Machining method for large-taper gas compressor guide blade

Abstract

The invention discloses a machining method for a large-taper gas compressor guide blade, and relates to the technical field of gas compressor guide blade machining. According to the machining method, the machining mode of the large-taper guide blade is changed, a five-axis Sidalagger machine tool is adopted, and milling machining is integrated through the root radius compensation technology; the problems that the joint of the rotary circular truncated cone and the air channel cannot be machined in place due to the fact that turning and cylindrical grinding cannot be inclined, the air channel is deformed due to the fact that the air inlet and outlet edges of the air channel are prone to curling, and the throat is out of tolerance due to the fact that the rotary circular handle and the air channel center are not unified are solved, machining consistency is achieved, and product quality is further improved; meanwhile, the machining chain is shortened, the types of equipment and tools are reduced, the tool cost is saved, the machining period is shortened, the working efficiency is greatly improved, and the working quality is strongly guaranteed. The machining method of the large-taper gas compressor guide blade can be obtained.

Description

Technical Field

[0001] The invention relates to the technical field of compressor guide vane processing, and in particular to a processing method for a large-taper compressor guide vane. Background Art

[0002] The high-temperature alloy compressor guide vane processed by our factory has a dovetail structure on the large end side and a rotary table and rotary handle structure on the small end side. The airway and the rotary table have a 10-degree taper angle at the junction. The airway is extremely thin, with a maximum thickness of only 5mm, a large chord width (98.6mm), and a maximum thickness of 0.3mm on the outlet edge. The size and shape tolerances are strict. Because the blade is too thin, the rotary table diameter is smaller than the airway chord width, and the rotary handle side taper is large, conventional turning and external cylindrical grinding cannot connect the overlapping parts and fillets between the rotary table and the airway, resulting in low processing efficiency and difficulty in ensuring precision, which seriously affects the quality of the blade and brings great difficulties to processing. Summary of the invention

[0003] The purpose of the present invention is to solve the above technical problems and to provide a method for processing large-taper compressor guide vanes.

[0004] A method for processing a large-taper compressor guide vane is carried out according to the following steps:

[0005] Step S1: milling the handle;

[0006] The guide vane die forging blank is clamped on the fixture, and the process handle is processed according to the size and parallelism suitable for clamping of the five-axis small Starrag machine tool to obtain the processed die forging blank;

[0007] Step S2: rough milling;

[0008] The air inlet and outlet sides, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface and the inner back arc of the rotary table of the dovetail structure of the processed die forging blank obtained in step S1 are respectively rough-milled to obtain a die forging blank after rough milling;

[0009] Step S3: semi-finishing milling;

[0010] The dovetail structure of the rough-milled die forging blank obtained in step S2 is semi-finished by respectively performing semi-finishing milling on the air inlet and outlet sides, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface, the inner back arc of the rotary table, the air inlet and outlet sides of the rotary handle, the side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table, and the chamfer between the rotary handle and the rotary table to obtain the semi-finished die forging blank;

[0011] Step S4: fine milling;

[0012] The dovetail structure of the semi-finished forging blank obtained in step S3 is finely milled on the inlet and outlet sides, inner back radial direction, side surface where the airway and the rotary table are connected, the airway, fillet, conical surface, rotary table, side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table and the rotary handle, the rotary table chamfer and the inlet and outlet sides of the rotary handle to complete the processing of the large-taper compressor guide vane.

[0013] Beneficial effects of the present invention:

[0014] The present invention changes the processing method of large-taper guide vanes, adopts a five-axis small Starrag machine tool, and integrates milling processing through root radius compensation technology to eliminate the problems of the rotary table and the airway joint being unable to be processed in place due to the inability to tilt during turning and external cylindrical grinding, airway deformation caused by easy curling of the air inlet and outlet edges of the airway, and throat tolerance caused by the inconsistency between the rotary handle and the airway center, so as to achieve processing consistency and further improve product quality; at the same time, the processing chain is shortened, the types of equipment and tooling are reduced, tooling costs are saved, the processing cycle is shortened, work efficiency is greatly improved, and a strong guarantee is provided for work quality.

