Blade for a turbomachine

Abstract

A blade (10) for a turbomachine is provided. The blade (10) includes an airfoil (16) having at least one thickening (22) on a pressure side (20) of the airfoil (16). The thickening (22) has a region (B) of constant thickness (D). A turbomachine, a compressor and a turbine having stator vanes and/or rotor blades including at least one such blade (10) is also provided.

Claims

1. A blade for a turbomachine, the blade comprising: an airfoil having at least one thickening on a pressure side of the airfoil, wherein the thickening has a region of constant thickness; wherein the thickening has at least one edge region whose thickness decreases continuously from the region of constant thickness to a nominal thickness of the airfoil without the thickening; wherein the edge region surrounds the region of constant thickness in a U-shaped manner.

2. The blade as recited in claim 1 wherein the region of constant thickness has a surface area equal to at least 20% of a total surface area of the thickening.

3. The blade as recited in claim 1 wherein a maximum length of the region of constant thickness is at least 1% or no more than 90% of a maximum total length of the thickness.

4. The blade as recited in claim 1 wherein the thickening or the region of constant thickness is configured in the shape of a rectangle.

5. The blade as recited in claim 4 wherein the rectangle has a long-side to short-side ratio of 10:1.

6. The blade as recited in claim 5 wherein the rectangle has a long-side to short-side ratio of 5:1.

7. The blade as recited in claim 6 wherein the rectangle has a long-side to short-side ratio of 2:1.

8. The blade as recited in claim 1 wherein the thickening is spaced apart from a leading edge or from a trailing edge of the airfoil.

9. The blade as recited in claim 1 wherein the thickness of the region of constant thickness is at least 0.1 mm or 4% of a maximum airfoil thickness or no more than 1 mm or no more than 16% of a maximum airfoil thickness or is equal to no more than a value of a radius of the leading edge or of a radius of the trailing edge of the airfoil.

10. The blade as recited in claim 9 wherein the thickness of the region of constant thickness is no more than 0.5 mm.

11. The blade as recited in claim 1 wherein the thickening extends from a radially outer end portion or end of the airfoil over no more than 20% or no less than 5% of a duct height.

12. The blade as recited in claim 1 wherein an axial extent of the thickening is no more than 70% or no less than 10% of a chord length of the airfoil at a level of the thickening.

13. The blade as recited in claim 12 wherein the axial extent is a maximum axial extent of the thickening.

14. The blade as recited in claim 1 wherein the blade is designed as a stator vane or as a rotor blade.

15. The blade as recited in claim 1 wherein the blade is designed as a variable stator vane.

16. The blade as recited in claim 1 wherein the airfoil is delimited by a radially outer shroud or a radially inner shroud.

17. A turbomachine comprising stator vanes or rotor blades including at least one blade as recited in claim 1.

18. A gas turbine comprising the turbomachine as recited in claim 17.

19. A compressor of a turbomachine, the compressor comprising stator vanes or rotor blades including at least one blade as recited in claim 1.

20. A low-pressure or high-pressure compressor comprising the compressor as recited in claim 19.

21. A turbine of a turbomachine comprising stator vanes or rotor blades including at least one blade as recited in claim 1.

22. A low-pressure or high-pressure turbine comprising the turbine as recited in claim 21.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) In the drawing,

(2) FIG. 1 is a perspective view of an exemplary embodiment of an inventive blade for a turbomachine;

(3) FIG. 2 is a side view of the blade shown in FIG. 1;

(4) FIG. 3 is a cross-sectional view showing the blade in the region of a thickening; and

(5) FIG. 4 shows schematically a trailing edge region of the blade of FIG. 3.

DETAILED DESCRIPTION

(6) FIG. 1 shows, in perspective view, an exemplary embodiment of an inventive blade 10 for a turbomachine with a low- or high-pressure compressor or turbine 100 (shown schematically), for example, for an aircraft engine 1000, such as a gas turbine. FIG. 1 will be described below in conjunction with FIGS. 2 and 3. FIG. 2 shows a side view of the blade 10 shown in FIG. 1, and FIG. 3 shows a cross-sectional view of blade 10 in the region of a thickening 22. In the exemplary embodiment shown, blade 10 includes a blade root 12, a radially inner shroud 14, an airfoil 16, as well as a radially outer shroud 18. On a pressure side 20 of airfoil 16, a thickening 22, which may also be referred to as a patch, is located in the region designated by reference character I. As can be seen, thickening 22 is placed like a postage stamp on pressure side 20 in the radially outer region of airfoil 16 toward a trailing edge 24, and, in the present case, has a substantially rectangular shape having two rounded corners. Thickening 22 has a region B which has a constant thickness D and is surrounded in a U-shaped manner by an edge region R. Thickness D of edge region R decreases continuously from region B of constant thickness D to a nominal thickness of airfoil 16 without thickening 22. In other words, the transition from region B of constant thickness D into the original aerodynamic profile is continuous, so that, outside of thickening 22, airfoil 16 has an aerodynamically optimized blade profile P again. Upwardly; i.e., radially outwardly, thickening 22 has no edge region R, but adjoins radially outer shroud 18.

(7) Thickening 22 is spaced apart from trailing edge 24 by a distance A (FIG. 3). Distance A is approximately equal to a radius HKR (FIG. 4) of trailing edge 24. Therefore, trailing edge 24 itself is not modified by thickening 22. In the present case, the maximum total length or axial extent AE of thickening 22 is approximately two-thirds of chord length S of airfoil 16 at the level of thickening 22, so that a leading edge 26 of airfoil 16 also remains unmodified. In the present case, region B of constant thickness D extends axially over approximately two-thirds of the total length of thickening 22, so that edge region R extends over approximately one-third of the total length of thickening 22.

(8) In the present case, the maximum radial extent RE (FIG. 2) or height of thickening 22 is approximately 15% or less of a duct height H, as measured from outer shroud 18. As shown in FIG. 2, duct height H is determined in the region of trailing edge 24 and is equal to the radial extent or height of airfoil 16 between radial shrouds 14, 18, possibly plus a tolerance. Region B of thickening 22; i.e., the region of constant distance from the original blade profile P, has a thickness D which, in the present case, may be selected between 0.1 mm and a value equal to radius HKR of trailing edge 24.

(9) The parameter values given in the documents for defining measurement conditions for the characterization of specific properties of the subject matter of the present invention are to be considered as within the scope of the present invention, even in the context of deviations, e.g., due to measurement errors, system errors, DIN tolerances, and the like.

LIST OF REFERENCE NUMERALS

(10) 10 blade 12 blade root 14 shroud 16 airfoil 18 shroud 20 pressure side 22 thickening 24 trailing edge 26 leading edge I region B region of constant thickness D thickness R edge region P airfoil profile HKR radius of trailing edge 24 S chord length H duct height RE radial extent AE axial extent