CN115600328A - Chamfer angle molding method and machining method of compressor blade - Google Patents
Chamfer angle molding method and machining method of compressor blade Download PDFInfo
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- CN115600328A CN115600328A CN202110778660.2A CN202110778660A CN115600328A CN 115600328 A CN115600328 A CN 115600328A CN 202110778660 A CN202110778660 A CN 202110778660A CN 115600328 A CN115600328 A CN 115600328A
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Abstract
The invention discloses a chamfer molding method and a processing method of a compressor blade, wherein the chamfer molding method comprises the following steps: inputting a basic model of the compressor blade without the chamfer angle, wherein the basic model comprises a platform; determining a plurality of chamfering arcs in a chamfering area on a basic model; respectively selecting a plurality of points on each chamfering arc according to the same rule, and connecting the points at corresponding positions on the plurality of chamfering arcs to form a closed curve to obtain a blade-shaped profile of the chamfering area; and replacing the profile of the blade profile section of the compressor blade at the corresponding position in the basic model with the obtained profile of the chamfered area to obtain a blade model with a chamfer. According to the method, the design model of the compressor blade is subjected to chamfering modeling, the integrity of the blade profile line of the chamfer area of the design model of the compressor blade is effectively guaranteed, the condition of breakage caused by direct chamfering by adopting CAD/CAM software is avoided, and therefore the design model is conveniently used for subsequent strength calculation and production and manufacturing.
Description
Technical Field
The invention relates to a chamfer angle molding method and a chamfer angle processing method for a compressor blade.
Background
Rotor blades and stator blades are common components in aircraft engines, compressor parts of gas turbines, and ground axial compressors. Chamfering compressor blades at their root and tip is a very important task, both for design and production manufacturing. The strength of the compressor blade is calculated before production and manufacturing so as to avoid the compressor blade not conforming to the use strength. The strength calculation of the compressor blades is generally performed in the relevant software, which requires a complete design model of the compressor blades. The obtaining of the complete design model of the compressor blade generally includes drawing a base model, and chamfering the blade root and the blade tip of the base model of the compressor blade through CAD/CAM (computer aided design and computer aided manufacturing) software. The mode of chamfering the basic model of the compressor blade through the CAD/CAM may cause a 'breakage' phenomenon, which brings problems to subsequent blade strength calculation and influences the processing effect in subsequent production and manufacturing.
Disclosure of Invention
The technical problem to be solved by the invention is that the mode of chamfering the basic model of the compressor blade through the CAD/CAM in the prior art may generate 'damage', and the defects of subsequent blade strength calculation and production and manufacturing are influenced, and the invention provides a chamfer molding method and a processing method of the compressor blade.
The invention solves the technical problems through the following technical scheme:
the invention provides a chamfer molding method of a compressor blade, wherein a platform of the compressor blade is integrally molded at the blade root and/or the blade tip of the compressor blade, a chamfer with a radius of R is arranged at the joint of the compressor blade and the platform, and the chamfer molding method comprises the following steps:
s1, inputting a basic model of the compressor blade without a chamfer angle, wherein the basic model comprises the platform;
s2, determining one chamfering circular arc of the chamfering area on the basic model:
selecting a point X on a blade profile line at the root and/or the tip of the compressor blade, selecting a point P on the edge platform in the normal direction of the point X, solving the normal vector of the point P and combiningObtaining the sphere center O of the sphere S1 according to the chamfer radius R, and calculating the minimum value l of the distance from the coordinate point of the blade profile of the compressor blade to the sphere center O min ；
Moving the point P in the normal direction of the point X, finding the point A and the point B respectively, so that l is located at the point A min >R, point l at B min <R, then obtaining a tangent of the ball S1 and the blade profile surface of the compressor blade through a dichotomy, calculating a tangent point C of the ball S1 and the surface of the platform and a tangent point D of the ball S1 and the surface of the blade of the compressor blade, wherein an arc passing through the tangent point C and the tangent point D, with the circle center of O and the radius of R, is a chamfer arc;
s3, repeating the step S2, and determining a plurality of chamfer arcs in the circumferential direction of the compressor blade;
s4, respectively selecting a plurality of points on each chamfering arc according to the same rule, and connecting the points at corresponding positions on the chamfering arcs to form a closed curve to obtain a molded line of the blade-shaped section of the chamfering area;
and S5, replacing the blade-shaped molded line at the corresponding position in the basic model with the obtained blade-shaped molded line of the chamfer area to obtain the blade model with the chamfer.
