Vane or blade for an axial flow compressor
A compressor vane or compressor blade is provided. The axial flow compressor includes an axial direction, a radial direction, a compressor hub and a compressor casing. The vane or blade includes an airfoil with airfoil sections having a span, a chamber line and a leading edge at which the chamber line includes a leading edge blade angle with the axial direction of the compressor and a trailing edge at which the chamber line includes a trailing edge blade angle with the axial direction of the compressor. The airfoil sections are stacked at the leading edge on a straight line extending along a radial direction of the compressor from the compressor hub towards a compressor casing and in that the leading edge angles of the airfoil sections vary along the span and are larger for airfoil sections close to the hub and close to the wall than for mid-span airfoil sections.
1. A compressor stator vane or compressor rotor blade for an axial flow compressor wherein the axial flow compressor includes an axial direction, a radial direction, a compressor hub, and a compressor casing, the stator vane or rotor blade comprising:
an airfoil with a plurality of airfoil sections including a span, a camber line and a leading edge at which the camber line includes a leading edge blade angle with the axial direction of the compressor and a trailing edge at which the chamber line includes a trailing edge blade angle with the axial direction of the compressor,
wherein the plurality of airfoil sections are stacked at the leading edge on a straight line extending along the radial direction of the compressor from the compressor hub towards a compressor casing, and
wherein the leading edge blade angle of the plurality of airfoil sections varies along the span and the leading edge blade angle is larger for the plurality of airfoil sections close to the compressor hub and close to the casing than for mid-span airfoil sections,
wherein the trailing edge blade angle of the plurality of airfoil sections varies along the span and the trailing edge blade angle is larger for airfoil sections close to the compressor hub and/or close to the casing than for mid-span airfoil section, and
wherein a first variation in the trailing edge blade angle of the airfoil sections is smaller than a second variation in the leading edge blade angle of the airfoil sections.
2. The stator vane or rotor blade as claimed in claim 1 , wherein the leading edge blade angle of the plurality of airfoil sections is the largest towards the casing.
3. The stator vane or rotor blade as claimed in claim 1 , wherein a first increase in leading edge blade angle of the plurality of airfoil sections relative to mid-span airfoil sections are the largest towards the casing.
4. The stator vane as claimed in claim 1 , wherein the trailing edge blade angle of the airfoil sections are the largest towards the casing.
5. The stator vane as claimed in claim 1 , wherein a second increase in the trailing edge blade angle of the airfoil sections relative to mid-span airfoil sections are the largest towards the casing.
6. The stator vane or rotor blade as claimed in claim 1 , wherein the leading edge blade angle of the airfoil sections of the stator vanes or the rotor blades and/or the trailing edge blade angle of the airfoil sections of the stator vanes include a minimum between 30% and 70% span of the airfoil.
7. The stator vane or rotor blade as claimed in claim 1 , wherein the trailing edge is curved.
8. An axial flow compressor including an axial direction, a radial direction, a compressor hub, and a compressor casing, comprising:
a plurality of stator vanes or rotor blades, each comprising:
an airfoil with a plurality of airfoil sections including a span, a camber line and a leading edge at which the camber line includes a leading edge blade angle with the axial direction of the compressor and a trailing edge at which the chamber line includes a trailing edge blade angle with the axial direction of the compressor,
wherein the plurality of airfoil sections are stacked at the leading edge on a straight line extending along the radial direction of the compressor from the compressor hub towards a compressor casing,
wherein the leading edge blade angle of the plurality of airfoil sections varies along the span and the leading edge blade angle is larger for the plurality of airfoil sections close to the compressor hub and close to the casing than for mid-span airfoil sections,
wherein the trailing edge blade angle of the plurality of airfoil sections varies along the span and the trailing edge blade angle is larger for airfoil sections close to the compressor hub and/or close to the casing than for mid-span airfoil section, and
wherein a first variation in the trailing edge blade angle of the airfoil sections is smaller than a second variation in the leading edge blade angle of the airfoil sections.
9. The compressor as claimed in claim 8 , wherein the leading edge blade angle of the plurality of airfoil sections is the largest towards the casing.
10. The compressor as claimed in claim 8 , wherein a first increase in leading edge blade angle of the plurality of airfoil sections relative to mid-span airfoil sections are the largest towards the casing.
11. The compressor as claimed in claim 8 , wherein the trailing edge blade angle of the airfoil sections are the largest towards the casing.
12. The compressor as claimed in claim 8 ,
wherein a second increase in the trailing edge blade angle of the airfoil sections relative to mid-span airfoil sections are the largest towards the casing.
13. The compressor as claimed in claim 8 , wherein the leading edge blade angle of the airfoil sections of the stator vanes or the rotor blades and/or the trailing edge blade angle of the airfoil sections of the stator vanes include a minimum between 30% and 70% span of the airfoil.
14. The compressor as claimed in claim 8 , wherein the trailing edge is curved.