Methods for separating rotor blade cuffs from rotor blade bodies

Patent metadata

Field	Value
Publication number	US-10196140-B2
Application number	US-201615097134-A
Country	US
Kind code	B2
Filing date	Apr 12, 2016
Priority date	Apr 12, 2016
Publication date	Feb 5, 2019
Grant date	Feb 5, 2019

Abstract

A rotor blade disassembly method includes applying spanwise support to a rotor blade body and heating a bond disposed on an end of the rotor blade body. The method also includes removing the spanwise support from the rotor blade body and exerting shear stress on the bond using weight of the rotor blade body. A blade disassembly system is also described.

First claim

What is claimed is:

1. A rotor blade disassembly method for removing a blade cuff from a rotor blade body, comprising:
applying a spanwise support to the rotor blade body, horizontally, in a first position;
heating a bond connecting the blade cuff to an end of the rotor blade body;
removing the spanwise support from the rotor blade body such that the rotor blade body is in a second position other than the first position;
exerting shear stress on the heated bond using weight of the rotor blade body while in the second position; and
removing the blade cuff from the rotor blade body.

2. The disassembly method as recited in claim 1 , wherein applying spanwise support to the rotor blade body further comprises receiving the rotor blade body in a blade cradle.

3. The disassembly method as recited in claim 2 , wherein the applying spanwise support to the rotor blade body further comprises engaging the rotor blade body against an inboard support, a mid-span support, and an outboard support of the blade cradle.

4. The disassembly method as recited in claim 3 , further including disengaging one or more of the inboard support, the mid-span support, and the outboard support from the rotor blade body.

5. The disassembly method as recited in claim 1 , wherein the heating the bond comprises:
applying a first amount of heat to an inboard end of the blade cuff coupled to the rotor blade body by the bond; and applying a second amount of heat to an outboard end of the blade cuff, wherein the first amount of heat is greater than the second amount of heat.

6. The disassembly method as recited in claim 5 , wherein the applying the first amount of heat to the inboard end and outboard end of the blade cuff includes heating the bond to a temperature below a maximum short term operating temperature of the rotor blade body.

7. The disassembly method as recited in claim 1 , wherein the applying spanwise support to the rotor blade body comprises orienting a chord defined by the rotor blade body vertically relative to the direction of gravity.

8. The disassembly method as recited in claim 1 , further comprising applying endwise support to the rotor blade body.

9. The disassembly method as recited in claim 1 , further comprising seating the blade cuff coupled to the rotor blade body by the bond in a cuff seat, and pivoting the rotor blade body relative to the blade cuff using the weight of the rotor blade body.

10. The disassembly method as recited in claim 1 , further comprising exerting an opposed axial forces against the cuff and the rotor blade body, and displacing the blade cuff axially relative to the blade body.

11. The disassembly method as recited in claim 1 , further comprising removing fasteners coupling the blade cuff to the rotor blade body.

12. The disassembly method as recited in claim 1 , wherein the rotor blade comprises:
a composite blade body with an inboard, an outboard end, and an intervening mid-span segment defined between first and second airfoil surfaces; and
the blade cuff having first and second prongs disposed on the inboard end of the composite blade body,
wherein the bond includes a first bond layer coupling the first prong of the blade cuff to the first airfoil surface of the composite blade body,
wherein the bond includes a second bond layer coupling the second prong of the blade cuff to the second airfoil surface of the composite blade body.

13. The disassembly method as recited in claim 1 , further including seating a root plate cover over an inboard end of the rotor blade.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Lehto Ryan
• Boyle Eric C
• Lofstrom Sven R
• Littlejohn David

Classifications

• F01D25/285

  Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures · CPC title

• F05D2230/70

  Disassembly methods · CPC title

• Y10T29/49318

  Repairing or disassembling · CPC title

• B64C27/48

  Root attachment to rotor head · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title