Cooling passages for a mid-turbine frame

Patent metadata

Field	Value
Publication number	US-9995171-B2
Application number	US-201514598452-A
Country	US
Kind code	B2
Filing date	Jan 16, 2015
Priority date	Jan 16, 2015
Publication date	Jun 12, 2018
Grant date	Jun 12, 2018

Abstract

A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.

First claim

What is claimed is:

1. A mid-turbine frame for a gas turbine engine comprising:
an outer frame case;
an inner frame case;
at least one spoke connecting the outer frame case to the inner frame case, wherein the spoke includes an inlet passage branching between a first branch extending in a radial direction and a second branch extending an axial direction and the inlet passage is defined by an inner surface of the spoke;
a plug located within the first branch;
a transfer tube coupled to a cup boss, wherein the transfer tube and the cup boss fluidly connect a portion of the second branch in the at least one spoke and the inner frame case; and
a restricting ring located within the second branch.

2. The mid-turbine frame of claim 1 , wherein the plug contacts the at least one spoke and the inner frame case.

3. The mid-turbine frame of claim 1 , wherein the plug includes an opening having a conical portion on a radially outer end that tapers to a cylindrical channel on a radially inner end.

4. The mid-turbine frame of claim 1 , further comprising a swirler tube connected to the inner frame case for directing cooling airflow in a direction of rotation of a low pressure rotor, wherein the transfer tube is fixed relative to the at least one spoke and moveable relative to the cup boss.

5. The mid-turbine frame of claim 1 , wherein the transfer tube is fixed relative to the at least one spoke and moveable relative to the cup boss.

6. The mid-turbine frame of claim 1 , wherein the second branch extends from the at least one spoke through the transfer tube and the cup boss to the inner frame case.

7. A gas turbine engine comprising:
a mid-turbine frame located axially between a first turbine and a second turbine, the mid-turbine frame comprising:
an outer frame case;
an inner frame case;
at least one spoke connecting the outer frame case to the inner frame case, wherein the spoke includes an inlet passage branching between a first branch extending in a radial direction and a second branch extending in an axial direction and the inlet passage is defined by an inner surface of the spoke;
a plug located within the first branch;
a transfer tube coupled to a cup boss, wherein the transfer tube and the cup boss fluidly connect a portion of the second branch in the at least one spoke and the inner frame case;
a swirler tube connected to the fluid communicating fitting for directing cooling airflow in a direction of rotation of a low pressure rotor, wherein a first portion of the second branch includes a first diameter and a second portion includes a second diameter smaller than the first diameter to meter the flow of cooling airflow; and
a restricting ring located within the second branch.

8. The gas turbine engine of claim 7 , wherein the transfer tube is fixed relative to the at least one spoke and moveable relative to the cup boss.

9. A method of cooling a portion of a gas turbine engine comprising:
directing a cooling airflow through an inlet passage in a spoke in a mid-turbine frame, wherein the inlet passage is defined by an inner surface of the spoke, wherein the inlet passage includes a first branch and a second branch extending from the first branch in an axial direction and a first portion of the cooling airflow travels through the first branch into a bearing support cavity; and
directing a portion of the cooling airflow through the inlet passage into a low-rotor cavity, wherein the portion of the cooling airflow traveling through the second branch into the low-rotor cavity is greater than the first portion of the cooling airflow traveling through the first branch into the bearing support cavity; and
restricting the portion of the cooling airflow through the first branch with a plug and restricting the first portion of the cooling airflow through the second branch with a restricting ring.

10. The method of claim 9 , further comprising directing the cooling fluid in the second branch through a swirler tube configured to direct the portion of the cooling airflow in a direction of rotation of a low-rotor cavity.

Assignees

• United Technologies Corp

Inventors

• Burdick Andrew D
• Cherolis Anthony P
• Treat Christopher
• Lemoine Jonathan
• Mayer Robert Russell
• Farah Jorge I
• Mosley John H

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title

• F01D5/081 Primary

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F01D25/162

  Bearing supports · CPC title

• F01D25/125

  of bearings · CPC title