Balanced turbine engine portion and turbine engine

Patent metadata

Field	Value
Publication number	US-10415424-B2
Application number	US-201415037549-A
Country	US
Kind code	B2
Filing date	Nov 24, 2014
Priority date	Nov 26, 2013
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A balanced turbomachine part including one angular sector arranged to form a balancing ring centered about a ring axis. The angular sector includes a plurality of fasteners, a bearing face having a complementary shape to the balancing ring, the angular sector bearing on the bearing face. The part further includes a plurality of balancing masses each fastened to the corresponding fastener of the angular sector, at least one of the balancing masses also acting as a fastener for fastening the angular sector on the bearing face.

First claim

The invention claimed is:

1. A balanced turbomachine part comprising:
at least one angular sector arranged to form a balancing ring centered about a ring axis, the angular sector including a plurality of fasteners each adapted to fasten at least one respective balancing mass, the fasteners each including a threading axis, all the threading axes substantially converging at a same point on the ring axis;
a bearing face having a shape complementary to the balancing ring, the angular sector bearing on the bearing face; and
a plurality of balancing masses each fastened to the corresponding fastener of the angular sector, at least one of the balancing masses also acting as a fastener for fastening the angular sector to the bearing face,
wherein the fasteners are nuts, and the balancing masses are screws,
wherein a perimeter of the balancing ring includes a plurality of nut locations substantially evenly distributed along the balancing ring, each of the nut locations including a through hole and a mounting system for mounting the nut, and
wherein the mounting system includes a portion of the balancing ring in a form of a side flare forming a nut support, a width of the nut support being greater than a width of the nut, the nut support including two side extensions presenting an L-shaped cross section.

2. The balanced turbomachine part according to claim 1 , wherein the angle of the angular sector is between 20° and 360°.

3. The balanced turbomachine part according to claim 1 , wherein the threading axis of each of the fasteners is substantially radially oriented with respect to the angular sector.

4. The balanced turbomachine part according to claim 1 , wherein each fastener is held in place by side extensions crimped by folding.

5. The balanced turbomachine part according to claim 1 , wherein the balancing ring has a cylindrical or frustro-conical revolution shape.

6. The balanced turbomachine part according to claim 1 , wherein the fasteners are substantially evenly distributed along the angular sector.

7. The balanced turbomachine part according to claim 1 , wherein the turbomachine part is a turbomachine inlet cone.

8. A method for balancing a turbomachine part comprising a bearing face, the method comprising:
providing at least one angular sector for forming a balancing ring centered about a ring axis, the angular sector including a plurality of fasteners each adapted to fasten at least one respective balancing mass, the fasteners each including a threading axis, all the threading axes substantially converging at a same point on the ring axis;
bringing the angular sector to bear on the bearing face of the turbomachine part to be balanced so as to form a balancing ring; and
fastening at least one balancing mass on one of the fasteners of the angular sector so as to fasten the angular sector and to balance the turbomachine part,
wherein the fasteners are nuts, and the balancing masses are screws,
wherein a perimeter of the balancing ring includes a plurality of nut locations substantially evenly distributed along the balancing ring, each of the nut locations including a through hole and a mounting system for mounting the nut, and
wherein the mounting system includes a portion of the balancing ring in a form of a side flare forming a nut support, a width of the nut support being greater than a width of the nut, the nut support including two side extensions presenting an L-shaped cross section.

9. A turbomachine comprising one balanced turbomachine part according to claim 1 .

10. The balanced turbomachine part according to claim 1 , wherein the mounting system includes two outgrowths extending radially inward on either side of the nut support, the outgrowths forming stops.

11. The balanced turbomachine part according to claim 10 , wherein each nut includes a platen including an aperture corresponding to the through hole at the nut location, a first face which abuts the nut support when the nut is positioning on the mounting system, and a second face including side edges which rest on the side extensions of the nut support.

12. The balanced turbomachine part according to claim 11 , wherein the aperture of the nut is extending by a sleeve that extends substantially perpendicular to the second face of the platen.

13. The balanced turbomachine part according to claim 1 , wherein the screws include a first screw and a second screw, a mass of the first screw being different than a mass of the second screw.

Assignees

• Snecma
• Safran Aircraft Engines

Inventors

• Le Strat Jean-Luc
• Pohier Herve

Classifications

• G01M1/36

  by adjusting position of masses built-in the body to be tested · CPC title

• F16F15/34

  Fastening arrangements therefor · CPC title

• F01D5/027 Primary

  Arrangements for balancing (for balancing rotating bodies in general F16F15/32; for compensating imbalance G01M1/36) · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F05D2230/60

  Assembly methods · CPC title