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Turbomachine casing comprising a cavity-free shroud and yokes reinforced by stiffeners
US10371009B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10371009-B2 |
| Application number | US-201515113543-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jan 20, 2015 |
| Priority date | Jan 23, 2014 |
| Publication date | Aug 6, 2019 |
| Grant date | Aug 6, 2019 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
The invention relates to a turbomachine casing (1) comprising: a hub (2), an outer shroud (3), and yokes (11) projecting from the outer shroud (3), for attaching the housing (1), characterized in that it comprises at least one stiffener (10) extending between pairs of yokes (11) facing each other, and comprising a central part (18) and side arms (19) projecting from the central part (18).
First claim
Opening claim text (preview).
The invention claimed is: 1. A turbine engine casing comprising: a hub, an outer shell ring, and clevises protruding from the outer shell ring, for attaching the casing, wherein the turbine engine casing further comprises at least one stiffener extending between pairs of clevises facing each other, said at least one stiffener having the general shape of an H, and comprising a central part and lateral arms protruding from the central part. 2. The casing according to claim 1 , wherein the stiffener comprises ends that are integral with the clevises. 3. The casing according to claim 1 , wherein the stiffener comprises ends that are attached to the clevises via attachment elements. 4. The casing according to claim 1 , wherein the lateral arms have a section wider in their center than at their ends. 5. The casing according to claim 1 , wherein the lateral arms have a section narrower in their center than at their ends. 6. The casing according to claim 1 , wherein the lateral arms have a section of substantially constant width. 7. The casing according to claim 1 , said casing being an exhaust casing of a turbine engine and comprising a plurality of structural arms positioned circumferentially between the hub and the outer shell ring, the clevises being positioned in alignment with the structural arms. 8. A turbine engine comprising: a casing according to claim 1 , link rods attached on the one hand to the clevises of the casing via attachment elements, and on the other hand to a support of the turbine engine, the stiffener being configured to assume the forces applied by the link rods to the casing.
Assignees
Inventors
Classifications
Mounting on supporting structures or systems · CPC title
Supporting or mounting arrangements, e.g. for turbine casing · CPC title
given by its similarity to a letter, e.g. T-shaped · CPC title
Retaining bolts or nuts · CPC title
Operations & Transport · mapped topic
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Frequently asked questions
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- What does patent US10371009B2 cover?
- The invention relates to a turbomachine casing (1) comprising: a hub (2), an outer shroud (3), and yokes (11) projecting from the outer shroud (3), for attaching the housing (1), characterized in that it comprises at least one stiffener (10) extending between pairs of yokes (11) facing each other, and comprising a central part (18) and side arms (19) projecting from the central part (18).
- Who is the assignee on this patent?
- Snecma, Safran Aircraft Engines
- What technology area does this patent fall under?
- Primary CPC classification F01D25/162. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Aug 06 2019 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).