Blade member and structural member
US-2024102389-A1 · Mar 28, 2024 · US
Turbomachine element
US9726197B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9726197-B2 |
| Application number | US-201214125454-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jun 11, 2012 |
| Priority date | Jun 14, 2011 |
| Publication date | Aug 8, 2017 |
| Grant date | Aug 8, 2017 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A turbomachine element including an airfoil set including a plurality of airfoils that are offset from one another in a lateral direction, and upstream from at least one end of each airfoil, a group of a plurality of vortex generator devices that are mutually offset both laterally and axially.
First claim
Opening claim text (preview).
The invention claimed is: 1. A turbomachine element comprising: an airfoil set including a plurality of airfoils offset from one another in a lateral direction; and a group of a plurality of parallel fins arranged upstream, in an axial direction perpendicular to said lateral direction, from at least one end of each airfoil of the airfoil set, the fins of each group being mutually offset both laterally and axially. 2. A turbomachine element according to claim 1 , wherein each group of fins includes at least three fins. 3. A turbomachine element according to claim 1 , wherein the fins are straight. 4. A turbomachine element according to claim 1 , wherein the airfoil set is an outlet guide vane set. 5. A turbomachine element according to claim 1 , wherein a height of the fins is 2% to 8% of a height of the airfoils. 6. A turbomachine element according to claim 1 , wherein the airfoils of the set are arranged radially around a central axis, each airfoil including a proximal end and a distal end. 7. A turbomachine element according to claim 6 , wherein the group of the plurality of fins is situated upstream from the proximal end of each airfoil. 8. A turbomachine comprising: at least one turbomachine element comprising: an airfoil set including a plurality of airfoils offset from one another in a lateral direction; and a group of a plurality of parallel fins arranged upstream, in an axial direction perpendicular to said lateral direction, from at least one end of each airfoil, the fins of each group being mutually offset both laterally and axially. 9. A turbomachine comprising: at least one compressor element comprising: an airfoil set including a plurality of airfoils offset from one another in a lateral direction; and a group of a plurality of parallel fins arranged upstream, in an axial direction perpendicular to said lateral direction, from at least one end of each airfoil, the fins of each group being mutually offset both laterally and axially.
Assignees
Inventors
Classifications
Blade shapes · CPC title
- F01D5/145Primary
Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title
Vortex generators, turbulators, or the like, for mixing · CPC title
especially adapted for elastic fluid pumps · CPC title
Cross-Sectional Technologies · mapped topic
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Frequently asked questions
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- What does patent US9726197B2 cover?
- A turbomachine element including an airfoil set including a plurality of airfoils that are offset from one another in a lateral direction, and upstream from at least one end of each airfoil, a group of a plurality of vortex generator devices that are mutually offset both laterally and axially.
- Who is the assignee on this patent?
- Boniface Jean-Christophe Gerard Roger, Perrot Vincent, Pesteil Agnes, and 1 more
- What technology area does this patent fall under?
- Primary CPC classification F01D5/145. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Aug 08 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).