[0015] The invention can obtain a method for processing large-taper compressor guide vanes. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 An axial side view showing a die forging blank in the present invention;

[0017] Figure 2 An axial view showing a guide vane product of the present invention;

[0018] Figure 3 A top view showing a guide vane product of the present invention;

[0019] Figure 4 A diagram showing the use of a K-knife to process an uncut portion in the present invention;

[0020] Figure 5 A diagram showing an uncut portion of the same size as the rounded corner left after the rounding process in the present invention;

[0021] Figure 6 A diagram showing the cutting process at the quadrant points of the inverted R around the intersection of the rotary table and the airway in the present invention;

[0022] Figure 7 A diagram showing that there is an inverted R between the rotating frustum and the airway in the present invention;

[0023] Figure 8 A diagram showing an uncut portion of the same size as R left after machining the rotary table surface in the present invention;

[0024] Fig. 9 A diagram showing the cutting process along the quadrant point of the inverted R at the intersection of the rotary table and the airway in the present invention;

[0025] Fig.10 A flow chart showing rough milling in step S3 of embodiment 1;

[0026] Fig.11 A flow chart showing the semi-finishing milling in step S3 of embodiment 1;

[0027] Fig.12 A flow chart showing the fine milling in step S3 of Example 1. DETAILED DESCRIPTION

[0028] Specific implementation method 1: This implementation method is a method for processing a large-taper compressor guide vane, which is carried out according to the following steps:

[0029] Step S1: milling the handle;

[0030] The guide vane die forging blank is clamped on the fixture, and the process handle is processed according to the size and parallelism suitable for clamping of the five-axis small Starrag machine tool to obtain the processed die forging blank;

[0031] Step S2: rough milling;

[0032] The air inlet and outlet sides, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface and the inner back arc of the rotary table of the dovetail structure of the processed die forging blank obtained in step S1 are respectively rough-milled to obtain a die forging blank after rough milling;

[0033] Step S3: semi-finishing milling;

[0034] The dovetail structure of the rough-milled die forging blank obtained in step S2 is semi-finished by respectively performing semi-finishing milling on the air inlet and outlet sides, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface, the inner back arc of the rotary table, the air inlet and outlet sides of the rotary handle, the side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table, and the chamfer between the rotary handle and the rotary table to obtain the semi-finished die forging blank;

[0035] Step S4: fine milling;

[0036] The dovetail structure of the semi-finished forging blank obtained in step S3 is finely milled on the inlet and outlet sides, inner back radial direction, side surface where the airway and the rotary table are connected, the airway, fillet, conical surface, rotary table, side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table and the rotary handle, the rotary table chamfer and the inlet and outlet sides of the rotary handle to complete the processing of the large-taper compressor guide vane.

[0037] Specific implementation method 2: The difference between this implementation method and specific implementation method 1 is that in step S1, the guide vane die forging blank is clamped on a four-axis device using a three-thimble clamp.

[0038] The other steps are the same as those in the first specific implementation.

[0039] Specific implementation method three: The difference between this implementation method and specific implementation method one or two is that the processing handle of the blank processed in step S1 is parallel to the inner back radial surface of the blade.

[0040] The other steps are the same as those in the first or second embodiment.

[0041] Specific implementation method four: The difference between this implementation method and specific implementation methods one to three is that in step S2, the air inlet and outlet sides, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface and the inner back arc of the rotary table of the dovetail structure of the processed die forging blank are rough milled in sequence.

[0042] The other steps are the same as those in Specific Embodiments 1 to 3.

[0043] Specific embodiment five: The difference between this embodiment and any one of specific embodiments one to four is that in step S3, the dovetail structure of the die forging blank after rough milling, the air inlet and outlet side, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface, the inner back arc of the rotary table, the air inlet and outlet side of the rotary handle, the side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table, and the chamfer between the rotary handle and the rotary table are semi-finished milled in sequence.

[0044] The other steps are the same as those in Specific Embodiments 1 to 4.

[0045] Specific embodiment six: The difference between this embodiment and specific embodiments one to five is that: in step S4, the dovetail structure of the semi-finished die forging blank, the air inlet and outlet sides, the inner back radial direction, the side surface where the airway and the rotary table are connected, the airway, the fillet, the conical surface, the rotary table, the side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table and the rotary handle, the rotary table chamfer and the air inlet and outlet sides of the rotary handle are sequentially fine-milled.

[0046] The other steps are the same as those in Specific Embodiments 1 to 5.

[0047] Specific embodiment seven: The difference between this embodiment and specific embodiments one to six is ​​that in steps S3 and S4, when processing the airway, the uncut part with the same size as the reverse R after the rounded corner processing is processed by root radius compensation.

