Turbine stator assembly with a radial degree of freedom between a guide vane assembly and a sealing ring
US-12116897-B2 · Oct 15, 2024 · US
Sealing arrangement for a turbomachine, a guide vane arrangement, and a turbomachine with such a sealing arrangement
US9784131B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9784131-B2 |
| Application number | US-201414312428-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jun 23, 2014 |
| Priority date | Jun 27, 2013 |
| Publication date | Oct 10, 2017 |
| Grant date | Oct 10, 2017 |
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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 sealing arrangement 15 , a guide vane arrangement, and a turbomachine 11 with such a sealing arrangement 15 , wherein the sealing arrangement 15 is designed for a guide vane ring 60 of a turbomachine 11 , wherein the sealing arrangement 15 comprises a thin-walled annular structure 80 that is substantially closed on all sides, and wherein the annular structure 80 delimits an annular interior space 105 , wherein a hollow cell structure 109 , which is designed so as to mechanically support the annular structure 80 , is provided in the annular interior space 105.
First claim
Opening claim text (preview).
The invention claimed is: 1. A sealing arrangement ( 15 ) for a guide vane ring ( 60 ) of a turbomachine ( 11 ), wherein the sealing arrangement ( 15 ) comprises a thin-walled annular structure ( 80 ) that is substantially closed on all sides, and wherein the annular structure ( 80 ) delimits an annular interior space ( 105 ), wherein a hollow cell structure ( 109 ), which is designed to mechanically support the annular structure ( 80 ), is provided in the annular interior space ( 105 ), wherein the annular structure ( 80 ) comprises at least one passage opening ( 115 , 135 ), which connects the annular interior space ( 105 ) to the surroundings of the sealing arrangement ( 15 ), wherein the at least one passage opening ( 115 , 135 ) is designed for pressure equalization of the annular interior space ( 105 ) with the surroundings, wherein at least one other passage opening ( 135 ) is provided for pressure equalization of the annular interior space ( 105 ), wherein the passage opening ( 115 ) and the other passage opening ( 135 ) are arranged on the same side ( 120 ) of the annular structure ( 80 ). 2. A sealing arrangement ( 15 ) for a guide vane ring ( 60 ) of a turbomachine ( 11 ), wherein the sealing arrangement ( 15 ) comprises a thin-walled annular structure ( 80 ) that is substantially closed on all sides, and wherein the annular structure ( 80 ) delimits an annular interior space ( 105 ), wherein a hollow cell structure ( 109 ), which is designed to mechanically support the annular structure ( 80 ), is provided in the annular interior space ( 105 ), wherein a sealing structure ( 85 ) is provided in a radially inner-lying manner at the annular structure ( 80 ), which has a honeycomb or foam-like design, wherein the hollow cell structure ( 109 ) comprises a first mean pore size and the sealing structure ( 85 ) comprises a second mean pore size, wherein the first mean pore size of the hollow cell structure ( 109 ) is smaller than the second mean pore size of the sealing structure ( 85 ).
Assignees
Inventors
Classifications
Foam · CPC title
- F01D11/001Primary
for sealing space between stator blade and rotor · CPC title
Cross-Sectional Technologies · mapped topic
with facing materials having honeycomb-like structure · CPC title
Shroud seal segments · CPC title
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Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US9784131B2 cover?
- The invention relates to a sealing arrangement 15 , a guide vane arrangement, and a turbomachine 11 with such a sealing arrangement 15 , wherein the sealing arrangement 15 is designed for a guide vane ring 60 of a turbomachine 11 , wherein the sealing arrangement 15 comprises a thin-walled annular structure 80 that is substantially closed on all sides, and wherein the annular struc…
- Who is the assignee on this patent?
- MTU Aero Engines AG
- What technology area does this patent fall under?
- Primary CPC classification F01D11/001. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Oct 10 2017 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).