Eliminating method for low-melting-point alloy of blade inner cavities

A low-melting-point, blade-in-the-blade technology, applied in the engine field, can solve the problems of residual low-melting point alloys and residues, and achieve the effect of reducing removal time and improving work efficiency

Active Publication Date: 2017-05-31
CHINA HANGFA SOUTH IND CO LTD
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  • Abstract
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  • Claims
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Problems solved by technology

Since the low-melting-point alloy and the hot oil will be mixed together during the melting process of the low-melting-point alloy, when the guide vane 1 is taken out, the hot oil may remain in the cavity channel of the airfoil 12, thereby resulting in residual low-melting-point alloys

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  • Eliminating method for low-melting-point alloy of blade inner cavities
  • Eliminating method for low-melting-point alloy of blade inner cavities
  • Eliminating method for low-melting-point alloy of blade inner cavities

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Embodiment Construction

[0020] In order to have a clearer understanding of the technical features, purposes and effects of the present invention, the specific implementation manners of the present invention will now be described with reference to the accompanying drawings. Wherein, the same parts adopt the same reference numerals.

[0021] figure 1 It is a structural schematic diagram of a guide vane of a gas turbine engine; figure 2 for another angle figure 1 Schematic diagram of the structure of the guide vane; image 3 It is a schematic diagram of the structure and principle of the device used in the method for removing the low-melting-point alloy in the inner cavity of the blade according to a specific embodiment of the present invention. see Figure 1-3 As shown, the present invention provides a method for removing low-melting-point alloys in the inner cavity of a blade. The blade 1 is composed of an outer edge plate 11, a blade body 12, and an inner edge plate 13. The blade body 12 is prov...

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Abstract

The invention provides an eliminating method for low-melting-point alloy of blade inner cavities. The eliminating method comprises the following steps that (A) a plurality of blades are clamped on a mounting disc through mounting frames according to the same encircling direction, conveyed oil in a cooling tank is sprayed into an oil barrel through a spraying opening after being heated till the temperature is 180 DEG C, and the mounting disc is lowered to enable the blades to be stored in the hot oil of the oil barrel for 5-8 min; and (B) the mounting disc begins to revolve according to the speed being 20-30 RPM, after revolving is conducted for 8-10 min, the mounting disc is lifted to enable the bottom face of the mounting frames to rise to the position above the oil barrel, and thus eliminating of the low-melting-point alloy of the blades is completed. According to the eliminating method for the low-melting-point alloy of the blade inner cavities, on the one hand, the eliminating time of the low-melting-point alloy is effectively reduced; and in addition, the effect that the blade inner cavities after eliminating operation is free of residues is effectively guaranteed, and additionally, low-melting-point alloy eliminating operation can be continuously conducted in batches, so that working efficiency is greatly improved.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a method for removing low-melting-point alloys from the inner cavity of a hollow guide vane of a gas turbine engine. Background technique [0002] figure 1 It is a structural schematic diagram of a guide vane of a gas turbine engine, figure 2 for another angle figure 1 Schematic diagram of the structure of the guide vane, see Figure 1-2 As shown, the guide vane 1 is composed of an outer edge plate 11, a blade body 12, and an inner edge plate 13. The blade body 12 is provided with a trailing edge hole 121, and the middle part of the outer edge plate 11 is provided with an outer edge cavity. 111, the middle part of the inner edge plate 13 is provided with an inner edge cavity 131, and the blade body 12 is provided with a cavity connecting the trailing edge hole 121 with the outer edge cavity 111 and the inner edge cavity 131. lumen channel, [0003] In the process of process...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23F4/04
CPCC23F4/04
Inventor 蒋志平张小青叶利丽
Owner CHINA HANGFA SOUTH IND CO LTD
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