Method of producing suspension for a structure in a turbojet engine using a hyperstatic trellis with pre-stressed link elements

Patent metadata

Field	Value
Publication number	US-10132241-B2
Application number	US-201414320795-A
Country	US
Kind code	B2
Filing date	Jul 1, 2014
Priority date	Jul 4, 2013
Publication date	Nov 20, 2018
Grant date	Nov 20, 2018

Abstract

A method of manufacturing an assembly including a first structure which is arranged to be rigidly connected to a housing of a turbojet engine; a second annular structure surrounding the first structure; and a hyperstatic trellis of connecting rods which maintains the first structure relative to the second structure, is provided. The method includes mounting the connecting rods of the hyperstatic trellis between the structures; and pre-stressing at least one of the connecting rods to a pre-determined level, which is carried out before the mounting thereof between the structures.

First claim

The invention claimed is:

1. A method of manufacturing an assembly comprising a first structure arranged to be rigidly connected to a housing of a turbojet engine, a second annular structure surrounding the first structure, and a hyperstatic trellis comprising a plurality of connecting rods, the plurality of connecting rods maintaining the first structure relative to the second annular structure, said method comprising;
mounting said plurality of connecting rods of the hyperstatic trellis between said first structure and said second annular structure;
pre-stressing at least one of said plurality of connecting rods to a predetermined level; carried out before the mounting of said plurality of connecting rods between said first structure and said second annular structure, said pre-stressing corresponding to a slight lengthening of said at least one of said plurality of connecting rods thereby placing said at least one of said plurality of connecting rods in a pre-stressed state; and
maintaining the pre-stressed state of said at least one of said plurality of connecting rods during mounting of said at least one of said plurality of connecting rods between said first structure and said second annular structure.

2. The method of manufacturing an assembly according to claim 1 , wherein each of said plurality of connecting rods comprises a spindle, a first end, and a second end, each of the first end and the second end being connected to a corresponding first and second yoke, each yoke being suitable for fixing to one of said first structure and said second annular structure, said pre-stressing step comprising:
placing the yokes of said at least one of said plurality of connecting rods in jaws of a traction actuator;
applying the pre-stressing at said predetermined level to the yokes of at least one of said plurality of connecting rods by operating said traction actuator;
installing shells around the spindle of said at least one of said plurality of connecting rods and locking the shells to each other to maintain separation of the yokes while the traction actuator maintains the pre-stressing at said predetermined level; and
releasing the pre-stressing applied to the yokes of said at least one of said plurality of connecting rods by the traction actuator.

3. The method of manufacturing an assembly according to claim 2 , further comprising removing the shells after said at least one of said plurality of connecting rods is mounted,
wherein the removing the shells includes the shells from each other.

4. The method of manufacturing an assembly according to claim 2 , wherein the shells comprise at least one non-deformable element extending along the spindle over most of a length of the spindle.

5. The method of manufacturing an assembly according to claim 4 , fasteners retain the shells along the spindle in order to maintain the separation of the yokes.

6. The method of manufacturing an assembly according to claim 4 , wherein each of said first and second yokes have a larger cross-section than the spindle in at least one direction perpendicular to the spindle, and wherein each shell has at least two contact surfaces which are oriented outwards in opposite directions and suitable for resting on a face of each of said first and second yokes which is turned towards the spindle.

7. The method of manufacturing an assembly according to claim 4 , wherein fasteners apply pressure to the shells against the spindle, preventing said spindle from retracting by friction against the non-deformable element.

8. The method according to claim 2 , wherein each connecting rod of said plurality of connecting rods is profiled and slightly flattened about a plane perpendicular to a plane of each of said yokes.

9. The method according to claim 1 , wherein the plurality of connecting rods comprises three pairs of connecting rods which are tangential to the first structure and converging in the pairs on the second annular structure.

10. The method according to claim 1 , wherein said plurality of connecting rods is arranged in a triangular shape between the first structure and the second annular structure, said plurality of connecting rods being tangential to the first structure.

11. The method according to claim 1 , wherein predetermined level is determined by calculating the stresses in the plurality of connecting rods for an ultimate load situation.

12. The method according to claim 1 , wherein each connecting rod of the plurality of connecting rods has a solid cross-section.

13. The method of manufacturing an assembly according to claim 2 , wherein a maintaining device for maintaining the separation of the yokes of the spindle comprises shells which comprises non-deformable elements extending along the spindle over most of a length of the spindle.

14. The method of manufacturing an assemble according to claim 13 , wherein fasteners retain the shells along the spindle in order to maintain the separation of the yokes.

15. The method of manufacturing an assembly according to claim 13 , wherein said yokes have a larger cross-section than the spindle in at least one direction perpendicular to the spindle, and wherein each shell has at least two contact surfaces which are oriented outwards in opposite directions and suitable for resting on a face of each of said yokes which is turned towards the spindle.

16. The method of manufacturing an assembly according to claim 13 , wherein fasteners apply pressure to the shells against the spindle, preventing said spindle from retracting by friction against the at least one non-deformable element.

17. A method of manufacturing an assembly comprising a first structure arranged to be rigidly connected to a housing of a turbojet engine, a second annular structure surrounding the first structure, and a hyperstatic trellis comprising a plurality of connecting rods, the plurality of connecting rods maintaining the first structure relative to the second annular structure, said method comprising:
mounting said plurality of connecting rods of the hyperstatic trellis between said first structure and said second annular structure; and
pre-stressing at least one of said plurality of connecting rods to a predetermined level, carried out before the mounting of said plurality of connecting rods between said first structure and said second annular structure,
wherein each of said plurality of connecting rods comprises a spindle, a first end and a second end, each first end and second end being connected to a corresponding first and second yoke, each yoke being suitable for fixing to one of said first structure and said second annular structure,
wherein said pre-stressing comprises:
placing each of the first and second yokes of said at least one of said plurality of connecting rods in jaws of a traction actuator;
applying the pre-stressing at said predetermined level to the first and second yokes of said at least one of said plurality connecting rods by operating said traction actuator;
installing shells around the spindle of said at least one of said plurality of connecting rods and locking the shells to each other to maintain separation of the first and second yokes while the traction actuator maintains the pre-stressing at said predetermined level; and
releasing the pre-stressing applied to the first and second yokes of said at least one of said plurality of connecting rods by the traction actuator, and

wherein the method further comprises removing the shells after said at least one of said plurality of connecting rods is mounted.

18. A method of manufacturing an a

Assignees

• Safran Aircraft Engines

Inventors

• Bellabal Francois Robert
• Florent Nicolas

Classifications

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F01D25/30

  Exhaust heads, chambers, or the like · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F02C7/20 Primary

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• Y10T29/49288

  Connecting rod making · CPC title