Gas turbine engine having outlet guide vanes
US-2024418094-A1 · Dec 19, 2024 · US
Aerofoil blade or vane
US9200535B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9200535-B2 |
| Application number | US-201213688892-A |
| Country | US |
| Kind code | B2 |
| Filing date | Nov 29, 2012 |
| Priority date | Dec 15, 2011 |
| Publication date | Dec 1, 2015 |
| Grant date | Dec 1, 2015 |
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Abstract
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An aerofoil blade or vane for the turbine of a gas turbine engine is provided. The blade or vane includes an aerofoil portion which, in use, extends radially across a working gas annulus of the engine. A coolant inlet is formed at an end of the aerofoil portion for the entry of a cooling air flow into the portion. A corresponding coolant exhaust is formed at the trailing edge of the aerofoil portion for spent cooling air to flow from the portion. A passage within the aerofoil portion connects the inlet to the exhaust. A fence within the aerofoil portion extends radially and forwardly from a start position at the end of the aerofoil portion adjacent the trailing edge to an end position. The passage forms a loop which extends along one side of the fence, wraps around the end position, and extends along the other side of the fence.
First claim
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The invention claimed is: 1. An aerofoil blade or vane for the turbine of a gas turbine engine, the blade or vane including: an aerofoil body comprising a base end, a trailing edge, a leading edge and an internal space and which, in use, extends radially across a working gas annulus of the engine, a coolant inlet being formed at the base end of the aerofoil body for entry of a flow of cooling air into the internal space, a corresponding coolant exhaust being formed at the trailing…
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- What does patent US9200535B2 cover?
- An aerofoil blade or vane for the turbine of a gas turbine engine is provided. The blade or vane includes an aerofoil portion which, in use, extends radially across a working gas annulus of the engine. A coolant inlet is formed at an end of the aerofoil portion for the entry of a cooling air flow into the portion. A corresponding coolant exhaust is formed at the trailing edge of the aerofoil po…
- Who is the assignee on this patent?
- Rolls Royce Plc
- What technology area does this patent fall under?
- Primary CPC classification F01D25/12. 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).