Variable thickness composite stator blade and molding method thereof

A composite material and stator blade technology, which is applied in the field of variable thickness composite material stator blades and their forming, and variable thickness stator blade integral forming fields, which can solve the problem of inability to meet the requirements of large variable thickness, high rigidity and high strength, and comprehensive performance that cannot meet the requirements of aero-engine stators. Blades and other issues, to achieve the effect of economic benefits, forward-looking and obvious technical advantages

Active Publication Date: 2019-11-12
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, domestic stator blades are made of metal, glass fiber reinforced plastic or low-performance carbon fiber composite materials, but the overall performance cannot meet the higher requirements of aero-engine stator blades. It is urgent to develop a lightweight, high sti

Method used

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  • Variable thickness composite stator blade and molding method thereof
  • Variable thickness composite stator blade and molding method thereof
  • Variable thickness composite stator blade and molding method thereof

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Embodiment 1

[0053] The variable thickness composite material stator blade described in the embodiment of the present invention includes a leading edge plate, a variable thickness blade body, and a trailing edge plate, and the variable thickness blade body is located between the leading edge plate and the trailing edge plate, and the leading edge plate, The variable-thickness airfoil and trailing edge plate are made of the same composite material, and the three are integrally formed. The windward side of the airfoil is protected by wear-resistant non-metallic wrapping. The reinforcement used for the manufacturing materials of the leading edge plate, blade body and trailing edge plate is T800 carbon fiber twill fabric, the resin matrix is ​​toughened 603 epoxy resin, and the grade of the prepared prepreg is T800-6k-XW / 603. After curing, the thickness of single layer is 0.2mm.

[0054] The thickness of the blade body is gradually changed from 5.5mm to 1.0mm from the root of the leading edge ...

Embodiment 2

[0066] The variable thickness composite material stator blade described in the embodiment of the present invention includes a leading edge plate, a variable thickness blade body, and a trailing edge plate, and the variable thickness blade body is located between the leading edge plate and the trailing edge plate, and the leading edge plate, The variable-thickness airfoil and trailing edge plate are made of the same composite material, and the three are integrally formed. The windward side of the airfoil is protected by wear-resistant non-metallic wrapping. The reinforcement used for the manufacturing materials of the leading edge plate, blade body and trailing edge plate is T800 carbon fiber twill fabric, the resin matrix is ​​toughened 602 epoxy resin, and the grade of the prepared prepreg is T800-6k-XW / 602. After curing, the thickness of single layer is 0.2mm.

[0067] The thickness of the blade body is gradually changed from 6.0mm to 1.2mm from the root of the leading edge ...

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Abstract

The invention relates to a variable thickness composite stator blade and a molding method thereof, in particular to the variable thickness stator blade integral molding technology and belongs to the technical field of advanced composites. The blade comprises a front edge plate, a variable thickness blade body and a rear edge plate which are integrally formed by the same material. The windward sideof the blade body is protected through a wear-resistant nonmetal edge wrapper. A forming mold is designed to a combined mold communicating four combined modules, and the forming mold is provided witha closed mold cavity. Tapered guiding and limiting matching surfaces are designed between the modules. Through combination of an extracted blade body neutral surface and a net volume filling method,a side line contour of laid prepreg layers conforming to the total thickness of different areas of the blade body is simulated and designed. A preform of the blade is manufactured from a continuous-filament woven fabric prepreg on four forming molds. Metal is embedded and inlaid in the corresponding position. The embedded part and the blade body are subjected to co-curing preparation through the hot pressing process. The molding method ensures that the stator blade can meet the requirements for the structural strength and stiffness and also meet the requirement for the precision of the moldedsurface of the aerodynamic configuration.

Description

technical field [0001] The invention relates to a variable-thickness composite stator vane and a molding method thereof, in particular to an integral forming technology of a variable-thickness stator vane, which belongs to the technical field of advanced composite materials. Background technique [0002] Resin-based composites have become a popular research material for aero-engine cold-end parts due to their good specific strength and specific modulus. After decades of development, resin-based composite materials have been widely used in the external casings, rotors and stator blades, containment casings, engine nacelles and thrust reversers of large bypass ratio turbofan engines and small bypass ratio afterburning turbofan engines. There are important applications in the device. [0003] More and more fiber-reinforced resin-based composites are used in the stator parts of aero-engines. For example, P&W's PW4056 / 4168 / 4084 engine fan outlet guide blades are made of pressed...

Claims

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Application Information

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IPC IPC(8): F01D9/04F01D25/00B29C70/34B29L31/08
CPCF01D9/041F01D25/005B29C70/342B29L2031/082
Inventor 杨智勇孙建波郭鸿俊易凯左小彪耿东兵程雷金鑫
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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