A machining method for large-taper compressor guide vanes

Abstract

A method for processing large-taper compressor guide blades relates to the technical field of compressor guide blade processing. The present invention changes the processing method of large-taper guide blades, 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 connection being unable to be processed in place due to the inability to tilt during turning and cylindrical grinding, the deformation of the airway due to the easy curling of the airway inlet and outlet edges, and the throat tolerance caused by the inconsistency between the rotary handle and the airway center. The problems achieve consistency in processing 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. The present invention can obtain a method for processing large-taper compressor guide blades.

Description

Technical Field

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

[0002] Our factory processes a high-temperature alloy compressor guide vane with a dovetail structure on the large end and a rotary table and swivel handle on the small end. The airway and rotary table meet at a 10-degree taper angle. 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. Stringent dimensional and geometric tolerances are required. Due to the thinness of the vane, the rotary table diameter is smaller than the airway chord width, and the large taper on the rotary handle side makes conventional turning and external cylindrical grinding unable to connect the overlapping area and fillet between the rotary table and the airway. This results in low processing efficiency and difficulty in ensuring precision, seriously affecting blade quality and causing great difficulties in processing. Summary of the Invention

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

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

[0005] Step S1: milling the handle;

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

[0007] Step S2: rough milling;

[0008] The dovetail structure of the die forging blank obtained in step S1 is subjected to rough milling on the air inlet and outlet sides, the inner back radial side, the side surface where the air channel and the rotary table meet, the air channel, the fillet, the tapered surface, and the inner back arc of the rotary table to obtain a rough-milled die forging blank;

[0009] Step S3: semi-finishing milling;

[0010] The dovetail structure of the rough-milled die forging blank obtained in step S2 is semi-finished on the air inlet and outlet sides, the inner back radial direction, the side surface where the air channel and the rotary table meet, the air channel, the fillet, the tapered 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 interface between the rotary handle and the rotary table, and the chamfer between the rotary handle and the rotary table to obtain a semi-finished die forging blank;

[0011] Step S4: fine milling;

[0012] 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 air duct and the rotary table are connected, the air duct, 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 respectively subjected to fine milling 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. This eliminates the problems of the rotary table and the airway connection being unable to be processed properly due to the inability to tilt during turning and external cylindrical grinding, airway deformation caused by easy curling of the airway inlet and outlet edges, and throat deviation caused by the misalignment between the rotary handle and the airway center. This achieves processing consistency and further improves product quality. At the same time, it shortens the processing chain, reduces the number of equipment and tooling types, saves tooling costs, shortens the processing cycle, greatly improves work efficiency, and provides a strong guarantee for work quality.

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

[0016] Figure 1 An axial side view of a die forging blank according to the present invention is shown;

[0017] Figure 2 An axial view of a guide vane product according to the present invention is shown;

[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 inverted R left after rounding in the present invention;

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

[0022] Figure 7 A diagram showing an inverted R between the rotating table 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] Figure 9 A diagram showing a cutting operation along the inverted R quadrant at the intersection of the rotary table and the airway in the present invention;

[0025] Figure 10 A flow chart showing rough milling in step S3 of Example 1;

[0026] Figure 11 Flowchart showing semi-finishing milling in step S3 of embodiment 1;

[0027] Figure 12 Flowchart showing the fine milling in step S3 of Example 1. DETAILED DESCRIPTION

[0028] Specific embodiment 1: This embodiment 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 a fixture, and the process handle is processed according to the size and parallelism suitable for clamping on a five-axis small Starrag machine tool to obtain the processed die forging blank;

[0031] Step S2: rough milling;

[0032] The dovetail structure of the die forging blank obtained in step S1 is subjected to rough milling on the air inlet and outlet sides, the inner back radial side, the side surface where the air channel and the rotary table meet, the air channel, the fillet, the tapered surface, and the inner back arc of the rotary table to obtain a rough-milled die forging blank;

[0033] Step S3: semi-finishing milling;

[0034] The dovetail structure of the rough-milled die forging blank obtained in step S2 is semi-finished on the air inlet and outlet sides, the inner back radial direction, the side surface where the air channel and the rotary table meet, the air channel, the fillet, the tapered 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 interface between the rotary handle and the rotary table, and the chamfer between the rotary handle and the rotary table to obtain a semi-finished die forging blank;

[0035] Step S4: fine milling;

[0036] 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 air duct and the rotary table are connected, the air duct, 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 respectively subjected to fine milling to complete the processing of the large-taper compressor guide vane.

