Rotor in blisk or bling design of an aircraft engine

Patent metadata

Field	Value
Publication number	US-10408233-B2
Application number	US-201715415359-A
Country	US
Kind code	B2
Filing date	Jan 25, 2017
Priority date	Jan 27, 2016
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

A rotor in BLISK or BLING design of an aircraft engine, comprising: a rotor disc that, at its radially outer area, forms an annulus which delimits the flow channel of the aircraft engine radially inside; and a plurality of rotor blades that project from the annulus; wherein the rotor disc forms a first structure and a second structure which are arranged at a distance from each other in the radial direction, wherein the first structure and the second structure respectively have an arm that protrudes upstream and/or downstream in the axial direction. An arm of the first structure arranged upstream and an arm of the second structure arranged upstream and/or an arm of the first structure arranged downstream and an arm of the second structure arranged downstream are connected to each other by means of a damping element that comprises an elastomer or is formed from an elastomer.

First claim

What is claimed is:

1. A rotor in BLISK or BLING configuration of an aircraft engine, comprising:
a rotor disc or ring including a radially outer area that forms an annulus that delimits a radially interior side of a flow channel of the aircraft engine, and
a plurality of rotor blades that project from the annulus,
wherein the rotor disc or ring includes a first structure and a second structure, which are arranged at a distance from each other in a radial direction, wherein the first structure and the second structure each respectively have an arm that projects at least one chosen from upstream and downstream in an axial direction,
a damping element,
wherein the arm of the first structure is fixedly connected to a first portion of the damping element and the arm of the second structure is fixedly connected to a second portion of the damping element such that the arm of the first structure and the arm of the second structure are connected to each other by the damping element and kinetic energy between the arm of the first structure and the arm of the second structure is dissipated internally of the damping element, with at least one chosen from the arm of the first structure and the arm of the second structure both being arranged upstream, and, the arm of the first structure and the arm of the second structure both being arranged downstream, and
wherein the damping element comprises an elastomer.

2. The rotor according to claim 1 , wherein the damping element forms a ring or ring segments.

3. The rotor according to claim 1 , wherein the damping element is connected to the respective arm in an end area of the respective arm.

4. The rotor according to claim 1 , and further comprising bolted joints mounting the damping element at the respective arm.

5. The rotor according to claim 1 , wherein the damping element is fixedly connected at the respective projecting arm by a form-locking connection.

6. The rotor according to claim 1 , wherein the damping element includes a radially inner end and a radially outer end and is respectively held inside an edging at the radially inner end and at the radially outer end, wherein the edging is mounted at the respective projecting arm.

7. The rotor according to claim 1 , wherein the damping element includes a radially inner end and a radially outer end and forms a bulge at the radially inner end and at the radially outer end, which is held inside a recess in a positive-locking manner at the respective arms of the first and the second structure.

8. The rotor according to claim 1 , wherein the damping element forms meshing outer and inner fingers, wherein the outer fingers are fixedly connected to the arm of the first structure and the inner fingers are fixedly connected to the arm of the second structure, and wherein at least some of the meshing fingers are connected to each other by the elastomer or by a fiber-reinforced elastomer.

9. The rotor according to claim 1 , wherein the elastomer is a rubber.

10. The rotor according to claim 1 , wherein the elastomer is a viscoelastic material.

11. The rotor according to claim 1 , wherein the elastomer is reinforced with a fiber-reinforced material at least in partial areas.

12. The rotor according to claim 1 , wherein the damping element includes multiple material layers, wherein at least one of the multiple material layers includes the elastomer.

13. The rotor according to claim 1 , wherein the first structure is formed by the annulus of the rotor disc or ring.

14. The rotor according to claim 1 , wherein the second structure is formed by a connection structure.

15. The rotor according to claim 14 , wherein the arm of the connection structure projects downstream in the axial direction and is configured to be coupled to at least one chosen from a high-pressure shaft, a medium-pressure shaft, and a low-pressure shaft of the aircraft engine.

16. The rotor according to claim 14 , wherein the rotor disc or ring is a fan in BLISK configuration, wherein the plurality of rotor blades are fan blades and the rotor disc is a fan disc, and wherein the arm of the connection structure projects upstream in the axial direction and is configured to be connected to a nose cone of the fan.

17. The rotor according claim 1 , wherein the damping element has a modulus of elasticity that is smaller than a modulus of elasticity of the material of the rotor disc or ring by at least a factor of 10.

18. An aircraft engine including the rotor according to claim 1 .

19. The rotor according claim 1 , wherein the damping element has a modulus of elasticity that is smaller than a modulus of elasticity of the material of the rotor disc or ring by at least a factor of 50.

20. A fan in BLISK configuration of an aircraft engine, comprising:
a fan disc,
a plurality of fan blades that are connected to the fan disc,
wherein the fan disc forms an annulus that delimits a radially interior side of a flow channel of the aircraft engine, wherein the annulus includes at least one chosen from an arm that projects upstream in an axial direction and an arm that projects downstream in the axial direction,
wherein the fan disc forms a connection structure that includes at least one chosen from an arm that projects upstream in the axial direction and an arm that projects downstream in the axial direction,
wherein the arm of the annulus and the arm of the connection structure are arranged at a distance from each other in a radial direction,
a damping element,
wherein the arm of the annulus is fixedly connected to a first portion of the damping element and the arm of the connection structure is fixedly connected to a second portion of the damping element such that the arm of the annulus and the arm of the connection structure are connected to each other by the damping element and kinetic energy between the arm of the annulus and the arm of the connection structure is dissipated internally of the damping element, with at least one chosen from the arm of the annulus and the arm of the connection structure both being arranged upstream, and, the arm of the annulus and the arm of the connection structure both being arranged downstream, and
wherein the damping element comprises an elastomer.

21. A rotor in BLISK or BLING configuration of an aircraft engine, comprising:
a rotor disc or ring including a radially outer area that forms an annulus that delimits a radially interior side of a flow channel of the aircraft engine, and
a plurality of rotor blades that project from the annulus,
wherein the rotor disc or ring includes a first structure and a second structure, which are arranged at a distance from each other in a radial direction, wherein the first structure and the second structure each respectively have an arm that projects at least one chosen from upstream and downstream in an axial direction,
a damping element,
wherein the arm of the first structure and the arm of the second structure are connected to each other by the damping element, and with at least one chosen from the arm of the first structure and the arm of the second structure both being arranged upstream, and, the arm of the first structure and the arm of the second structure both being arranged downstream, and
wherein the damping element comprises an elastomer,
wherein the damping element includes meshing outer and inner fingers, wherein one of the inner fingers and the outer fingers are connected to the arm of the first structure and the other of the inner fingers and the outer fingers are connect

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Klauke Thomas

Classifications

• F01D5/34

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title

• F01D5/10 Primary

  Anti- vibration means {(specially adapted for radial flow machines or engines F01D5/04)} · CPC title

• F05D2300/501

  Elasticity · CPC title

• F05D2300/43

  Synthetic polymers, e.g. plastics; Rubber · CPC title

• F04D29/668 Primary

  damping or preventing mechanical vibrations · CPC title