WO2019184855A1 - 一种航空发动机整体叶盘的加工方法及设备 - Google Patents

一种航空发动机整体叶盘的加工方法及设备 Download PDF

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Publication number
WO2019184855A1
WO2019184855A1 PCT/CN2019/079475 CN2019079475W WO2019184855A1 WO 2019184855 A1 WO2019184855 A1 WO 2019184855A1 CN 2019079475 W CN2019079475 W CN 2019079475W WO 2019184855 A1 WO2019184855 A1 WO 2019184855A1
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axis
shaft
leaf disc
leaf
drives
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PCT/CN2019/079475
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English (en)
French (fr)
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高素芳
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北京汉飞航空科技有限公司
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Publication of WO2019184855A1 publication Critical patent/WO2019184855A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H7/00—Processes or apparatus applicable to both electrical discharge machining and electrochemical machining
    • B23H7/02—Wire-cutting
    • B23H7/08—Wire electrodes
    • B23H7/10—Supporting, winding or electrical connection of wire-electrode
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H11/00—Auxiliary apparatus or details, not otherwise provided for
    • B23H11/003—Mounting of workpieces, e.g. working-tables
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
    • B23H7/00—Processes or apparatus applicable to both electrical discharge machining and electrochemical machining
    • B23H7/02—Wire-cutting

Definitions

  • the invention relates to a method and a device for processing an overall blade of an aircraft engine, and belongs to the technical field of electric discharge machining.
  • the integral blade disc is designed as a whole with the blades and discs of the engine rotor. It can be manufactured by integral machining or welding (the blade and the disc material can be different) without the need to machine the boring head and the boring.
  • the overall structure has the advantages that the radial height of the rim of the blade disc, the thickness and the size of the blade head can be greatly reduced, and the weight reduction effect is obvious; the rotor component of the engine
  • the structure is greatly simplified; the escape loss of gas in the gap of the root of the split tooth structure is eliminated; the fretting wear caused by improper assembly of the blade and the wheel disc, the crack and the failure caused by the damage of the lock piece are avoided, thereby contributing to the improvement of the engine Work efficiency and reliability are further enhanced.
  • the integral leaf disc has so many advantages, but it also encounters many problems during the processing of the whole leaf disc.
  • the whole leaf disc processing mainly adopts two methods of numerical control milling and electrochemical electrolysis, but each has its own advantages and disadvantages.
  • CNC milling technology is a common processing method for the whole leaf disc.
  • the whole leaf disc channel is a special curved cavity structure.
  • the traditional milling method uses the end mill side milling, and the side milling cutter is subjected to radial force.
  • the depth of the milling depth is increased, and the rigidity of the tool is deteriorated.
  • Under the action of the radial force the deformation, vibration and wear of the tool are intensified, and the efficiency of the force is significantly reduced.
  • the numerical control milling slotting method solves some of the above problems.
  • the cutting force of CNC milling is large, the blade is susceptible to deformation, the tool and the leaf disc are easy to interfere, and the tool wear is serious.
  • Another processing method of the whole leaf disc is numerically controlled electrolytic processing.
  • electrolytic processing There are also some shortcomings in electrolytic processing. There are many influencing factors in processing, and the processing stability and repeatability are relatively poor, especially when processing closed whole leaf disc parts.
  • the leaf channel is complicated by bending and twisting, and the flushing problem is difficult to solve.
  • the current requirements are high, and the electrolyte and electrolysis products need special treatment, and the environmental pollution is serious.
  • the present invention provides a method and a device for processing an overall blade of an aircraft engine.
  • the utility model relates to a processing device for an overall blade of an aircraft engine, wherein an X-axis table is placed on a machine bed, a Y-axis table is placed on an X-axis table, and an X-axis table and a Y-axis table are crossed by a two-axis direction;
  • the A-axis turret is placed on the Y-axis table, the Z-axis table is placed on the A-axis turret of the machine, the Z-axis table is connected to the C-axis turret, the C-axis turret is connected to the leaf disc, and the C-axis turret is connected to the Z-axis table.
  • the Z-axis table is placed at the upper end of the column, and the U-axis and the V-axis are connected under the Z-axis table.
  • the upper arm is connected to the U-axis and the V-axis.
  • the Z-axis is placed at the lower end of the column, and the Z-axis is connected to the lower arm. On the bed behind the column.
  • the central axis of the A-axis turret is parallel to the axis of the X-axis table.
  • the A-axis turntable of the machine tool rotates the leaf disc with the central axis of the A-axis turntable.
  • the Z-axis table moves the leaf disc vertically to adjust the cutting height of the leaf disc.
