Impingement structure for jet engine mid-turbine frame
US-10344618-B2 · Jul 9, 2019 · US
Vane for jet engine mid-turbine frame
US2016258305A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2016258305-A1 |
| Application number | US-201515032017-A |
| Country | US |
| Kind code | A1 |
| Filing date | Jan 23, 2015 |
| Priority date | Jan 28, 2014 |
| Publication date | Sep 8, 2016 |
| Grant date | — |
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- Title
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Abstract
Official abstract text for this publication.
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
Opening claim text (preview).
What is claimed is: 1 . An apparatus comprising: a radially outward segment portion; a radially inward segment portion; a vane that extends between the radially outward segment portion and the radially inward segment portion. 2 . The apparatus of claim 1 , wherein the vane defines a channel. 3 . The apparatus of claim 1 , wherein the radially outward segment portion comprises a radially inner surface and the radially inward segment portion comprises a radially outer surface. 4 . The apparatus of claim 3 , wherein the radially inner surface and the outer surface define a gas flow path. 5 . The apparatus of claim 4 , wherein the flow path is axial. 6 . The apparatus of claim 2 , wherein a support strut is disposed within the channel. 7 . The apparatus of claim 2 , wherein at least one of an air service line and an oil service line are disposed within the channel. 8 . The apparatus of claim 4 , wherein the gas flow path provides fluid communication a high pressure turbine and a low pressure turbine. 9 . The apparatus of claim 1 , further comprising a perforated structure that is disposed radially outward of the radially outward segment portion. 10 . The apparatus of claim 9 , wherein each of a plurality of perforations in the perforated structure are configured to receive cooling air. 11 . The apparatus of claim 1 , wherein an annular structure is formed from the radially outward segment portion and the radially inward segment portion. 12 . 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, the inner annular structure is situated radially inward of the outer annular structure; and a vane that extend radially outward from the inner annular structure through the outer annular structure. 13 . The MTF of claim 12 , wherein the vane defines a channel. 14 . The MTF of claim 13 , wherein a support strut is disposed within the channel. 15 . The MTF of claim 13 , wherein at least one of an air service line and an oil service line are disposed within the channel.
Assignees
Inventors
Classifications
Fluid supply conduits to nozzles or the like · CPC title
Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title
Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title
Supporting or mounting arrangements, e.g. for turbine casing · CPC title
Cooling · CPC title
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Frequently asked questions
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- What does patent US2016258305A1 cover?
- 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 v…
- Who is the assignee on this patent?
- United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F01D9/04. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Thu Sep 08 2016 00:00:00 GMT+0000 (Coordinated Universal Time) (A1). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 4 related publications on this page (citations in our corpus or others sharing the same primary CPC).