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US-2024417070-A1 · Dec 19, 2024 · US
Turbomachine
US9453423B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9453423-B2 |
| Application number | US-201313760598-A |
| Country | US |
| Kind code | B2 |
| Filing date | Feb 6, 2013 |
| Priority date | Feb 10, 2012 |
| Publication date | Sep 27, 2016 |
| Grant date | Sep 27, 2016 |
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Abstract
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A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides.
First claim
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What is claimed is: 1. A turbomachine comprising: at least one blade row group situated in a main flow path and including at least an upstream row of blades and a downstream row of further blades, adjacent to each other in a main flow direction, rear edges of the blades of the upstream row and front edges of the further blades of the downstream row being situated at an edge distance in a peripheral direction varying starting from a main flow path center in a direction of both main flow limiters, the edge distance either increasing or decreasing on both sides of the main flow path center, the edge distance decreasing in the direction of one of the main flow limiters up to a minimum and then increasing. 2. The turbomachine as recited in claim 1 wherein the rear edges of the blades of the upstream row have a curved contour and the front edges of the further blades of the downstream row have a linear contour. 3. The turbomachine as recited in claim 1 wherein the rear edges of the blades of the upstream row have a linear contour and the front edges of the further blades of the downstream row have a curved contour. 4. The turbomachine as recited in claim 1 wherein the rear edges and the front edges have a curved contour. 5. The turbomachine as recited in claim 1 wherein the rear edges and the front edges intersect the main flow path center at an angle φ=90°. 6. The turbomachine as recited in claim 1 wherein the rear edges and the front edges intersect the main flow path center at an angle φ90°. 7. A turbomachine comprising: at least one blade row group situated in a main flow path and including at least an upstream row of blades and a downstream row of further blades, adjacent to each other in a main flow direction, rear edges of the blades of the upstream row and front edges of the further blades of the downstream row being situated at an edge distance in a peripheral direction varying starting from a main flow path center in a direction of both main flow limiters, the edge distance increasing or decreasing on both sides of the main flow path center, the edge distance decreasing in the direction of one of the main flow limiters up to a minimum and is then constant. 8. The turbomachine as recited in claim 7 wherein the rear edges of the blades of the upstream row have a curved contour and the front edges of the further blades of the downstream row have a linear contour. 9. The turbomachine as recited in claim 7 wherein the rear edges of the blades of the upstream row have a linear contour and the front edges of the other blades of the downstream row have a curved contour. 10. The turbomachine as recited in claim 7 wherein the rear edges and the front edges intersect the main flow path center at an angle φ=90°. 11. The turbomachine as recited in claim 7 wherein the rear edges and the front edges intersect the main flow path center at an angle φ90°.
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- What does patent US9453423B2 cover?
- A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge d…
- Who is the assignee on this patent?
- Mtu Aero Engines Gmbh
- What technology area does this patent fall under?
- Primary CPC classification F01D9/00. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Sep 27 2016 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).