Method of assembling and balancing rotor blades

Patent metadata

Field	Value
Publication number	US-9598168-B2
Application number	US-201314033700-A
Country	US
Kind code	B2
Filing date	Sep 23, 2013
Priority date	Sep 23, 2013
Publication date	Mar 21, 2017
Grant date	Mar 21, 2017

Abstract

A method of assembling a rotor blade assembly includes determining a first spanwise moment of a first component of the rotor blade assembly and comparing the first spanwise moment to a target first spanwise moment. The first spanwise moment of the first component is adjusted based on a result of the comparison. A second spanwise moment of a second component of the rotor blade assembly is determined and compared to a target second spanwise moment. The second spanwise moment of the second component is adjusted based on a result of the comparison. The first component is assembled to the second component, resulting in a rotor blade assembly meeting a target spanwise moment of the rotor blade assembly.

First claim

What is claimed:

1. A method of assembling a rotor blade assembly comprising:
determining a first spanwise moment of a first component of the rotor blade assembly;
comparing the first spanwise moment to a target first spanwise moment;
adjusting the first spanwise moment of the first component based on a result of the comparison to provide a balanced first component;
determining a second spanwise moment of a second component of the rotor blade assembly;
comparing the second spanwise moment to a target second spanwise moment;
adjusting the second spanwise moment of the second component based on a result of the comparison to provide a balanced second component;
assembling the balanced first and second components to provide the rotor blade assembly meeting a target spanwise moment of the rotor blade assembly, wherein:
the first component comprises one of a leading edge assembly, a trailing edge pocket assembly, and a spar assembly; and
the second component comprises another one of the leading edge assembly, the trailing edge pocket assembly, and the spar assembly.

2. The method of claim 1 , wherein the adjusting the first spanwise moment comprises affixing one or more structural film adhesive layers to the first component.

3. The method of claim 2 , wherein a number and/or size of the one or more structural film adhesive layers is determined by the result of the comparison of the first spanwise moment to the target first spanwise moment.

4. The method of claim 1 , further comprising
determining a third spanwise moment of a third component of the rotor blade assembly;
comparing the third spanwise moment to a target third spanwise moment; and
adjusting the third spanwise moment of the third component based on a result of the comparison to provide a balanced third component;
wherein the assembling further comprises assembling the balanced third component with the balanced first and/or second component.

5. The method of claim 4 , wherein adjusting the third spanwise moment comprises removing material from the third component.

6. The method of claim 1 , wherein the first spanwise moment and/or the second spanwise moment are determined by placing the first component and/or the second component on a balance fixture comprising a plurality of load cells and reading the load at each of the load cells.

7. The method of claim 6 , wherein the plurality of load cells comprises three load cells, and the determining comprises calculating the moment using Equation (1):
M=R 1× FA 1+ R 2× FA 2+ R 3× FA 3  (1)

where:
M is the spanwise moment of the first or second component;
R1 is a radial distance of a first of the three load cells from a main rotor axis;
FA1 is a force applied by the first or second component to the first load cell;
R2 is a radial distance of a second of the three load cells;
FA2 is a force applied by the second component to the second load cell;
R3 is a radial distance of a third of the three load cells; and
FA3 is a force applied by the third component to the second load cell.

8. The method of claim 1 , wherein adjusting the trailing edge pocket assembly spanwise moment comprises affixing one or more structural film adhesive layers to the trailing edge pocket assembly.

9. The method of claim 8 , wherein a number and/or size of the one or more structural film adhesive layers is determined by the result of the comparison of the pocket spanwise moment to the target pocket spanwise moment.

10. The method of claim 1 , wherein adjusting the leading edge assembly spanwise moment comprises removing material from the spar assembly.

11. The method of claim 10 , wherein the material is one or more counterweights.

12. The method of claim 1 , wherein the trailing edge pocket assembly spanwise moment and/or the spar spanwise moment are determined by placing the trailing edge pocket assembly and/or the spar assembly on a balance fixture comprising a plurality of load cells.

13. The method of claim 12 , wherein the plurality of load cells is three load cells.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Leahy Kevin P
• Caputo Frank

Classifications

• B64C2027/4736

  from composite materials · CPC title

• G01M1/32

  by adding material to the body to be tested, e.g. by correcting-weights · CPC title

• Y10T29/37

  Impeller making apparatus · CPC title

• G01M1/34

  by removing material from the body to be tested, e.g. from the tread of tyres · CPC title

• B64C27/008 Primary

  Rotors tracking or balancing devices · CPC title