Fluid diodes with ridges to control boundary layer in axial compressor stator vane
AssigneeROLLS-ROYCE plc
InventorMasayoshi Shimo
Life of this patent
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Abstract
An entrance stator in a turbofan has an airfoil shape with a leading edge and a trailing edge connected by surfaces which define a suction side and a pressure side. The entrance stator has a channel with an opening on the pressure side, extending to an exit on the suction side, having a pressure gradient between the opening and the exit. The channels are preceded with a ridge. The channels and the ridges control the boundary layer, enabling higher efficiencies. The channels and ridges add energy to the boundary layer to prevent separation.
Claims20
A turbofan comprising:
- a inlet passage;
- a fan in the inlet passage, the inlet passage separating into a bypass passage and core passage downstream of the fan;
- the core passage having an entrance proximate to the fan and an outlet downstream of a compressor;
- an entrance stator located within the core passage aft of the entrance and forward of the compressor;
- the entrance stator fixed to an inner casing and an outer casing, the entrance stator extending radially between the inner and outer casing;
- the outer casing separating the bypass passage from the core passage;
- the entrance stator having an airfoil shape with a leading edge and a trailing edge connected by surfaces which define a suction side and a pressure side;
- the entrance stator having a channel with an opening on the pressure side, the channel extending from the opening to an exit on the suction side, wherein there is a pressure gradient between the opening and the exit, wherein the pressure gradient ensures flow from the opening on the pressure side to the exit on the suction side.
In a turbofan with a plurality of stators between a fan and a rotor of a compressor, wherein the fan and compressor rotor are coaxial, each stator having a leading edge, trailing edge, suction surface and pressure surface, the suction and pressure surfaces extending between the leading and trailing edge;
- a method of increasing the efficiency of the compressor comprising:
- injecting high pressure air from the pressure surface via a passage between the pressure surface and the suction surface into a boundary layer on the suction surface,
- restricting the flow of fluid from the suction surface through the passage towards the pressure surface;
- tripping the fluid flow proximate a boundary layer on the suction surface from laminar to turbulent on the suction surface upstream of the injected high pressure air, thereby increasing the efficiency of the compressor.
A stator vane comprising:
- a leading edge, trailing edge, a first surface from the leading edge to the trailing edge and a second surface oppositely disposed from the first surface extending from the trailing edge to the leading edge in the shape of an aerofoil;
- a one-way channel with an opening on the first surface, the one-way channel extending from the opening to an exit on the second surface,
- a pressure gradient between the opening and the exit of the one-way channel;
- and,
- a ridge extending from the second surface forward of the exit, proximate to the opening and the exit;
- wherein the first surface is in fluid communication via the one-way channel with the second surface, and wherein the pressure gradient ensures flow from the opening on the pressure side to the exit on the suction side.
Dependencies are inferred from the claim text.