  • the C-axis turntable connects the leaf disc to rotate horizontally, so that the molybdenum wire can cut different angles. The flow path between the blades.
  • One end of the molybdenum wire is connected to the wire barrel, and the other end of the molybdenum wire is connected to the wire barrel through the lower arm and the upper arm, that is, the molybdenum wire is coiled and connected to the wire barrel.
  • the V-axis table is connected below the Z-axis table
  • the U-axis table is connected to the lower end of the V-axis table
  • the upper arm is connected to the U-axis table.
  • the utility model relates to a processing device for an overall blade of an aeroengine, comprising a rotating shaft and a linear shaft of the machine tool, wherein the X axis is at the lower end, the Y axis is placed on the X axis, the two axes are at a 90 degree cross, and the X axis and the Y axis are driven by the leaf disc.
  • the blank moves horizontally; the A-axis turret is placed on the Y-axis, the A-axis of the machine tool drives the leaf discs to rotate around X, and the Z1 axis is placed on the A-axis, which drives the leaf disc to move vertically, adjusting the cutting height of the leaf disc; C-axis turret connection On the Z1 axis, the C axis controls the horizontal rotation of the leaf disc so that the molybdenum wire can cut the blades of different angular directions; the Z axis is placed at the upper end of the column, the V axis is connected to the lower side, the U axis is connected to the lower end of the V axis, and the upper arm is connected to the U axis.
  • the Z2 axis is placed at the lower end of the column and the lower arm is connected to the Z2 axis.
  • the X-axis and Y-axis of the machine tool drive the blade blank to move horizontally; the Z-axis and Z2 axis of the machine tool drive the vertical movement of the upper and lower wire arms to control the opening of the molybdenum wire in the processing area; the blank parts of the leaf disk are clamped on the C-axis turntable.
  • the horizontal rotation of the leaf disc is controlled by the C axis, so that the molybdenum wire can cut the blades of different angular directions.
  • the A-axis of the machine tool drives the leaf discs to rotate around X respectively, and realizes multi-angle cutting trajectory by linkage with the U-axis and the V-axis;
  • the disc moves vertically to adjust the cutting height of the leaf disc;
  • the U-axis and the V-axis drive the upper arm to horizontally move the yaw molybdenum wire to cut the angle.
  • a method for processing an overall blade of an aircraft engine comprising the following steps;
  • Step 1 the X-axis and the Y-axis of the machine tool drive the blade blank to move horizontally to the starting point;
  • Step 2 The Z1 axis drives the leaf disc to move vertically, and adjusts the cutting height of the leaf disc.
  • Step 3 The blank part of the leaf disc is clamped on the C-axis turntable, and the horizontal rotation of the leaf disc is controlled by the C-axis, so that the molybdenum wire can cut the flow path between the blades in different angular directions.
  • Step 4 The A-axis of the machine tool drives the leaf discs to rotate around X respectively, and drives the molybdenum wire to realize the cutting of the contour path of the flow path between the blades by interlocking with the U-axis, the V-axis, the X-axis and the Y-axis, and the continuous molybdenum wire spark discharge
  • the workpiece is subjected to discharge etching to cut out the shape of the formed flow path.
  • the invention has the advantages that the traditional wire cutting processing principle is applied to the groove processing of the whole leaf disk flow channel, and the machining vibration deformation problem has little influence and no influence due to the no cutting force and stress in the wire electric discharge machining process. There is a problem with tool wear. Significantly reduced processing costs and improved processing efficiency.
  • Figure 1 is a schematic view of the structure before assembly of the present invention.
  • Figure 2 is a schematic view of the assembled structure of the present invention.
  • Figure 3 is a view showing the processing state of the present invention.
  • Figure 4 is a structural view of the wire barrel device of the present invention.
  • Embodiment 1 As shown in FIG. 1 , FIG. 2 , FIG. 3 and FIG. 4 , a method for processing an overall blade of an aircraft engine, comprising the following steps;
  • Step 1 the X-axis and the Y-axis of the machine tool drive the blade blank to move horizontally to the starting point;
  • Step 2 The Z1 axis drives the leaf disc to move vertically, and adjusts the cutting height of the leaf disc.
  • Step 3 The blank part of the leaf disc is clamped on the C-axis turntable, and the horizontal rotation of the leaf disc is controlled by the C-axis, so that the molybdenum wire 15 can cut the flow path between the blades in different angular directions.
  • Step 4 the A-axis of the machine tool drives the leaf discs to rotate around the X-axis respectively, and the molybdenum wire 15 is driven by the U-axis, the V-axis, the X-axis, and the Y-axis to realize the cutting of the contour path of the flow passage between the blades, and the spark is continuously passed through the molybdenum wire 15
  • the discharge discharges the workpiece to cut out the shape of the formed runner.
