Mid-turbine frame and gas turbine engine including same

Patent metadata

Field	Value
Publication number	US-9976431-B2
Application number	US-201514803210-A
Country	US
Kind code	B2
Filing date	Jul 20, 2015
Priority date	Jul 22, 2014
Publication date	May 22, 2018
Grant date	May 22, 2018

Abstract

A mid-turbine frame for a gas turbine engine ducts gases between a high pressure turbine and a low pressure turbine. The mid-turbine frame may include an outer flowpath ring, an inner flowpath ring, and a plurality of vanes extending therebetween. The outer flowpath ring comprises a unitary structure, while the inner flowpath ring and the plurality of vanes comprises a plurality of segments.

First claim

What is claimed:

1. A mid-turbine frame for a gas turbine engine comprising: a duct that extends between a high pressure turbine and a low pressure turbine, the duct comprising an outer flowpath ring and an inner flowpath ring; wherein the inner flowpath ring is situated radially inward of the outer flowpath ring; wherein the outer flowpath ring comprises a unitary structure; and wherein the inner flowpath ring comprises a plurality of segments that together form the inner flowpath ring; and wherein each segment includes a first tenon that defines a first axial terminus of each segment and a second tenon that defines a second axial terminus of each segment; wherein the first tenon of a first segment is joined to the second tenon of a second segment by a seal that clamps the first tenon and the second tenon together; wherein the seal comprises: a male seal structure having a body and a protruding member extending away from the body, and female seal structure defining a receiving member having an aperture configured to receive the protruding member; and wherein the seal extends from a forward edge to an aft edge of each of the first and second tenons.

2. The mid-turbine frame of claim 1 , wherein the inner flowpath ring comprises a plurality of inner arcing surfaces, each of the inner arcing surfaces carrying at least one vane that extends radially outward from the inner arcing surface toward the outer flowpath ring.

3. The mid-turbine frame of claim 1 , wherein each of the segments are formed as a unitary structure.

4. The mid-turbine frame of claim 2 , wherein each vane includes a channel.

5. The mid-turbine frame of claim 1 , further comprising a fastener configured to be coupled to the protruding member to retain the protruding member in contact with the receiving member.

6. The mid-turbine frame of claim 5 , wherein the receiving member is coupled to a radially inward portion of the first and second tenons and the male seal structure is coupled to a radially outward portion of the first and second tenons.

7. The mid-turbine frame of claim 1 , wherein the duct defines a hot gas path between the high pressure turbine and the low pressure turbine.

8. The mid-turbine frame of claim 2 , wherein the plurality of vanes are coupled to the outer flowpath ring.

9. The mid-turbine frame of claim 8 , wherein said coupling comprises welding and brazing.

10. The mid-turbine frame of claim 2 , wherein two of the vanes extend from each segment.

11. The mid-turbine frame of claim 2 , wherein each segment comprises a first segment portion coupled to a second segment portion.

12. A gas turbine engine comprising: a compressor section, a combustor section, a high pressure turbine, a mid-turbine frame, and a low pressure turbine in serial flow communication, wherein the mid-turbine frame comprises: a duct that extends between the high pressure turbine and the low pressure turbine, the duct comprising an outer flowpath ring and an inner flowpath ring; wherein the inner flowpath ring is situated radially inward of the outer flowpath ring; wherein the outer flowpath ring comprises a unitary structure; and wherein the inner flowpath ring comprises a plurality of segments that together form the inner flowpath ring; and wherein each segment includes a first tenon that defines a first axial terminus of each segment and a second tenon that defines a second axial terminus of each segment; wherein the first tenon of a first segment is joined to the second tenon of a second segment by a seal that clamps the first tenon and the second tenon together; wherein the seal comprises: a male seal structure having a body and a protruding member extending away from the body, and a female seal structure defining a receiving member having an aperture configured to receive the protruding member; and wherein the seal extends from a forward edge to an aft edge of each of the first and second tenons.

13. The mid-turbine frame of claim 12 , wherein the inner flowpath ring comprises a plurality of inner arcing surfaces, each of the inner arcing surfaces carrying at least one vane that extends radially outward from the inner arcing surface toward the outer flowpath ring.

14. The mid-turbine frame of claim 12 , wherein each of the segments are formed as a unitary structure.

15. The mid-turbine frame of claim 13 , wherein the plurality of vanes are coupled to the outer flowpath ring.

Assignees

• United Technologies Corp

Inventors

• Wilber John E

Classifications

• F16J15/3464

  Mounting of the seal · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D9/044

  permanently, e.g. by welding, brazing, casting or the like · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title