US 2013/0156603 A1Published application

Aerofoil blade or vane

AssigneeROLLS-ROYCE plc

InventorsAnthony John RAWLINSON, Matthew ADAMS, Peter Philip RAMWELL

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Abstract

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.

Claims11

Dependent claims

An aerofoil blade or vane for the turbine of a gas turbine engine, the blade or vane including:

an aerofoil portion which, in use, extends radially across a working gas annulus of the engine, a coolant inlet being formed at an end of the aerofoil portion for entry of a flow of cooling air into the aerofoil portion, a corresponding coolant exhaust being formed at the trailing edge of the aerofoil portion for the flow of spent cooling air from the aerofoil portion, and a passage within the aerofoil portion connecting the inlet to the exhaust, and
a fence within the aerofoil portion, the fence extending radially and forwardly from a start position at said end of the aerofoil portion adjacent the trailing edge to an end position;
wherein 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 to connect the inlet to the exhaust.

Dependencies are inferred from the claim text.

Facts

Application: 13/688,892Filed 29 Nov 2012
Priority: GB 1121531.615 Dec 2011
Published: 20 Jun 2013
Term ends: Not estimatedThe source records don’t support an estimate.

Classification5 codes

F01D 25/12
Cooling ; Heating; Heat-insulation: cooling
F01D 5/187
Hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades: convection cooling
F05D 2250/185
Patterned: serpentine-like
F01D
Non-positive displacement machines or engines

Family

US 9,200,535 B2Related patent
US 2013/0156603 A1This patent

From the US filing history. Foreign family members aren’t listed.

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