Compact Aero-Thermo Model Based Tip Clearance Management
US-2015378364-A1 · Dec 31, 2015 · US
Rotor of a turbomachine compressor, with an optimised inner end wall
US9200638B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9200638-B2 |
| Application number | US-201013498696-A |
| Country | US |
| Kind code | B2 |
| Filing date | Oct 1, 2010 |
| Priority date | Oct 2, 2009 |
| Publication date | Dec 1, 2015 |
| Grant date | Dec 1, 2015 |
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Abstract
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A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.
First claim
Opening claim text (preview).
The invention claimed is: 1. A rotor of a turbomachine compressor, comprising: a rotor disk which holds blades each of which has an extrados surface and an intrados surface, wherein the disk is fitted, at its radially outer end, with a wall forming an inner end of an annular flow channel of a primary gas flow in the turbomachine, wherein this wall is formed from multiple angular sectors, each of which is delimited between the extrados surface of a first blade and the intrados…
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Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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Frequently asked questions
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- What does patent US9200638B2 cover?
- A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axi…
- Who is the assignee on this patent?
- Boston Eric Jacques, Chartoire Alexandre Franck Arnaud, Iliopoulou Vasiliki, and 4 more
- What technology area does this patent fall under?
- Primary CPC classification F04D29/321. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Dec 01 2015 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).