Composite material casing of stiffening shape

Patent metadata

Field	Value
Publication number	US-10995634-B2
Application number	US-201816123339-A
Country	US
Kind code	B2
Filing date	Sep 6, 2018
Priority date	Sep 6, 2017
Publication date	May 4, 2021
Grant date	May 4, 2021

Abstract

A gas turbine casing made of composite material, the casing presenting an axisymmetric shape and including, in an axial direction: an upstream flange; a retention zone presenting thickness greater than the remainder of the casing; and a downstream flange. The casing presents, in section on a plane defined by the axial direction and by a radial direction, a profile including at least first and second inclined portions that are inclined relative to each other and relative to the axis of the casing. The first and second inclined portions meet at a point situated between the retention zone and one of the flanges, this point corresponding to the vertex of an angle formed by the first and second inclined portions. The distance between the vertex of the angle and the mean radius of the casing lies in the range 1.5% and 4% of the mean radius of the casing.

First claim

The invention claimed is:

1. A gas turbine casing made of composite material comprising reinforcement densified by a matrix, said casing presenting an axisymmetric shape around an axis defining an axial direction of the casing, the casing comprising: an upstream flange; a retention zone presenting a maximum thickness of the casing; and a downstream flange; wherein the casing presents, in section on a plane defined by the axial direction and by a radial direction, a profile including at least first and second inclined portions that are inclined relative to each other and relative to the axis of the casing, the first and second inclined portions meeting at a point situated between the retention zone and one of the upstream and downstream flanges, said point corresponding to a vertex of an angle formed by the first and second inclined portions, and wherein a distance between the vertex of the angle and a mean radius of the casing relative to the axis lies in the range 1.5% to 4% of said mean radius of the casing.

2. The casing according to claim 1 , wherein the mean radius of the casing lies in the range 1 m to 2 m.

3. The casing according to claim 1 , wherein the mean radius of the casing is 1.7 m.

4. The casing according to claim 1 , wherein the angle formed by the first and second inclined portions is directed towards an inside of the casing in the radial direction.

5. The casing according to claim 1 , wherein the angle formed by the first and second inclined portions is directed towards an outside of the casing in the radial direction.

6. The casing according to claim 1 , wherein the vertex of the angle formed by the first and second inclined portions lies between the retention zone and the downstream flange.

7. The casing according to claim 1 , wherein the distance between the vertex of the angle and the mean radius of the casing lies in the range 2% and 3.5% of said mean radius of the casing.

8. A gas turbine engine having the casing according to claim 1 .

9. An aircraft having one or more of the gas turbine engine according to claim 8 .

10. A method of fabricating a composite material casing for a gas turbine engine, said casing presenting an axisymmetric shape around an axis defining an axial direction of the casing, the method comprising: using three-dimensional or multilayer weaving to weave a fiber texture as a single piece in the form of a strip; shaping said fiber texture by winding it onto support tooling so as to obtain a fiber preform that comprises, in the axial direction, a first portion forming a preform for an upstream flange, a second portion presenting a maximum thickness of the fiber preform in order to form a retention zone preform, and a third portion forming a preform for a downstream flange; and densifying the fiber preform with a matrix, wherein the fiber preform presents in section on a plane defined by the axial direction and by a radial direction a profile that includes at least first and second inclined portions that are inclined relative to each other and relative to the axial direction, the first and second inclined portions meeting at a point situated between the second portion of the fiber preform forming the retention zone preform and the first portion forming the upstream flange preform or the third portion forming the downstream flange preform, said point corresponding to a vertex of an angle formed by the first and second inclined portions, and wherein a distance between the vertex of the angle and a mean radius of the fiber preform relative to the axis lies in the range 1.5% to 4% of the mean radius of the fiber preform.

11. The method according to claim 10 , wherein the mean radius of the casing lies in the range 1 m to 2 m.

12. The method according to claim 10 , wherein the angle formed by the first and second inclined portions is directed towards an inside of the fiber preform in the radial direction.

13. The method according to claim 10 , wherein the angle formed by the first and second inclined portions is directed towards an outside of the fiber preform in the radial direction.

14. The method according to claim 10 , wherein the vertex of the angle formed by the first and second inclined portions lies between the retention zone preform and the downstream flange.

15. The method according to claim 10 , wherein the distance between the vertex of the angle and the mean radius of the casing lies in the range 2% and 3.5% of said mean radius of the fiber preform.

Assignees

• Safran Aircraft Engines

Inventors

• Zaccardi Cédric
• Saurat Mathilde Anaëlle Mélissia

Classifications

• B29B11/16

  comprising fillers or reinforcement {(non-woven fabrics per se D04H1/00, D04H3/00)} · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• 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

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title