Zoned surface roughness
AssigneeGKN Aerospace Sweden AB
InventorPeter Johansson
Life of this patent
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Abstract
The invention concerns a transition duct for a multi-stage compressor of a gas turbine engine. Regions of the inner surface of the duct are provided with a predetermined and dissimilar surface roughness to optimise gas flow efficiency within the duct.
Claims14
An apparatus comprising a multi-stage compressor, comprising:
- a first and second compressor coaxially located with respect to a central axis of a gas turbine engine,
- wherein an outlet of the first compressor is in fluid communication with an inlet of the second compressor through a duct, the duct defining a channel for gas flow and comprising an inner gas facing wall and an opposing outer gas facing wall defining the inner surfaces of the channel, and wherein regions of the inner surfaces of the channel have a predetermined and dissimilar surface roughness, and wherein at least one region of the inner surface of the channel against which flowing gas impinges is provided with a surface roughness which is lower than regions of the inner surfaces against which flow gas does not impinge.
A transition duct for a multi-stage compressor of a gas turbine engine, said duct arranged in use to communicate gas between a first and second compressor coaxially located with respect to a central axis of a gas turbine engine, wherein the duct defines a channel for gas flow and comprises an inner gas facing wall and an opposing outer gas facing wall defining the inner surfaces of the channel, and wherein regions of the inner surfaces of the channel have a predetermined and dissimilar surface roughness, and wherein at least one region of the inner surface of the channel against which flowing gas impinges is provided with a surface roughness which is lower than regions of the inner surfaces against which flow gas does not impinge.
Dependencies are inferred from the claim text.