In the scheme, by adopting the method, the completeness of the blade profile line of the chamfered area of the design model after the compressor blade is chamfered can be effectively ensured, and the condition of 'damage' caused by direct chamfering by adopting CAD/CAM software is avoided, so that the design model is conveniently utilized for subsequent strength calculation and production and manufacturing.
Preferably, in step S2, the tangent point D is obtained by:
s21, finding a point D on the compressor blade 1 So that the point D 1 The absolute value of the difference between the distance to the center O of the sphere and the chamfer radius R is smallest;
s22, at point D 1 The circumferential direction of the located blade profile line is selected to be positioned at a point D 1 Points D on both sides 2 And D 3 Determining a passing point D 1 、D 2 、D 3 A ball S2 with four points X, and determining the center O of the ball S2 1 ；
S23The center O of the ball S1 and the center O of the ball S2 1 Connected into a straight line, and the tangent point D is positioned at the sphere center O and the sphere center O 1 And the distance to the center O of the sphere is R.
In the scheme, the boundary of the chamfer arc on the blade profile surface of the compressor blade can be quickly obtained by the method.
Preferably, point D 2 And D 3 And when the blades are selected, the blades are positioned in the same blade profile of the compressor blade.
In this scenario, point D 2 And D 3 The same side of the compressor blade is selected to enable the obtained result to be more accurate.
Preferably, in step S4, the obtained profile line of the chamfered region is smoothed.
In this scheme, adopt smooth and smooth processing to make the chamfer effect better.
Preferably, step S5 further comprises the steps of:
s51, determining an upper end blade profile and a lower end blade profile which are respectively the same as the blade profile at the upper boundary and the lower boundary of the chamfer arc in the basic model of the compressor blade;
and S52, correspondingly replacing all blade profile molded lines between the upper end blade profile and the lower end blade profile in the basic model of the compressor blade with the blade profile molded lines of the chamfer area obtained in the step S4 to obtain the blade model with the chamfer.
Preferably, the method further comprises the following steps after step S5:
and S6, generating a blade profile line coordinate point of the blade model with the chamfer and outputting the blade profile line coordinate point.
In the scheme, the generated blade model with the chamfer angle generates a blade profile line coordinate point which can be input into a numerical control machine tool for processing the compressor blade.
The invention also provides a processing method of the compressor blade, which comprises the step of chamfering the blade root and/or the blade tip of the compressor blade by adopting the chamfering molding method of the compressor blade.
Preferably, the processing method further comprises the following steps:
generating a blade molded line coordinate point by the blade model with the chamfer;
and inputting the blade profile line coordinate point into a numerical control machine tool, and starting the numerical control machine tool for processing to obtain the compressor blade.
The positive progress effects of the invention are as follows: according to the method, the design model of the compressor blade is subjected to chamfering modeling, the integrity of the blade profile line of the chamfer area of the design model of the compressor blade can be effectively ensured, the condition of breakage caused by direct chamfering by adopting CAD/CAM software is avoided, and therefore the design model is conveniently used for subsequent strength calculation and production and manufacturing.
Drawings
FIG. 1 is a schematic flow chart of a chamfer molding method for a compressor blade according to a preferred embodiment of the present invention.
FIG. 2 is a schematic view of the chamfer profile of a compressor blade in a preferred embodiment of the invention.
FIG. 3 is a schematic representation of a blade profile at the root of a compressor blade on a platform according to a preferred embodiment of the present invention.
FIG. 4 is a schematic diagram illustrating the solution of the tangent point position between the sphere S1 and the rim platform according to the preferred embodiment of the invention.
Fig. 5 is a schematic diagram illustrating the solution of the tangent point position between the spherical ball S1 and the surface of the compressor blade in the preferred embodiment of the present invention.
