Blade member and structural member
US-2024102389-A1 · Mar 28, 2024 · US
Blade for a fan of a turbomachine, notably of the unducted fan type, corresponding fan and corresponding turbomachine
US9630704B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9630704-B2 |
| Application number | US-201214347940-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 28, 2012 |
| Priority date | Sep 29, 2011 |
| Publication date | Apr 25, 2017 |
| Grant date | Apr 25, 2017 |
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Abstract
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A blade for a fan of a turbomachine, for example of unducted fan type, a corresponding fan, and a corresponding turbomachine. The blade includes a mechanism arranged, at a single location, to locally, as the fan rotates, disturb a distribution of flow around the blade so as to form two independent main vortices downstream.
First claim
Opening claim text (preview).
The invention claimed is: 1. A turbomachine with an unducted fan, comprising: two coaxial and contra-rotating fans, respectively upstream and downstream, the upstream and downstream fans comprising a plurality of blades, wherein the blades of the upstream fan comprise means arranged, at a single location, to locally disturb, as the upstream fan rotates, distribution of flow around the blade, to form two independent main vortices downstream, wherein the means consists of a single protuberance formed on a leading edge of the blade, and which is defined by a span position h such that 0.75 H<h<0.85 H, H being a height of the blade. 2. The turbomachine as claimed in claim 1 , wherein the single protuberance is defined by its span height d such that 0.05 H<d<0.2 H, H being the height of the blade. 3. The turbomachine as claimed in claim 1 , wherein the single protuberance is defined by a chord width l such that c/16<l<c/8, c being a length of a local chord of the blade at the span position h of the single protuberance. 4. The turbomachine as claimed in claim 1 , further comprising a notch formed in the leading edge of the blade and which is adjacent to the single protuberance. 5. The turbomachine as claimed in claim 1 , wherein a trailing edge of the blades of the upstream fan is free of any protuberance or concavity.
Assignees
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Classifications
Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title
Units of two or more coaxial propellers · CPC title
to drive unshrouded, high solidity propeller · CPC title
Cross-Sectional Technologies · mapped topic
Cross-Sectional Technologies · mapped topic
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Frequently asked questions
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- What does patent US9630704B2 cover?
- A blade for a fan of a turbomachine, for example of unducted fan type, a corresponding fan, and a corresponding turbomachine. The blade includes a mechanism arranged, at a single location, to locally, as the fan rotates, disturb a distribution of flow around the blade so as to form two independent main vortices downstream.
- Who is the assignee on this patent?
- Snecma, Onera (Off Nat Aerospatiale)
- What technology area does this patent fall under?
- Primary CPC classification F01D5/141. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Apr 25 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).