Rotor blade for a turbomachine and turbomachine

Patent metadata

Field	Value
Publication number	US-9482099-B2
Application number	US-201113522258-A
Country	US
Kind code	B2
Filing date	Jan 14, 2011
Priority date	Jan 16, 2010
Publication date	Nov 1, 2016
Grant date	Nov 1, 2016

Abstract

The invention relates to a blade ( 2 ) of a turbomachine, in particular a rotor blade of a gas turbine, which has a variable transition radius (Rv 1 ) in the vicinity of at least one platform overhang ( 16 ), and to a turbomachine having at least one such blade ( 2 ).

First claim

The invention claimed is:

1. A rotor blade for a turbomachine, comprising:
a blade root;
a blade pan;
a platform, wherein the platform is disposed between the blade root and the blade pan; and
a platform overhang disposed on the platform, wherein the platform overhang has a variable transition radius in a transition area to the platform;
wherein the variable transition radius has a step-like configuration.

2. A rotor blade for a turbomachine, comprising:
a blade root;
a blade pan;
a platform, wherein the platform is disposed between the blade root and the blade pan;
a first platform overhang disposed on the platform; and
a second platform overhang disposed on the platform;
wherein the first platform overhang has a first variable transition radius in a first transition area to the platform;
wherein the second platform overhang has a second variable transition radius in a second transition area to the platform;
wherein one of the transition areas is divided into a first end section with a small transition radius, a second end section with a large transition radius, and an intermediate section with a transition radius that increases from the first end section to the second end section; and
wherein the second variable transition radius of the second platform overhang includes a constant transition radius.

3. The rotor blade according to claim 2 , wherein at least one of the variable transition radii is disposed on a blade-root side of the platform.

4. The rotor blade according to claim 2 , wherein at least one of the variable transition radii, in a region of the platform with a high load, is smaller than in a region of the platform with a low load.

5. The rotor blade according to claim 2 , wherein the intermediate section transition radius increases in a direction of rotation of the rotor blade.

6. The rotor blade according to claim 2 , wherein the first variable transition radius is a minimum in a region of the platform with a high load.

7. The rotor blade according to claim 2 , wherein the first variable transition radius is a maximum in a region of the platform with a low load.

8. The rotor blade according to claim 2 , wherein the small and large transition radii are constant.

9. The rotor blade according to claim 2 , wherein a blade pan side transition area between the blade pan and one of the first and second platform overhangs has a constant transition radius.

10. The rotor blade according to claim 2 , wherein the at least one of the transition areas has plural variable transition radii.

11. The rotor blade according to claim 2 , further comprising a further variable transition radius disposed on a blade root side of one of the first and second platform overhangs.

12. The rotor blade according to claim 2 , wherein the small transition radius is in a region of the platform opposed from a direction of rotation of the rotor blade.

13. The rotor blade according to claim 2 , wherein the large transition radius is in a region of the platform in a direction of rotation of the rotor blade.

14. A turbomachine, comprising:
a rotor blade according to claim 2 .

15. The turbomachine according to claim 14 , wherein the turbomachine is a gas turbine aircraft engine.

Assignees

• Schlemmer Markus
• Pikul Bartlomiej
• Mtu Aero Engines Gmbh

Inventors

• Schlemmer Markus
• Pikul Bartlomiej

Classifications

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2250/20

  Three-dimensional · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/16 Primary

  for counteracting blade vibration · CPC title