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CN108327165B - Manufacturing method of titanium alloy framework composite material casing - Google Patents

Manufacturing method of titanium alloy framework composite material casing Download PDF

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Publication number
CN108327165B
CN108327165B CN201810100368.3A CN201810100368A CN108327165B CN 108327165 B CN108327165 B CN 108327165B CN 201810100368 A CN201810100368 A CN 201810100368A CN 108327165 B CN108327165 B CN 108327165B
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titanium alloy
composite material
alloy framework
slurry
manufacturing
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CN108327165A (en
Inventor
黄东
魏战雷
张朋
南海
包建文
李建崇
李岩
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AECC Beijing Institute of Aeronautical Materials
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AECC Beijing Institute of Aeronautical Materials
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
    • B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
    • B29C45/1418—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles the inserts being deformed or preformed, e.g. by the injection pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C1/00—Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K15/00—Electron-beam welding or cutting
    • B23K15/0006—Electron-beam welding or cutting specially adapted for particular articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
    • B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
    • B29C45/1418—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles the inserts being deformed or preformed, e.g. by the injection pressure
    • B29C2045/14237—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles the inserts being deformed or preformed, e.g. by the injection pressure the inserts being deformed or preformed outside the mould or mould cavity
    • B29C2045/14245—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles the inserts being deformed or preformed, e.g. by the injection pressure the inserts being deformed or preformed outside the mould or mould cavity using deforming or preforming means outside the mould cavity

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Powder Metallurgy (AREA)

Abstract

The invention relates to a manufacturing method of a titanium alloy framework composite material casing, which comprises the following steps: step one, preparing a titanium alloy framework by adopting an investment casting process, wherein the investment casting process comprises the following steps: the shell refractory material is yttrium oxide, and the binder is zirconium diacetate; step two, mounting the titanium alloy framework into a die cavity of a composite material forming die, and then injecting composite material slurry into the die cavity, wherein the slurry comprises polyimide resin and carbon fiber, and the temperature of the slurry is as follows: 270-300 ℃, curing temperature: curing at 310-370 ℃ for 1.5-3 hours. By the method, the surface of the titanium alloy framework is subjected to electron beam texturing treatment, so that the connecting area of the titanium alloy and the resin matrix composite material is increased, the bonding strength of the titanium alloy and the resin matrix composite material is improved, and the developed intermediate case of the titanium alloy framework composite material has the characteristics of light weight and high strength.

Description

一种钛合金骨架复合材料机匣的制造方法A kind of manufacturing method of titanium alloy skeleton composite material casing

技术领域technical field

本发明涉及铸造技术领域及树脂基复材制造领域，特别涉及到一种钛合金骨架复合材料机匣的制造方法。The invention relates to the technical field of casting and the field of resin-based composite material manufacturing, in particular to a manufacturing method of a titanium alloy skeleton composite material casing.

背景技术Background technique

新一代航空发动机，其推重比将达到12～15，而中介机匣作为发动机冷端的重要承力部件，工作温度将提高到370℃左右，且有很高的减重要求。但由于中介机匣结构复杂，是发动机的主承力结构，如全部采用复合材料，机匣的强度、刚度则难以满足要求。此外全复合材料的耐370℃的复材机匣，整体成形难度大，因此科研人员开始研制以钛合金为骨架，具有一定耐温能力的包覆树脂基复合材料的钛合金骨架复合材料组合构件的制造方法。The thrust-to-weight ratio of a new generation of aero-engines will reach 12 to 15, and the intermediate casing, as an important load-bearing component of the engine's cold end, will increase its working temperature to about 370°C, and has high requirements for weight reduction. However, due to the complex structure of the intermediate casing, which is the main load-bearing structure of the engine, if all composite materials are used, the strength and rigidity of the casing are difficult to meet the requirements. In addition, the 370°C-resistant composite casing of all-composite materials is difficult to form as a whole. Therefore, researchers began to develop titanium alloy skeleton composite components with titanium alloy as the skeleton and coated with resin matrix composite materials with certain temperature resistance. manufacturing method.

发明内容SUMMARY OF THE INVENTION

本发明的目的是：通过对钛合金骨架的表面进行电子束毛化处理，增大了钛合金与树脂基复合材料的连接面积，提高了钛合金与树脂基复合材料的结合强度。The purpose of the invention is to increase the connection area between the titanium alloy and the resin-based composite material and improve the bonding strength of the titanium alloy and the resin-based composite material by carrying out electron beam texturing treatment on the surface of the titanium alloy skeleton.

