Cooling passages for a mid-turbine frame

Patent metadata

Field	Value
Publication number	US-10309308-B2
Application number	US-201514598732-A
Country	US
Kind code	B2
Filing date	Jan 16, 2015
Priority date	Jan 16, 2015
Publication date	Jun 4, 2019
Grant date	Jun 4, 2019

Abstract

A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a mid-turbine frame including:
an inner frame case; and
at least one spoke connected to the inner frame case, wherein the at least one spoke includes a fluid passage in fluid communication with a channel on a radially inner end of the fluid passage, the channel located in a plug separate from the at least one spoke, the plug contacting the at least one spoke and adjacent to the inner frame case, the plug including a conical portion tapering to the channel; and

a cavity located radially inward from the mid-turbine frame in fluid communication with the channel; and
wherein an outlet of the channel directs a fluid into the cavity circumferentially relative to a longitudinal axis of a gas turbine shaft.

2. The gas turbine engine of claim 1 , wherein the cavity forms a bearing support cavity and is at least partially defined by the inner frame case and a bearing support member.

3. The gas turbine engine of claim 2 , wherein the cavity forms a torque box.

4. The gas turbine engine of claim 1 , where the channel extends in a circumferential direction at an angle between 30 and 80 degrees relative to a base portion of the at least one spoke.

5. A mid-turbine frame in a gas turbine engine comprising:
a hollow spoke including a fluid passage in fluid communication with a channel on a radially inner end of the fluid passage, wherein the channel is located in a plug separate from the hollow spoke, the plug contacting the hollow spoke, adjacent to an inner frame case, and located radially outward from the inner frame case relative to a longitudinal axis of the gas turbine engine; and
the inner frame case at least partially defining a cavity radially inward from the inner frame case, wherein the channel is in fluid communication with the cavity and the hollow spoke is directly connected to the inner frame case and the channel includes a cylindrical cross section located in the plug and the plug includes a conical portion tapering to the channel.

6. The mid-turbine frame of claim 5 , wherein the cavity is at least partially defined by the inner frame case and a bearing support member and the cavity forms a torque box.

7. The mid-turbine frame of claim 5 , wherein the channel extends in a circumferential direction relative to an a longitudinal axis of the gas turbine engine at an angle between 30 and 80 degrees relative to a base portion of the hollow spoke.

8. The mid-turbine frame of claim 5 , wherein an outlet of the channel directs a fluid into the cavity circumferentially relative to a longitudinal axis of the gas turbine engine.

9. The mid-turbine frame of claim 5 , wherein a radially inner most surface of the plug contacts a radially outer surface of the inner frame case.

10. The mid-turbine frame of claim 5 , wherein a plurality of fasteners extend through the inner frame case into the hollow spoke.

11. A method of cooling a portion of a gas turbine engine comprising:
directing cooling airflow through a hollow spoke in a mid-turbine frame, the hollow spoke including a fluid passage in fluid communication with a channel on a radially inner end of the fluid passage, the channel located in a plug separate from the hollow spoke, the plug contacting the hollow spoke and adjacent to an inner frame case, the plug including a conical portion tapering to the channel; and
directing the cooling airflow into a cavity on a radially inner end of the hollow spoke, wherein an outlet of the channel directs the cooling airflow into the cavity circumferentially relative to a longitudinal axis of the gas turbine engine.

12. The method of claim 11 , wherein the channel extends in a circumferential direction at an angle between 30 and 80 degrees relative to a base portion of the hollow spoke.

13. The method of claim 11 , wherein the cavity forms a torque box and is at least partially defined by the inner frame case and a bearing support member.

Assignees

• United Technologies Corp

Inventors

• Cherolis Anthony P
• Lienau Jeffrey J
• Newman Robert
• Wang Cheng-Zhang

Classifications

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F05D2220/3213

  an intermediate stage of the turbine · CPC title

• F05D2240/90

  Mounting on supporting structures or systems · CPC title

• F01D9/065

  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

• Y02T50/675

  Cross-Sectional Technologies · mapped topic