Aerofoil assembly and a method of manufacturing an aerofoil assembly

• US 8,656,589 B2
• Filed: 12/29/2006
• Issued: 02/25/2014
• Est. Priority Date: 01/31/2006
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Kurt-Elli, Hilmi
• Primary Examiner(s): Bryant, David
• Assistant Examiner(s): BESLER, CHRISTOPHER JAMES
• Application Number:
  US11/647,441
• Publication Number:
  US 20070175032A1
• Time in Patent Office: 2,615 Days
• Field of Search: 298/892, 298/892.3, 294/020.6, 294/021.8, 294/02, 29/6, 294/020.9, 294/021.1, 294/022.1
• US Class Current: 29/889.2
• CPC Class Codes: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F01D 5/34 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 Class Codes: F04D 29/023 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/38 Blades for axial flow compressors F04D29/324
• CPC Class Codes: F04D 29/666 by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
• CPC Class Codes: F05D 2230/312 by plasma spraying
• CPC Class Codes: F05D 2230/313 by physical vapour deposition
• CPC Class Codes: F05D 2230/314 by chemical vapour deposition
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment manufacture with deposition of material F05D2230/30
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: F05D 2300/125 Magnesium
• CPC Class Codes: F05D 2300/2118 Zirconium oxides
• CPC Class Codes: F05D 2300/611 Coating
• CPC Class Codes: Y10T 29/4932 Turbomachine making
• CPC Class Codes: Y10T 29/49321 Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
• CPC Class Codes: Y10T 29/49325 Shaping integrally bladed rotor
• CPC Class Codes: Y10T 29/49746 by applying fluent material, e.g., coating, casting

Abstract

An aerofoil assembly, for example a bladed rotor assembly (40B) comprises a rotor (42) carrying a plurality of rotor blades (44), at least one of the rotor blades (44) having a coating (46) on the surface of the rotor blade (44). At least one of the rotor blades (44) has a coating (46) having a different thickness, a different area of contact with the surface of the rotor blade (44), a different position of contact on the surface of the rotor blade (44), a different shape of contact on the surface of the rotor blade (44) and/or a different composition compared to at least one of the other rotor blades (44). The coating (46) is applied in a non-uniform manner to reduce the vibration level of the rotor blade (44), or rotor blades (44), with the highest vibration response for a given excitation by changing the bladed rotor assembly (40B) mode shapes and the relative vibration of the rotor blades (44).

Claims

1. A method of manufacturing an aerofoil assembly comprising the steps of:

(a) forming a structure carrying a plurality of aerofoils, the structure and aerofoils forming the aerofoil assembly, the aerofoils having physical differences,

(b) exciting and measuring a vibration behaviour of each aerofoil,

(c) exciting and measuring a vibration behaviour of the aerofoil assembly,

(d) analysing the vibration behaviour of the aerofoil assembly and the vibration behaviour of the aerofoils,

(e) determining where to add material to, or remove material from, a surface of at least one of the aerofoils of the aerofoil assembly in a non-uniform manner to reduce a vibration level of the aerofoil, or aerofoils, with the highest vibration for the given excitation by changing aerofoil assembly mode shapes and a relative vibration of the aerofoils in the aerofoil assembly so that a collective vibration behaviour of the aerofoil assembly of vibrationally interacting aerofoils is improved, and

(f) adding material to, or removing material from, the surface of the at least one of the aerofoils of the aerofoil assembly in the determined non-uniform manner to reduce the vibration level of the aerofoil, or aerofoils, with the highest vibration for the given excitation by changing the aerofoil assembly mode shapes and the relative vibration of the aerofoils in the aerofoil assembly so that the collective vibration behaviour of the aerofoil assembly of vibrationally interacting aerofoils is improved,

wherein step (b) follows step (a), step (c) follows step (a), step (d) follows steps (b) and (c), step (e) follows step (d), and step (f) follows step (e).

2. A method as claimed in claim 1 further comprising adding material on, or removing material from, the surface of at least one of the aerofoils differently compared to at least one of the other aerofoils.