  • Embodiment 2 As shown in FIG. 1 , FIG. 2 , FIG. 3 and FIG. 4 , a processing device for an aeroengine integral leaf disc comprises a column, a bed, each rotating shaft and a linear shaft, and the X-axis table 10 is placed On the machine bed 11, the Y-axis table 9 is placed on the X-axis table 10, and the X-axis table 10 intersects the two-axis direction of the Y-axis table 90 at 90 degrees.
  • the A-axis turntable 8 is placed on the Y-axis table 9, the Z1-axis table 7 is placed on the A-axis turntable 8 of the machine tool, the Z1-axis table 7 is connected to the C-axis turntable 6, and the C-axis turntable 6 is connected to the leaf disc 13, the machine tool
  • the A-axis turntable 8 rotates the leaf discs 13 about the X-axis 10, respectively, and the X-axis 10 is horizontally mounted.
  • the Z1 axis table 7 drives the leaf disc 13 to move vertically, adjusts the cutting height of the leaf disc 13, the C-axis turret 6 is connected to the Z1 axis table 7, and the C-axis turret 6 controls the leaf disc 13 to rotate horizontally so that the molybdenum wire 15 can be cut. Flow paths between the blades at different angular directions.
  • the Z-axis table 4 is placed at the upper end of the column 12, the U-axis and the V-axis 5 are connected under the Z-axis table 4, the upper arm 3 is connected to the U-axis and the V-axis 5, and the Z2 axis 14 is placed at the lower end of the column 12, and the Z2 axis 14
  • the lower arm 2 is connected, and the package device 1 is placed on the bed 11 behind the column 12.
  • the molybdenum wire 15 is connected to the wire barrel device 1.
  • the other end of the molybdenum wire 15 is connected to the wire barrel device 1 after being connected to the lower wire arm 2 and the upper wire arm 3, that is, the molybdenum wire 15 is wound around the wire of the wire barrel device 1.
  • the left bracket 16 of the package device 1 is connected to one end of the package 18 through a left insulating disk 20, and the right bracket 17 of the package device 1 is connected to one end of the package 18 through a right insulating disk 19.
  • Embodiment 3 As shown in FIG. 1, FIG. 2, FIG. 3 and FIG. 4, a method and a device for processing an overall aero-engine leaf disc (a nine-axis five-link EDM wire cutting machine), the principle of the conventional wire cutting process Applied to the whole leaf disc flow channel slotting processing, due to the absence of cutting force in the wire EDM, the machining vibration deformation problem has little effect, and there is no problem of tool wear. Significantly reduced processing costs and improved processing efficiency.
  • a method for processing an overall blade of an aircraft engine comprising the following steps;
  • the X and Y axes of the machine tool move the blade blank horizontally.
  • the Z-axis and Z2 axis of the machine tool drive the upper and lower arm to move vertically, and control the size of the opening of the molybdenum wire 15 in the processing area.
  • the Z1 axis drives the leaf disc to move vertically, adjusting the cutting height of the leaf disc.
  • the blank part of the leaf disc is clamped on the C-axis turret, and the horizontal rotation of the leaf disc is controlled by the C-axis, so that the molybdenum wire 15 can cut the blades of different angular directions.
  • the A-axis of the machine tool drives the leaf discs to rotate around X respectively, and realizes multi-angle cutting trajectory by interlocking with the U-axis and the V-axis.
  • the U-axis and the V-axis drive the upper arm to horizontally move the yaw molybdenum wire 15 to cut the angle.
  • the moving fine metal wire (copper wire or molybdenum wire 15) is used as one electrode, the workpiece is used as the other electrode, and the C-axis controls the horizontal rotation of the blade, so that the molybdenum wire 15 can cut blades of different angular directions.
  • the molybdenum wire 15 is driven by the U-axis, the V-axis, the B-axis, the X-axis, and the Y-axis to realize the cutting of the contour path of the flow path between the blades, and the workpiece is subjected to discharge etching through continuous spark discharge to cut the molding.
  • the shape of the runner is shaped.
  • Embodiment 4 As shown in FIG. 1, FIG. 2, FIG. 3 and FIG. 4, a processing device for an aeroengine integral blade disc, the movement axis of the X-axis table 10 is an X-axis, and the movement axis of the Y-axis table 9
  • the movement axis of the Z axis table 4 is the Z axis
  • the movement axis of the Z1 axis table 7 is the Z1 axis
  • the movement axis of the Z2 axis table 14 is the Z2 axis
  • the movement axis of the U axis table is the U axis.
