Impingement structure for jet engine mid-turbine frame

Patent metadata

Field	Value
Publication number	US-10344618-B2
Application number	US-201515032019-A
Country	US
Kind code	B2
Filing date	Jan 23, 2015
Priority date	Jan 28, 2014
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

A mid-turbine frame (“MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

First claim

What is claimed is:

1. An apparatus, comprising:
a radially inward segment portion;
a radially outward segment portion;
a radially outward perforated structure coupled to the radially outward segment portion;
a seal comprising a first member and a second member, at least a portion of the radially outward segment portion is disposed radially between the first member and the second member; and
a slot proximate to the seal, the slot configured to relay cooling air through the seal and into a hot gas path,
wherein the slot is formed in the radially outward segment portion, and
wherein the second member of the seal comprises a threaded female member threaded onto a threaded male member of the first member whereby the first member is coupled to the second member.

2. The apparatus of claim 1 , wherein a vane extends from the radially inward segment portion to the radially outward segment portion.

3. The apparatus of claim 2 , further comprising a radially inward perforated structure coupled to the radially inward segment portion.

4. The apparatus of claim 2 , wherein the vane defines a channel.

5. The apparatus of claim 2 , wherein the segment at least partially defines a hot gas path between a high pressure turbine (“HPT”) and a low pressure turbine (“LPT”).

6. The apparatus of claim 1 , wherein the radially inward segment portion and the radially outward segment portion comprise a segment, the segment comprises a first tenon that defines a first axial terminus of the segment and a second tenon that defines a second axial terminus of the segment.

7. The apparatus of claim 6 , wherein the seal clamps a second segment to the segment.

8. The apparatus of claim 1 , further comprising a tortuous gutter.

9. The apparatus of claim 8 , wherein the tortuous gutter comprises a narrow passage between the seal, a first tenon of the segment, and the perforated structure.

10. The apparatus of claim 1 , wherein the radially outward perforated structure comprises a temperature resistant alloy.

11. The apparatus of claim 1 , wherein at least a portion of the radially outward perforated structure is disposed radially between the first member and the second member, the radially outward perforated structure is coupled to the radially outward segment portion via the seal.

12. The apparatus of claim 1 , wherein the radially outward perforated structure and the radially outward segment are clamped between the first member and the second member.

13. The apparatus of claim 12 , wherein the radially outward perforated structure is clamped radially between the second member and the radially outward segment, and the radially outward segment is clamped radially between the radially outward perforated structure and the first member.

Assignees

• United Technologies Corp

Inventors

• Wilber John E

Classifications

• F05D2300/17

  Alloys · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D9/065 Primary

  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

• F01D25/12 Primary

  Cooling · CPC title