本发明的技术方案是：The technical scheme of the present invention is:

提供一种钛合金骨架复合材料机匣的制造方法，包括如下步骤：Provided is a manufacturing method of a titanium alloy skeleton composite material casing, comprising the following steps:

步骤一、采用熔模铸造工艺制备钛合金骨架，熔模铸造工艺中：型壳耐火材料为氧化钇，粘结剂为二醋酸锆；对钛合金骨架的表面进行电子束毛化处理，形成高度1-2mm的毛刺，且毛刺密度为5-8个/cm2；Step 1. Use investment casting process to prepare titanium alloy skeleton. In the investment casting process, the refractory shell is yttrium oxide, and the binder is zirconium diacetate; the surface of the titanium alloy skeleton is subjected to electron beam texturing treatment to form a high 1-2mm burr, and the burr density is 5-8/cm2;

步骤二、将钛合金骨架安装到复合材料成型模具的模腔中，之后在模腔中注入复合材料料浆，料浆包括聚酰亚胺树脂和碳纤维，料浆温度为：270～300℃，固化温度：310～370℃，固化时间1.5～3小时。Step 2: Install the titanium alloy skeleton into the cavity of the composite material forming mold, and then inject the composite material slurry into the mold cavity. The slurry includes polyimide resin and carbon fiber. Curing temperature: 310～370℃, curing time 1.5～3 hours.

复杂的钛合金骨架构件可以采用熔模铸造制作，型壳面层及邻面层耐火材料为稳定化处理后的氧化钇，粘结剂为醋酸锆，耐火材料为稳定化处理后的氧化钇。热等静压的惰性气体为氩气，温度为920±10℃，保温时间2～2.5h，压力控制在110～140MPa。The complex titanium alloy skeleton member can be produced by investment casting. The refractory material of the shell surface layer and the adjacent surface layer is stabilized yttrium oxide, the binder is zirconium acetate, and the refractory material is stabilized yttrium oxide. The inert gas of the hot isostatic pressing is argon, the temperature is 920±10℃, the holding time is 2～2.5h, and the pressure is controlled at 110～140MPa.

本发明的优点是：通过本方法，对钛合金骨架的表面进行电子束毛化处理，增大了钛合金与树脂基复合材料的连接面积，提高了钛合金与树脂基复合材料的结合强度，研制出的钛合金骨架复合材料中介机匣具有重量轻，强度高的特点。The advantages of the present invention are: through the method, the surface of the titanium alloy skeleton is subjected to electron beam texturing treatment, which increases the connection area between the titanium alloy and the resin-based composite material, and improves the bonding strength of the titanium alloy and the resin-based composite material. The developed titanium alloy skeleton composite material intermediate receiver has the characteristics of light weight and high strength.

附图说明Description of drawings

图1为现有技术部件的示意图；1 is a schematic diagram of a prior art component;

图2为现有技术部件的局部示意图；Figure 2 is a partial schematic view of a prior art component;

具体实施方式Detailed ways

下面对本发明做进一步详细说明。The present invention will be described in further detail below.

提供一种钛合金骨架复合材料机匣的制造方法，包括如下步骤：Provided is a manufacturing method of a titanium alloy skeleton composite material casing, comprising the following steps:

步骤一、采用熔模铸造工艺制备钛合金骨架，熔模铸造工艺中：型壳耐火材料为氧化钇，粘结剂为二醋酸锆；对钛合金骨架的表面进行电子束毛化处理，形成高度1-2mm的毛刺，且毛刺密度为5-8个/cm2；Step 1. Use investment casting process to prepare titanium alloy skeleton. In the investment casting process, the refractory shell is yttrium oxide, and the binder is zirconium diacetate; the surface of the titanium alloy skeleton is subjected to electron beam texturing treatment to form a high 1-2mm burr, and the burr density is 5-8/cm2;

步骤二、将钛合金骨架安装到复合材料成型模具的模腔中，之后在模腔中注入复合材料料浆，料浆包括聚酰亚胺树脂和碳纤维，料浆温度为：270～300℃，固化温度：310～370℃，固化时间1.5～3小时。Step 2: Install the titanium alloy skeleton into the cavity of the composite material forming mold, and then inject the composite material slurry into the mold cavity. The slurry includes polyimide resin and carbon fiber. Curing temperature: 310～370℃, curing time 1.5～3 hours.

复杂的钛合金骨架构件可以采用熔模铸造制作，型壳面层及邻面层耐火材料为稳定化处理后的氧化钇，粘结剂为醋酸锆，耐火材料为稳定化处理后的氧化钇。热等静压的惰性气体为氩气，温度为920±10℃，保温时间2～2.5h，压力控制在110～140MPa。The complex titanium alloy skeleton member can be produced by investment casting. The refractory material of the shell surface layer and the adjacent surface layer is stabilized yttrium oxide, the binder is zirconium acetate, and the refractory material is stabilized yttrium oxide. The inert gas of the hot isostatic pressing is argon, the temperature is 920±10℃, the holding time is 2～2.5h, and the pressure is controlled at 110～140MPa.

