corp

Inventors

• Wang Cheng-Zhang
• Glahn Jorn A
• Cloud David F
• Munsell Peter M
• Crawley Jr Clifton J
• Newman Robert
• Stearns Michelle Diana

Classifications

• F05D2260/97

  Reducing windage losses · CPC title

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2260/14

  Preswirling · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title