Mass offset for damping performance

• US 10,641,109 B2
• Filed: 03/11/2014
• Issued: 05/05/2020
• Est. Priority Date: 03/13/2013
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Rapp, Brandon M., Hough, Matthew Andrew
• Primary Examiner(s): Sanchez-Medina, Reinaldo
• Application Number:
  US14/203,681
• Publication Number:
  US 20150125304A1
• Time in Patent Office: 2,247 Days
• Field of Search: 416190, 416193 R, 416193 A, 416248, 416500
• CPC Class Codes: F01D 11/008 by spacer elements between the blades, e.g. independent interblade platforms
• CPC Class Codes: F01D 5/22 Blade-to-blade connections, e.g. for damping vibrations
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine rotor assembly includes a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. Adjacent platforms are separated from each other by a gap. A damper is positioned at an offset position within the gap to contact the inner surfaces of the adjacent platforms.

Claims

1. A gas turbine engine rotor assembly comprising:

a plurality of blades spaced apart from each other for rotation about an axis, each of the blades including a platform having an inner surface and an outer surface, and wherein adjacent platforms are separated from each other by a gap; and

a damper defined by a center of mass and positioned to have an outer surface that abuts directly against the inner surfaces of the adjacent platforms across the gap, and wherein a first portion of the outer surface of the damper contacts the inner surface of one of the adjacent platforms at a first edge of the gap and a second portion of the outer surface of the damper contacts the inner surface of the other of the adjacent platforms at a second edge of the gap that is opposite of the first edge of the gap such that the damper is in contact with the first and second edges while extending across the gap, and wherein the center of mass of the damper is aligned with the gap between adjacent platforms and is positioned closer to one of the adjacent platforms than the other of the adjacent platforms, and wherein the center of mass is offset from a centerline of the gap between adjacent platforms.

2. The gas turbine engine rotor assembly according to claim 1, wherein a range of offset of the center of mass is from greater than 0% up to 80%.

3. The gas turbine engine rotor assembly according to claim 2, wherein less than 20% of the damper remains under one of the adjacent platforms and up to 80% of the damper remains under the other of the adjacent platforms such that the damper provides an unequal load split between adjacent blades.

4. The gas turbine engine rotor assembly according to claim 1, wherein the inner surfaces of the adjacent platforms comprise contact surfaces that extend in a common direction such that the first portion of the outer surface of the damper contacts the contact surface of the one of the adjacent platforms at the first edge of the gap and the second portion of the outer surface of the damper contacts the contact surface of the other of the adjacent platforms at the second edge of the gap such that the damper provides an unequal load split between adjacent blades that comprises a first percentage for the first portion of the outer surface of the damper and a second percentage for the second portion of the outer surface of the damper wherein the first percentage is greater than the second percentage.

5. The gas turbine engine rotor assembly according to claim 4, wherein the first percentage is approximately 60% and wherein the second percentage is approximately 40%.

6. The gas turbine engine rotor assembly according to claim 1, wherein the damper provides an unequal load split between adjacent blades.

7. The gas turbine engine according to claim 1, including a rotor disk that supports the plurality of blades, and wherein each blade includes a root that fits into a corresponding slot in the rotor disk.

8. The gas turbine engine rotor assembly according to claim 1, wherein the gap is defined by a circumferential width and a radial depth, and wherein the center of mass of the damper is positioned circumferentially closer to one of the adjacent platforms than the other platform.

9. A gas turbine engine rotor assembly comprising:

a rotor disk defining an axis of rotation;

a plurality of blades supported by the rotor disk and spaced apart from each other for rotation about the axis of rotation, the plurality of blades including at least a first blade having a first platform and a second blade having a second platform separated from the first platform by a gap, and wherein each of the first and second platforms includes an inner surface and an outer surface; and

a damper defined by a center of mass and positioned to have an outer surface that abuts directly against the inner surfaces of the first and second platforms across the gap such that the center of mass is aligned with the gap between the first and second platforms and is positioned closer to one of the first and second platforms than the other of the first and second platforms so that the damper provides an unequal load split between the first and second blades, and wherein a first portion of the outer surface of the damper contacts the inner surface of one of the first and second platforms at a first edge of the gap and a second portion of the outer surface of the damper contacts the inner surface of the other of the first and second platforms at a second edge of the gap that is opposite of the first edge of the gap such that the damper is in contact with the first and second edges while extending across the gap, and wherein the center of mass is offset from a centerline of the gap between the first and second platforms.