  • the movement axis of the V-axis table is the V-axis
  • the central axis of the A-axis turret 8 is parallel to the movement axis of the X-axis table 10
  • the Z-axis is parallel to the movement axis of the Z-axis
  • the movement of the X-axis and the Y-axis is a cross line
  • the axis of the C-axis turntable 6 is a C-axis.
  • Embodiment 5 As shown in FIG. 1 , FIG. 2 , FIG. 3 and FIG. 4 , a processing device for an aeroengine integral leaf disc comprises a column, a bed, each rotating shaft and a linear shaft, and the X-axis table 10 is placed On the machine bed 11, the Y-axis table 9 is placed on the X-axis table 10, and the X-axis table 10 intersects the two-axis direction of the Y-axis table 90 at 90 degrees.
  • the A-axis turntable 8 is placed on the Y-axis table 9, the Z1-axis table 7 is placed on the A-axis turntable 8 of the machine tool, the Z1-axis table 7 is connected to the C-axis turntable 6, and the C-axis turntable 6 is connected to the leaf disc 13, the machine tool
  • the A-axis turntable 8 rotates the blade disc 13 with the central axis of the A-axis turntable 8, the central axis of the A-axis turntable 8 is perpendicular to the movement axis of the X-axis table 10, and the Z1 axis table 7 drives the leaf disc 13 to move vertically, adjusting the leaf
  • the cutting height of the disk 13, the C-axis turret 6 is connected to the Z1 axis table 7, and the C-axis turret 6 controls the horizontal rotation of the blade 13, so that the molybdenum wire 15 can cut the flow path between the blades in different angular directions.
  • the Z-axis table 4 is placed at the upper end of the column 12, and the U-axis table and the V-axis table 5 are connected under the Z-axis table 4.
  • the structure is connected to the V-axis table under the Z-axis table 4, and the lower end of the V-axis table is connected to the U.
  • the shaft table, the upper arm 3 is connected to the U-axis table, the Z2 axis table 14 is placed at the lower end of the column 12, the Z2 axis table 14 is connected to the lower arm 2, and the drum device 1 is placed at the bed 11 behind the column 12. on.
  • One end of the molybdenum wire 15 is connected to the wire barrel device 1, and the other end of the molybdenum wire 15 is connected to the wire barrel device 1 after being connected to the lower wire arm 2 and the upper wire arm 3, that is, the molybdenum wire 15 is wound and connected to the wire barrel device 1.
  • the placement is for connection.
  • Embodiment 6 A processing device for an aeroengine integral leaf disc, comprising each rotating shaft and a linear shaft of the machine tool, the X axis is located at the lower end, the Y axis is placed on the X axis, and the two axes are at a 90 degree intersection, the X axis, Y
  • the shaft moves the blade blank horizontally.
  • the A-axis turret is placed on the Y-axis.
  • the A-axis of the machine tool drives the leaf discs to rotate around X, and the Z1 axis is placed on the A-axis to drive the leaf disc to move vertically to adjust the cutting height of the leaf disc.
  • the C-axis turret is connected to the Z1 axis, and the C-axis controls the horizontal rotation of the leaf disc so that the molybdenum wire can cut the blades of different angular directions.
  • the Z axis is placed at the upper end of the column, the V axis is connected below the Z axis, the U axis is connected to the lower end of the V axis, the upper arm is connected to the U axis, the Z2 axis is placed at the lower end of the column, and the lower arm is connected to the Z2 axis.
  • the X-axis and Y-axis of the machine tool move the blade blank horizontally.
  • the Z axis and Z2 axis of the machine tool drive the upper arm and the lower arm to move vertically, and control the size of the opening of the molybdenum wire in the processing area.
  • the blank parts of the leaf disc are clamped on the C-axis turret, and the horizontal rotation of the leaf disc is controlled by the C-axis, so that the molybdenum wire can cut the blades of different angular directions, and the A-axis of the machine tool drives the leaf discs to rotate around X respectively, through the U-axis, V-axis linkage realizes multi-angle cutting trajectory.
  • the Z1 axis drives the leaf disc to move vertically, adjusting the cutting height of the leaf disc.
  • the U-axis and the V-axis drive the upper arm to move the yaw molybdenum wire horizontally.

