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Device for cooling a wall of a component of a gas turbine
US2016356498A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2016356498-A1 |
| Application number | US-201615171446-A |
| Country | US |
| Kind code | A1 |
| Filing date | Jun 2, 2016 |
| Priority date | Jun 5, 2015 |
| Publication date | Dec 8, 2016 |
| Grant date | — |
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- Title
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Abstract
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A device for cooling a wall of a component of a gas turbine, where a flow passes parallel to the wall, having at least one inflow duct provided in the wall that issues into a recess of the wall for supplying cooling air, wherein a center axis of the inflow duct is aligned to an impact wall of double-convex design inside the recess.
First claim
Opening claim text (preview).
1 . A device for cooling a wall of a component of a gas turbine, where a flow passes parallel to the wall, having at least one inflow duct provided in the wall that issues into a recess of the wall for supplying cooling air, wherein a center axis of the inflow duct is aligned to an impact wall of double-convex design inside the recess. 2 . The device in accordance with claim 1 , wherein the impact wall is designed as a spheroid dome. 3 . The device in accordance with claim 1 , wherein the center axis of the inflow duct is arranged parallel or at an angle to the surface of the wall of the component. 4 . The device in accordance with claim 1 , wherein the impact wall is designed symmetrical to a symmetry plane including the center axis of the inflow duct and arranged perpendicular to the wall of the component. 5 . The device in accordance with claim 1 , wherein the center axis of the inflow duct intersects with the center of the impact wall. 6 . The device in accordance with claim 1 , wherein the wall of the component and the impact wall are provided with a thermal barrier coating. 7 . The device in accordance with claim 1 , wherein the transition area from the impact wall to the wall of the component is designed without any steps. 8 . The device in accordance with claim 1 , wherein the recess is designed in the form of a diffuser. 9 . The device in accordance with claim 1 , wherein the recess is designed as a singular recess opened towards the surface of the wall of the component. 10 . The device in accordance with claim 1 , wherein the component is designed in the form of a combustion chamber tile.
Assignees
Inventors
Classifications
the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title
Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title
- F23R3/005Primary
Combined with pressure or heat exchangers · CPC title
convex · CPC title
in gas turbines · CPC title
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Frequently asked questions
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- What does patent US2016356498A1 cover?
- A device for cooling a wall of a component of a gas turbine, where a flow passes parallel to the wall, having at least one inflow duct provided in the wall that issues into a recess of the wall for supplying cooling air, wherein a center axis of the inflow duct is aligned to an impact wall of double-convex design inside the recess.
- Who is the assignee on this patent?
- Rolls Royce Deutschland Ltd & Co Kg
- What technology area does this patent fall under?
- Primary CPC classification F23R3/005. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Thu Dec 08 2016 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 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).