10. The gas turbine engine rotor assembly according to claim 9, wherein the inner surfaces of the first and second platforms comprise contact surfaces that extend in a common direction such that the first portion of the outer surface of the damper contacts the contact surface of the one of the first and second platforms at the first edge of the gap and the second portion of the outer surface of the damper contacts the contact surface of the other of the first and second platforms at the second edge of the gap such that the damper provides an unequal load split that comprises a first percentage for the first portion of the outer surface of the damper and a second percentage for the second portion of the outer surface of the damper wherein the first percentage is greater than the second percentage.

11. The gas turbine engine rotor assembly according to claim 10, wherein the first percentage is approximately 60% for the first blade and the second percentage is approximately 40% for the second blade.

12. The gas turbine engine rotor assembly according to claim 9, wherein a range of offset of the center of mass is from greater than 0% up to 80%.

13. The gas turbine engine rotor assembly according to claim 12, wherein less than 20% of the damper remains under one of the first and second platforms and up to 80% of the damper remains under the other of the first and second platforms.

14. The gas turbine engine rotor assembly according to claim 9, wherein the damper provides a load split of approximately 60% for the first blade and approximately 40% for the second blade.

15. The gas turbine engine rotor assembly according to claim 9, wherein the gap is defined by a circumferential width and a radial depth, and wherein the center of mass is positioned circumferentially closer to one of the first and second platforms than the other of the first and second platforms.

21. The gas turbine engine according to claim 10, wherein a range of offset of the center of mass is from greater than 0% up to 80%.

22. The gas turbine engine according to claim 21, wherein less than 20% of the damper remains under one of the first and second platforms and up to 80% of the damper remains under another of the first and second platforms.

16. A gas turbine engine comprising:

a compressor section; and

a turbine section downstream of the compressor section, the turbine section including

at least one turbine stage having a rotor disk defining an axis of rotation;

a plurality of blades supported by the rotor disk and spaced apart from each other for rotation about the axis of rotation, the plurality of blades including at least a first blade having a first platform and a second blade having a second platform separated from the first platform by a gap, and wherein each of the first and second platforms includes an inner surface and an outer surface; and

a damper defined by a center of mass and positioned to have an outer surface that abuts directly against the inner surfaces of the first and second platforms across the gap, and wherein the center of mass of the damper is aligned with the gap between the first and second and is positioned closer to one of the first and second platforms than the other of the first and second platforms, and wherein the inner surfaces of the first and second platforms comprise contact surfaces that extend in a common direction such that a first portion of the outer surface of the damper contacts the contact surface of one of the first and second platforms at a first edge of the gap and a second portion of the outer surface of the damper contacts the contact surface of the other of the first and second platforms at a second edge of the gap that is opposite of the first edge of the gap such that the damper is in contact with the first and second edges while extending across the gap.

17. The gas turbine engine according to claim 16 wherein the gap is defined by a circumferential width and a radial depth, and wherein the center of mass of the damper is positioned circumferentially closer to one of the first and second platforms than the other of the first and second platforms such that the damper provides an unequal load split between the first and second blades.

18. The gas turbine engine according to claim 17, the damper provides the unequal load split that comprises a first percentage for the first portion of the outer surface of the damper and a second percentage for the second portion of the outer surface of the damper wherein the first percentage is greater than the second percentage.

19. The gas turbine engine according to claim 18, wherein the first percentage is approximately 60% for the first blade and the second percentage is approximately 40% for the second blade.

20. The gas turbine engine according to claim 17, wherein the center of mass is offset from a centerline of the gap between the first and second platforms.

23. The gas turbine engine according to claim 16, wherein the damper provides a load split of approximately 60% for the first blade and approximately 40% for the second blade.

24. The gas turbine engine according to claim 16, further comprising a fan section, wherein the turbine section drives the fan section via a geared architecture.