Stator vane assembly for a turbomachine
AssigneeROLLS-ROYCE plc
InventorShahrokh Shahpar
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Abstract
A stator vane assembly for a turbomachine comprising a plurality of circumferentially arranged stator vanes (32), the axial position of the stator vanes (32) and/or the pitch angle circumferentially between adjacent stator vanes (32) is varied circumferentially around the stator vane assembly. The stator vane assembly reduces the pressure distortion upstream of the fan outlet stator vanes (32), reduces the circumferential pressure variation and this reduces blade forced response excitation, noise generation and aerodynamic losses.
Claims30
A stator vane assembly for a turbomachine comprising a plurality of circumferentially arranged stator vanes, the turbomachine comprising a rotor arranged within a duct defined at least partially by a casing, the rotor comprises a plurality of rotor blades, at least one structure extending across the duct, the stator vanes being arranged between the structure and the rotor blades, the pitch angle circumferentially between adjacent stator vanes being varied circumferentially around the stator vane assembly wherein the stator vanes are arranged with three or more different pitch angles between adjacent stator vanes and the pitch angles between adjacent stator vanes progressively changes circumferentially around the stator vane assembly from a maximum pitch angle between adjacent stator vanes to a minimum pitch angle between adjacent stator vanes wherein the stator vanes are arranged with a plurality of maximum pitch angles between adjacent stator vanes and a plurality of minimum pitch angles between adjacent stator vanes.
A stator vane assembly for a turbomachine comprising a plurality of circumferentially arranged stator vanes, the turbomachine comprising a rotor arranged within a duct defined at least partially by a casing, the rotor comprising a plurality of rotor blades, at least one structure extending across the duct, the stator vanes being arranged between the structure and the rotor blades, the axial position of the stator vanes being varied circumferentially around the stator vane assembly, the stator vanes being arranged at three or more axial positions, the axial positions of the stator vanes progressively changes circumferentially around the stator vane assembly from a stator vane at an upstream axial position to a stator vane at a downstream axial position, and a plurality of stator vanes at the upstream axial position and a plurality of stator vanes at the downstream axial position.
A fan outlet stator vane assembly for a turbofan gas turbine engine comprising a plurality of circumferentially arranged fan outlet stator vanes, the turbofan gas turbine engine comprising a fan rotor arranged within a fan duct defined at least partially by a fan casing, the fan rotor comprising a plurality of fan rotor blades, a pylon extending across the fan duct to carry the turbofan gas turbine engine and a fairing extending across the fan duct, the fan outlet stator vanes being arranged between the pylon and the fairing and the fan rotor blades, the fan outlet guide vanes being arranged downstream of the fan rotor blades and upstream of the pylon and the fairing, the pitch angle circumferentially between adjacent fan outlet stator vanes being varied circumferentially around the fan outlet stator vane assembly, the fan outlet stator vanes being arranged with three or more different pitch angles between adjacent fan outlet stator vanes, the pitch angles between adjacent fan outlet stator vanes progressively changes circumferentially around the fan outlet stator vane assembly from a maximum pitch angle between adjacent fan outlet stator vanes to a minimum pitch angle between adjacent fan outlet stator vanes and the fan outlet stator vanes being arranged with a plurality of maximum pitch angles between adjacent fan outlet stator vanes and a plurality of minimum pitch angles between adjacent fan outlet stator vanes.
A fan outlet stator vane assembly for a turbofan gas turbine engine comprising a plurality of circumferentially arranged fan outlet stator vanes, the turbofan gas turbine engine comprising a fan rotor arranged within a fan duct defined at least partially by a fan casing, the fan rotor comprising a plurality of fan rotor blades, a pylon extending across the fan duct to carry the turbofan gas turbine engine and a fairing extending across the fan duct, the fan outlet stator vanes being arranged between the pylon and the fairing and the fan rotor blades, the fan outlet guide vanes being arranged downstream of the fan rotor blades and upstream of the pylon and the fairing, the axial position of the fan outlet stator vanes being varied circumferentially around the fan outlet stator vane assembly, the fan outlet stator vanes being arranged at three or more axial positions, the axial positions of the fan outlet stator vanes progressively changes circumferentially around the fan outlet stator vane assembly from a fan outlet stator vane at an upstream axial position to a fan outlet stator vane at a downstream axial position, a plurality of fan outlet stator vanes at the upstream axial position and a plurality of fan outlet stator vanes at the downstream axial position.
Dependencies are inferred from the claim text.