Bearing element and turbomachine with a bearing element

Patent metadata

Field	Value
Publication number	US-2017363100-A1
Application number	US-201715625743-A
Country	US
Kind code	A1
Filing date	Jun 16, 2017
Priority date	Jun 20, 2016
Publication date	Dec 21, 2017
Grant date	—

Abstract

A bearing element for at least one adjustable guide vane of a turbomachine, in particular an aircraft engine, is provided. The bearing element comprising a porous matrix made of carbon and/or graphite and at least one metallic phase or a metal salt that is at least partially arranged inside the pores of the matrix, so that what results is a metal-infiltrated or a metal-salt-infiltrated material.

First claim

1 . A bearing element for at least one adjustable guide vane of a turbomachine, in particular an aircraft engine, comprising a porous matrix made of carbon and/or graphite, as well as at least one metallic phase or a metal salt that is arranged at least partially inside the pores of the matrix, so that what results is a metal-infiltrated or a metal-salt-infiltrated material.

2 . The bearing element according to claim 1 , wherein it consists only of the porous matrix of carbon and/or graphite and the at least one metallic phase or the metal salt.

3 . The bearing element according to claim 1 , wherein a contact surface of the at least one adjustable guide vane has neither a coating nor a fitted bushing.

4 . The bearing element according to claim 3 , wherein the contact surface is embodied so as to be self-lubricating.

5 . The bearing element according to claim 1 , wherein it is formed as an inner cover band for a blade ring, or that it is connected to the inner cover band.

6 . The bearing element according to claim 1 , further comprising an inflow surface for a seal, in particular a seal with sealing lips or a labyrinth seal.

7 . The bearing element according to claim 3 , further comprising an inflow surface for a seal, in particular a seal with sealing lips or a labyrinth seal, wherein the contact surface for the at least one guide vane and the inflow surface for a seal are arranged at substantially opposite sides of the bearing element.

8 . The bearing element according to claim 1 , wherein the at least one metallic phase comprises a non-ferrous metal, in particular copper, silver or antimony, or a light metal, in particular aluminum, non-heat-treated aluminum or magnesium, or a metal salt, in particular a metallic phosphate, or that it comprises an alloy of these materials.

9 . The bearing element according to claim 1 , wherein the matrix of carbon and/or graphite at least in a partial area has a closed pore structure or an interconnected structure with open pores.

10 . The bearing element according to claim 1 , wherein the ratio of the thermal expansion coefficients of the matrix and of the at least one metallic phase is smaller than 0.6.

11 . The bearing element according to claim 1 , wherein the metallic phase or the metal salt in the matrix is distributed inside the bearing element according to the load conditions, in particular in an inhomogeneous manner.

12 . The bearing element according to claim 1 , wherein it is embodied as a section of a ring or as a full ring with bearings for the shaft ends of the adjustable guide vane.

13 . The bearing element according to claim 1 , which can be manufactured by means of a liquid infiltration process, in particular a spontaneous or a forced liquid infiltration process.

14 . A method for manufacturing a bearing element according to claim 1 , wherein
a) a matrix of carbon and/of graphite being arranged in an infiltration device, and b) a liquid phase with a metal or a metal salt being inserted into the matrix, in particular as an external pressure or an external force is being exerted.

15 . A turbomachine, in particular an aircraft engine with at least one bearing element according to the claim 1 .

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Ulrichsohn Bjorn
• Schruefer Susanne
• Schreiber Karl

Classifications

• F16C33/16

  Sliding surface consisting mainly of graphite · CPC title

• C10N2040/02

  Bearings · CPC title

• F16C2360/23

  Gas turbine engines · CPC title

• F01D11/02

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F16C2206/06

  Composite carbon material, e.g. carbon fibre reinforced carbon (C/C) · CPC title