Method of reducing asymmetric fluid flow effects in a passage
AssigneeROLLS-ROYCE plc
InventorAdam M Bagnall
Life of this patent
Estimating the term…
Abstract
A method of reducing the fluid flow effects of one or more flow modifiers (19) in a passage (16), the method comprising: providing a plurality of aerofoil structures (15) in the passage (16), wherein the geometry of each aerofoil structure (15) is initially substantially the same; and shortening the trailing edge (18) of one or more selected aerofoil structures (17) in a chordwise direction and over at least a spanwise portion of the one or more selected aerofoil structures such that, when in use, the direction of the fluid flow (20a, 20e) in the vicinity of the one or more selected aerofoil structures is altered and the fluid flow effects of the one or more flow modifiers (19) in the passage are reduced.
Claims10
A method of reducing the fluid flow effects of one or more obstacles in a passage of a gas turbine engine, the method comprising:
- providing a plurality of aerofoil structures in the passage upstream of the one or more obstacles, wherein the geometry of each aerofoil structure is substantially the same;
- shortening at least one trailing edge of one or more selected aerofoil structures in a chordwise direction and over at least a spanwise portion of the one or more selected aerofoil structures such that, when in use, the direction of the fluid flow in the vicinity of the one or more selected aerofoil structures is altered and the fluid flow effects of the one or obstacles in the passage are reduced;
- and
- arranging the aerofoil structures such that a setting angle of each aerofoil structure is approximately equal;
- and
- varying an amount that is shortened from each of the trailing edges such that at least one of the trailing edges is not shortened and is provided adjacent to at least one trailing edge that is shortened.
A gas turbine engine comprising an assembly for reducing the fluid flow effects of one or more obstacles in a passage, the assembly comprising:
- a plurality of aerofoil structures provided in the passage upstream of the obstacle, the geometry of each aerofoil structure being substantially the same except for one or more selected aerofoil structures comprising a plurality of trailing edges in a chordwise direction and over at least a spanwise portion of the one or more selected aerofoil structures such that, when in use, the direction of the fluid flow in the vicinity of the one or more selected aerofoil structures is altered and the fluid flow effects of the one or more flow modifiers in the passage are reduced,
- wherein:
- the aerofoil structures are arranged such that a setting angle of each aerofoil structure is approximately equal, and
- at least one of the trailing edges is not shortened and provided adjacent to at least one of the trailing edges that is shortened.
Dependencies are inferred from the claim text.