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Shell mould for manufacturing aircraft turbomachine bladed elements using the lost-wax moulding technique and comprising screens that form heat accumulators

A lost-wax casting and turbine unit technology, used in manufacturing tools, casting molding equipment, casting mold components, etc., can solve problems such as non-reach, and achieve the effects of reduced shrinkage, good fluidity, and reduced heat loss

Inactive Publication Date: 2014-09-24
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In fact, with this smaller thickness, problems can arise with respect to the material not reaching the cavity defining these trailing edges

Method used

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  • Shell mould for manufacturing aircraft turbomachine bladed elements using the lost-wax moulding technique and comprising screens that form heat accumulators
  • Shell mould for manufacturing aircraft turbomachine bladed elements using the lost-wax moulding technique and comprising screens that form heat accumulators
  • Shell mould for manufacturing aircraft turbomachine bladed elements using the lost-wax moulding technique and comprising screens that form heat accumulators

Examples

Experimental program
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Embodiment Construction

[0075] Referring to Figure 1 , there is shown a sector 1 of a turbine low pressure supply for an aircraft turbomachine. The sector comprises a plurality of blades 2 arranged between a first end 4 and a second end 6 . The two ends 4, 6 form outer and inner coronal sectors, respectively, and each comprise a platform 8 which delimits a main airflow 10 of the airflow. In addition to the platform 8 for additional aerodynamic functions, each end also includes a conventional structure that allows the bladed member to be mounted on the turbomachine model.

[0076] The object of the present invention is to manufacture a feeder sector 1 by the method of lost wax casting, a preferred embodiment of which will now be described with reference to FIGS. 2 to 6 .

[0077] First, a model, also called a replica, is made of wax, around which the ceramic shell mold that is intended to be formed later is made.

[0078] In FIGS. 2 to 4 , the model 100 is shown in a reversed position relative to th...

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Abstract

The present invention relates to a shell mould (200) for manufacturing aircraft turbomachine bladed elements using the lost-wax moulding technique, and comprising: - shell mould bladed elements (1b) comprising a blade portion (2b) situated between a first end part (4b) delimiting the impression of a platform (8b) and a second end part (6b) delimiting the impression of another platform (8b), the blade portion comprising a trailing edge zone (30b); - a metal feeder (12b) having a central axis (14b) around which the bladed elements (1b) are distributed; and according to the invention, the shell mould is equipped with one or a number of screens (29b) that form accumulators of heat and are arranged in a shell mould interior space (28b) facing the inwardly-directed trailing edge zones (30b).

Description

technical field [0001] The invention relates to the field of cluster manufacturing of aircraft turbomachine bladed components using lost wax casting techniques. Each bladed member may be a sector comprising multiple blades, such as a low pressure supply sector, or may be a single blade, such as a blade of a turbine or compressor wheel. [0002] The invention relates more particularly to the design of cluster-shaped shell molds, in which metal is cast to obtain bladed components of turbomachines. [0003] The invention relates to aircraft turbomachines of all types, in particular turbojets and turboprops. Background technique [0004] In the prior art, it is actually known to manufacture several aircraft turbomachine bladed components simultaneously, such as feeder sectors or individual blades, using lost-wax casting techniques. [0005] Remember that the lost wax precision casting technique involves creating in wax a pattern for each bladed member desired by injection into...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B22C9/04B22C9/22
CPCB22D25/02F05D2230/211B22C9/04B22C9/088B22C9/082B22C9/22
Inventor 迪迪尔·古尔驰蒂博·达龙
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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