Turbomachine rotor blade

Patent metadata

Field	Value
Publication number	US-9951631-B2
Application number	US-201414316035-A
Country	US
Kind code	B2
Filing date	Jun 26, 2014
Priority date	Jun 27, 2013
Publication date	Apr 24, 2018
Grant date	Apr 24, 2018

Abstract

A rotor blade for a turbomachine, including an airfoil ( 1 ) for flow deflection, a blade root ( 2 ) for attachment to a rotor of the turbomachine, an inner platform ( 3 ) between the airfoil and the blade root, and at least one pocket ( 4, 5 ) defined by two axially spaced walls ( 4.1, 4.2; 5.1, 5.2 ) extending from the side of the platform opposite the airfoil toward the blade root. A first ( 4.1, 5.1 ) of these walls has an outer side ( 4.1 A, 5.1 A) that faces away from the pocket and, in at least one cross section perpendicular to a radial longitudinal axis of the rotor blade, slopes outwardly.

First claim

What is claimed is:

1. A rotor blade for a turbomachine, comprising:
an airfoil for flow deflection;
a blade root for attachment to a rotor of the turbomachine;
an inner platform between the airfoil and the blade root; and
two axially spaced walls defining at least one pocket, the two axially spaced walls extending from the side of the platform opposite the airfoil toward the blade root;
the rotor blade being configured such that in the mounted state, facing pockets of adjacent rotor blades as well as the inner platforms, contact each other, so that their walls form two at least substantially closed, axially spaced sealing rings or flanges between the rotor and a ring defined by the inner platform,
a first of the walls having an outer side facing away from the pocket and, in at least one cross section perpendicular to a radial longitudinal axis of the rotor blade, slopes outwardly as it extends in a circumferential direction, so that the outer side of the first wall diverges in an axial direction with increasing distance as it extends in the circumferential direction from the rotor blade toward a rotor blade that is circumferentially adjacent in the mounted state.

2. The rotor blade as recited in claim 1 wherein end faces of the axially spaced walls of the adjacent rotor blades contact each other in the mounted state.

3. The rotor blade as recited in claim 1 wherein a second of the walls has an outer side at least substantially oriented in the circumferential direction.

4. The rotor blade as recited in claim 1 wherein a second of the walls has an outer side facing away from the pocket and, in at least one cross section perpendicular to the radial longitudinal axis of the rotor blade, slopes outwardly.

5. The rotor blade as recited in claim 1 wherein at least one outer side facing away from the pocket is at least substantially parallel to a pocket-facing inner side of the wall.

6. The rotor blade as recited in claim 1 wherein at least one outwardly sloping outer side facing away from the pocket is curved or at least substantially straight in at least one cross section perpendicular to the radial longitudinal axis of the rotor blade.

7. The rotor blade as recited in claim 1 wherein the first or second wall is curved axially inwardly toward the pocket, as viewed in a radial direction.

8. The rotor blade as recited in claim 1 wherein the pocket is formed by casting.

9. The rotor blade as recited in claim 1 wherein the pocket is formed by forging.

10. The rotor blade as recited in claim 1 further comprising two further axially spaced walls defining a further pocket located opposite in a circumferential direction extending from the side of the platform opposite the airfoil toward the blade root, at least one first of the further walls having a further outer side facing away from the pocket and, in at least one cross section perpendicular to a radial longitudinal axis of the rotor blade, sloping outwardly.

11. A turbomachine comprising: a rotor and at least one rotor blade as recited in claim 1 , the at least one rotor blade being attached to the rotor.

12. The turbomachine as recited in claim 11 wherein the rotor blade is attached to the rotor in a form-locking or detachable manner.

13. A gas turbine comprising the turbomachine as recited in claim 12 .

Assignees

• MTU Aero Engines AG

Inventors

• Skura Krzysztof
• Kozdras Marcin
• Sosnowka Lukasz
• Feldmann Manfred
• Schill Manfred

Classifications

• F05D2250/712

  concave · CPC title

• F05D2250/292

  tapered · CPC title

• F01D5/3007 Primary

  of axial insertion type · CPC title

• F05D2250/38

  angled, e.g. sweep angle · CPC title