Aerofoil for an axial flow turbomachine
First Claim
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1. A turbine stator vane 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, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, the aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of an axial direction, the trailing edge 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 aerofoil sections about the straight trailing edge, the aerofoil having an axial width which is substantially constant over substantially all of a radial height of the aerofoil, and a chord line at mid-height of the aerofoil sections being shorter than chord lines in the aerofoil sections at the platform and tip regions.
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Abstract
A turbine stator vane for use in an axial flow gas turbine. The vane has an aerofoil, the pressure face of which is convex between platform and tip regions in a plane which extends both radially of the turbine and transversely of the general working fluid flow direction between the vanes. The trailing edge 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 of the aerofoil is substantially constant over substantially all of the aerofoil radial height and the chord line at mid-height aerofoil sections 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.
45 Citations
20 Claims
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1. A turbine stator vane 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, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, the aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of an axial direction, the trailing edge 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 aerofoil sections about the straight trailing edge, the aerofoil having an axial width which is substantially constant over substantially all of a radial height of the aerofoil, and a chord line at mid-height of the aerofoil sections being shorter than chord lines in the aerofoil sections at the platform and tip regions.
- View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A turbine stage, comprising:
- a row of stator vanes, each stator vane including a vane aerofoil spanning an annular path for a turbine working fluid and having a radially inner platform region, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, the vane aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of an axial direction, the trailing edge of the vane 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 vane aerofoil sections about the straight trailing edge, the vane aerofoil having an axial width which is substantially constant over substantially all of a radial height of the vane aerofoil, and a chord line at mid-height of the vane aerofoil sections being shorter than chord lines in the vane aerofoil sections at the platform and tip regions; and
a row of rotor blades in flow sequence with the vanes, the blades comprising blade aerofoils each having a radially inner platform region, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, each blade aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of the axial direction, said convex and concave curvatures of the blade aerofoil pressure and suction surfaces being achieved by rotational displacement of blade aerofoil sections about a radial line through the blade aerofoil, each blade aerofoil having outlet angles which are smaller near its platform and tip regions than at mid-height. - View Dependent Claims (11, 12, 13, 14, 15, 16)
- a row of stator vanes, each stator vane including a vane aerofoil spanning an annular path for a turbine working fluid and having a radially inner platform region, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, the vane aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of an axial direction, the trailing edge of the vane 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 vane aerofoil sections about the straight trailing edge, the vane aerofoil having an axial width which is substantially constant over substantially all of a radial height of the vane aerofoil, and a chord line at mid-height of the vane aerofoil sections being shorter than chord lines in the vane aerofoil sections at the platform and tip regions; and
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17. A stator vane for a gas turbine engine whose aerofoil section profiles in X-Y coordinates at the platform region, mid-height region, and tip region are substantially as shown in Tables 1-3, 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 coordinates at the platform region, mid-height region, and tip region are substantially as shown in Tables 4-6, respectively, within dimensional limits of variation of X and Y of ±
- 5% of chordal length.
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19. A turbine stage, comprising:
- a row of stator vanes, each stator vane including a vane aerofoil spanning an annular path for a turbine working fluid and having a radially inner platform region, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, the vane aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of an axial direction, the trailing edge of the vane 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 vane aerofoil sections about the straight trailing edge, the vane aerofoil having an axial width which is substantially constant over substantially all of a radial height of the vane aerofoil, and a chord line at mid-height of the vane aerofoil sections being shorter than chord lines in the aerofoil sections at the platform and tip regions; and
a row of blades in flow sequence with the vanes, the blades comprising blade aerofoils each having a radially inner platform region, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, each blade aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of the axial direction, said convex and concave curvatures of the blade aerofoil pressure and suction surfaces being achieved by rotational displacement of blade aerofoil sections about a radial line through the blade aerofoil, each blade aerofoil having outlet angles which are smaller near its platform and tip regions than at mid-height, whose blade aerofoil section profiles in X-Y coordinates at the platform region, mid-height region, and tip region are substantially as shown in Tables 4-6, respectively, within dimensional limits of variation of X and Y of ±
5% of chordal length.
- a row of stator vanes, each stator vane including a vane aerofoil spanning an annular path for a turbine working fluid and having a radially inner platform region, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, the vane aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of an axial direction, the trailing edge of the vane 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 vane aerofoil sections about the straight trailing edge, the vane aerofoil having an axial width which is substantially constant over substantially all of a radial height of the vane aerofoil, and a chord line at mid-height of the vane aerofoil sections being shorter than chord lines in the aerofoil sections at the platform and tip regions; and
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20. A turbine stage, comprising:
- a row of stator vanes, each stator vane including a vane aerofoil spanning an annular path for a turbine working fluid and having a radially inner platform region, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, the vane aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of an axial direction, the trailing edge of the vane 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 vane aerofoil sections about the straight trailing edge, the vane aerofoil having an axial width which is substantially constant over substantially all of a radial height of the vane aerofoil, and a chord line at mid-height of the vane aerofoil sections being shorter than chord lines in the vane aerofoil sections at the platform and tip region, whose vane aerofoil section profiles in X-Y coordinates at the platform region, mid-height region, and tip region are substantially as shown in Tables 1-3, respectively, within dimensional limits of variation of X and Y of ±
5% of chordal length; and
a row of blades in flow sequence with the vanes, whose blade aerofoil section profiles in X-Y coordinates at the platform region, mid-height region, and tip region are substantially as shown in Tables 4-6, respectively, within dimensional limits of variation of X and Y of ±
5% of chordal length.
- a row of stator vanes, each stator vane including a vane aerofoil spanning an annular path for a turbine working fluid and having a radially inner platform region, a radially outer tip region, an axially forward leading edge and an axially rearward trailing edge, the vane aerofoil having a pressure surface and a suction surface which are respectively convex and concave between the platform region and the tip region in a plane extending both radially of the annular path and transversely of an axial direction, the trailing edge of the vane 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 vane aerofoil sections about the straight trailing edge, the vane aerofoil having an axial width which is substantially constant over substantially all of a radial height of the vane aerofoil, and a chord line at mid-height of the vane aerofoil sections being shorter than chord lines in the vane aerofoil sections at the platform and tip region, whose vane aerofoil section profiles in X-Y coordinates at the platform region, mid-height region, and tip region are substantially as shown in Tables 1-3, respectively, within dimensional limits of variation of X and Y of ±
Specification
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Current AssigneeSiemens Energy Global GmbH & Co. KG (Siemens AG)
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Original AssigneeALSTOM Power Inc. (General Electric Company)
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InventorsHaller, Brian Robert
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Primary Examiner(s)VERDIER, CHRISTOPHER M
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Application NumberUS09/958,821Publication NumberTime in Patent Office802 DaysField of Search415/183, 415/191, 415/192, 415/208.1, 415/208.2, 415/211.2, 416/223.R, 416/223.A, 416/238, 416/243, 416/242, 416/DIG.2, 416/DIG.5US Class Current415/192CPC Class CodesF01D 5/141 Shape, i.e. outer, aerodyna...F01D 9/02 Nozzles; Nozzle boxes; Stat...Y10S 416/02 Formulas of curvesY10S 416/05 Variable camber or chord le...
