Aerofoil for an axial flow turbomachine
First Claim
1. A turbine stator vane (41) for use in a ring of similar vanes arranged in an axial flow turbine having an annular path for a turbine working fluid, the vane comprising an aerofoil spanning the annular path and having a radially inner platform region (45), a radially outer tip region (46), an axially forward leading edge (44) and an axially rearward trailing edge (43), the aerofoil having a pressure surface (47) and a suction surface (42) which, are respectively convex and concave between the platform region (45) and the tip region (46) in a plane (48) extending both radially of the annular path and transversely of the axial direction, the trailing edge (43) of the aerofoil being straight from the platform region to the tip region and oriented radially of the annular path, and said convex and concave curvatures of the aerofoil pressure and suction surfaces being achieved by rotational displacement of the aerofoil sections about the straight trailing edge, the axial width (W) of the aerofoil being substantially constant over substantially all of the aerofoil radial height and the chord line at mid-height aerofoil sections (44) being shorter than the chord lines in aerofoil sections at platform or tip regions.
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Accused Products
Abstract
A turbine stator vane (41) for use in an axial flow gas turbine. The vane has an aerofoil the pressure face of which is convex between platform (45) and tip (46) regions in a plane (48) which extends both radially of the turbine and transversely of the general working fluid flow direction between the vanes. The trailing edge (43) of the aerofoil is straight from platform to tip, and the spanwise convex and concave curvatures of the aerofoil pressure and suction surfaces respectively are achieved by rotational displacement of the aerofoil sections about the straight trailing edge. However, the axial width (W) of the aerofoil is substantially constant over substantially all of the aerofoil radial height and the chord line at mid-height aerofoil sections (44) is shorter than the chord lines in aerofoil sections at platform or tip regions. Reducing chord length at the mid-height region in this way lowers aerodynamic profile losses without unduly affecting vane performance. Also disclosed is a turbine rotor blade designed to form a stage pair with the stator vane.
21 Citations
20 Claims
- 1. A turbine stator vane (41) for use in a ring of similar vanes arranged in an axial flow turbine having an annular path for a turbine working fluid, the vane comprising an aerofoil spanning the annular path and having a radially inner platform region (45), a radially outer tip region (46), an axially forward leading edge (44) and an axially rearward trailing edge (43), the aerofoil having a pressure surface (47) and a suction surface (42) which, are respectively convex and concave between the platform region (45) and the tip region (46) in a plane (48) extending both radially of the annular path and transversely of the axial direction, the trailing edge (43) of the aerofoil being straight from the platform region to the tip region and oriented radially of the annular path, and said convex and concave curvatures of the aerofoil pressure and suction surfaces being achieved by rotational displacement of the aerofoil sections about the straight trailing edge, the axial width (W) of the aerofoil being substantially constant over substantially all of the aerofoil radial height and the chord line at mid-height aerofoil sections (44) being shorter than the chord lines in aerofoil sections at platform or tip regions.
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17. A stator vane for a gas turbine engine whose aerofoil section profiles in X-Y co-ordinates at the platform, mid-height, and tip regions are substantially as shown in Tables 1 to 3, respectively, within dimensional limits of variation of X and Y of ±
- 5% of chordal length.
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18. A rotor blade for a gas turbine engine whose aerofoil section profiles in X-Y co-ordinates at the platform, mid-height, and tip regions are substantially as shown in Tables 4 to 6, respectively, within dimensional limits of variation of X and Y of ±
- 5% of chordal length.
Specification