Cooling passages for a mid-turbine frame

Patent metadata

Field	Value
Publication number	US-9732628-B2
Application number	US-201514663495-A
Country	US
Kind code	B2
Filing date	Mar 20, 2015
Priority date	Mar 20, 2015
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. A passage extends through at least one spoke, the inner frame case, and the bearing support member.

First claim

What is claimed is:

1. A mid-turbine frame for a gas turbine engine comprising:
an inner frame case;
a bearing support member located adjacent the inner frame case;
at least one spoke attached to the inner frame case;
a passage extending through the at least one spoke, the inner frame case, and the bearing support member; and
a fitting connecting the at least one spoke to the inner frame case, wherein the fitting includes a transfer tube connecting the at least one spoke to a cup boss with an inlet to the cup boss having a first cross sectional shape and an outlet to the cup boss having a second different cross sectional shape.

2. The mid-turbine frame of claim 1 , wherein the first cross sectional shape is circular and the second cross sectional shape is non-circular.

3. The mid-turbine frame of claim 2 , wherein a centerline of the first cross sectional shape is offset from a centerline of the second cross sectional shape.

4. The mid-turbine frame of claim 1 , wherein the cup boss includes a base portion having a curvature.

5. The mid-turbine frame of claim 4 , wherein the curvature of the base portion matches a curvature of the inner frame case.

6. The mid-turbine frame of claim 1 , further comprising a swirler tube connected to the bearing support member for directing cooling airflow in a direction of rotation of a low pressure turbine.

7. The mid-turbine frame of claim 6 , wherein the swirler tube includes a base portion for engaging the bearing support member and a passage portion that extends from the base portion.

8. The mid-turbine frame of claim 7 , wherein the base portion includes a curvature that matches a curvature of the bearing support member.

9. The mid-turbine frame of claim 7 , wherein the base portion includes at least one locating tab for engaging a portion of the bearing support member if oriented incorrectly relative to the bearing support member.

10. 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 inner frame case;
a bearing support member located adjacent the inner frame case;
at least one spoke attached to the inner frame case;
a passage extending through the at least one spoke, the inner frame case, and the bearing support member; and
a fitting connecting the at least one spoke to the inner frame case, wherein the fitting includes a cup boss having an inlet to the cup boss having a first cross sectional shape and an outlet to the cup boss having a second different cross sectional shape.

11. The gas turbine engine of claim 10 , wherein the first cross sectional shape is circular and the second cross sectional shape is non-circular.

12. The gas turbine engine of claim 10 , wherein a centerline of the first cross sectional shape is offset from a centerline of the second cross sectional shape.

13. The gas turbine engine of claim 10 , wherein the cup boss includes a base portion having a curvature that matches a curvature of the inner frame case.

14. The gas turbine engine of claim 10 , further comprising a swirler tube connected to the bearing support member for directing cooling airflow in a direction of rotation of a low pressure turbine.

15. The gas turbine engine of claim 14 , wherein the swirler tube includes a base portion for engaging the bearing support member and a passage portion that extends from the base portion.

16. The gas turbine engine of claim 15 , wherein the base portion includes a curvature that matches a curvature of the bearing support member.

17. The gas turbine engine of claim 15 , wherein the base portion includes at least one locating tab for engaging a portion of the bearing support member if oriented incorrectly relative to the bearing support member.

Assignees

• United Technologies Corp

Inventors

• Cherolis Anthony P
• Winn Joshua Daniel
• Lemoine Jonathan

Classifications

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F02C7/18

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

• F01D25/162

  Bearing supports · CPC title

• F01D25/12

  Cooling · CPC title

• F01D25/125 Primary

  of bearings · CPC title