초록 ▼

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-s

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.

대표청구항 ▼

The invention claimed is: 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 rotat

The invention claimed is: 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.