[0037] Specific embodiment 2: This embodiment differs from specific embodiment 1 in that: in step S1 , the guide vane die forging blank is clamped on a four-axis device using a three-thimble fixture.

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

[0039] Specific embodiment three: This embodiment differs from specific embodiment one or two in that: the blank processing handle 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 embodiment four: The difference between this embodiment and specific embodiments one to three is that: in step S2, the air inlet and outlet sides, 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 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 where the air channel and the rotary table are connected, the air channel, 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 die forging blank after semi-finishing milling, the air inlet and outlet side, the inner back radial direction, the side surface where the air duct and the rotary table are connected, the air duct, 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 side of the rotary handle are fine-milled in sequence.

[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 portion with the same size as the rounded corner left after the rounding 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 inverted 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] Example 1: A method for machining a large-taper compressor guide vane, wherein all machining parts of the compressor guide vane are integratedly machined using a five-axis small Starrag milling machine, specifically according to 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 the 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 radial side, the side surface where the air channel and the rotary table meet, the air channel, the fillet, the tapered surface, and the inner arc of the rotary table of the dovetail structure of the die forging blank obtained in step S1 are subjected to rough milling in sequence to obtain a die forging blank after rough milling;

[0057] Step S3: semi-finishing milling;

[0058] The dovetail structure of the rough-milled die forging blank obtained in step S2 is semi-finished milled in sequence on the air inlet and outlet sides, the inner back radial direction, the side surface where the air channel and the rotary table meet, the air channel, the fillet, the tapered 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 interface 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;

[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 air duct and the rotary table are connected, the air duct, 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 small Starrag milling machine, with roughing and finishing milling carried out separately. It is required that the rotary table and rotary handle should not be processed during roughing to avoid deformation.

[0063] 1. Optimize processing sequence:

[0064] First, during rough milling, semi-finishing milling and finishing milling, the side where the air channel and the rotary table meet is machined first, and then the air channel is machined to avoid curling. Secondly, during semi-finishing milling, the semi-finishing of the inlet and outlet sides of the rotary handle is machined twice to avoid blade deformation. Finally, during finishing milling, the dovetail inlet and outlet sides and the inner back radial direction are finished first, and then the rest of the parts are finished to avoid slight deformation of the blade caused by cutting stress during finishing of the air channel, 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 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, an uncut part of the same size as the R will be left. Figure 5 The mid-section line is the area that cannot be cut. This area can be solved by using 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 As shown in the figure, 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 on it. That is, all the 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, it will move along the quadrant points of the inverted R around the intersection of the rotary table and the airway, avoiding the rotary table. The tool path is as follows Figure 6 shown.

[0069] 2.2. Incomplete rotary table milling:

[0070] There is also an inverted R between the rotating table and the airway (such as Figure 7 As shown), 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 hatched area 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 a radius equal to the inverted R is also selected for machining, and root radius compensation is performed. 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 of the inverted R at the intersection of the rotary table and the airway to avoid the airway. The tool path is as follows Figure 9 shown.

Claims

1. A method for processing large-taper compressor guide vanes, characterized in that The processing method is carried out in the following steps: Step S1: milling the handle; The guide vane die forging blank is clamped on a fixture, and the process handle is processed according to the size and parallelism suitable for clamping on a 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 radial side, the side surface where the air channel and the rotary table meet, the air channel, the fillet, the tapered surface, and the inner arc of the rotary table of the dovetail structure of the die forging blank obtained in step S1 are subjected to rough milling in sequence 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 milled in sequence on the air inlet and outlet sides, the inner back radial direction, the side surface where the air channel and the rotary table meet, the air channel, the fillet, the tapered 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 interface 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 subjected to precision milling in sequence on the air inlet and outlet sides, the inner back radial direction, the side surface where the air channel and the rotary table meet, the air channel, the fillet, the tapered surface, the rotary table, the side arc of the rotary handle, the surface where the rotary handle and the rotary table meet, the rotary handle, the rotary table chamfer, and the air inlet and outlet sides of the rotary handle, thereby completing the processing of the large-taper compressor guide vane; In steps S3 and S4, when processing the airway, the uncut portion with the same size as the inverted R left after the fillet processing is processed by root radius compensation; in steps S3 and S4, when processing the rotary table surface, the uncut portion with the same size as the inverted R left after processing is processed by root radius compensation.

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 machining 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.

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