Part-fastening structure
US-2015369273-A1 · Dec 24, 2015 · US
Alignment system and methodology to account for variation in a gas turbine engine
US10570944B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10570944-B2 |
| Application number | US-201615265205-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 14, 2016 |
| Priority date | Dec 21, 2012 |
| Publication date | Feb 25, 2020 |
| Grant date | Feb 25, 2020 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.
First claim
Opening claim text (preview).
What is claimed is: 1. An alignment system comprising: a bushing that is non-round in cross-section taken perpendicular to a longitudinal axis of the bushing, where said bushing comprises a set of tabs and a bushing aperture extending through the bushing along the longitudinal axis, where the bushing aperture is rectilinear in cross-section taken perpendicular to the longitudinal axis; and a fastener with a threaded section that passes through the bushing, and an interface section and a head, said head receivable between said set of tabs, where said interface section is rectilinear in cross-section taken perpendicular to the longitudinal axis and located coaxially with respect to the longitudinal axis between said head and said threaded section, and said interface and said head have different cross-sectional shapes taken perpendicular to the longitudinal axis, wherein the interface section and the bushing aperture are configured to provide an anti-rotation interface therebetween with the interface section disposed in the bushing aperture. 2. The alignment system as recited in claim 1 , wherein said interface section is axially between said threaded section and said head. 3. The alignment system as recited in claim 2 , wherein said interface section corresponds with said bushing aperture such that the interface section and the bushing aperture have a same cross-sectional shape taken perpendicular to the longitudinal axis. 4. The alignment system as recited in claim 1 , wherein said set of tabs includes two (2) tabs. 5. The alignment system as recited in claim 1 , further comprising an undercut between each of said tabs of said set of tabs and a body of said bushing. 6. The alignment system as recited in claim 1 , further comprising a seal with an aperture to receive said set of tabs.
Assignees
Inventors
Classifications
Specially-shaped necks (F16B35/06 takes precedence) · CPC title
Retaining components in desired mutual position · CPC title
Bearing supports · CPC title
Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title
- F16B33/002Primary
Means for preventing rotation of screw-threaded elements (F16B39/00 takes precedence) · CPC title
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Frequently asked questions
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- What does patent US10570944B2 cover?
- A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.
- Who is the assignee on this patent?
- United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F16B33/002. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Feb 25 2020 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).