3. A method as claimed in claim 1, wherein

the forming of a structure carrying a plurality of aerofoils includes forming a stator carrying a plurality of stator vanes, the stator vanes having physical differences;

and

adding material to, or removing material from, the surface of at least one of the aerofoils of the aerofoil assembly includes adding material on, or removing material from, the surface of at least one of the stator vanes differently compared to at least one of the other stator vanes.

4. A method as claimed in claim 1, wherein

the forming of a structure carrying a plurality of aerofoils includes forming a rotor carrying a plurality of rotor blades, the rotor blades having physical differences;

and

adding material to, or removing material from, the surface of at least one of the aerofoils of the aerofoil assembly includes adding material on, or removing material from, the surface of at least one of the rotor blades differently compared to at least one of the other rotor blades.

5. A method as claimed in claim 4 further comprising applying a coating on the surface of at least one of the rotor blades, applying the coating on the surface of the at least one of the rotor blades such that the coating has a different thickness, a different area of contact with the surface of the rotor blade, a different position of contact on the surface of the rotor blade, a different shape of contact on the surface of the rotor blade and/or a different composition compared to at least one of the other rotor blades.

6. A method as claimed in claim 5 further comprising applying the coating to a plurality of the rotor blades.

7. A method as claimed in claim 6 further comprising applying the coating to all of the rotor blades.

8. A method as claimed in claim 5 further comprising applying the coating to all of the surfaces of all of the rotor blades and removing coating from at least one of the rotor blades.

9. A method as claimed in claim 5 further comprising applying the coating on a surface of a plurality of the rotor blades, the coating on the plurality of rotor blades having a different thickness, a different area of contact with the surface of the rotor blade, a different position of contact on the surface of the rotor blade, a different shape of contact on the surface of the rotor blade and/or a different composition compared to at least one of the other rotor blades.

10. A method as claimed in claim 9 further comprising applying the coating on the surface of the plurality of the rotor blades, the coating on the plurality of rotor blades having a different thickness, a different area of contact with the surface of the rotor blade, a different position of contact on the surface of the rotor blade, a different shape of contact on the surface of the rotor blade and/or a different composition compared to a plurality of the other rotor blades.

11. A method as claimed in claim 10 further comprising applying the coating on a surface of each of the rotor blades, the coating on each of the rotor blades having a different thickness, a different area of contact with the surface of the rotor blade, a different position of contact on the surface of the rotor blade, a different shape of contact on the surface of the rotor blade and/or a different composition compared to all of the other rotor blades.

12. A method as claimed in claim 5 further comprising exciting each individual rotor blade and measuring the vibration behaviour of the individual rotor blade before assembling the rotor blades into the rotor assembly.

13. A method as claimed in claim 5 further comprising constraining all of the rotor blades except for one unrestrained rotor blade, exciting the unrestrained rotor blade, measuring the vibration behaviour of the unrestrained rotor blade and repeating for each rotor blade.

14. A method as claimed in claim 5 further comprising constraining the rotor so as to minimise rotor blade interaction, exciting the rotor blades and measuring the vibration behaviour of each rotor blade.

15. A method as claimed in claim 5 further comprising analysing the measured vibration behaviour of the rotor blades, determining where to apply coatings to the rotor assembly such that the coating is applied in a non-uniform manner to reduce the vibration level of the rotor blade, or rotor blades, with the highest vibration response for a given excitation by changing the bladed rotor assembly mode shapes and the relative vibration of the rotor blades.

16. A method as claimed in claim 5 wherein the rotor carries a plurality of radially outwardly extending rotor blades.

17. A method as claimed in claim 5 wherein the rotor blades are integral with the rotor.

18. A method as claimed in claim 17 further comprising securing the rotor blade using a method selected from the group comprising friction welding, laser welding and diffusion bonding.

19. A method as claimed in claim 17 further comprising machining the rotor blades and rotor from a solid member.

20. A method as claimed in claim 5 wherein the rotor blades have roots, the rotor has a plurality of slots in the periphery of the rotor and the roots of the rotor blades are located in the slots in the periphery of the rotor.

21. A method as claimed in claim 5 wherein the rotor is selected from the group comprising a disc and a drum.

22. A method as claimed in claim 5 wherein the rotor is selected from the group comprising a fan rotor, a compressor rotor and a turbine rotor.

