Turbomachine rotor blade

Patent metadata

Field	Value
Publication number	US-10577940-B2
Application number	US-201715420457-A
Country	US
Kind code	B2
Filing date	Jan 31, 2017
Priority date	Jan 31, 2017
Publication date	Mar 3, 2020
Grant date	Mar 3, 2020

Abstract

A rotor blade for a turbomachine includes an airfoil having a leading edge, a trailing edge, a root, and a tip. The airfoil defines a chord extending from the leading edge to the trailing edge and a span extending from the root to the tip. A first particle-filled damper is positioned within the airfoil between fifty percent of the chord and one hundred percent of the chord.

First claim

What is claimed is:

1. A rotor blade for a turbomachine, comprising:
an airfoil including a leading edge, a trailing edge, a root, and a tip, the airfoil defining a chord extending from the leading edge to the trailing edge and a span extending from the root to the tip;
a tip shroud coupled to the tip of the airfoil, or a part span shroud coupled to a pressure-side wall or a suction-side wall of the airfoil;
a first particle-filled damper positioned within the airfoil between fifty percent of the chord and one hundred percent of the chord; and
a second particle-filled damper positioned within the tip shroud or the part span shroud, between a radially inner surface of either the tip shroud or the part span shroud and a radially outer surface of either the tip shroud or the part span shroud.

2. The rotor blade of claim 1 , wherein the first particle-filled damper is positioned within the airfoil between seventy-five percent of the chord and one hundred percent of the chord.

3. The rotor blade of claim 1 , wherein the first particle-filled damper is positioned within the airfoil between fifty percent of the span and one hundred percent of the span.

4. The rotor blade of claim 3 , wherein the first particle-filled damper is positioned within the airfoil between seventy-five percent of the span and one hundred percent of the span.

5. The rotor blade of claim 1 , wherein the first particle-filled damper is positioned within the airfoil between seventy-five percent of the chord and the one hundred percent of the chord and between fifty percent of the span and seventy-five percent of the span.

6. The rotor blade of claim 1 , further comprising:
a third particle-filled damper positioned within the airfoil, the third particle-filled damper being spaced apart from the first particle-filled damper along the span or the chord.

7. The rotor blade of claim 6 , wherein the third particle-filled damper is positioned within the airfoil between fifty percent of the chord and the one hundred percent of the chord and between twenty-five percent of the span and seventy-five percent of the span.

8. The rotor blade of claim 1 , further comprising:
a third particle-filled damper positioned within the airfoil between zero percent of the chord and the fifty percent of the chord.

9. The rotor blade of claim 1 , wherein at least one of the first particle-filled damper or the second particle-filled damper comprises a housing, a plurality of particles contained within the housing, and a plurality of ribs within the housing.

10. The rotor blade of claim 1 , further comprising:
a third particle-filled damper positioned within the airfoil and spaced apart from the first particle-filed damper along the span.

11. A turbomachine, comprising:
a compressor section;
a combustion section; and
a turbine section including one or more rotor blades, each rotor blade comprising:
an airfoil including a leading edge, a trailing edge, a root, and a tip, the airfoil defining a chord extending from the leading edge to the trailing edge and a span extending from the root to the tip;
a tip shroud coupled to the tip of the airfoil, or a part span shroud coupled to a pressure-side wall or a suction-side wall of the airfoil;
a first particle-filled damper positioned within the airfoil between fifty percent of the chord and one hundred percent of the chord; and
a second particle-filled damper positioned within the tip shroud or the part span shroud, between a radially inner surface of either the tip shroud or the part span shroud and a radially outer surface of either the tip shroud or the part span shroud.

12. The turbomachine of claim 11 , wherein the first particle-filled damper is positioned within the airfoil between seventy-five percent of the chord and one hundred percent of the chord.

13. The turbomachine of claim 11 , wherein the first particle-filled damper is positioned within the airfoil between fifty percent of the span and one hundred percent of the span.

14. The turbomachine of claim 13 , wherein the first particle-filled damper is positioned within the airfoil between seventy-five percent of the span and one hundred percent of the span.

15. The turbomachine of claim 11 , wherein the first particle-filled damper is positioned within the airfoil between seventy-five percent of the chord and one hundred percent of the chord and between fifty percent of the span and seventy-five percent of the span.

16. The turbomachine of claim 11 , further comprising:
a third particle-filled damper positioned within the airfoil, the third particle-filled damper being spaced apart from the first particle-filled damper along the span or the chord.

17. The turbomachine of claim 16 , wherein the third particle-filled damper is positioned within the airfoil between fifty percent of the chord and one hundred percent of the chord and between twenty-five percent of the span and seventy-five percent of the span.

18. The turbomachine of claim 11 , further comprising:
a third particle-filled damper positioned within the airfoil between zero percent of the chord and fifty percent of the chord.

19. The turbomachine of claim 11 , wherein at least one of the first particle-filled damper or the second particle-filled damper comprises a housing, a plurality of particles contained within the housing, and a plurality of ribs within the housing.

20. The turbomachine of claim 11 , further comprising:
a third particle-filled damper positioned within the airfoil and spaced apart from the first particle-filed damper along the span.

Assignees

• Gen Electric

Inventors

• Hoskin Robert Frank
• Brittingham Robert Alan
• Potter Brian Denver
• Erno Daniel Jason
• Delvaux John Mcconnell

Classifications

• F01D5/225

  by shrouding · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F01D5/16 Primary

  for counteracting blade vibration · CPC title