ROTORS WITH MODULUS MISTUNED AIRFOILS

• US 20160053617A1
• Filed: 04/09/2014
• Published: 02/25/2016
• Est. Priority Date: 04/16/2013
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Grelotti, Robert A., Morris, Robert J.
• Granted Patent: US 10,808,543 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• 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: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2240/30 Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
• CPC Class Codes: F05D 2260/961 by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
• CPC Class Codes: F05D 2300/609 Grain size
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A rotor assembly for a gas turbine engine includes a rotor defining an outer periphery; and a plurality of blades attached to the outer periphery. The plurality of blades includes a material property different than the other of the plurality of blades to provide mistuning of the rotor.

Claims

1. A rotor assembly for a gas turbine engine comprising:

a rotor defining an outer periphery; and

a plurality of blades arranged on the outer periphery, wherein at least one of the plurality of blades includes a material property different than at least one of the other plurality of blades.

2. The rotor assembly as recited in claim 1, wherein the rotor comprises an integrally bladed rotor with the plurality of blades welded to the rotor.

3. The rotor assembly as recited in claim 1, wherein the rotor comprises a plurality of slots receiving root portions of each of the plurality of blades.

4. The rotor assembly as recited in claim 1, wherein each of the plurality of blades includes a common geometric shape.

5. The rotor assembly as recited in claim 1, wherein the material property comprises a material modulus of at least one of the plurality of blades.

6. The rotor assembly as recited in claim 1, wherein the material property comprises a grain structure, wherein at least one of the plurality of blades includes a grain structure different than at least one of the other of the plurality of blades.

7. The rotor assembly as recited in claim 1, wherein the plurality of blades includes alternating blades with differing material properties.

8. The rotor assembly as recited in claim 1, wherein the plurality of blades comprises a plurality of alternating blades fabricated from a different material.

9. The rotor assembly as recited in claim 1, wherein the plurality of blades comprises an airfoil.

10. A gas turbine engine comprising:

a compressor section;

a combustor in fluid communication with the compressor section;

a turbine section in fluid communication with the combustor, wherein the turbine section drives the compressor section; and

a rotor within at least one of the compressor section and turbine section including a plurality of blades, wherein at least one of the plurality of blades includes a material property different than the other of the plurality of blades.

11. The gas turbine engine as recited in claim 10, the rotor comprises an integrally bladed rotor and each of the plurality of blades is attached to the rotor at a weld joint.

12. The rotor assembly as recited in claim 10, wherein the rotor comprises a plurality of slots receiving root portions of each of the plurality of blades.

13. The gas turbine engine as recited in claim 10, wherein each of the plurality of blades includes a common geometric shape.

14. The gas turbine engine as recited in claim 10, wherein the material property comprises a material modulus of at least one of the plurality of blades.

15. The gas turbine engine as recited in claim 10, wherein the material property comprises a grain structure, wherein at least one of the plurality of blades includes a grain structure different than at least one of the other of the plurality of blades.

16. The gas turbine engine as recited in claim 10, wherein the plurality of blades includes alternating blades with differing material properties.

17. The gas turbine engine as recited in claim 10, wherein the plurality of blades comprises a plurality of alternating blades fabricated from a different material.

18. The gas turbine engine as recited in claim 10, including a fan section and the rotor comprises a fan rotor supporting a plurality of fan blades.

19. A method of fabricating a bladed rotor comprising:

forming a rotor to include an outer periphery;

forming a first blade to include a first material characteristic;

forming a second blade to include a second material characteristic different than the first material characteristic; and

assembling the first blade to the rotor; and

assembling the second blade to the rotor relative to the first blade to provide a desired mistune of the bladed rotor.

20. The method as recited in claim 19, wherein the bladed rotor comprises an integrally bladed rotor and the method includes the steps of bonding the first blade to the rotor, and bonding the second blade to the rotor relative to the first blade to provide a desired mistune of the integrally bladed rotor.

21. The method as recited in claim 20, including inertia bonding the first blade and the second blade to the rotor.

22. The method as recited in claim 20, including forming a plurality of first blades and a second plurality of second blades and bonding the first plurality of blades and the second plurality of blades to the rotor to provide a desired mistuning of the rotor.

23. The method as recited in claim 20, wherein the first material characteristic comprises a first modulus and the second material characteristic comprises a second modulus different than the first modulus.

24. The method as recited in claim 23, including first forging process for forming the first blade with the first modulus and a second forging process for forming the second blade with the second modulus.

25. The method as recited in claim 19, including forming the first blade and the second blade to include an identical geometric shape.

26. The method as recited in claim 19, wherein the first blade comprises a first material composition and the second blade comprises a second material composition different than the first material.