TURBINE BLADE AND METHOD FOR MACHINING SAME

Abstract

A turbine blade for a gas turbine, having a blade root and an aerodynamically curved blade airfoil arranged above the blade root. The blade airfoil has a pressure-side and a suction-side blade wall, together extending from a leading edge, that can receive a flow of working medium, to a trailing edge. A multiplicity of cooling air outlet openings are formed on the pressure-side blade wall, which extend upstream from the trailing edge with respect to the flow direction, and through these openings cooling air that is conveyed through the interior of the blade airfoil can exit. At least one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners. At least the lower corner, pointing towards the leading edge, of the cooling air outlet opening forms a relief notch, which projects outwardly from the rectangular shape, with a rounded notch bottom.

Claims

1. A turbine blade for a gas turbine, comprising: a blade root and an aerodynamically curved blade leaf arranged above the blade root, wherein the blade leaf has a pressure-side blade wall and a suction-side blade wall which extend together from a leading edge, onto which a working medium can flow, of the blade leaf to a trailing edge of the blade leaf, wherein a plurality of cooling-air outlet openings are formed on the pressure-side blade wall which, starting from the trailing edge, each extend upstream relative to a direction of flow of a working medium which flows around the blade leaf and through which cooling air routed through an inside of the blade leaf can issue, wherein at least one of the cooling-air outlet openings has an essentially rectangular or trapezoidal shape with rounded corners, wherein at least a lower corner, facing the leading edge, of this at least one cooling-air outlet opening forms a relief notch which projects outward from the rectangular shape and has a rounded notch base.

2. The turbine blade as claimed in claim 1, wherein the relief notch continues a line of a lower edge of the cooling outlet opening, and in that the rounded notch base arranged above the lower edge of the cooling-air outlet opening faces in the direction of the leading edge of the blade leaf.

3. The turbine blade as claimed in claim 1, wherein the relief notch extends, starting from a lower edge of the cooling-air outlet opening, obliquely downward at an obtuse angle, and wherein the rounded notch base arranged below the lower edge of the cooling-air outlet opening faces in the direction of the blade root.

4. The turbine blade as claimed in claim 3, wherein the relief notch widens out, starting from its notch base, in the manner of a chalice.

5. The turbine blade as claimed in claim 1, wherein the at least one cooling-air outlet opening is the lowest cooling-air outlet opening.

6. A method for machining a turbine blade with a blade root and an aerodynamically curved blade leaf, wherein the blade leaf has a pressure-side blade wall and a suction-side blade wall which extend together from a leading edge, onto which a working medium can flow, of the blade leaf to a trailing edge of the blade leaf, wherein a plurality of cooling-air outlet openings are formed on the pressure-side blade wall which, starting from the trailing edge, each extend upstream relative to the direction of a working medium which flows around the blade leaf and through which cooling air routed through the inside of the blade leaf can issue, and wherein one of the cooling-air outlet openings has an essentially rectangular or trapezoidal shape with rounded corners, the method comprising: forming a relief notch which projects outward from the rectangular shape and has a rounded notch base in at least a lower corner, facing the leading edge, of this at least one cooling-air outlet opening in order to produce a turbine blade as claimed in claim 1.

7. The turbine blade as claimed in claim 1, wherein the at least one of the cooling-air outlet openings widens out in the direction in which the cooling air issues.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Further features and advantages of the present invention will become clear with the aid of the following description embodiments with reference to the attached drawings, in which:

[0012] FIG. 1 shows a perspective view of a known turbine blade;

[0013] FIG. 2 shows an enlarged view of the detail labeled with the reference numeral II which shows a cooling-air outlet opening of a known design;

[0014] FIG. 3 shows a perspective view of the turbine blade shown in FIG. 1 after a method according to an embodiment of the present invention has been performed;

[0015] FIG. 4 shows an enlarged view of the detail labeled with the reference numeral IV which shows a cooling-air outlet opening with a relief notch according to a first embodiment of the present invention;

[0016] FIG. 5 shows a perspective view of the turbine blade shown in FIG. 1 after a method according to an embodiment of the present invention has been performed; and

[0017] FIG. 6 shows an enlarged view of the detail labeled with the reference numeral VI which shows a cooling-air outlet opening with a relief notch according to a second embodiment of the present invention.

DETAILED DESCRIPTION OF INVENTION

[0018] The same reference numerals refer below to similar components or component regions.

