Blade and rotor for a turbomachine and turbomachine

Patent metadata

Field	Value
Publication number	US-10844726-B2
Application number	US-201816163633-A
Country	US
Kind code	B2
Filing date	Oct 18, 2018
Priority date	Oct 23, 2017
Publication date	Nov 24, 2020
Grant date	Nov 24, 2020

Abstract

The invention relates to a blade for a turbomachine, comprising a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element, as well as a blade root for connection of the blade at a main rotor body, wherein the blade comprises a crack-affecting device, which, in the radial direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile. The invention further relates to a rotor for a turbomachine having at least one such blade, a turbomachine having at least one such blade, and/or with such a rotor as well as a method for producing a blade.

First claim

What is claimed is:

1. A blade for a turbomachine, comprising:
a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element; and
a blade root for connection of the blade at a main rotor body;
wherein the blade comprises a crack-affecting device, which, in at least the radial direction and/or in the peripheral direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile,
wherein the crack-affecting device has at least two profile regions at least partially along the pressure side and/or the suction side, and at least one first profile region of the at least two profile regions extends at least partially around the blade from a leading edge of the blade to a trailing edge of the blade, so that a full region, a terminating region, and a region free of the crack-affecting device are formed,
wherein the extension of the full region along the axial extension of the pressure side and/or of the suction side is in a range that corresponds to at least 30% of the extension of the pressure side or of the suction side and/or the extension of the free region along the axial extension of the pressure side and/or of the suction side is in a region that corresponds to at least 5% of the extension of the pressure side or of the suction side.

2. The blade according to claim 1 , wherein, in that the crack-affecting device comprises at least one depression that partially or fully extends around the blade element in the axial direction.

3. The blade according to claim 2 , wherein the depression is arranged radially above a fillet, which is formed in the connecting region of the blade element to the blade root.

4. The blade according to claim 1 , wherein the crack-affecting device comprises a pedestal, wherein the pedestal is arranged between the blade element and the blade root and has a larger cross-sectional thickness than the blade element.

5. The blade according to claim 4 , wherein two mutually adjoining profile regions of the at least two profile regions have a transition angle lying between 0° and 180°.

6. The blade according to claim 4 , wherein, with a maximum blade thickness, the blade is configured with a ratio of the pedestal thickness to the maximum blade thickness that lies in the range of 15 to 150 and the ratio of the pedestal thickness to the maximum blade thickness is present over the entire axial longitudinal extension of at least one of the profile regions.

7. The blade according to claim 4 , wherein, with a maximum peripheral extension of the blade root, the blade is configured with a ratio of the pedestal thickness to the maximum peripheral extension of the blade root that is in the range of 1% to 10%.

8. The blade according to claim 4 , wherein a ratio of pedestal height to maximum blade thickness is in the range of 4 to 60.

9. The blade according to claim 4 , wherein, with a blade chord length, a ratio of the blade chord length to a maximum pedestal height is in the range of 2 to 60.

10. The blade according to claim 4 , wherein the at least two profile regions have different concave and/or convex surfaces, and/or in that the at least two profile regions adjoin each other continuously and/or discontinuously.

11. The blade according to claim 1 , wherein the crack-affecting device comprises at least one rounding, which is arranged radially above a fillet that is formed in the connecting region of the blade element at the blade root.

12. The blade according to claim 1 , wherein the crack-affecting device has continuous transition regions in adjoining blade regions.

13. The blade according to claim 1 , wherein the crack-affecting device comprises at least one depression extending in the axial direction in a radially inner endwall.

14. The blade according to claim 1 , wherein the crack-affecting device comprises depressions extending on both sides of the blade element in the axial direction in the radially inner endwall.

15. The blade according to claim 1 , wherein the blade is coupled to the main rotor body of a blisk.

16. The blade according to claim 1 , wherein the blade is configured and arranged in a turbomachine.

17. A method for producing a blade at a rotor disk from a blank of a blisk, wherein, in a transition region between a root of a blade element and a main rotor body, the blade has a crack-directing device, wherein the crack-directing device has a first profile region adjoining the blade element, wherein the crack-directing device has a second profile region adjoining the rotor disk, wherein the method comprises the following steps:
milling of the first profile region with a first milling tool having a first diameter; and
milling of the second profile region with the first milling tool and/or with a second milling tool having a second diameter differing from the first diameter,
wherein the first profile region extends at least partially around the blade from a leading edge of the blade to a trailing edge of the blade, so that a full region, a terminating region, and a region free of the crack-directing device are formed,
wherein the extension of the full region along the axial extension of the pressure side and/or of the suction side is in a range that corresponds to at least 30% of the extension of the pressure side or of the suction side and/or the extension of the free region along the axial extension of the pressure side and/or of the suction side is in a region that corresponds to at least 5% of the extension of the pressure side or of the suction side.

18. A blade for a turbomachine, comprising,
a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element; and
a blade root for connection of the blade to a main rotor body;
wherein the blade comprises a crack-directing device, which, in at least the radial direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile,
wherein the crack-directing device has at least two profile regions at least partially along the pressure side and/or the suction side, and at least one first profile region of the at least two profile regions extends at least partially around the blade from a leading edge of the blade to a trailing edge of the blade, so that a full region, a terminating region, and a region free of the crack-directing device are formed,
wherein the extension of the full region along the axial extension of the pressure side and/or of the suction side is in a range that corresponds to at least 30% of the extension of the pressure side or of the suction side and/or the extension of the free region along the axial extension of the pressure side and/or of the suction side is in a region that corresponds to at least 5% of the extension of the pressure side or of the suction side.

Assignees

• MTU Aero Engines AG

Inventors

• Horn Wolfgang
• Theurich Daniel
• Becker Martin
• Stettner Axel
• Schuette Wilfried
• Junge Michael
• Hackenberg Hans-Peter
• Halcoussis Alexander
• Wolf Hannes

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• C23C28/042

  including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• B32B7/00

  Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers · CPC title

• F05D2230/313

  by physical vapour deposition · CPC title