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Method of manufacturing metal reinforcements for turbine engine blades

A kind of reinforcement, metal technology, applied in the direction of blade supporting elements, metal processing, metal processing equipment, etc., can solve the problems of complex manufacturing, high manufacturing cost, consumption, etc., and achieve the effect of reducing manufacturing cost

Active Publication Date: 2016-05-11
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

[0010] However, the metal reinforcement at the leading edge of the blade is a complex component to manufacture, requiring many complex remachining and machining operations, consuming high manufacturing costs

Method used

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  • Method of manufacturing metal reinforcements for turbine engine blades
  • Method of manufacturing metal reinforcements for turbine engine blades
  • Method of manufacturing metal reinforcements for turbine engine blades

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0048] In all views, common elements have the same reference numerals unless otherwise indicated.

[0049] figure 1 is a side view of a blade comprising a metal structural reinforcement of the leading edge obtained by the manufacturing method according to the invention.

[0050] The blades 10 shown in the figures are for example moving fan blades of a turbine engine (not shown).

[0051] The blade 10 includes an aerodynamic surface 12 extending in a first axial direction 14 between a leading edge 16 and a trailing edge 18 and generally perpendicular to the first direction 14 between a foot 22 and a head 24. The second axial direction 20 extends.

[0052] The aerodynamic surface 12 forms an upper surface 13 and a lower surface 11 of the blade 10, the upper surface 13 of the blade 10 being shown in figure 1 middle. The lower surface 11 and the upper surface 13 form the sides of the blade 10 connecting the leading edge 16 and the trailing edge 18 of the blade 10 .

[0053] I...

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PUM

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Abstract

The invention relates to a method of manufacturing a metal reinforcement (30) for the leading or trailing edge of a turbine engine blade (10), said metal reinforcement comprising a reinforcement foot (32) and a head (34). Said method comprises successively the steps of manufacturing a plurality of V-shaped conical elements (30a, 30b, 30c, 30d) forming different parts of said metal reinforcement (30) such that said metal reinforcement (30) dividing into a plurality of parts distributed between said foot (32) and said head (34); the step of positioning said parts on a tool whose shape corresponds to that of said turbine engine blade similar to said leading edge or trailing edge; a step of rigidly connecting said different parts to form said complete profile of said one-piece metal reinforcement (30) by rejoining said different parts.

Description

technical field [0001] The invention relates to a method of manufacturing metal reinforcements for composite or metal turbine engine blades. [0002] More specifically, the invention relates to a method of manufacturing a metal reinforcement for a leading edge of a turbine engine blade. Background technique [0003] The field of the invention is that of turboengines, and more particularly of fan blades for turboengines made of synthetic or metallic material, in which the leading edge comprises a metallic structural reinforcement. [0004] However, the invention is also applicable to the manufacture of metal reinforcements for reinforcing the leading edges of turbine engine blades. [0005] Recall that said leading edge corresponds to the front part of the aerodynamic profile, which faces the airflow, dividing it into a lower surface airflow and an upper surface airflow. The trailing edge corresponds to the rear part of the aerodynamic profile where the underflow and overfl...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P15/04F01D5/14F04D29/38B29C67/00B22F3/105
CPCB22F5/009B22F2003/247B22F2003/248B22F2998/10B23K15/006B23K37/047B23P15/04C22C14/00F01D5/147F01D5/282F05D2240/121F05D2240/303B29C66/12461B29C66/12463B29C66/301B29C66/53B29C66/721B29C66/742B29L2031/08B29L2031/082F05D2230/234F05D2230/236F05D2300/702B29C65/484B29C65/48B29C65/483F04D29/324Y10T29/49318Y10T29/49826Y10T29/4998B23K2101/001Y02P10/25F05D2220/36F01D5/288F05D2300/133B22F10/64B22F10/66B22F10/25B23K1/00B22F3/168B22F3/24B33Y80/00
Inventor 蒂里·吉恩·埃米尔·弗莱什吉恩-弗朗索瓦·弗朗蒙特斯特凡·安德鲁·莱韦克利蒂希亚·桑切斯
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A