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  • Chemical & Material Sciences (AREA)
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Abstract

一种航空发动机整体叶盘的加工方法及设备，属于电火花加工技术领域。包含机床各转转轴及直线轴，X轴位于下端，Y轴置于X轴上，两轴方向成90度交叉，X、Y轴带动叶盘毛坯水平移动。A轴转台置于Y轴上，机床的A轴带动叶盘分别围绕X旋转，Z1轴置于A轴上，带动叶盘垂直移动，调整叶盘的切割高度。C轴转台连接在Z1轴上，C轴控制叶盘水平旋转，使钼丝可以切割不同角向的叶片。Z轴置于立柱上端，下面连接V轴，V轴下端连接U轴，上线臂连接到U轴上，Z2轴置于立柱下端，下线臂连接在Z2轴上，丝桶置于立柱后方。

Description

一种航空发动机整体叶盘的加工方法及设备 技术领域
本发明涉及一种航空发动机整体叶盘的加工方法及设备，属于电火花加工技术领域。
背景技术
整体叶盘是把发动机转子的叶片和轮盘设计成一个整体，采用整体加工或焊接(叶片和轮盘材料可以不同)方法制造而成，无需加工榫头和榫槽。
与传统的叶片和轮毂装配结构相比，这种整体结构的优点是：叶盘的轮缘径向高度、厚度和叶片原榫头部位尺寸均可大大减小，减重效果明显；发动机转子部件的结构大为简化；消除了分体结构榫齿根部缝隙中气体的逸流损失；避免了叶片和轮盘装配不当造成的微动磨损、裂纹以及锁片损坏带来的故障，从而有利于提高发动机工作效率，可靠性得以进一步提升。
整体叶盘具有如此多的优点，但是在整体叶盘的加工过程中，也遇到了很多的问题。现阶段整体叶盘加工主要采用数控铣削和电化学电解加工两种方式，但都各有利弊。
数控铣削技术是整体叶盘常用的加工方法，整体叶盘通道是特殊曲面型腔结构，传统的铣削加工方法采用立铣刀分层侧铣，侧铣刀具受径向力作用，随着通道铣削深度的加深刀具悬伸量加长，刀具的刚性变差，在径向力的作用之下刀具变形、振动、磨损加剧，力口工效率显著降低。针对整体叶盘复杂通道侧铣加工存在的问题，数控铣削开槽插铣方法解决了一些上述问题，但是，数控铣削切削力大，叶片易受变形，刀具与叶盘易发生干涉，刀具磨损严重等问题依然存在。整体叶盘另一种加工方法是数控电解加工，电解加工也存在一些不足之处，加工的影响因素多，且加工稳定性和重复性都比较 差，尤其是加工闭式整体叶盘零件时，叶盘流道弯扭复杂，且冲液问题也难于解决。电流要求高，电解液和电解产物需要专门处理，环境污染严重。
发明内容
为了克服现有技术的不足,本发明提供一种航空发动机整体叶盘的加工方法及设备。
一种航空发动机整体叶盘的加工设备，X轴工作台置于机床床身上，Y轴工作台置于X轴工作台上，X轴工作台与Y轴工作台的两轴方向承度交叉；A轴转台置于Y轴工作台上，Z轴工作台置于机床的A轴转台上，Z轴工作台连接C轴转台，C轴转台连接叶盘，C轴转台连接在Z轴工作台上，Z轴工作台置于立柱上端，Z轴工作台下面连接U轴及V轴，上线臂连接到U轴及V轴上，Z轴置于立柱下端，Z轴连接下线臂，丝筒置于立柱后方的床身上。
A轴转台的中心轴线与X轴工作台的轴线平行。
机床的A轴转台带动叶盘以A轴转台的中心轴线旋转，Z轴工作台带动叶盘垂直移动，调整叶盘的切割高度，C轴转台连接叶盘水平旋转，使钼丝能够切割不同角向的叶片间流道。
钼丝的一端连接在丝筒，钼丝的另一端经过与下线臂及上线臂连接后与丝筒连接，即钼丝盘绕连接在丝筒上。
Z轴工作台下面连接V轴工作台，V轴工作台下端连接U轴工作台，上线臂连接到U轴工作台上。
一种航空发动机整体叶盘的加工设备，包含机床各转转轴及直线轴，X轴位于下端，Y轴置于X轴上，两轴方向成90度交叉，X轴、Y轴带动叶盘毛坯水平移动；A轴转台置于Y轴上，机床的A轴带动叶盘分别围绕X旋转，Z1轴置于A轴上，带动叶盘垂直移动，调整叶盘的切割高度；C轴转台连接在Z1轴上，C轴控制叶盘水平旋转，使钼丝可以切割不同角向的叶片；Z轴 置于立柱上端，下面连接V轴，V轴下端连接U轴，上线臂连接到U轴上，Z2轴置于立柱下端，下线臂连接在Z2轴上。