[0019] FIG. 1 shows a known turbine blade 1 for a gas turbine, which in the present case is a rotor blade. The turbine blade 1 comprises a blade root 2 and an aerodynamically curved blade leaf 3 arranged above the blade root 2. The blade leaf 3 has a pressure-side blade wall 4 and a suction-side blade wall 5 which extend together from a leading edge 7, onto which a working medium can flow in the direction of the arrow 6, of the blade leaf 3 to a trailing edge 8 of the blade leaf 3. A series of cooling-air outlet openings 9, which in the present case are designed as so-called cutback openings, are provided on the pressure-side blade wall 4 along the trailing edge 8. The cooling-air outlet openings 9 each extend upstream relative to the direction of flow of the working medium which flows around the blade leaf 3 and serve to emit cooling air, routed through cooling ducts (not illustrated in detail in the present case) which are present inside the blade leaf 3, essentially axially into a flow duct of the working medium. The cooling-air outlet openings 9 have an essentially rectangular or trapezoidal shape with rounded corners 10 which in the present case each widens out in the direction in which the cooling air issues. In FIG. 1, the shapes of the lowest cooling-air outlet opening 9 and the top three cooling-air outlet openings 9 are considered as rather rectangular, even though they widen out slightly in the direction in which the cooling air issues, whilst all the other cooling-air outlet openings 9 have a rather trapezoidal design.

[0020] FIG. 2 shows an enlarged view of the lowest cooling-air outlet opening 9 which is characterized in that, in the region thereof, the thermal stresses are particularly high or highest during the operation of the turbine blade 1.

[0021] FIGS. 3 and 4 show a turbine blade 1 according to a first embodiment of the present invention which has been produced starting from the turbine blade 1 illustrated in FIGS. 1 and 2.

[0022] The turbine blade 1 shown in FIGS. 3 and 4 differs from the turbine blade 1 shown in FIGS. 1 and 2 only in terms of the embodiment of the lowest cooling-air outlet opening 9, as can be seen by comparing FIGS. 2 and 4. Starting from the cooling-air outlet opening 9 illustrated in FIG. 2, the lower corner 10, facing the leading edge, of the cooling-air outlet opening 9 shown in FIG. 4 has been provided with a relief notch 11 which projects outward from the rectangular shape and has a rounded notch base 12. In the present case, the relief notch 11 continues the line of the lower edge 13 of the cooling outlet opening 9, wherein the notch base 12 arranged above the lower edge 13 of the cooling outlet opening 9 faces in the direction of the leading edge 7 of the blade leaf 3. Such a relief notch 11 can be introduced into the cooling-air outlet opening 9 illustrated in FIG. 2, for example, using a material-removal machining method. It results in a significant reduction in thermal stresses in the region of the cooling-air outlet opening 9 during the operation of the turbine blade 1, which entails an appreciable extension of the lifetime of the turbine blade 1.

[0023] It should be noted that it is of course also alternatively possible to manufacture the turbine blade 1 shown in FIGS. 3 and 4 as part of a new production process. Thus, the turbine blade 1 illustrated in FIGS. 3 and 4 can, for example, be cast and if required thermally and/or mechanically treated thereafter. The cooling-air outlet opening 9 illustrated in FIG. 4 is particularly well suited to being produced by casting as the relief notch 11 does not create any undercut regions which would make the geometry of the casting core or cores unnecessarily complicated.

[0024] FIGS. 5 and 6 show a turbine blade 1 according to a second embodiment of the present invention which has been produced starting from the turbine blade 1 illustrated in FIGS. 1 and 2.

[0025] The turbine blade 1 illustrated in FIGS. 5 and 6 differs from the turbine blade 1 shown in FIGS. 1 and 2 only in terms of the embodiment of the lowest cooling-air outlet opening 9, as can be seen by comparing FIGS. 2 and 6. Starting from the cooling-air outlet opening 9 illustrated in FIG. 2, the lower corner 10, facing the leading edge 7, of the cooling-air outlet opening 9 shown in FIG. 6 has been provided with a relief notch 11 which projects outward from the rectangular shape and has a rounded notch base 12. The relief notch 11 extends, starting from the lower edge 13 of the cooling outlet opening 9, obliquely downward at an obtuse angle. The notch base 12 arranged below the lower edge 13 of the cooling outlet opening 9 faces in the direction of the blade root 2, wherein the relief notch 11 widens out, starting from its notch base 12, in the manner of a chalice.

[0026] The relief notch 11 shown in FIG. 6 can also be introduced into the cooling-air outlet opening 9 illustrated in FIG. 2, for example, using a material-removal machining method. It results in a significant reduction in thermal stresses in the region of the cooling-air outlet opening 9 during the operation of the turbine blade 1, which entails an appreciable extension of the lifetime of the turbine blade 1. With reference to the reduction of stress, the shape of the cooling-air outlet opening 9 or its relief notch 11 illustrated in FIG. 6 is more favorable than the shape shown in FIG. 4. However, it has undercuts which can be produced using casting only at a high cost, when the turbine blade 1 illustrated in FIGS. 5 and 6 is produced as part of a new production process.

[0027] Although the invention has been illustrated and described in detail by the preferred exemplary embodiment, the invention is not limited by the disclosed examples and other variations can be derived therefrom by a person skilled in the art without going beyond the protective scope of the invention. In particular, further cooling-air outlet openings 9 and/or a cooling-air outlet opening 9 other than the lowest one can also be provided with a relief notch 11.