A turbine blade is provided, comprising a stator-side end located toward a stationary stator cylinder of the turbine, a rotor-side end located toward an axial rotor of the turbine, a leading edge located between the stator-side end and the rotor-side end, a trailing edge located between the stator-side end and the rotor-side end and located down-stream of the leading edge with respect to a fluid flow direction, wherein the rotor-side and stator-side ends have a negative sweep angle as measured between the instantaneous tangent of the blade surface and the fluid flow direction. Also, a turbine blade is provided, comprising a stator-side end located toward a stationary stator cylinder of the turbine, a rotor-side end located toward an axial rotor of the turbine, a delivery side located between the stator-side end and the rotor-side end, a suction side located between the stator-side end and the rotor-side end and located down-stream of the leading edge with respect to a fluid flow direction, wherein the rotor-side end is inclined toward the delivery side and the stator-side end is inclined with respect to a fluid flow direction.
1. A turbine blade adapted for installation in a turbine engine having a stationary stator cylinder and a rotatably supported rotor, comprising:
a stator-side end located toward the stationary stator cylinder of the turbine engine;
a rotor-side end located toward the rotatably supported rotor of the turbine engine;
a leading edge located between the stator-side end and the rotor-side end; and
a trailing edge located between the stator-side end and the rotor-side end and located down-stream of the leading edge with respect to a fluid flow direction,
wherein both the rotor-side and the stator-side ends each respectively have a negative sweep angle as measured between the instantaneous tangent of a blade form curve and the fluid flow direction; and
wherein rotor-side instantaneous tangents and stator-side instantaneous tangents intersect a longitudinal plane, the plane extending from an axis of rotation of the rotatably supported rotor and passing through a point disposed in a middle region of the leading edge, and wherein portions of rotor-side instantaneous tangents and stator-side instantaneous tangents radially outward from the points of intersection are on a same side of the longitudinal plane.
2. The turbine blade of claim 1 , wherein negative sweep results in the direction of flow being rotated in a mathematically negative direction in order to achieve a coincidence of the direction of flow with respect to the instantaneous tangent of the blade surface.
3. The turbine blade of claim 1 , wherein the negative sweep angle of the rotor-side and stator-side ends transitions into a positive sweep in a region between the leading edge and trailing edge.
4. The turbine blade as claimed in claim 1 , wherein the rotor-side end negative sweep has a range between 0° and 90° .
5. The turbine blade as claimed in claim 4 , wherein the rotor-side end negative sweep has a range between 50° and 80° .
6. The turbine blade as claimed in claim 1 , wherein the stator-side end negative sweep has a range between 0° and 90° .
7. The turbine blade as claimed in claim 1 , wherein the turbine blade is a stationary guide blade or a rotating blade.
8. The turbine blade as claimed in claim 1 , wherein the leading edge is arranged in front of the trailing edge in the axial direction of flow at the stator-side end or the rotor-side end.
9. The turbine blade as claimed in claim 1 , wherein the turbine blade is arranged in a turbomachine.
10. The turbine blade as claimed in claim 1 , wherein a second up-stream turbine guide blade is located at a constant axial distance from the turbine blade.
11. The turbine blade as claimed in claim 10 , wherein a trailing edge of the second up-stream guide blade is located at a constant axial distance from the leading edge of the blade at the rotor-side end.
12. A turbine blade, comprising:
a stator-side end located toward a stationary stator cylinder of a turbine;
a rotor-side end located toward an axial rotor of the turbine;
a delivery side located between the stator-side end and the rotor-side end; and
a suction side located between the stator-side end and the rotor-side end and located down-stream of a leading edge of the blade with respect to a fluid flow direction,
wherein a rotor-side end blade form curve is inclined toward the delivery side, and a stator-side end blade form curve is inclined with respect to the fluid flow direction and inclined toward the delivery side,
wherein the stator-side end blade form curve incline angle is 70° with respect to the fluid flow direction.
13. A turbine blade, comprising:
a stator-side end located toward a stationary stator cylinder of a turbine;
a rotor-side end located toward an axial rotor of the turbine;
a delivery side located between the stator-side end and the rotor-side end; and
a suction side located between the stator-side end and the rotor-side end and located down-stream of a leading edge of the blade with respect to a fluid flow direction.,
wherein a rotor-side end blade form curve is inclined toward the delivery side, and a stator-side end blade form curve is inclined with respect to the fluid flow direction and inclined toward the delivery side,
wherein the rotor-side end blade form curve is inclined at an angle between 0° and 90° viewed in the direction of flow, where the rotor-side end blade faun curve incline angle is defined as the acute angle between the instantaneous blade form curve tangent of the rotor and a radial axis emanating from a rotor longitudinal axis of rotation and intersecting the auxiliary tangent at an inner casing.
14. The turbine blade as claimed in claim 13 , wherein the rotor-side end blade form curve incline angle is 75°.
15. The turbine blade as claimed in claim 12 , is a stationary guide blade or a rotating blade.
16. The turbine blade as claimed in claim 12 , wherein the turbine blade is arranged in a turbomachine.
17. The turbine blade as claimed in claim 12 , wherein a second up-stream turbine guide blade is located at a constant axial distance from the turbine blade.
18. The turbine blade as claimed in claim 17 , wherein a trailing edge of the second up-stream guide blade is located at a constant axial distance from the leading edge of the turbine blade at the rotor-side end.