机床的X轴、Y轴带动叶盘毛坯水平移动；机床的Z轴、Z2轴带动上下线臂垂直移动，控制加工区域钼丝开口的大小；叶盘的毛坯零件装夹在C轴转台上，通过C轴控制叶盘水平旋转，使钼丝可以切割不同角向的叶片，机床的A轴带动叶盘分别围绕X旋转，通过和U轴、V轴联动实现多角度切割轨迹；Z1轴带动叶盘垂直移动，调整叶盘的切割高度；U轴、V轴带动上线臂水平移动偏摆钼丝切割角度。
一种航空发动机整体叶盘的加工方法，含有以下步骤；
步骤1；机床的X轴、Y轴带动叶盘毛坯水平移动到起切点；
步骤2；Z1轴带动叶盘垂直移动，调整叶盘的切割高度。
步骤3；叶盘的毛坯零件装夹在C轴转台上，通过C轴控制叶盘水平旋转，使钼丝可以切割不同角向的叶片间流道外。
步骤4；机床的A轴带动叶盘分别围绕X旋转，通过和U轴、V轴、X轴、Y轴联动带动钼丝实现叶片间流道外形轨迹的切割，通过不断的钼丝火花放电对工件进行放电蚀除，以切割出成型的流道外形。
本发明的优点是将传统的线切割加工原理应用到整体叶盘流道开槽掏料加工中，由于电火花线切割加工中无切削力及应力，加工振动变形问题影响很小，同时也不存在刀具磨损问题。大幅降低了加工成本，提高了加工效率。
附图说明
当结合附图考虑时，通过参照下面的详细描述，能够更完整更好地理解本发明以及容易得知其中许多伴随的优点，但此处所说明的附图用来提供对本发明的进一步理解，构成本发明的一部分，本发明的示意性实施例及其说明用于解释本发明，并不构成对本发明的不当限定，如图其中：
图1为本发明装配前结构示意图。
图2为本发明装配后结构示意图。
图3为本发明加工状态图。
图4为本发明丝筒装置结构图。
下面结合附图和实施例对本发明进一步说明。
具体实施方式
显然，本领域技术人员基于本发明的宗旨所做的许多修改和变化属于本发明的保护范围。
本技术领域技术人员可以理解，除非特意声明，这里使用的单数形式“一”、“一个”、“所述”和“该”也可包括复数形式。应该进一步理解的是，本说明书中使用的措辞“包括”是指存在所述特征、整数、步骤、操作、元件和/或组件，但是并不排除存在或添加一个或多个其他特征、整数、步骤、操作、元件、组件和/或它们的组。应该理解，当称元件、组件被“连接”到另一元件、组件时，它可以直接连接到其他元件或者组件，或者也可以存在中间元件或者组件。这里使用的措辞“和/或”包括一个或更多个相关联的列出项的任一单元和全部组合。
本技术领域技术人员可以理解，除非另外定义，这里使用的所有术语(包括技术术语和科学术语)具有与本发明所属领域中的普通技术人员的一般理解相同的意义。
为便于对本发明实施例的理解，下面将做进一步的解释说明，且各个实施例并不构成对本发明实施例的限定。
实施例1：如图1、图2、图3及图4所示，一种航空发动机整体叶盘的加工方法，含有以下步骤；
步骤1；机床的X轴、Y轴带动叶盘毛坯水平移动到起切点；
步骤2；Z1轴带动叶盘垂直移动，调整叶盘的切割高度。
步骤3；叶盘的毛坯零件装夹在C轴转台上，通过C轴控制叶盘水平旋转，使钼丝15可以切割不同角向的叶片间流道外。
步骤4；机床的A轴带动叶盘分别围绕X轴旋转，通过U轴、V轴、X轴、Y轴联动带动钼丝15实现叶片间流道外形轨迹的切割，通过不断的钼丝15火花放电对工件进行放电蚀除，以切割出成型的流道外形。
实施例2：如图1、图2、图3及图4所示，一种航空发动机整体叶盘的加工设备，包含立柱、床身、各旋转轴及直线轴，X轴工作台10置于机床床身11上，Y轴工作台9置于X轴工作台10上，X轴工作台10与Y轴工作台9的两轴方向成90度交叉。A轴转台8置于Y轴工作台9上，Z1轴工作台7置于机床的A轴转台8上，Z1轴工作台7连接C轴转台6，C轴转台6连接叶盘13，机床的A轴转台8带动叶盘13分别围绕X轴10旋转，X轴10是水平安装。
