Rotor blade arrangement for a turbo machine

Patent metadata

Field	Value
Publication number	US-9371733-B2
Application number	US-201113885311-A
Country	US
Kind code	B2
Filing date	Nov 5, 2011
Priority date	Nov 16, 2010
Publication date	Jun 21, 2016
Grant date	Jun 21, 2016

Abstract

In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade ( 1 ), the moving blade system having at least one cavity ( 3 ) in which at least one tuning mass ( 2 ) is movably situated, the tuning mass and/or the cavity is/are adapted in such a way that the tuning mass rests against an inner wall ( 3.1 ) of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine.

First claim

What is claimed is:

1. A moving blade system for a turbomachine, comprising:
at least one moving blade; and
at least one tuning mass movably situated in at least one cavity of the moving blade system,
at least one of the tuning mass and the cavity being adapted so that the tuning mass rests against an inner wall of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine,
wherein one of the first and second predefined operating states is proximate to a natural frequency of the moving blade system having a tuning mass resting against the inner wall or positioned at a distance therefrom, wherein the proximate operating state is between 0.9 to 0.99 times of the natural frequency of the moving blade.

2. The moving blade system as recited in claim 1 wherein the adaptation is of at least one of the following: a mass, shape, surface, center of gravity or inertia tensor of the tuning mass, a shape of the inner wall, and a surface of the inner wall.

3. The moving blade system as recited in claim 1 wherein the tuning mass is elastically supported in the cavity, the tuning mass and its elastic support being adapted in such a way that the tuning mass rests against the inner wall in the first operating state and is at least temporarily positioned a distance from the inner wall in the second operating state.

4. The moving blade system as recited in claim 1 wherein at least one of the tuning mass and the cavity is adapted in such a way that the tuning mass carries out knocks against the inner wall in the predefined operating state of the turbomachine.

5. The moving blade system as recited in claim 1 wherein the at least one moving blade includes a plurality of moving blades and the moving bade system includes an outer ring, the plurality of blades, and an inner ring, and wherein the cavity is provided in or on one of the inner ring and the outer ring.

6. The moving blade system as recited in claim 5 wherein the at least one moving blade includes a plurality of moving blades, and wherein the cavity is under a platform of one of the moving blades of the moving blade system.

7. The moving blade system as recited in claim 1 wherein the at least one moving blade includes a plurality of moving blades, each having a corresponding vane, and wherein the cavity is provided in one of the vanes.

8. A turbomachine comprising at least one moving blade system as recited in claim 1 .

9. A gas turbine comprising the turbomachine as recited in claim 8 .

10. A method for designing the moving blade system as recited in claim 1 wherein at least one of the at least one tuning mass and the cavity accommodating the tuning mass is adapted in such a way that the tuning mass rests against the inner wall in the predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in the second operating state.

11. A method for operating the moving blade system as recited in claim 1 comprising:
resting the tuning mass against the inner wall in a first operating state; and
at least temporarily moving the tuning mass away from the inner wall in the second operating state.

Assignees

• Hartung Andreas
• Mtu Aero Engines Gmbh

Inventors

• Hartung Andreas

Classifications

• Y10T29/49336

  Blade making · CPC title

• F01D5/16 Primary

  for counteracting blade vibration · CPC title

• F01D5/12 Primary

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• F05D2250/241

  spherical · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic