Mid-turbine frame rod and turbine case flange

Patent metadata

Field	Value
Publication number	US-10060291-B2
Application number	US-201414769843-A
Country	US
Kind code	B2
Filing date	Feb 18, 2014
Priority date	Mar 5, 2013
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A turbine section of a gas turbine engine includes a first turbine supported for rotation about an axis, a second turbine spaced axially aft of the for first turbine section for rotation about the axis, and a mid-turbine frame disposed between the first turbine and the second turbine defining a passage between the first turbine and the second turbine. A first case surrounds the first turbine and a second case surrounding the second turbine and attached to the first case. The mid-turbine frame is disposed between the first turbine section and the second turbine section and includes at least one support structure extending through an interface between the first turbine case and the second turbine case.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a fan including a plurality of fan blades rotatable about an axis;
a compressor section;
a combustor in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor, wherein the turbine section includes a first turbine section disposed within a first case with, a first flange and a second turbine section disposed within a second case with a second flange, wherein the first flange is attached to the second flange; and
a mid-turbine frame disposed between the first turbine section and the second turbine section, the mid-turbine frame including an airfoil and at least one support structure, the at least one support structure extending through an interface between the first turbine case and the second turbine case, wherein both the first flange and the second flange extend transverse to the axis.

2. The gas turbine engine as recited in claim 1 , wherein the airfoil directs flow between the first turbine section and the second turbine section.

3. The gas turbine engine as recited in claim 1 , wherein an outer end of the support structure is attached at the interface between the first case and the second case.

4. The gas turbine engine as recited in claim 1 , including a boss through which the support structure extends and a fastening member for securing the support structure to the boss.

5. The gas turbine engine as recited in claim 4 , wherein the at least one support structure supports rotation of at least one rotatable shaft extending through the turbine section.

6. The gas turbine engine as recited in claim 1 , wherein the first case and the second case each comprise continuous uninterrupted structures.

7. A turbine section of a gas turbine engine comprising:
a first turbine supported for rotation about an axis;
a second turbine spaced axially aft of the first turbine section for rotation about the axis;
a mid-turbine frame disposed between the first turbine and the second turbine defining a passage between the first turbine and the second turbine, the mid-turbine frame including an airfoil and a support structure;
a first case including a first flange, the first case surrounding the first turbine; and
a second case including a second flange, the second case surrounding the second turbine and the second flange is attached to the first flange of the first case, wherein the support structure of the mid-turbine frame extends through an interface between the first case and the second case, wherein both the first flange and the second flange extend transverse to the axis.

8. The turbine section as recited in claim 7 , wherein the airfoil directs flow between the first turbine section and the second turbine section.

9. The turbine section as recited in claim 8 , wherein the support structure includes an outer end that is attached at the interface between the first case and the second case.

10. The turbine section as recited in claim 9 , including a boss through which the outer end of the support structure extends and a fastening member for securing the outer end of the support structure to the boss.

11. The turbine section as recited in claim 9 , wherein the support structure supports rotation of at least one rotatable shaft extending through the turbine section.

12. The turbine section as recited in claim 7 , wherein the first case and the second case each comprise continuous uninterrupted structures.

Assignees

• United Technologies Corp

Inventors

• Kumar Keshava B

Classifications

• F02K3/06

  with front fan · CPC title

• F01D25/243 Primary

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F02C7/20

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

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title