[0048] The other steps are the same as those in Specific Embodiments 1 to 6.

[0049] Specific embodiment eight: The difference between this embodiment and specific embodiments one to seven is that when processing the rotary table surface in steps S3 and S4, the uncut parts with the same size as the reverse R after processing are processed by root radius compensation.

[0050] The other steps are the same as those in Specific Embodiments 1 to 7.

[0051] The following examples are used to verify the beneficial effects of the present invention:

[0052] Embodiment 1: A method for processing a large-taper compressor guide vane, wherein each processing part of the compressor guide vane is integratedly processed by a five-axis small Starrag milling machine, and the method is specifically performed in the following steps:

[0053] Step S1: milling the handle;

[0054] The guide vane die forging blank is clamped on a four-axis device, and a three-thimble fixture is used to process the process handle according to the size and parallelism suitable for clamping on a five-axis Starrag machine tool to obtain a processed die forging blank. The processed blank process handle is parallel to the inner back radial surface of the blade;

[0055] Step S2: rough milling;

[0056] The air inlet and outlet sides, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface and the inner back arc of the rotary table of the dovetail structure of the processed die forging blank obtained in step S1 are rough milled in sequence to obtain a die forging blank after rough milling;

[0057] Step S3: semi-finishing milling;

[0058] The dovetail structure of the die forging blank obtained after rough milling in step S2 is semi-finished milled on the air inlet and outlet sides, the inner back radial direction, the side surface where the airway and the rotary table are connected, the airway, the fillet, the conical surface, the inner back arc of the rotary table, the air inlet and outlet sides of the rotary handle, the side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table, and the chamfer between the rotary handle and the rotary table to obtain the die forging blank after semi-finished milling;

[0059] Step S4: fine milling;

[0060] The dovetail structure of the semi-finished forging blank obtained in step S3, including the air inlet and outlet sides, the inner back radial direction, the side surface where the airway and the rotary table are connected, the airway, the fillet, the conical surface, the rotary table, the side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table and the rotary handle, the rotary table chamfer and the air inlet and outlet sides of the rotary handle, are fine-milled in sequence to complete the processing of the large-taper compressor guide vane.

[0061] Note: In the above processing, the rounded corners need to be milled with a K tool and tool tip programming.

[0062] The die forging blank after the process handle is processed is integratedly processed by a full-sequence five-axis Starrag milling machine. Rough and fine milling are carried out separately. It is required that the rotary table and rotary handle should not be processed during rough milling to avoid deformation.

[0063] 1. Optimize processing sequence:

[0064] First, when rough milling, semi-finishing milling and finishing milling, the side where the airway connects with the rotary table should be processed first, and then the airway should be processed to avoid curling. Secondly, when semi-finishing, the semi-finishing of the inlet and outlet sides of the rotary handle should be processed twice to avoid blade deformation. Finally, when finishing milling, the dovetail inlet and outlet sides and the inner back radial direction should be finished first, and then the rest of the parts should be finished to avoid slight deformation of the blade caused by cutting stress during finishing of the airway, which may affect the test results. The specific steps are as follows Figure 10-12 shown.

[0065] 2. Treatment of inadequate processing of the overlapping parts of the airway and the rotary table:

[0066] 2.1. Incomplete airway milling:

[0067] Since the diameter of the rotating cone is smaller than the airway chord width (such as Figure 3 As shown), and there is an inverted R between the rotating cone surface and the airway (as shown Figure 4 As shown in the figure, in steps S3 and S4, when machining the airway, the K tool can only move along the quadrant point trajectory of the inverted R, and after the fillet machining, there will be an uncut part with the same size as R. Figure 5 The mid-section line is the area that cannot be cut. This area can be solved by the root radius compensation technology.

[0068] Application example: First, set the airway as blade and the rotary table as hub. Then the side of the rotary table close to the airway is defined as the Hub platform (e.g. Figure 6 When machining the original angle, a K tool with a radius equal to the inverted R is selected for machining, and root radius compensation is performed at the same time, that is, all spatial intersection surfaces between the rotary table and the airway are considered to have inverted R. At this time, the K tool will continue milling along the airway, and at the same time, the tool will move along the quadrant points of the inverted R around the intersection of the rotary table and the airway to avoid the rotary table. The tool path is as follows Figure 6 shown.

