Gas turbine combustion chamber with a shingle attachment by means of catching elements
US-2017167730-A1 · Jun 15, 2017 · US
Combustor shell attachment
US10808930B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10808930-B2 |
| Application number | US-201816022080-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jun 28, 2018 |
| Priority date | Jun 28, 2018 |
| Publication date | Oct 20, 2020 |
| Grant date | Oct 20, 2020 |
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- Title
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Abstract
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A combustor shell is provided. The combustor shell may include a first aperture at least partially defined by an inner wall of the combustor shell and passing from a diffuser-facing side of the combustor shell to a combustor-facing side of the combustor shell. The combustor shell may include a spacer comprising a first segment coupled to a first flange, wherein the first flange is disposed on the diffuser-facing side of the combustor shell, wherein an outer wall of the spacer is coupled with at least a portion of an inner wall of the combustor shell.
First claim
Opening claim text (preview).
What is claimed is: 1. A combustor shell comprising: a first aperture at least partially defined by an inner wall of the combustor shell and passing from a diffuser-facing side of the combustor shell to a combustor-facing side of the combustor shell; and a spacer comprising a first segment coupled to a first flange, wherein the first flange is disposed on the diffuser-facing side of the combustor shell, wherein an outer wall of the spacer is coupled with at least a portion of the inner wall of the combustor shell, wherein the spacer comprises threads on a spacer inner wall of the spacer. 2. The combustor shell of claim 1 , wherein the first aperture of the combustor shell is an oblong shape. 3. The combustor shell of claim 1 , wherein the spacer is configured to engage an attachment feature of a combustor panel. 4. The combustor shell of claim 3 , wherein a contact length between the spacer and the attachment feature is greater than a distance between the diffuser-facing side of the combustor shell and the combustor-facing side of the combustor shell. 5. The combustor shell of claim 1 , wherein the spacer further comprises a second flange coupled with the first segment and disposed on the combustor-facing side of the combustor shell. 6. The combustor shell of claim 1 , wherein the spacer further comprises a spacer aperture at least partially defined by the spacer inner wall of the spacer. 7. A gas turbine engine comprising, a combustor, the combustor comprising the combustor shell in accordance with claim 1 . 8. A method of mounting a combustor panel to a combustor shell, comprising: inserting a spacer into the combustor shell, the spacer comprising a spacer aperture at least partially defined by an inner wall of the spacer, wherein the spacer comprises threads on the inner wall of the spacer; engaging an attachment feature of the combustor panel through the spacer aperture; and engaging a nut on the attachment feature. 9. The method of claim 8 , further comprising machining a first aperture into the combustor shell. 10. The method of claim 8 , further comprising torquing the nut. 11. A combustor shell comprising: a first aperture at least partially defined by an inner wall of the combustor shell and passing from a diffuser-facing side of the combustor shell to a combustor-facing side of the combustor shell; and a spacer comprising a first segment coupled to a first flange, wherein the first flange is disposed on the diffuser-facing side of the combustor shell, wherein an outer wall of the spacer is coupled with at least a portion of the inner wall of the combustor shell, wherein the spacer further comprises a second flange coupled with the first segment and disposed on the combustor-facing side of the combustor shell. 12. A gas turbine engine comprising, a combustor, the combustor comprising the combustor shell in accordance with claim 11 .
Assignees
Inventors
Classifications
Efficient propulsion technologies, e.g. for aircraft · CPC title
Assembling combustion chamber liners or subparts · CPC title
- F23R3/60Primary
Support structures; Attaching or mounting means · CPC title
in gas turbines · CPC title
Retaining components in desired mutual position · CPC title
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Frequently asked questions
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- What does patent US10808930B2 cover?
- A combustor shell is provided. The combustor shell may include a first aperture at least partially defined by an inner wall of the combustor shell and passing from a diffuser-facing side of the combustor shell to a combustor-facing side of the combustor shell. The combustor shell may include a spacer comprising a first segment coupled to a first flange, wherein the first flange is disposed on t…
- Who is the assignee on this patent?
- United Technologies Corp, Raytheon Tech Corp
- What technology area does this patent fall under?
- Primary CPC classification F23R3/60. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Oct 20 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 4 related publications on this page (citations in our corpus or others sharing the same primary CPC).