Z1轴工作台7带动叶盘13垂直移动，调整叶盘13的切割高度，C轴转台6连接在Z1轴工作台7上，C轴转台6控制叶盘13水平旋转，使钼丝15可以切割不同角向的叶片间流道。
Z轴工作台4置于立柱12上端，Z轴工作台4下面连接U轴及V轴5，上线臂3连接到U轴及V轴5上，Z2轴14置于立柱12下端，Z2轴14连接下线臂2，丝筒装置1置于立柱12后方的床身11上。
钼丝15的一端连接在丝筒装置1，钼丝15的另一端经过与下线臂2及上线臂3连接后与丝筒装置1连接，即钼丝15盘绕连接在丝筒装置1的丝筒18上，丝筒装置1的左支架16通过左绝缘盘20连接丝筒18的一端，丝筒装置1的右支架17通过右绝缘盘19连接丝筒18的一端。
实施例3：如图1、图2、图3及图4所示，一种航空发动机整体叶盘的 加工方法及设备(九轴五联动电火花线切割机床)，将传统的线切割加工原理应用到整体叶盘流道开槽掏料加工中，由于电火花线切割加工中无切削力，加工振动变形问题影响很小，同时也不存在刀具磨损问题。大幅降低了加工成本，提高了加工效率。
一种航空发动机整体叶盘的加工方法，含有以下步骤；
机床的X、Y轴带动叶盘毛坯水平移动。
机床的Z轴、Z2轴带动上下线臂垂直移动，控制加工区域钼丝15开口的大小。
Z1轴带动叶盘垂直移动，调整叶盘的切割高度。
叶盘的毛坯零件装夹在C轴转台上，通过C轴控制叶盘水平旋转，使钼丝15可以切割不同角向的叶片。
机床的A轴带动叶盘分别围绕X旋转，通过和U轴、V轴联动实现多角度切割轨迹。
U轴、V轴带动上线臂水平移动偏摆钼丝15切割角度。
在电火花线切割加工中，移动的细金属导线(铜丝或钼丝15)作一个电极，工件作为另一个电极，C轴控制叶盘水平旋转，使钼丝15可以切割不同角向的叶片间流道外，通过U轴、V轴、B轴、X轴、Y轴联动带动钼丝15实现叶片间流道外形轨迹的切割，通过不断的火花放电对工件进行放电蚀除，以切割出成型的流道外形。
实施例4：如图1、图2、图3及图4所示，一种航空发动机整体叶盘的加工设备，X轴工作台10的移动轴线为X轴，Y轴工作台9的移动轴线为Y轴，Z轴工作台4的移动轴线为Z轴，Z1轴工作台7的移动轴线为Z1轴，Z2轴工作台14的移动轴线为Z2轴，U轴工作台的移动轴线为U轴，V轴工作台的移动轴线为V轴，A轴转台8的中心轴线与X轴工作台10的移动轴线 平行，Z轴、Z2轴与Z轴的移动轴线平行，X轴与Y轴的移动轴线为十字线，C轴转台6的轴线为C轴。
实施例5：如图1、图2、图3及图4所示，一种航空发动机整体叶盘的加工设备，包含立柱、床身、各旋转轴及直线轴，X轴工作台10置于机床床身11上，Y轴工作台9置于X轴工作台10上，X轴工作台10与Y轴工作台9的两轴方向成90度交叉。A轴转台8置于Y轴工作台9上，Z1轴工作台7置于机床的A轴转台8上，Z1轴工作台7连接C轴转台6，C轴转台6连接叶盘13，机床的A轴转台8带动叶盘13以A轴转台8的中心轴线旋转，A轴转台8的中心轴线与X轴工作台10的移动轴线垂直，Z1轴工作台7带动叶盘13垂直移动，调整叶盘13的切割高度，C轴转台6连接在Z1轴工作台7上，C轴转台6控制叶盘13水平旋转，使钼丝15可以切割不同角向的叶片间流道。
Z轴工作台4置于立柱12上端，Z轴工作台4下面连接U轴工作台及V轴工作台5，结构为Z轴工作台4下面连接V轴工作台，V轴工作台下端连接U轴工作台，上线臂3连接到U轴工作台上，Z2轴工作台14置于立柱12下端，Z2轴工作台14连接下线臂2，丝筒装置1置于立柱12后方的床身11上。
钼丝15的一端连接在丝筒装置1，钼丝15的另一端经过与下线臂2及上线臂3连接后与丝筒装置1连接，即钼丝15盘绕连接在丝筒装置1上。
所述置于为连接。
实施例6：一种航空发动机整体叶盘的加工设备，包含机床各转转轴及直线轴，X轴位于下端，Y轴置于X轴上，两轴方向成90度交叉，X轴、Y轴带动叶盘毛坯水平移动。A轴转台置于Y轴上，机床的A轴带动叶盘分别围绕X旋转，Z1轴置于A轴上，带动叶盘垂直移动，调整叶盘的切割高度。 C轴转台连接在Z1轴上，C轴控制叶盘水平旋转，使钼丝可以切割不同角向的叶片。Z轴置于立柱上端，Z轴下面连接V轴，V轴下端连接U轴，上线臂连接到U轴上，Z2轴置于立柱下端，下线臂连接在Z2轴上。
