Belly band seal with anti-rotation structure
US-2016376902-A1 · Dec 29, 2016 · US
Belly band seals
US2018347366A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2018347366-A1 |
| Application number | US-201815962709-A |
| Country | US |
| Kind code | A1 |
| Filing date | Apr 25, 2018 |
| Priority date | Jun 2, 2017 |
| Publication date | Dec 6, 2018 |
| Grant date | — |
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- Title
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- Abstract
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- Assignees and inventors
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- Key dates
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- First independent claim
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- CPC / IPC classifications
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Abstract
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The present application provides a rotor for use in a turbine engine. The rotor may include a first rotor disc, a second rotor disc adjacent to the first rotor disc, and a belly band seal positioned between the first rotor disc and the second rotor disc. The belly band seal may include a band seal with a locking tab brazed thereon.
First claim
Opening claim text (preview).
What is claimed: 1 . A rotor for use in a turbine engine, comprising: a first rotor disc; a second rotor disc adjacent to the first rotor disc; and a belly band seal positioned between the first rotor disc and the second rotor disc; the belly band seal comprising a band seal with a locking tab brazed thereon. 2 . The rotor of claim 1 , wherein the first rotor disc comprises a first slot and the second rotor disc comprises a second slot. 3 . The rotor of claim 2 , wherein the band seal is positioned within the first slot and the second slot. 4 . The rotor of claim 1 , wherein the first disc comprises a first counter-groove and the second disc comprises a second counter-groove. 5 . The rotor of claim 4 , wherein the locking tab is positioned within the first counter-groove and the second counter-groove. 6 . The rotor of claim 5 , wherein the locking tab is positioned within the first counter-groove and the second counter-groove in a form fit. 7 . The rotor of claim 1 , wherein the locking tab comprises a circular or an elliptical shape. 8 . The rotor of claim 1 , wherein the belly band seal comprises a plurality of segments. 9 . The rotor of claim 8 , wherein the belly band seal comprises four segments. 10 . The rotor of claim 1 , wherein the belly band seal comprises a counter spring. 11 . The rotor of claim 10 , wherein the counter spring is positioned on the band seal opposite the locking tab. 12 . The rotor of claim 1 , wherein the belly band seal comprises a plurality of locking tabs. 13 . The rotor of claim 1 , wherein the belly band seal separates an air cavity and a hot gas path. 14 . The rotor of claim 1 , wherein the rotor comprises a turbine rotor. 15 . A method of positioning a belly band seal between a first rotor disc and a second rotor disc, comprising: brazing a locking tab on to band seal of the belly band seal; positioning the band seal within a first slot on the first rotor disc and a second slot on the second rotor disc; and positioning the locking tab within a first counter-groove on the first rotor disc and a second counter-groove on the second rotor disc. 16 . A rotor for use in a turbine engine, comprising: a first rotor disc; a second rotor disc adjacent to the first rotor disc; wherein the first rotor disc comprises a first counter-groove and the second rotor disc comprises a second counter-groove; and a belly band seal positioned between the first rotor disc and the second rotor disc; the belly band seal comprising a band seal with a locking tab brazed thereon; and wherein the locking tab is positioned within the first counter-groove and the second counter-groove. 17 . The rotor of claim 16 , wherein the first rotor disc comprises a first slot, wherein the second rotor disc comprises a second slot, and wherein the band seal is positioned within the first slot and the second slot. 18 . The rotor of claim 16 , wherein the locking tab is positioned within the first counter-groove and the second counter-groove in a form fit. 19 . The rotor of claim 16 , wherein the locking tab comprises a circular or an elliptical shape. 20 . The rotor of claim 16 , wherein the belly band seal comprises a counter spring.
Assignees
Inventors
Classifications
Arrangement of seals · CPC title
by a form fit connection, e.g. by interlocking · CPC title
- F01D5/066Primary
Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps · CPC title
Retaining components in desired mutual position · CPC title
- F01D11/005Primary
Sealing means between non relatively rotating elements · CPC title
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Frequently asked questions
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- What does patent US2018347366A1 cover?
- The present application provides a rotor for use in a turbine engine. The rotor may include a first rotor disc, a second rotor disc adjacent to the first rotor disc, and a belly band seal positioned between the first rotor disc and the second rotor disc. The belly band seal may include a band seal with a locking tab brazed thereon.
- Who is the assignee on this patent?
- General Electric Technology Gmbh
- What technology area does this patent fall under?
- Primary CPC classification F01D5/066. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Thu Dec 06 2018 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 1 related publication on this page (citations in our corpus or others sharing the same primary CPC).