Description of the reference numerals:
Vane surface 101
Chamfered region 300
Detailed Description
The invention will be more clearly and completely described below by way of examples and with reference to the accompanying drawings, without thereby limiting the scope of the invention to these examples.
The axial-flow compressor is multi-stage compression equipment with the airflow flowing direction consistent or nearly consistent with the rotating axial lead direction of a working wheel, is formed by correspondingly and alternately arranging a root tip flow passage and a series of stator-rotor blades, and is commonly used for an aircraft engine or a gas turbine; the combination of adjacent stator and rotor blades is referred to as a stage. The stator blades and the rotor blades are both referred to as compressor blades. As shown in FIG. 2, to facilitate installation of the compressor blade 100, a platform 200 of the compressor blade 100 is integrally formed at the root and/or tip of the compressor blade 100. The compressor blade 100 and platform 200 connection is typically chamfered. Because the application occasions of the compressor blade 100 require that the machining precision of the compressor blade 100 is ensured, the compressor blade 100 is generally produced by adopting automatic machining equipment, and the integrity of the design model line of the compressor blade 100 needs to be ensured so as to avoid that the machining is influenced by the missing of the coordinate point of the blade profile line led out by the design model.
As shown in fig. 1 to 5, the embodiment discloses a chamfer molding method for a compressor blade 100, which can effectively ensure the integrity of a profile line of a design model of the compressor blade 100 in a chamfer area 300, and avoid the occurrence of "damage" in the direct chamfer of the design model of the blade by using CAD/CAM software, thereby facilitating subsequent strength calculation and production and manufacturing by using the design model. As shown in fig. 1, the chamfer molding method of the compressor blade 100 includes the steps of:
s1, inputting a basic model of the compressor blade 100 without the chamfer, wherein the basic model comprises the platform 200. The base model of the compressor blade 100 may be obtained by an aerodynamic design method.
S2, determining one chamfering arc of the chamfering area 300 on the basic model, and specifically comprising the following steps:
as shown in fig. 3, assuming that the chamfer radius of the chamfer area 300 is R, selecting a point X on a blade profile line at the blade root and/or the blade tip of the compressor blade 100, selecting a point P on the platform 200 in the normal direction of the point X, calculating the normal vector of the point P, obtaining the spherical center O of the sphere S1 according to the chamfer radius R, and calculating the minimum value l of the distance from the coordinate point of the blade profile line of the compressor blade 100 to the spherical center O min 。
Then, as shown in FIG. 4, moving the point P in the normal direction of the point X, finding the point A and the point B, respectively, so that l is located at the point A min >R, point l at B min <And R is selected from the group consisting of. Then, the tangent between the sphere S1 and the blade profile surface of the compressor blade 100 is obtained through a bisection method, a tangent point C between the sphere S1 and the platform surface 201 and a tangent point D between the sphere S1 and the blade surface 101 of the compressor blade 100 are calculated, and an arc passing through the tangent point C and the tangent point D, with the circle center being the point O and the radius being R, is a chamfer arc.
And S3, repeating the step S2, and determining a plurality of chamfer arcs in the circumferential direction of the compressor blade 100. In this step, as many chamfer arcs as possible are determined in the circumferential direction of the compressor blade 100, so that the chamfer area 300 results in a profile line with a smoother profile section. In the chamfering molding step, the pressure surface side of the blade of the compressor blade 100 may be selected first to perform chamfering molding, and then the suction surface side, the leading edge region and the trailing edge region of the blade of the compressor blade 100 may be chamfered by the same method. Of course, the suction side or the leading and trailing edge regions of the compressor blade 100 may be first chamfered, and are not limited herein.
And S4, respectively selecting a plurality of points on each chamfering arc according to the same rule, and connecting the points at corresponding positions on the chamfering arcs to form a closed curve to obtain the blade-shaped profile of the chamfering area 300.
In this step, assuming that N points (including end points at both ends of the chamfering arc) are uniformly selected on each chamfering arc, the points at the corresponding positions on each chamfering arc are connected into a closed curve in the circumferential direction, and the blade-shaped profile of the N chamfering regions 300 can be obtained. Wherein, the upper boundary and the lower boundary of the profile line of the chamfer area 300 are respectively a closed curve formed by the end points of the two ends of the chamfer arc.
