Composite material casing of stiffening shape

Patent metadata

Field	Value
Publication number	US-2019072003-A1
Application number	US-201816123339-A
Country	US
Kind code	A1
Filing date	Sep 6, 2018
Priority date	Sep 6, 2017
Publication date	Mar 7, 2019
Grant date	—

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

1 . A gas turbine casing made of composite material comprising reinforcement densified by a matrix, said casing presenting an axisymmetric shape, the casing comprising, in an axial direction: an upstream flange; a retention zone presenting thickness greater than the remainder 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 flanges, said point corresponding to the vertex of an angle formed by the first and second inclined portions, and wherein the distance between the vertex of the angle and the mean radius of the casing lies in the range 1.5% to 4% of said mean radius of the casing.

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

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

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

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

6 . A 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 . A 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 a casing according to claim 1 .

9 . An aircraft having one or more engines according to claim 8 .

10 . A method of fabricating a composite material casing for a gas turbine, 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 texture by winding it onto support tooling so as to obtain a fiber preform that comprises, in an axial direction, a first portion forming a preform for an upstream flange, a second portion presenting thickness greater than the thickness of the remainder of the 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 during shaping, the fiber texture is shaped in such a manner as to obtain a fiber preform presenting 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 preform forming a retention zone preform and the first portion forming an upstream flange preform or the third portion forming a downstream flange preform, said point corresponding to the vertex of an angle formed by the first and second inclined portions, and wherein the distance between the vertex of the angle and the mean radius of the preform lies in the range 1.5% to 4% of the mean radius of the preform.

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

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

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

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

15 . A 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 casing.

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

• F01D25/243 Primary

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F04D29/522 Primary

  especially adapted for elastic fluid pumps · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title