机床的X轴、Y轴带动叶盘毛坯水平移动。机床的Z轴、Z2轴带动上线臂及下线臂垂直移动，控制加工区域钼丝开口的大小。叶盘的毛坯零件装夹在C轴转台上，通过C轴控制叶盘水平旋转，使钼丝可以切割不同角向的叶片，机床的A轴带动叶盘分别围绕X旋转，通过和U轴、V轴联动实现多角度切割轨迹。Z1轴带动叶盘垂直移动，调整叶盘的切割高度。U轴、V轴带动上线臂水平移动偏摆钼丝切割角度。
如上所述，对本发明的实施例进行了详细地说明，但是只要实质上没有脱离本发明的发明点及效果可以有很多的变形，这对本领域的技术人员来说是显而易见的。因此，这样的变形例也全部包含在本发明的保护范围之内。

Claims (8)

  1. 一种航空发动机整体叶盘的加工设备，其特征在于X轴工作台置于机床床身上，Y轴工作台置于X轴工作台上，X轴工作台与Y轴工作台的两轴方向承度交叉；A轴转台置于Y轴工作台上，Z轴工作台置于机床的A轴转台上，Z轴工作台连接C轴转台，C轴转台连接叶盘，C轴转台连接在Z轴工作台上，Z轴工作台置于立柱上端，Z轴工作台下面连接U轴及V轴，上线臂连接到U轴及V轴上，Z轴置于立柱下端，Z轴连接下线臂，丝筒置于立柱后方的床身上。
  2. 根据权利要求1所述的一种航空发动机整体叶盘的加工设备，其特征在于A轴转台的中心轴线与X轴工作台的轴线平行。
  3. 根据权利要求1所述的一种航空发动机整体叶盘的加工设备，其特征在于机床的A轴转台带动叶盘以A轴转台的中心轴线旋转，Z轴工作台带动叶盘垂直移动，调整叶盘的切割高度，C轴转台连接叶盘水平旋转，使钼丝能够切割不同角向的叶片间流道。
  4. 根据权利要求1所述的一种航空发动机整体叶盘的加工设备，其特征在于钼丝的一端连接在丝筒，钼丝的另一端经过与下线臂及上线臂连接后与丝筒连接，即钼丝盘绕连接在丝筒上。
  5. 根据权利要求1所述的一种航空发动机整体叶盘的加工设备，其特征在于Z轴工作台下面连接V轴工作台，V轴工作台下端连接U轴工作台，上线臂连接到U轴工作台上。
  6. 根据权利要求1所述的一种航空发动机整体叶盘的加工设备，其特征在于包含机床各转转轴及直线轴，X轴位于下端，Y轴置于X轴上，两轴方向成90度交叉，X轴、Y轴带动叶盘毛坯水平移动；A轴转台置于 Y轴上，机床的A轴带动叶盘分别围绕X旋转，Z1轴置于A轴上，带动叶盘垂直移动，调整叶盘的切割高度；C轴转台连接在Z1轴上，C轴控制叶盘水平旋转，使钼丝可以切割不同角向的叶片；Z轴置于立柱上端，下面连接V轴，V轴下端连接U轴，上线臂连接到U轴上，Z2轴置于立柱下端，下线臂连接在Z2轴上。
  7. 根据权利要求1所述的一种航空发动机整体叶盘的加工设备，其特征在于机床的X轴、Y轴带动叶盘毛坯水平移动；机床的Z轴、Z2轴带动上下线臂垂直移动，控制加工区域钼丝开口的大小；叶盘的毛坯零件装夹在C轴转台上，通过C轴控制叶盘水平旋转，使钼丝可以切割不同角向的叶片，机床的A轴带动叶盘分别围绕X旋转，通过和U轴、V轴联动实现多角度切割轨迹；Z1轴带动叶盘垂直移动，调整叶盘的切割高度；U轴、V轴带动上线臂水平移动偏摆钼丝切割角度。
  8. 一种航空发动机整体叶盘的加工方法，其特征在于含有以下步骤；
    步骤1；机床的X轴、Y轴带动叶盘毛坯水平移动到起切点；
    步骤2；Z1轴带动叶盘垂直移动，调整叶盘的切割高度；
    步骤3；叶盘的毛坯零件装夹在C轴转台上，通过C轴控制叶盘水平旋转，使钼丝可以切割不同角向的叶片间流道外；
    步骤4；机床的A轴带动叶盘分别围绕X旋转，通过和U轴、V轴、X轴、Y轴联动带动钼丝实现叶片间流道外形轨迹的切割，通过不断的钼丝火花放电对工件进行放电蚀除，以切割出成型的流道外形。
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