23. A method as claimed in claim 5 wherein the coating comprises a metallic bond coating and a ceramic coating.

24. A method as claimed in claim 23 wherein the metallic bond coating is selected from the group comprising a MCrAlY coating, a MCrAl coating, a MCr coating, an aluminide coating, a platinum aluminide coating, a diffused platinum coating and a diffused chromium coating.

25. A method as claimed in claim 23 wherein the ceramic coating is selected from the group comprising zirconia and magnesia-alumina spinel.

26. A method as claimed in claim 5 further comprising applying the coating by a method from the group comprising plasma spraying, air plasma spraying, vacuum plasma spraying, physical vapour deposition, chemical vapour deposition and plating and diffusion heat treatment.

27. A method as claimed in claim 2 further comprising removing material from the surface of at least one aerofoil and adding material to the surface of the at least one aerofoil on the structure.

28. A method as claimed in claim 1 further comprising providing a mathematical model of the bladed assembly, the mathematical model having design information of the bladed assembly and the vibration behaviour of each aerofoil, using the mathematical model to determine where to add material to, or remove material from, the surface of the at least one of the aerofoils.

29. A method as claimed in claim 1 further comprising considering more than one mode of vibration and giving more importance to a particular mode of vibration than other modes of vibration.

30. A method as claimed in claim 28 further comprising selecting the mathematical model from the group consisting of a reduced order model representation of the structure of the aerofoil assembly and a finite element representation of the structure of aerofoil assembly.

31. A method of manufacturing an aerofoil assembly comprising the steps of:

(a) forming a structure carrying a plurality of aerofoils, the structure and aerofoils forming the aerofoil assembly, the aerofoils having physical differences,

(b) exciting and measuring a vibration behaviour of the aerofoil assembly,

(c) analysing a vibration behaviour of the aerofoil assembly,

(d) determining where to add material to, or remove material from, a surface of at least one of the aerofoils of the aerofoil assembly in a non-uniform manner to reduce a vibration level of the aerofoil, or aerofoils, with the highest vibration for the given excitation by changing aerofoil assembly mode shapes and a relative vibration of the aerofoils in the aerofoil assembly so that a collective vibration behaviour of the aerofoil assembly of vibrationally interacting aerofoils is improved, and

(e) adding material to, or removing material from, the surface of the at least one of the aerofoils of the aerofoil assembly in the determined non-uniform manner to reduce the vibration level of the aerofoil, or aerofoils, with the highest vibration for the given excitation by changing the aerofoil assembly mode shapes and the relative vibration of the aerofoils in the aerofoil assembly so that the collective vibration behaviour of the aerofoil assembly of vibrationally interacting aerofoils is improved,

wherein step (b) follows step (a), step (c) follows step (a), step (d) follows steps (b) and (c), and step (e) follows step (d).

32. A method of manufacturing an aerofoil assembly comprising the steps of:

(a) forming a structure carrying a plurality of aerofoils, the structure and aerofoils forming the aerofoil assembly, the aerofoils having physical differences,

(b) exciting and measuring a vibration behaviour of each aerofoil,

(c) analysing a vibration behaviour of the aerofoils,

(d) determining where to add material to, or remove material from, a surface of at least one of the aerofoils of the aerofoil assembly in a non-uniform manner to reduce a vibration level of the aerofoil, or aerofoils, with the highest vibration for the given excitation by changing aerofoil assembly mode shapes and a relative vibration of the aerofoils in the aerofoil assembly so that a collective vibration behaviour of the aerofoil assembly of vibrationally interacting aerofoils is improved, and

(e) adding material to, or removing material from, the surface of the at least one of the aerofoils of the aerofoil assembly in the determined non-uniform manner to reduce the vibration level of the aerofoil, or aerofoils, with the highest vibration for the given excitation by changing the aerofoil assembly mode shapes and the relative vibration of the aerofoils in the aerofoil assembly so that the collective vibration behaviour of the aerofoil assembly of vibrationally interacting aerofoils is improved,

wherein step (b) follows step (a), step (c) follows step (a), step (d) follows steps (b) and (c), and step (e) follows step (d).