Claims (1)

1.一种钛合金骨架复合材料机匣的制造方法，包括如下步骤：1. a manufacturing method of a titanium alloy skeleton composite material casing, comprising the steps: 步骤一、采用熔模铸造工艺制备钛合金骨架，熔模铸造工艺中：型壳耐火材料为氧化钇，粘结剂为二醋酸锆；对钛合金骨架的表面进行电子束毛化处理，形成高度1-2mm的毛刺，且毛刺密度为5-8个/cm2；Step 1. Use investment casting process to prepare titanium alloy skeleton. In the investment casting process, the refractory shell is yttrium oxide, and the binder is zirconium diacetate; the surface of the titanium alloy skeleton is subjected to electron beam texturing treatment to form a high 1-2mm burr, and the burr density is 5-8/cm 2 ; 步骤二、将钛合金骨架安装到复合材料成型模具的模腔中，之后在模腔中注入复合材料料浆，料浆包括聚酰亚胺树脂和碳纤维，料浆温度为：270～300℃，固化温度：310～370℃，固化时间1.5～3小时。Step 2: Install the titanium alloy skeleton into the cavity of the composite material forming mold, and then inject the composite material slurry into the mold cavity. The slurry includes polyimide resin and carbon fiber. Curing temperature: 310～370℃, curing time 1.5～3 hours.
CN201810100368.3A 2018-01-31 2018-01-31 Manufacturing method of titanium alloy framework composite material casing Active CN108327165B (en)

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Publication number Priority date Publication date Assignee Title
CN108356689B (en) * 2018-01-31 2020-08-11 中国航发北京航空材料研究院 Manufacturing method of titanium alloy intermediate casing support plate and flow channel
CN112711886B (en) * 2020-12-29 2024-04-09 中国航空工业集团公司西安飞机设计研究所 Finite element comparison modeling method for texturing connecting piece

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CN102151787A (en) * 2011-05-30 2011-08-17 哈尔滨工业大学 600-DEG C high-temperature titanium alloy fired mold casting type shell surface painting and preparation method thereof
CN102785428A (en) * 2012-08-02 2012-11-21 镇江江科机电工程有限公司 Wear resistant and self-lubricating PPS (polyphenylene sulfide)-metallic composite and preparation method thereof
CN104400283A (en) * 2014-09-25 2015-03-11 北京航星机器制造有限公司 Welding device for titanium alloy skin structural member for framework
CN104626543A (en) * 2015-01-12 2015-05-20 中国科学院宁波材料技术与工程研究所 Welding method for thermoplastic composite material
CN106624632A (en) * 2016-12-06 2017-05-10 上海航天精密机械研究所 Titanium alloy polyhedron rudder frame and preparation method thereof
CN107108010A (en) * 2014-12-09 2017-08-29 肖特兄弟公司 Fiber reinforcement part including nanostructured
CN107552360A (en) * 2017-07-07 2018-01-09 江苏欧钛克复合材料技术有限公司 A kind of method for improving polymer matrix composites surface spraying coating bond strength
CN107571985A (en) * 2017-08-25 2018-01-12 中国航空工业集团公司沈阳飞机设计研究所 A kind of ultralight whole wing structure of truss-like

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102151787A (en) * 2011-05-30 2011-08-17 哈尔滨工业大学 600-DEG C high-temperature titanium alloy fired mold casting type shell surface painting and preparation method thereof
CN102785428A (en) * 2012-08-02 2012-11-21 镇江江科机电工程有限公司 Wear resistant and self-lubricating PPS (polyphenylene sulfide)-metallic composite and preparation method thereof
CN104400283A (en) * 2014-09-25 2015-03-11 北京航星机器制造有限公司 Welding device for titanium alloy skin structural member for framework
CN107108010A (en) * 2014-12-09 2017-08-29 肖特兄弟公司 Fiber reinforcement part including nanostructured
CN104626543A (en) * 2015-01-12 2015-05-20 中国科学院宁波材料技术与工程研究所 Welding method for thermoplastic composite material
CN106624632A (en) * 2016-12-06 2017-05-10 上海航天精密机械研究所 Titanium alloy polyhedron rudder frame and preparation method thereof
CN107552360A (en) * 2017-07-07 2018-01-09 江苏欧钛克复合材料技术有限公司 A kind of method for improving polymer matrix composites surface spraying coating bond strength
CN107571985A (en) * 2017-08-25 2018-01-12 中国航空工业集团公司沈阳飞机设计研究所 A kind of ultralight whole wing structure of truss-like

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