The blade profile at the upper boundary of the blade profile line of the chamfer area 300 is a plane in a closed curve formed by the spherical ball S1 and all tangent points of the blade surface 101, and the blade profile at the lower boundary of the blade profile line of the chamfer area 300 is a plane in a closed curve formed by the spherical ball S1 and all tangent points of the platform surface 201.
The blade profile between the upper boundary and the lower boundary in the chamfered region 300 is a plane in a closed curve formed by N-2 points with the same reference numerals except for the end points of the two ends of the chamfered arc on the blade profile line of the chamfered region 300.
And S5, replacing the blade profile line of the compressor blade 100 at the corresponding position in the basic model with the obtained blade profile line of the chamfer area 300 to obtain a blade model with a chamfer.
Specifically, referring to fig. 5, in the present embodiment, the tangent point D in step S2 is obtained through the following steps:
s21, finding a point D on the compressor blade 100 1 So that the point D 1 The absolute value of the difference between the distance to the center O of the sphere and the chamfer radius R is minimum;
s22, at point D 1 The circumferential direction of the located blade profile line is selected to be positioned at a point D 1 Points D on both sides 2 And D 3 Determining a passing point D 1 、D 2 、D 3 A ball S2 with four points X, and determining the center O of the ball S2 1 ；
S23, the center O of the ball S1 and the center O of the ball S2 1 Are connected into a straight line, and the tangent point D is positioned at the sphere center O and the sphere center O 1 And the distance to the center O of the sphere is R.
The boundary of the chamfer arc on the airfoil surface of the compressor blade 100 can be quickly obtained by the above method.
And, point D 2 And D 3 And when selected, should be located on the same airfoil of the compressor blade 100. Point D 2 And D 3 The same profile of the compressor blade 100 is selected to obtain more accurate results.
In step S4 in the present embodiment, the obtained profile line of the chamfered region 300 is subjected to a smoothing process. And the chamfering effect is better by adopting smoothing treatment.
Of course, in other embodiments, the smoothing process may not be performed. The concrete can be judged by designers according to the concrete condition after the design model is chamfered.
In this embodiment, step S5 further includes the following steps:
s51, determining an upper end blade profile and a lower end blade profile which are respectively identical to the blade profile at the upper boundary and the blade profile at the lower boundary of the chamfer arc in the basic model of the compressor blade 100.
S52, all blade profile molded lines between the upper end blade profile and the lower end blade profile in the basic model of the compressor blade 100 are correspondingly replaced by the blade profile molded lines of the chamfer area 300 obtained in the step S4, and the blade model with the chamfer is obtained.
Preferably, the method further comprises the following steps after step S5:
and S6, generating a blade profile line coordinate point of the blade model with the chamfer and outputting the blade profile line coordinate point. And generating a blade model with chamfers, generating a blade profile coordinate point, and inputting the blade profile coordinate point into a numerical control machine tool for processing the compressor blade 100.
The invention also provides a processing method of the compressor blade 100, which comprises the step of chamfering the blade root and/or the blade tip of the compressor blade 100 by adopting the chamfering modeling method of the compressor blade 100.
Specifically, the machining method of the compressor blade 100 further includes the following steps:
generating a blade profile line coordinate point by the blade model with the chamfer;
and inputting the coordinate points of the blade profile lines into a numerical control machine, and starting the numerical control machine to process to obtain the compressor blade 100.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes or modifications to these embodiments may be made by those skilled in the art without departing from the principle and spirit of this invention, and these changes and modifications are within the scope of this invention.
