Rotor assembly for use in a turbofan engine and method of assembling

Patent metadata

Field	Value
Publication number	US-10047763-B2
Application number	US-201514968306-A
Country	US
Kind code	B2
Filing date	Dec 14, 2015
Priority date	Dec 14, 2015
Publication date	Aug 14, 2018
Grant date	Aug 14, 2018

Abstract

A rotor assembly for use in a turbofan engine is provided. The rotor assembly includes an annular spool including a first blade opening defined therein, a first rotor blade configured to be radially inserted through the first blade opening, and a fairing positioned on a radially outer side of the annular spool. The first rotor blade includes a blade portion and a flange portion that extends substantially perpendicularly relative to the blade portion such that the flange portion is positioned on a radially inner side of the annular spool. The fairing is configured to receive a fastener radially inserted through the flange portion and the annular spool such that the first rotor blade is secured to the annular spool.

First claim

What is claimed is:

1. A rotor assembly for use in a turbofan engine, said rotor assembly comprising:
an annular spool comprising a first blade opening defined therein;
a first rotor blade configured to be radially inserted through said first blade opening, said first rotor blade comprising a blade portion and a flange portion that extends substantially perpendicularly relative to said blade portion, said flange portion positioned on a radially inner side of said annular spool; and
a fairing positioned on a radially outer side of said annular spool, wherein said fairing is configured to receive a fastener radially inserted through said flange portion and said annular spool such that said first rotor blade is secured to said annular spool.

2. The rotor assembly in accordance with claim 1 further comprising a second rotor blade configured to be radially inserted through a second blade opening defined in said annular spool, said second blade opening positioned adjacent said first blade opening, wherein said fairing is sized to extend between said first rotor blade and said second rotor blade.

3. The rotor assembly in accordance with claim 2 , wherein said fairing comprises a convex side edge configured to mate with said first rotor blade, and a concave side edge configured to mate with said second rotor blade.

4. The rotor assembly in accordance with claim 1 , wherein said fairing comprises a threaded opening defined therein, said threaded opening configured to threadably engage the fastener.

5. The rotor assembly in accordance with claim 1 , wherein said flange portion is oriented to extend circumferentially along the radially inner side of said annular spool.

6. The rotor assembly in accordance with claim 1 further comprising a radius filler positioned between a bent portion of said first rotor blade and a side wall of said first blade opening.

7. The rotor assembly in accordance with claim 1 , wherein said rotor blade is fabricated from a non-metallic material.

8. A turbofan engine comprising:
a low-pressure compressor comprising:
an annular spool comprising a first blade opening defined therein;
a first rotor blade configured to be radially inserted through said first blade opening, said first rotor blade comprising a blade portion and a flange portion that extends substantially perpendicularly relative to said blade portion, said flange portion positioned on a radially inner side of said annular spool; and
a fairing positioned on a radially outer side of said annular spool, wherein said fairing is configured to receive a fastener radially inserted through said flange portion and said annular spool such that said first rotor blade is secured to said annular spool.

9. The turbofan engine in accordance with claim 8 further comprising a second rotor blade configured to be radially inserted through a second blade opening defined in said annular spool, said second blade opening positioned adjacent said first blade opening, wherein said fairing is sized to extend between said first rotor blade and said second rotor blade.

10. The turbofan engine in accordance with claim 9 , wherein said fairing comprises a concave side edge configured to mate with said first rotor blade, and a convex side edge configured to mate with said second rotor blade.

11. The turbofan engine in accordance with claim 8 , wherein said fairing comprises a threaded opening defined therein, said threaded opening configured to threadably engage the fastener.

12. The turbofan engine in accordance with claim 8 , wherein said flange portion is oriented to extend circumferentially along the radially inner side of said annular spool.

13. The turbofan engine in accordance with claim 8 further comprising a radius filler positioned between a bent portion of said first rotor blade and a side wall of said first blade opening.

14. The turbofan engine in accordance with claim 8 , wherein said rotor blade is fabricated from a non-metallic material.

15. A method of assembling a rotor assembly for use in a turbofan engine, said method comprising:
defining a first blade opening within an annular spool;
inserting a first rotor blade through the first blade opening from a radially inner side of the annular spool, wherein the first rotor blade includes a blade portion and a flange portion that extends substantially perpendicularly relative to the blade portion such that the flange portion is positioned on a radially inner side of the annular spool;
positioning a fairing on a radially outer side of the annular spool; and
inserting a fastener through the flange portion, the annular spool, and into the fairing such that the first rotor blade is secured to the annular spool.

16. The method in accordance with claim 15 further comprising:
defining a threaded opening in the fairing;
defining a first fastener opening in the annular spool;
defining a second fastener opening in the flange portion of the first rotor blade; and
aligning the threaded opening, the first fastener opening, and the second fastener opening prior to inserting the fastener.

17. The method in accordance with claim 16 , wherein inserting a fastener comprises threadably engaging the fastener with the threaded opening in the fairing.

18. The method in accordance with claim 15 further comprising:
defining a second blade opening within the annular spool;
inserting a second rotor blade through the second blade opening from the radially inner side of the annular spool; and
extending the fairing between the first rotor blade and the second rotor blade.

19. The method in accordance with claim 15 , wherein inserting a first rotor blade comprises orienting the flange portion of the first rotor blade to extend circumferentially along the radially inner side of the annular spool.

20. The method in accordance with claim 15 further comprising positioning a radius filler between a bent portion of the first rotor blade and a side wall of the first blade opening.

Assignees

• Gen Electric

Inventors

• Anderson Todd Alan
• Kray Nicholas Joseph
• Walker Bryant Edward

Classifications

• F05B2260/30

  Retaining components in desired mutual position · CPC title

• F04D29/324

  Blades · CPC title

• F04D29/322 Primary

  Blade mountings · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title