[0069] 2.2. Incomplete milling of rotary table:

[0070] There is also an inverted R between the rotating table and the airway (such as Figure 7 As shown in the figure below, the principle is the same as 2.1. When machining the rotary table surface in steps S3 and S4, the K tool can only move along the quadrant point trajectory of the inverted R. After machining, there will be an uncut part with the same size as R. Figure 8 The section line area (as shown) is the area that cannot be cut, which can also be solved by the root radius compensation technology.

[0071] Application example: First, stretch the rotating platform to make it intersect with the airway, and set the stretched rotating platform as blade and the airway as shroud. Then, the side of the airway close to the rotating platform is defined as shroud platform (e.g. Figure 8 When machining the rotary table, a K tool with the same radius as the inverted R is also selected for machining, and root radius compensation is performed on it, that is, all spatial intersection surfaces between the extended rotary table and the airway are considered to have inverted R. At this time, the K tool will continue milling along the rotary table, and at the same time, it will move along the quadrant point of the inverted R at the intersection of the rotary table and the airway to avoid the airway. The tool path is as follows Fig. 9 shown.

Claims

1. A method for processing a large-taper compressor guide vane, characterized in that The processing method is carried out according to the following steps: Step S1: milling the handle; The guide vane die forging blank is clamped on the fixture, and the process handle is processed according to the size and parallelism suitable for clamping of the five-axis small Starrag machine tool to obtain the processed die forging blank; Step S2: rough milling; The air inlet and outlet sides, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface and the inner back arc of the rotary table of the dovetail structure of the processed die forging blank obtained in step S1 are respectively rough-milled to obtain a die forging blank after rough milling; Step S3: semi-finishing milling; The dovetail structure of the rough-milled die forging blank obtained in step S2 is semi-finished by respectively performing semi-finishing milling on the air inlet and outlet sides, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface, the inner back arc of the rotary table, the air inlet and outlet sides of the rotary handle, the side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table, and the chamfer between the rotary handle and the rotary table to obtain the semi-finished die forging blank; Step S4: fine milling; The dovetail structure of the semi-finished forging blank obtained in step S3 is finely milled on the inlet and outlet sides, inner back radial direction, side surface where the airway and the rotary table are connected, the airway, fillet, conical surface, rotary table, side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table and the rotary handle, the rotary table chamfer and the inlet and outlet sides of the rotary handle to complete the processing of the large-taper compressor guide vane.

2. A method for processing a large-taper compressor guide vane according to claim 1, characterized in that In step S1, the guide vane die forging blank is clamped on a four-axis device using a three-thimble fixture.

3. The method for processing a large-taper compressor guide vane according to claim 1, characterized in that The processing handle of the blank processed in step S1 is parallel to the inner back radial surface of the blade.

4. The method for processing a large-taper compressor guide vane according to claim 1, characterized in that In step S2, the air inlet and outlet sides, the inner back radial direction, the side surface connecting the airway and the rotary table, the airway, the fillet, the conical surface and the inner back arc of the rotary table of the dovetail structure of the processed die forging blank are rough milled in sequence.

5. The method for processing a large-taper compressor guide vane according to claim 1, characterized in that In step S3, the dovetail structure of the rough-milled die forging blank, including the air inlet and outlet sides, the inner back radial direction, the side surface where the airway and the rotary table are connected, the airway, the fillet, the conical surface, the inner back arc of the rotary table, the air inlet and outlet sides of the rotary handle, the side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table, and the chamfer between the rotary handle and the rotary table, are semi-finished milled in sequence.

6. The method for machining a large-taper compressor guide vane according to claim 1, characterized in that In step S4, the dovetail structure of the semi-finished die forging blank, the air inlet and outlet sides, the inner back radial direction, the side surface where the airway and the rotary table are connected, the airway, the fillet, the conical surface, the rotary table, the side arc of the rotary handle, the connecting surface between the rotary handle and the rotary table and the rotary handle, the rotary table chamfer and the air inlet and outlet sides of the rotary handle are fine milled in sequence.

7. A method for processing a large-taper compressor guide vane according to claim 1 or 6, characterized in that In steps S3 and S4, when machining the airway, the uncut portion with the same size as the reverse R left after the fillet machining is processed by means of root radius compensation.

8. A method for processing a large-taper compressor guide vane according to claim 1 or 6, characterized in that When the rotary table surface is processed in steps S3 and S4, the uncut portion with the same size as the reverse R after processing is processed by means of root radius compensation.

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