Clamping composite assembly

Patent metadata

Field	Value
Publication number	US-12553347-B2
Application number	US-202519058724-A
Country	US
Kind code	B2
Filing date	Feb 20, 2025
Priority date	Feb 22, 2024
Publication date	Feb 17, 2026
Grant date	Feb 17, 2026

Abstract

The invention relates to a clamping composite assembly, wherein the clamping assembly comprises a first component with a first flange with first radial webs and first recesses between every two first webs adjacent in the circumferential direction; a second component with a second flange with second radial webs and second recesses between every two second webs adjacent in the circumferential direction; and a third component with a third flange; the first and second components are designed such that in an initial installation position the first and second components have a first angular position relative to one another around an installation and/or longitudinal axis of the clamping composite and by axially displacing the first and second components relative to one another parallel to this axis the second webs can be guided through the first recesses and the first webs can be guided through the second recesses in the axial direction.

First claim

What is claimed is:

1 . A clamping composite rotor for a gas turbine, comprising:
a first component with a first flange having first radial webs and first recesses between each of two neighboring first webs in the circumferential direction; a second component with a second flange having second radial webs and second recesses between each of two neighboring second webs in the circumferential direction; and a third component having a third flange; wherein the first component is a cone, and the second component is a configured and arranged to support rotating blades of the gas turbine and the third component is configured and arranged to support rotating blades of the gas turbine; wherein the first and the second component are configured and arranged that, in an initial installation position, the first and second component form a first angular position relative to each other around an installation and/or longitudinal rotational axis of the clamping composite rotor and by an axial displacement of the first and second components relative to each other and parallel to this axis; wherein the second webs pass through the first recesses and the first webs pass through the second recesses in the axial direction; wherein, in the installed clamping composite assembly, the first and second components have a second angular position relative to one another around the installation and/or longitudinal rotational axis of the clamping composite rotor, in which the second webs at least partially overlap the first webs in the circumferential direction; and the second webs are arranged in the axial direction between the first webs and the third flange and are clamped by a separate tension rod device of the rotor; wherein the tension rod device passes through the first component, second component and third component in the axial direction and is supported in the axial direction directly or indirectly on one of the sides of the first component facing away from the third component.

2 . The clamping composite rotor according to claim 1 , wherein the first recesses open radially outwards and the second recesses open radially inwards and/or the second component overlaps the first webs in the axial direction.

3 . The clamping composite rotor according to claim 1 , wherein a maximum outer diameter of the first flange is larger than a minimum inner diameter of a constriction of the second component, wherein the first flange is arranged in the axial direction between the constriction and the second flange and/or is at a distance from the constriction.

4 . The clamping composite rotor according to claim 1 , wherein axial webs engage in the first and/or second recesses.

5 . The clamping composite rotor according to claim 4 , wherein at least two of the axial webs are connected to one another or are integrally formed and/or arranged on the third or an additional component.

6 . The clamping composite rotor according to claim 1 , wherein there is a zero-play radial fit between the second flange and the first component and/or between the first flange and the second component.

7 . The clamping composite rotor according to claim 1 , wherein a fourth component with a fourth radial flange is arranged in the axial direction on a side of the third flange facing away from the first and/or second flange, wherein the first webs, second webs, the third flange and the fourth flange are clamped by the tension rod device.

8 . The clamping composite rotor according to claim 1 , wherein the third component secures the second component in a radially form-fitting manner with at least one outer axial projection being arranged on the third flange, which surrounds the second flange radially outward.

9 . The clamping composite rotor according to claim 1 , wherein the clamping composite rotor is configured and arranged in a gas turbine rotor, a turbine, compressor assembly and/or an aircraft engine.

10 . A method for installing the clamping composite rotor of claim 1 , comprising the steps of:
arranging the first and second components in the initial installation position; displacing the first and second components relative to each other parallel to the installation and/or longitudinal axis of the clamping assembly, so that the second webs are guided through the first recesses and the first webs through the second recesses in the axial direction; rotating the first and second components relative to each other around this axis into the second angular position; arranging the third component; and clamping the second webs in the axial direction between the first webs and the third flange by the tension rod device.

11 . The method according to claim 10 , wherein a fourth component is arranged and then the first webs, second webs, the third flange and the fourth flange are clamped by the tension rod device.

12 . A method for dismantling a clamping composite rotor according to claim 1 , comprising the steps of:
loosening a clamping of the second webs in the axial direction between the first webs and the third flange by the tension rod device; removing the third component; rotating the first and second components relative to each other around the assembly axis and/or longitudinal axis of the clamping assembly into the first angular position; displacing the first and second components relative to each other parallel to this axis, so that the second webs are passed through the first recesses and the first webs are passed through the second recesses in the axial direction; and separating the first and second components from each other.

Assignees

• MTU Aero Engines AG

Inventors

• Nachtigall Hermann

Classifications

• F01D5/025

  Fixing blade carrying members on shafts (attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00) · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F05D2260/33

  with a bayonet coupling · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title