Composite drive shafts

Patent metadata

Field	Value
Publication number	US-12152633-B2
Application number	US-202217872109-A
Country	US
Kind code	B2
Filing date	Jul 25, 2022
Priority date	Oct 29, 2018
Publication date	Nov 26, 2024
Grant date	Nov 26, 2024

Abstract

A mechanical system for an aerospace application includes a drive input connected to a first axial end of a first diaphragm member, and a drive output connected to a second axial end of a second diaphragm member. The drive output is an aerospace component. The first and second diaphragm members are formed with two axial ends and at least one undulation extending radially of the axial ends. The at least one undulation is intermediate the ends. A tubular portion connects the first and second diaphragm members. The first and second diaphragm members and the tubular member are formed of fiber reinforced polymer matrix composites. The first and second diaphragm members are connected to axial ends of the tubular member by welding of the axial ends of the tubular portion to one of the inner ends of each of said first and second diaphragm members. The aerospace component is a propeller.

First claim

The invention claimed is:

1. A mechanical system for an aerospace application comprising:
a drive input connected to a first axial end of a first diaphragm member, and a drive output connected to a second axial end of a second diaphragm member, and said drive output is an aerospace component;
said first and second diaphragm members being formed with two axial ends and at least one undulation extending radially of said axial ends, and said at least one undulation being intermediate said ends, and a tubular portion connecting said first and second diaphragm members, said first and second diaphragm members and said tubular member being formed of fiber reinforced polymer matrix composites, and said first and second diaphragm members being connected to axial ends of said tubular member;
joints formed by welding of said axial ends of said tubular portion to one of said inner ends of each of said first and second diaphragm members; and
said aerospace component is a propeller.

2. The mechanical connection as set forth in claim 1 , wherein reinforcement is provided by the axial end of one of said tubular portion and said first and second diaphragm members being radially within the axial end of the other of said tubular portion and one of said first and second diaphragm members.

3. The mechanical connection as set forth in claim 1 , wherein a separate reinforcement sleeve provides reinforcement.

4. The mechanical system as set forth in claim 1 , wherein said connection receives reinforcement.

5. The mechanical system as set forth in claim 4 , wherein said reinforcement is provided by the axial end of one of said tubular portion and said first and second diaphragm members being radially within the axial end of the other of said tubular portion and one of said first and second diaphragm members.

6. The mechanical system as set forth in claim 4 , wherein a separate fiber-reinforced polymer matrix composite sleeve provides said reinforcement.

7. The mechanical system as set forth in claim 6 , wherein said sleeve provides a radially extending step such that said sleeve has reinforcement portions at distinct radial positions.

8. The mechanical system as set forth in claim 7 , wherein said sleeve is radially inward of said joints.

9. The mechanical system as set forth in claim 6 , wherein said sleeve is radially inward of said joints.

10. The mechanical system as set forth in claim 9 , wherein a second sleeve is provided at a radially outer surface of said joints.

11. The mechanical system as set forth in claim 6 , wherein said sleeve is provided on a radially inner surface of said joints.

12. The mechanical system as set forth in claim 1 , wherein said at least one undulation extends radially outwardly of said ends.

13. The mechanical system as set forth in claim 1 , wherein said at least one undulation extends radially inwardly of said ends.

14. A mechanical system for an aerospace application comprising:
a drive input connected to a first axial end of a first diaphragm member, and a drive output connected to a second axial end of a second diaphragm member, and said drive output is an aerospace component;
said first and second diaphragm members being formed with two axial ends and at least one undulation extending radially of said axial ends, and said at least one undulation being intermediate said ends, and a tubular portion connecting said first and second diaphragm members, said first and second diaphragm members and said tubular member being formed of fiber reinforced polymer matrix composites, and said first and second diaphragm members being connected to axial ends of said tubular member;
joints formed by welding of said axial ends of said tubular portion to one of said inner ends of each of said first and second diaphragm members;
wherein said joints receive reinforcement;
wherein a separate fiber-reinforced polymer matrix composite sleeve provides said reinforcement;
wherein said sleeve provides a radially extending step such that said sleeve has reinforcement portions at distinct radial positions; and
wherein said sleeve is radially inward of said joints.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Schaefer Joyel M
• King Michael
• Reed Brayton
• Gurvich Mark R

Classifications

• F16D1/068 Primary

  involving gluing, welding or the like · CPC title

• Y10S285/919

  Resinous · CPC title

• Y10S138/02

  Glass fiber · CPC title

• F16D3/725

  with an intermediate member made of fibre-reinforced resin (made of rubber-like material F16D3/74; shafts made of fibre-reinforced resin F16C3/026) · CPC title

• F16D2250/0076

  Welding, brazing · CPC title