Balancing body for a continuous blade arrangement
AssigneeMTU Aero Engines AG
InventorsManfred Feldmann, Andreas Holzel, Amelia Frodyma
Life of this patent
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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.
Claims14
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 comprises a first stop (11) for form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder (6;
- 7) of the ring.
A continuous blade arrangement of a compressor or turbine stage of a gas turbine, comprising:
- a radially outer or inner ring (4, 5) with at least one axial shoulder (6, 7) having a balancing body (1) having a first stop (11) for form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder (6;
- 7) of the ring, which is attached in form-fitting manner to the shoulder by means of at least one stop (11, 14) in one peripheral direction.
A method for attaching a balancing body (1) to the ring (4, 5) of a continuous blade arrangement, comprising the steps of:
- providing 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 includes at least one stop (11, 14) for form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder (6;
- 7) of the ring;
- bringing the at least one stop (11, 14) plastically into alignment with an axial shoulder (6;
- 7) of the ring for form-fitting attachment of the balancing body to the shoulder in one peripheral direction.
A method for detaching a balancing body (1) from the ring (4, 5) of a continuous blade arrangement, comprising the steps of:
- providing 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 includes a least one stop (11, 14) for form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder (6;
- 7) of the ring;
- and
- bringing the at least one stop (11, 14) plastically out of alignment for the form-fitting attachment of the balancing body to an axial shoulder in one peripheral direction (6;
- 7) of the ring with the shoulder.
Dependencies are inferred from the claim text.