Rotor assembly for in-machine grinding of shroud member and methods of using the same

Patent metadata

Field	Value
Publication number	US-11299993-B2
Application number	US-201916665964-A
Country	US
Kind code	B2
Filing date	Oct 28, 2019
Priority date	Oct 28, 2019
Publication date	Apr 12, 2022
Grant date	Apr 12, 2022

Abstract

A turbomachine includes a shroud and a rotor, which includes first and second blades. A first blade tip and a second blade tip respectively include a base and a first layer. The second blade tip also includes an abrasive second layer layered over the respective first layer. The first layer has a lower material hardness than the shroud. The second layer has a lower thermal stability than the shroud and the first layer. The rotor performs a grind operation and, subsequently, a post-grind operation. The second layer, in the grind operation, contacts and removes material from the shroud, and wears away, thereby revealing the first layer of the second blade tip for the post-grind operation. The first layer of the first blade tip is spaced apart with at least some radial clearance from the shroud in the grind and post-grind operations.

First claim

We claim:

1. A turbomachine comprising:
a shroud;
a rotor rotatably supported within the shroud, the rotor including a first blade and a second blade, the first blade having a first blade tip oriented toward the shroud, the second blade having a second blade tip oriented toward the shroud;
the first blade tip and the second blade tip respectively including a base and a first layer layered over the base and disposed outward radially therefrom;
the second blade tip including an abrasive second layer layered over the first layer of the second blade tip such that the first layer of the second blade tip is disposed radially between the base and the abrasive second layer of the second blade tip;
the first layer of the first blade tip and the first layer of the second blade tip having a material hardness that is lower than that of the shroud;
the abrasive second layer having a lower thermal stability than the shroud and the first layer of the second blade tip;
the rotor configured to rotate within the shroud in a grind operation and, subsequently, in a post-grind operation;
the abrasive second layer of the second blade tip, in the grind operation, configured to contact and remove material from the shroud, and to wear away from the second blade tip to reveal the first layer of the second blade tip for the post-grind operation; and
the first layer of the first blade tip spaced apart with at least some radial clearance from the shroud in the grind operation and in the post-grind operation.

2. The turbomachine of claim 1 , wherein the first layer of the first blade tip and the first layer of the second blade tip comprise a common material.

3. The turbomachine of claim 2 , wherein the common material is a nickel-based alloy.

4. The turbomachine of claim 1 , wherein the second layer includes a plurality of abrasive particles that are embedded within a matrix.

5. The turbomachine of claim 4 , wherein the matrix includes a nickel-based alloy.

6. The turbomachine of claim 4 , wherein the matrix and the first layer of the second blade tip is made from a common material.

7. The turbomachine of claim 4 , wherein the plurality of abrasive particles are coated particles that are coated with a coating, the coated particles being embedded within the matrix.

8. The turbomachine of claim 7 , wherein the coating includes titanium.

9. The turbomachine of claim 4 , wherein the abrasive particles comprise a cubic boric nitride material.

10. The turbomachine of claim 1 , wherein the rotor is supported for rotation about an axis within the shroud;
wherein the first blade defines a first blade radius measured from the axis to the first blade tip;
wherein the second blade defines a second blade radius measured from the axis to the second blade tip;
wherein the second blade radius is greater than the first blade radius;
wherein the first layer of the first blade tip has a thickness greater than that of the first layer of the second blade tip.

11. A method of operating a turbomachine comprising:
providing a rotor that is supported for rotation within a shroud, the rotor including a first blade and a second blade, the first blade having a first blade tip oriented toward the shroud, the second blade having a second blade tip oriented toward the shroud, the first blade tip and the second blade tip respectively including a base and a first layer layered over the base and disposed outward radially therefrom, the second blade tip including an abrasive second layer layered over the first layer of the second blade tip such that the first layer of the second blade tip is disposed radially between the base and the abrasive second layer of the second blade tip, the first layer of the first blade tip and the first layer of the second blade tip having a material hardness that is lower than that of the shroud, the abrasive second layer having a lower thermal stability than the shroud and the first layer of the second blade tip;
rotating the rotor within the shroud in a grind operation during which:
the first layer of the first blade tip is spaced apart with at least some radial clearance from the shroud; and
the abrasive second layer of the second blade tip contacts and removes material from the shroud and wears away from the second blade tip to reveal the first layer of the second blade tip;
rotating the rotor within the shroud in a post-grind operation during which:
the first layer of the first blade tip is spaced apart with at least some radial clearance from the shroud; and
the first layer of the second blade tip is revealed and spaced apart with at least some radial clearance from the shroud.

12. The method of claim 11 , wherein rotating the rotor within the shroud in a grind operation includes performing a plurality of grind operation cycles in succession; and
wherein, during different ones of the plurality of grind operation cycles, a rotational speed of the rotor relative to the shroud is increased and subsequently decreased.

13. The method of claim 12 , wherein, during different ones of the plurality of cycles, at least one variable is different, the at least one variable chosen from a group consisting of:
a maximum rotational speed of the rotor relative to the shroud;
a hold time at which the rotor is maintained at the maximum rotational speed; and
an acceleration of the rotor.

14. The method of claim 11 , wherein providing the rotor includes providing the first layer of the first blade tip and the first layer of the second blade tip with a common material.

15. The method of claim 14 , wherein the common material is a nickel-based alloy.

16. The method of claim 11 , wherein providing the rotor includes providing the second layer with a plurality of abrasive particles that are embedded within a matrix.

17. The method of claim 16 , wherein the matrix includes a nickel-based alloy.

18. The method of claim 16 , wherein the matrix and the first layer of the second blade tip is made from a common material.

19. The method of claim 16 , wherein the plurality of abrasive particles are coated particles that are coated with a coating, the coated particles being embedded within the matrix.

20. A turbine section of a gas turbine engine comprising:
a shroud;
a rotor rotatably supported within the shroud, the rotor including a plurality of first blades and at least two second blades that are spaced apart equally about an axis of rotation of the rotor, the plurality of first blades respectively including a first blade tip oriented toward the shroud, the at least two second blades respectively including a second blade tip oriented toward the shroud;
the first blade tip and the second blade tip respectively including a base and a first layer layered over the base and disposed outward radially therefrom;
the second blade tip including an abrasive second layer layered over the first layer of the second blade tip such that the first layer of the second blade tip is disposed radially between the base and the abrasive second layer of the second blade tip;
the first layer of the first blade tip and the first layer of the second blade tip having a material hardness that is lower than that of the shroud;
the abrasive second layer having a lower thermal stability than the shroud and the first layer of the second blade tip;
the at least two second blades having greater blade radii than the plurality of first blades, the blade radii measured from the axis of rotation to the respective ones of the first blade tip and the second blade tip;
the ro

Assignees

• Honeywell Int Inc

Inventors

• Mittendorf Donald
• Amato Krista
• Conklin Nicole
• Ludwig Brent
• Morris Mark
• Stanley Ryon
• Tilman Donald
• Yun Heemann

Classifications

• F05D2300/506

  Hardness · CPC title

• F05D2300/611

  Coating · CPC title

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F05D2300/609

  Grain size · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title