Turbine blade
A turbine blade ( 2 ), with a root section ( 4 ), with a tip section ( 6 ) and with a blade leaf ( 12 ) which is provided with a number of coolant ducts ( 22 ) through which a coolant (K) is capable of flowing, outlet ducts ( 34 ) which issue in outlet ports ( 24 ) branching off, in the leading edge region ( 28 ) of the blade leaf ( 12 ), from a coolant duct ( 22 ) running essentially in the longitudinal direction (L) of the turbine blade ( 2 ) and spaced apart from the leading edge ( 14 ), the outlet ports ( 24 ) being arranged along at least two rows oriented essentially parallel to the leading edge ( 14 ), and the outlet ducts ( 34 ) being oriented, in the region of their respective outlet port ( 24 ), obliquely with respect to the longitudinal direction (L) of the turbine blade ( 2 ), in such a way that the coolant (K) flowing out in a root-side subsection ( 38 ) of each row possesses, in the region of the outlet ports ( 24 ), a velocity component pointing toward the tip section ( 6 ) of the turbine blade ( 2 ), and the coolant (K) flowing out in a tip-side subsection ( 42 ), continguous thereto, of each row has a velocity component pointing toward the root section ( 4 ), is designed for a particularly reliable and uniform cooling of the leading edge region ( 28 ), at the same time with the requirement for coolant (K) being kept particularly low. For this purpose, according to the invention, the transitional points ( 40 ) at which the orientation of the outlet ducts ( 34 ) changes are arranged so as to be offset relative to one another in the longitudinal direction (L) in each case for two adjacent rows.
1. A turbine blade, comprising:
a root section;
a tip section;
a blade leaf having a plurality of coolant ducts through which a coolant flows and having a leading edge with a leading edge region, the coolant ducts extending essentially in a longitudinal direction of the turbine blade and spaced apart from the leading edge;
a plurality of outlet ports arranged along at least two rows oriented on the blade leaf essentially parallel to the leading edge; and
a plurality of outlet ducts oriented obliquely with respect to the longitudinal direction of the turbine blade so that the coolant flowing out in a root-side subsection of each row possesses a velocity component oriented toward the tip section of the turbine blade and that the coolant flowing out in a tip-side subsection of each row has a velocity component oriented toward the root section, wherein:
the outlet ducts are configured with a plurality of transitional points, at which the orientation of the outlet ducts changes, arranged to be offset relative to one another in the longitudinal direction for two adjacent rows; and
the transitional points of two outer rows are arranged identically with respect to the longitudinal direction.
2. The turbine blade as claimed in claim 1 , wherein the coolant ducts extends substantially in a longitudinal direction of the turbine blade and the plurality of outlet ports are arranged along at least two rows oriented on the blade leaf substantially parallel to the leading edge.
3. The turbine blade as claimed in claim 1 , wherein the outlet ports in the leading edge region lie approximately on a plurality of grid dots of a regular grid.
4. The turbine blade as claimed in claim 1 , wherein angles of incidence of the outlet ducts with respect to the longitudinal direction are approximately identical for the root-side and the tip-side subsections of all the rows of outlet ports.
5. The turbine blade as claimed in claim 4 , wherein the turbine blade has at least three rows of the outlet ports.
6. The turbine blade of claim 1 , wherein the transitional point of a middle row is displaced with respect to two outer rows by the amount of three outlet ports.
7. The turbine blade as claimed in claim 1 , wherein the turbine blade is a guide vane.
8. The turbine blade as claimed in claim 1 , wherein the turbine blade is operatively connected to a gas turbine.
9. A gas turbine, comprising:
a compressor section that compresses air;
a combustion section that combusts a mixture of a fuel and the compressed air; and
a turbine blade adapted to allow a coolant to flow within the turbine blade from an inlet port through a plurality of outlet ducts, and through a series of outlet ports, the turbine blade including
a blade section having a plurality of the outlet ducts and having a leading edge with a leading edge region, the outlet ducts running essentially in the longitudinal direction of the turbine blade and spaced apart from the leading edge, configured with
(i) a plurality of the outlet ports arranged along a plurality of rows that are essentially parallel to the leading edge;
(ii) a plurality of the outlet ducts each coupled to pass fluid through one of the outlet ports and oriented obliquely with respect to the longitudinal direction of the turbine blade so that the coolant flowing out in a root-side subsection of each row possesses a velocity component oriented toward the tip section of the turbine blade and so that the coolant flowing out in a tip-side subsection of each row has a velocity component oriented toward the root section;
(iii) the outlet ducts arranged according to a plurality of transitional points at which the orientation of the outlet ducts in each row changes, with the transition points arranged to be offset relative to one another in the longitudinal direction for two adjacent rows; and
(iv) the transitional points of two outer rows arranged identically with respect to the longitudinal direction.
10. The gas turbine as claimed in claim 9 , wherein the outlet ports in the leading edge region lie approximately on a plurality of grid dots of a regular grid.
11. The gas turbine as claimed in claim 9 , wherein angles of incidence of the outlet ducts with respect to the longitudinal direction are approximately identical for a root-side and a tip-side subsections of all the rows of outlet ports.
12. The gas turbine as claimed in claim 11 , wherein the turbine blade has at least three rows of the outlet ports.
13. The turbine blade as claimed in claim 12 , wherein the transitional point of a middle row is displaced with respect to two outer rows by the amount of three outlet ports.
14. The gas turbine as claimed in claim 9 , wherein the turbine blade is a guide vane.
15. The gas turbine as claimed in claim 9 , wherein the gas turbine includes a plurality of the turbine blades.