Balancing body for a continuous blade arrangement

Patent metadata

Field	Value
Publication number	US-9816379-B2
Application number	US-201414219726-A
Country	US
Kind code	B2
Filing date	Mar 19, 2014
Priority date	May 27, 2013
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

The present invention relates to a balancing body ( 1 ) for fastening to a ring ( 4, 5 ) of a continuous blade arrangement of a compressor or turbine stage of a gas turbine, wherein the balancing body has a first stop ( 11 ) for the form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder ( 6; 7 ) of the ring.

First claim

What is claimed is:

1. A balancing body for fastening to a ring of a continuous blade arrangement of a compressor or turbine stage of a gas turbine, wherein the balancing body comprises a first stop for form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder of the ring wherein the first axial shoulder is an axial material projection from an outer shroud of the ring and at least one undercut section for the form-fitting attachment of the balancing body to the ring in a radial direction;
wherein the balancing body is distanced from adjacent rotating blades of the continuous blade arrangement.

2. The balancing body according to claim 1 , further comprising a second stop for form-fitting attachment of the balancing body in an opposite direction to a second axial shoulder of the ring in an opposite peripheral direction, the second axial shoulder projecting is an axial material projection from an outer shroud of the ring.

3. The balancing body according to claim 1 , further comprising:
a first radial flange and a second radial flange, axially distanced from the first flange and connected to it by an axial web for form-fitting attachment of the balancing body to the ring in an axial direction.

4. The balancing body according to the claim 3 , wherein, for the form-fitting attachment of the balancing body, the first stop and the second stop, which are disposed on the radial flanges in one peripheral direction, are formed integrally with the radial flanges, and/or that the radial flanges converge toward the ring, viewed in one direction of rotation (R).

5. The balancing body according to claim 1 , wherein, for the form-fitting attachment of the balancing body in an axial direction, the undercut section, which is disposed on the radial flanges, and/or the first stop and the second stop for the form-fitting attachment of the balancing body in one peripheral direction and formed integrally with the radial flanges.

6. The balancing body according to claim 1 , wherein the undercut section for engaging under the first axial shoulder and the second axial shoulder of the ring is configured and arranged for the form-fitting attachment of the balancing body in one peripheral direction.

7. The balancing body according to claim 1 , wherein the first stop for the form-fitting attachment of the balancing body in one peripheral direction extends web-like in a radial direction.

8. The balancing body according to claim 1 , wherein, for the form-fitting attachment of the balancing body in the one peripheral direction (R), the first stop is brought into alignment with the first axial shoulder by means of plastic deformation.

9. A continuous blade arrangement of a compressor or turbine stage of a gas turbine, comprising:
a radially outer or inner ring with at least one axial shoulder having a balancing body having a first stop for form-fitting attachment of the balancing body in the one peripheral direction (R) to a first axial shoulder of the ring and at least one undercut section for the form-fitting attachment of the balancing body to the ring in a radial direction, which is attached in form-fitting manner to the shoulder by means of at least one stop in one peripheral direction, wherein the first axial shoulder is an axial material projection from an outer shroud of the radially outer or inner ring;
wherein the balancing body is distanced from adjacent rotating blades of the continuous blade arrangement.

10. The continuous blade arrangement according to claim 9 , wherein the at least one axial shoulder extends axially away from a rotating blade arrangement of the continuous blade arrangement or toward the rotating blade arrangement.

11. A method for attaching a balancing body to the ring of a continuous blade arrangement, comprising the steps of:
providing a balancing body for fastening to a ring of a continuous blade arrangement of a compressor or turbine stage of a gas turbine, wherein the balancing body includes at least one stop for form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder of the ring and at least one undercut section for the form-fitting attachment of the balancing body to the ring in a radial direction, where the first axial shoulder is an axial material projection from an outer shroud of the ring;
bringing the at least one stop plastically into alignment with the first axial shoulder of the ring for form-fitting attachment of the balancing body to the first axial shoulder in the one peripheral direction;
wherein the balancing body is distanced from adjacent rotating blades of the continuous blade arrangement.

12. A method for detaching a balancing body from the ring of a continuous blade arrangement, comprising the steps of:
providing a balancing body for fastening to a ring of a continuous blade arrangement of a compressor or turbine stage of a gas turbine, wherein the balancing body includes a least one stop for form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder of the ring and at least one undercut section for the form-fitting attachment of the balancing body to the ring in a radial direction, where the first axial shoulder is an axial material projection from an outer shroud of the ring; and
bringing the at least one stop plastically out of alignment for the form-fitting attachment of the balancing body to the first axial shoulder in the one peripheral direction;
wherein the balancing body is distanced from adjacent rotating blades of the continuous blade arrangement.

Assignees

• MTU Aero Engines AG

Inventors

• Feldmann Manfred
• Holzel Andreas
• Frodyma Amelia

Classifications

• F05D2230/60

  Assembly methods · CPC title

• F01D5/027 Primary

  Arrangements for balancing (for balancing rotating bodies in general F16F15/32; for compensating imbalance G01M1/36) · CPC title

• Y10T29/4932

  Turbomachine making · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• Y10T29/49245

  Vane type or other rotary, e.g., fan · CPC title