Claims (8)
1. The chamfer modeling method for the compressor blade is characterized in that a platform of the compressor blade is integrally formed at the blade root and/or the blade tip of the compressor blade, a chamfer with the radius of R is arranged at the joint of the compressor blade and the platform, and the chamfer modeling method comprises the following steps:
s1, inputting a basic model of the compressor blade without a chamfer angle, wherein the basic model comprises the platform;
s2, determining one chamfering arc of the chamfering area on the basic model:
selecting a point X on a blade profile line at the blade root and/or the blade tip of the compressor blade, selecting a point P on the edge platform in the normal direction of the point X, solving the normal vector of the point P, obtaining the sphere center O of the sphere S1 according to the chamfer radius R, and calculating the minimum value l of the distance from the coordinate point of the blade profile line of the compressor blade to the sphere center O min ；
By moving point P in the normal direction of point X, point A and point B are found, respectively, such that l is located at point A min >R, point l at B min <R, then obtaining a tangent of the ball S1 and the blade profile surface of the compressor blade through a dichotomy, calculating a tangent point C of the ball S1 and the surface of the platform and a tangent point D of the ball S1 and the surface of the blade of the compressor blade, wherein an arc passing through the tangent point C and the tangent point D, with the circle center of O and the radius of R, is a chamfer arc;
s3, repeating the step S2, and determining a plurality of chamfer arcs in the circumferential direction of the compressor blade;
s4, respectively selecting a plurality of points on each chamfering circular arc according to the same rule, and connecting the points at corresponding positions on the plurality of chamfering circular arcs to form a closed curve to obtain a blade-shaped profile of the chamfering area;
and S5, replacing the blade-shaped molded line at the corresponding position in the basic model with the obtained blade-shaped molded line of the chamfer area to obtain the blade model with the chamfer.
2. The compressor blade fillet forming method as set forth in claim 1, wherein the tangent point D is obtained by:
s21, finding a point D on the compressor blade 1 So that the point D 1 The absolute value of the difference between the distance to the center O of the sphere and the chamfer radius R is smallest;
s22, at point D 1 The circumferential direction of the located blade profile line is selected to be positioned at a point D 1 Points D on both sides 2 And D 3 Determining a passing point D 1 、D 2 、D 3 Sphere S of four points of point X2, determining the sphere center O of the sphere S2 1 ；
S23, the center O of the ball S1 and the center O of the ball S2 1 Are connected into a straight line, and the tangent points D are positioned at the sphere center O and the sphere center O 1 And the distance to the center O of the sphere is R.
3. The compressor blade fillet forming method of claim 2, wherein the point D 2 And D 3 And the blades are positioned in the same blade profile of the compressor blade during selection.
4. The method for fillet forming of a compressor blade according to claim 1, wherein in step S4, the profile line of the resulting fillet area is smoothed.
5. The compressor blade fillet forming method according to claim 1, wherein the step S5 further includes the steps of:
s51, determining an upper end blade profile and a lower end blade profile which are respectively identical to the blade profile at the upper boundary and the lower boundary of the chamfer arc in the basic model of the compressor blade;
and S52, correspondingly replacing all blade profile molded lines between the upper end blade profile and the lower end blade profile in the basic model of the compressor blade with the blade profile molded lines of the chamfer area obtained in the step S4 to obtain the blade model with the chamfer.
6. The fillet forming method for compressor blades according to claim 1, further comprising the following steps after step S5:
and S6, generating a blade molded line coordinate point of the blade model with the chamfer and outputting the blade molded line coordinate point.
7. A method for machining a compressor blade, characterized by comprising chamfering a blade root and/or a blade tip of the compressor blade by the method for chamfering a compressor blade according to any one of claims 1 to 5.
8. The method of machining a compressor blade according to claim 7, further comprising the steps of:
generating a blade molded line coordinate point by the blade model with the chamfer;
and inputting the blade profile line coordinate point into a numerical control machine tool, and starting the numerical control machine tool for processing to obtain the compressor blade.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110778660.2A CN115600328A (en) | 2021-07-09 | 2021-07-09 | Chamfer angle molding method and machining method of compressor blade |
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| CN202110778660.2A CN115600328A (en) | 2021-07-09 | 2021-07-09 | Chamfer angle molding method and machining method of compressor blade |
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| CN202110778660.2A Pending CN115600328A (en) | 2021-07-09 | 2021-07-09 | Chamfer angle molding method and machining method of compressor blade |
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- 2021-07-09 CN CN202110778660.2A patent/CN115600328A/en active Pending
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