Composite housing with reinforcing geometry
A composite material, shell technology, applied in the direction of liquid fuel engines, components of pumping devices for elastic fluids, machines/engines, etc. Shell manufacturing and installation equipment, etc., to improve the characteristics of vibration modes and avoid vibration modes
Active Publication Date: 2019-03-12
SAFRAN AIRCRAFT ENGINES SAS
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AI Technical Summary
Problems solved by technology
However, this solution leads to a substantial increase in the overall size and weight of the housing
Furthermore, due to the complex omega-shape of the housing, it was found difficult to manufacture and install equipment (e.g. acoustic panels, wearable boxes) on this type of housing
Finally, the cavity formed by the Ω-shaped part requires filling material, further detrimental to the overall weight of the case
Method used
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Embodiment Construction
[0035] The invention is generally applicable to any gas turbine casing made of composite material.
[0036] The invention is described below in the context of its application to a fan casing of a gas turbine aeroengine.
[0037] Such as figure 1 As schematically shown in , such an engine includes, from upstream to downstream along the flow direction of the airflow: a fan 1 arranged at the inlet of the engine; a compressor 2; a combustion chamber 3; a high-pressure turbine 4; and a low-pressure turbine 5.
[0038] The engine is housed within a housing comprising a number of sections corresponding to the different elements of the engine. The fan 1 is thus surrounded by an axisymmetric fan housing 10 .
[0039] figure 2 The profile of the fan housing 10 is shown, which is parallel to the axis A of the housing 10 10 The radial direction D A and by the radial direction DR Sections in defined planes correspond to . In this example, the housing 10 is made of an organic matrix ...
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Abstract
A gas turbine 10 casing made of composite material, the casing presenting an axisymmetric shape and including, in an axial direction DA: an upstream flange 14; a retention zone 15 presenting thicknessgreater than the remainder of the casing; and a downstream flange 16. The casing 10 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 radiusof the casing lies in the range 1.5% and 4% of the mean radius of the casing.
Description
technical field [0001] The present invention relates to gas turbine casings, and more particularly, but not exclusively, to gas turbine fan casings for aircraft engines. Background technique [0002] In gas turbine aero-engines, the fan casing performs several functions. In particular, it defines an air inlet passage into the engine, which optionally supports abradable material facing the tips of the fan blades and / or a sound absorber structure for acoustic treatment at the engine inlet, which incorporates or supports a retaining shroud . [0003] Housings, such as fan housings, used to be made of metallic materials, but are now made of composite materials, i.e. fiber preforms of composite materials densified with an organic matrix, enabling the manufacture of components that, when they When made of metallic material, the part has a lower overall weight than the same part, while also having at least equal, if not greater, mechanical strength. A fan housing made of organic...
Claims
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IPC IPC(8): F04D29/52
CPCF04D29/522F05D2300/601F05D2300/603F01D25/24F05D2220/36F01D25/243F05D2240/14Y02T50/60B29B11/16B29C70/24B29L2031/7504F05D2260/96F05D2300/6033
Inventor 塞德里克·扎卡蒂玛蒂尔德·安内尔·梅丽西亚·索拉特
Owner SAFRAN AIRCRAFT ENGINES SAS