Mistuned laminate airfoil

• US 10,641,281 B2
• Filed: 08/08/2016
• Issued: 05/05/2020
• Est. Priority Date: 08/08/2016
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Foster, Larry, Klein, Myron L.
• Primary Examiner(s): Laurenzi, Mark A
• Assistant Examiner(s): Edwards, Loren C
• Application Number:
  US15/231,058
• Publication Number:
  US 20180038382A1
• Time in Patent Office: 1,366 Days
• Field of Search: 60805
• CPC Class Codes: F01D 25/04 Antivibration arrangements
• 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 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• 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: F02K 3/06 with front fan
• CPC Class Codes: F04D 29/023 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/327 with non identical blades
• CPC Class Codes: F04D 29/388 characterised by construction
• 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 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F05D 2260/961 by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/6034 Orientation of fibres, weaving, ply angle
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine includes a fan mounting a first group of blades and a second group of blades. The first group of blades and the second group of blades share a profile shape. The first group of blades have a first laminate composition, and the second group of blades have a second laminate composition, distinct from the first laminate composition. A frequency of a vibratory mode of the first group of blades is offset from a frequency of a vibratory mode of the second group of blades.

Claims

1. A fan for a gas turbine engine comprising:

the fan mounting a first group of blades and a second group of blades;

said first group of blades and said second group of blades sharing a profile shape;

wherein said first group of blades have a first laminate composition;

wherein said second group of blades have a second laminate composition, distinct from the first laminate composition, and said first group of blades and said second group of blades each include a corresponding root shape distinct from the corresponding root shape of the other of said first group of blades and said second group of blades, wherein each of the corresponding root shapes has a same layup structure as each other of the corresponding root shapes; and

wherein a frequency of a vibratory mode of the first group of blades is offset from a frequency of a vibratory mode of the second group of blades.

2. The fan of claim 1, wherein said first group of blades and said second group of blades are alternately arranged circumferentially around said fan.

3. The fan of claim 2, wherein each blade in said first group of blades is circumferentially adjacent a first blade of said second group of blades and a second blade of said second group of blades.

4. The fan of claim 1, wherein the frequency of the vibratory mode of the first group of blades is offset from the frequency of the vibratory mode of the second group of blades by at least 4%.

5. The fan of claim 4, wherein the frequency of the vibratory mode of the first group of blades is offset from the frequency of the vibratory mode of the second group of blades by at least 6%.

6. The fan of claim 1, wherein the first laminate composition is a first layup configuration, and wherein the second laminate composition is a second layup configuration distinct from the first layup configuration.

7. The fan of claim 6, wherein the first layup configuration includes at least one of a specific material layer orientation and a relative layer position, and wherein the second layup configuration includes at least one of a specific material layer orientation and a relative layer position.

8. The fan of claim 7, wherein the material layer orientation of the first layup configuration is distinct from the material layer orientation of the second layup configuration.

9. The fan of claim 7, wherein the relative layer position of the first layup configuration is distinct from the relative layer position of the second layup configuration.

10. The fan of claim 1, wherein each blade of said first group of blades, and each blade of said second group of blades is constructed at least partially of a polymer matrix composite.

11. The fan of claim 1, wherein the distinct root shapes of one of said first group of blades and said second group of blades includes a keying feature.

12. The fan of claim 1, wherein each blade structure is a single integral structure including a corresponding blade root.

13. A gas turbine engine comprising:

a compressor section;

a combustor fluidly connected to the compressor section;

a turbine section fluidly connected to the combustor;

a fan drivably connected to said turbine section, the fan including a first set of blades and a second set of blades, wherein each of said first set of blades and said second set of blades share a profile;

the first set of blades having a first vibratory mode; and

the second set of blades having a second vibratory mode distinct from the first vibratory mode; and

wherein said first set of blades and said second set of blades each include a corresponding root shape distinct from the corresponding root shape of the other of said first set of blades and said second set of blades, and each of the corresponding root shapes has a same layup structure as each other of the corresponding root shapes.

14. The gas turbine engine of claim 13, wherein the blades in the first set of blades are laminate blades having a first laminate composition and the blades in the second set of blades are laminate blades having a second laminate composition distinct from the first laminate composition.

15. The gas turbine engine of claim 14, wherein the first laminate composition is a first layup configuration, and wherein the second laminate composition is a second layup configuration distinct from the first layup configuration.

16. The gas turbine engine of claim 15, wherein the first layup configuration includes at least one of a specific material layer orientation and a relative layer position, and wherein the second layup configuration includes at least one of a specific material layer orientation and a relative layer position.

17. The gas turbine engine of claim 16, wherein the material layer orientation of the first layup configuration is distinct from the material layer orientation of the second layup configuration.

18. The gas turbine engine of claim 16, wherein the relative layer position of the first layup configuration is distinct from the relative layer position of the second layup configuration.

19. The gas turbine engine of claim 14, wherein said first set of blades and said second set of blades are arranged in a circumferentially alternating configuration.

20. The gas turbine engine of claim 14, wherein a vibratory mode of the first set of blades is offset from a vibratory mode of the second set of blades by at least 4%.