Seal for jet engine mid-turbine frame

Patent metadata

Field	Value
Publication number	US-10260365-B2
Application number	US-201515032024-A
Country	US
Kind code	B2
Filing date	Jan 23, 2015
Priority date	Jan 28, 2014
Publication date	Apr 16, 2019
Grant date	Apr 16, 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. A mid-turbine frame (“MTF”) for a jet engine comprising:
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; and
a seal comprising:
a male seal structure having a body and a protruding member extending away from the body;
a receiving member having an aperture configured to receive the protruding member; and
a fastener configured to be coupled to the protruding member to retain the protruding member in contact with the receiving member;

wherein the inner annular structure is situated radially inward of the outer annular structure;
wherein a first segment of the plurality of segments includes a first tenon that comprises a first axial terminus of the first segment;
wherein a second segment of the plurality of segments, adjacent the first segment, includes a second tenon that comprises a second axial terminus of the second segment;
wherein the first segment is joined to the second segment by the seal such that the first tenon and the second tenon are clamped between the body of the male seal structure and the receiving member;
wherein a circumferentially extending slot is defined in the first tenon;
wherein a tortuous gutter is defined by the seal; and
wherein the slot and the tortuous gutter are configured to flow cooling air into a hot gas path defined within the duct.

2. The MTF of claim 1 , further comprising a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel.

3. The MTF of claim 1 , wherein the hot gas path defined by the duct extends between the HPT and the LPT.

4. The MTF of claim 1 , further comprising a perforated structure that is disposed radially outward of the outer annular structure such that the perforated structure is disposed between the first tenon and the receiving member of the seal.

5. The MTF of claim 4 , wherein each of a plurality of perforations in the perforated structure are configured to permit cooling air to flow into and over the outer annular structure.

6. The MTF of claim 1 , wherein the tortuous gutter comprises a first narrow passage between the protruding member of the male seal structure and the first tenon and a second narrow passage defined between the body of the male seal structure and the first tenon.

7. The MTF of claim 1 , wherein the protruding member extends radially outward through the receiving member.

Assignees

• United Technologies Corp

Inventors

• Wilber John E

Classifications

• F05D2270/3062

  of the auxiliary fluid for heating or cooling purposes · CPC title

• F01D25/162

  Bearing supports · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title