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Blade body shaping method of ceramic matrix composite turbine guide blade with cooling cavity

A technology of turbine guide vanes and composite materials, which is applied in the field of airfoil shaping of ceramic matrix composite material turbine guide vanes, can solve problems such as complicated procedures and unreliable structure of turbine guide vanes, improve cooling effect, avoid air leakage problems, The effect of good process adaptability

Active Publication Date: 2022-03-01
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the above-mentioned technical problems, the object of the present invention is to provide a method for shaping the airfoil of a ceramic matrix composite turbine guide vane containing a cooling cavity, so as to solve the problem of using a ceramic matrix composite material to prepare a turbine guide vane containing a cooling cavity in the prior art. The process is complicated and the structure of the turbine guide vane is unreliable

Method used

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  • Blade body shaping method of ceramic matrix composite turbine guide blade with cooling cavity
  • Blade body shaping method of ceramic matrix composite turbine guide blade with cooling cavity
  • Blade body shaping method of ceramic matrix composite turbine guide blade with cooling cavity

Examples

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Effect test

Embodiment 1

[0035] A method for shaping the airfoil of a ceramic matrix composite turbine guide vane containing a cooling cavity, comprising the following steps:

[0036] (1) Taking each cooling cavity 1 of the blade body as a reference, prepare a mandrel 4 respectively, take the blade back 2 as a reference, prepare an outer mold 5 with a wall thickness of 5 mm, and prepare a wall thickness of 5 mm with the leaf basin 3 as a reference. 5mm outer mold two 6; wherein, the core mold 4, the outer mold one 5 and the outer mold two 6 all have some diameters perpendicular to the molding surface and are 2.5mm ventilation holes 7, and the core mold 4, the outer mold one 5 and the outer mold are prepared The materials of 26 are all high-purity graphite;

[0037] (2) Wrap the two-dimensional carbon fiber woven cloth along the mandrel 4 of each cooling cavity 1, the thickness of which is 0.52 times the thickness of the blade body, to form a single-cavity fiber prefabricated body, and then splicing ac...

Embodiment 2

[0041] A method for shaping the airfoil of a ceramic matrix composite turbine guide vane containing a cooling cavity, comprising the following steps:

[0042] (1) Taking each cooling chamber 1 of the blade body as a reference, prepare the mandrel 4 respectively, take the blade back 2 as a reference, prepare an outer mold-5 with a wall thickness of 3 mm, and prepare a wall thickness of 3 mm with the leaf basin 3 as a reference. 3mm outer mold two 6; wherein, core mold 4, outer mold one 5 and outer mold two 6 all have some diameters perpendicular to the profile surface and are 2mm ventilation holes 7, and core mold 4, outer mold one 5 and outer mold two are prepared 6 materials are electrode graphite;

[0043] (2) Wind the 2.5-dimensional silicon carbide fiber woven cloth along the mandrel 4 of each cooling cavity 1. The thickness of the winding is 0.5 times the thickness of the blade body to form a single-cavity fiber prefabricated body, and then spliced ​​according to the desi...

Embodiment 3

[0047] A method for shaping the airfoil of a ceramic matrix composite turbine guide vane containing a cooling cavity, comprising the following steps:

[0048] (1) Taking each cooling chamber 1 of the blade body as a reference, prepare the mandrel 4 respectively, take the blade back 2 as a reference, prepare an outer mold-5 with a wall thickness of 10 mm, and use the leaf pot 3 as a reference to prepare a wall thickness of Outer mold two 6 of 10mm; Wherein, mandrel 4, outer mold one 5 and outer mold two 6 all have some diameters perpendicular to the molded surface and are 5mm ventilation holes 7, prepare core mold 4, outer mold one 5 and outer mold two 6 materials are electrode graphite;

[0049] (2) Wrap the carbon fiber unidirectional tape along the mandrel 4 of each cooling cavity 1, the thickness of which is 0.6 times the thickness of the blade body, to form a single-cavity fiber prefabricated body, and then splicing according to the design drawing to form a split fiber pre...

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Abstract

The invention discloses a blade body shaping method of a ceramic matrix composite turbine guide blade with a cooling cavity, which comprises the following steps: preparing core molds, an outer mold I and an outer mold II of a blade body, then winding fiber cloth along each core mold, then splicing according to a design drawing to form a spliced fiber preform, and finally forming the spliced fiber preform into the ceramic matrix composite turbine guide blade with the cooling cavity. Then the same fiber cloth is wound along the periphery of the spliced fiber prefabricated body, the obtained whole blade body fiber prefabricated body is clamped among the first outer mold, the second outer mold and the core mold, the first outer mold and the second outer mold are fixed, finally, the first outer mold, the second outer mold, the whole blade body prefabricated body and the core mold are sewn into a whole through suture lines, and blade body shaping of the blade is completed. According to the method, integral shaping of the blade body containing the multiple cooling cavities can be completed at a time, the method is simple, the structural stability of the cooling cavities is greatly improved for the blade body parts prepared after shaping is conducted through the method, the air leakage problem among the multiple cooling cavities is avoided, and therefore the structural reliability and the cooling effect of components are improved.

Description

technical field [0001] The invention relates to the technical field of gas turbine engine manufacture, in particular to a blade body shaping method for a ceramic matrix composite material turbine guide vane with a cooling cavity. Background technique [0002] In gas turbine engine structures such as aeroengines and gas turbines, the role of the turbine system is to convert part of the heat and potential energy in the high-temperature gas into mechanical work to drive the compressor and accessories. The turbine system is the thermal load and power load of the gas turbine engine. The largest system is characterized by large output power, high operating temperature, light weight requirements, and small structural size. The main hot-end components in the turbine system include guide vanes, turbine outer rings, turbine disks, rotor blades, etc. Among them, the turbine inlet The guide vane is the part with the highest working temperature in the turbine system. Its function is to c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80F01D9/02F01D25/12
CPCC04B35/80F01D9/02F01D25/12C04B2235/5244C04B2235/5248C04B2235/5256Y02T50/60
Inventor 刘持栋张海昇栗尼娜刘小冲涂建勇陈超成来飞
Owner NORTHWESTERN POLYTECHNICAL UNIV
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