CN103136426B - Aviation blade circular arc leading-trailing edge process model generation method - Google Patents

Aviation blade circular arc leading-trailing edge process model generation method Download PDF

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CN103136426B
CN103136426B CN201310064932.8A CN201310064932A CN103136426B CN 103136426 B CN103136426 B CN 103136426B CN 201310064932 A CN201310064932 A CN 201310064932A CN 103136426 B CN103136426 B CN 103136426B
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blade
point
leading edge
circular arc
curve
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CN103136426A (en
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程云勇
朱真真
汪文虎
王增强
王丽雅
李维亮
杨杰
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Northwestern Polytechnical University
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Northwestern Polytechnical University
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Abstract

The invention discloses an aviation blade circular arc leading-trailing edge process model generation method which is used for solving the technical problem that process models are difficult to establish for processing circular arc leading-trailing edge blades in the prior art. The technical scheme includes a leading edge process model meeting requirements is determined by utilizing two tangent lines at an endpoint of a blade leading edge curve, an angular bisector of the blade leading edge curve and geometrical information of a blade leading edge point and the like according to the characteristic that the blade leading edge curve is tangent to blade basin and blade back curves and according to distance between a leading edge point of a set leading edge process model and a leading edge point of a CAD (computer-aided design) model. In engineering application, a user can obtain accurate circular arc leading-trailing edge process models quickly only by setting leading-trailing edge process allowances according to actual needs, and uses the process models for guiding high-quality processing of aviation blades.

Description

Aerial blade circular arc front and rear edge process modeling generation method
Technical field
The present invention relates to a kind of aerial blade front and rear edge process modeling generation method, particularly relate to a kind of aerial blade circular arc front and rear edge process modeling generation method.
Background technology
Aeromotor inside is made up of a series of blade, substantially as turbo blade, compressor blade, fan blade etc.; Aerial blade is as the core part of engine, and its model mostly is free form surface, and moulding process is comparatively complicated; Meanwhile, the Design and manufacture level of blade profile determines the performance of engine to a great extent; Therefore the manufacturing technology of aerial blade is one of technology comparatively complicated in machinery manufacturing industry.
The manufacture of aerial blade mainly includes the methods such as investment pattern precision casting, digital control processing and the processing of some solution.Adopt the method for digital control processing to carry out thin wall vane processing, easily produce larger problem on deformation, and the problem of process system due to workpiece, cutter, fixture and lathe composition itself, can produce when blade processing cut or process less than phenomenon; If directly processed based on blade cad model, the unmanageable problem of blade shape precision can be caused, thus affect the crudy of blade.The improvement of prior art to blade processing quality carries out reversible deformation compensation based on the thought of reversible deformation to the error in blade forming process; Mainly based on blade investment pattern precision casting forming method, casting technique model is set up to the research of blade production model.For the digital control processing of aviation thin-wall blade, on the basis of blade cad model, consider the allowance balance situation of blade blade position leaf basin, blade back, leading edge and trailing region, set up the numerical control processing technology model of blade, for guarantee blade processing quality, there is important using value.
Summary of the invention
Being difficult to set up the deficiency of process modeling in order to overcome prior art Machining Arc shape front and rear edge blade, the invention provides a kind of aerial blade circular arc front and rear edge process modeling generation method.The method is according to the feature of blade inlet edge curve and leaf basin, blade back contact of a curve, utilize two tangent lines and the angular bisector thereof at blade inlet edge endpoint curve place, and the geological information such as the leading edge point of blade, and according to the leading edge point of leading edge process modeling set and the distance size of former cad model leading edge point, determine the leading edge process modeling met the demands.In engineer applied, user only needs according to the actual requirements, and setting front and rear edge process allowance, can obtain circular arc front and rear edge blade production model accurately fast, process in order to instruct the high-quality of aerial blade.
The technical solution adopted for the present invention to solve the technical problems is: a kind of aerial blade circular arc front and rear edge process modeling generation method, is characterized in comprising the following steps:
Step one, read in aerial blade cad model;
Step 2, along vertical Z to intercepting a certain cross section of aerial blade, leading edge curve L and leaf basin, blade back point of contact are designated as P respectively 1, P 2, ask P 1, P 2place tangent line L 1, L 2and two intersection point O (O of tangent line x, O y);
Leading edge Curves at the equation of circle is: (x-x 0) 2+ (y-y 0) 2=r 2wherein, the center of circle is (x 0, y 0), radius is r; On calculated curve, the slope of any point is k i=(x i-x 0)/(y i-y 0), wherein (x i, y i) be any point on curve, then any point (x on curve i, y i) tangential equation: y=y i+ k i(x-x i);
By P 1the slope k at place 1try to achieve the tangent line L at this some place 1be respectively y=y 1+ k 1(x-x 1), by P 2the slope k at place 2try to achieve the tangent line L at 2 places 2be respectively y=y 2+ k 2(x-x 2); The then intersection point O (O of two tangent lines x, O y) coordinate be ( y 2 - k 2 x 2 - y 1 + k 1 x 1 k 1 - k 2 , k 1 k 2 ( x 1 - x 2 ) k 1 - k 2 ) .
The angular bisector L of two tangent line angles in step 3, calculation procedure two 3, utilize formula obtain the tangent slope k of angular bisector, then angular bisector is y 3=O y+ k (x 3-O x);
Angular bisector L in step 4, calculation procedure three 3with the intersection point of leading edge curve L, be the leading edge point P of circular arc front edge 0;
Step 5, setting process allowance δ, with leading edge point P 0for benchmark, along P 0the direction of O, asks a P 0distance be that the straight line of δ makes L 4;
Step 6, to obtain and L 1, L 2, L 4simultaneously tangent circle, utilizes point (x m, y m) to the range formula of straight line Ax+By+C=0 first at L 3on look for center of circle M (m x, m y) to L 1, L 2, L 4distance equal; And obtain this distance d m, as the radius of tangent circle M; Point of contact is designated as T respectively 1, T 2, T 3, intercept corresponding arc section, and smooth link line segment T 1p 1｀ T 2p 2and circular arc T 1t 2, segment of curve P 1t 3p 2be aerial blade circular arc front edge process modeling.
The invention has the beneficial effects as follows: due to the feature according to blade inlet edge curve and leaf basin, blade back contact of a curve, utilize two tangent lines and the angular bisector thereof at blade inlet edge endpoint curve place, and the geological information such as the leading edge point of blade, and according to the leading edge point of leading edge process modeling set and the distance size of former cad model leading edge point, determine the leading edge process modeling met the demands.In engineer applied, user only needs according to the actual requirements, and setting front and rear edge process allowance, can obtain circular arc front and rear edge blade production model accurately fast, process in order to instruct the high-quality of aerial blade.
Below in conjunction with drawings and Examples, the present invention is elaborated.
Accompanying drawing explanation
Fig. 1 is the process flow diagram of aerial blade circular arc front edge process modeling generation method of the present invention.
Fig. 2 is the process schematic of the inventive method aerial blade circular arc front edge process modeling generation method.
Fig. 3 is the aerial blade circular arc front edge process modeling schematic diagram that the inventive method embodiment generates.
Embodiment
With reference to Fig. 1 ~ 3.Aerial blade circular arc front and rear edge process modeling generation method concrete steps of the present invention are as follows:
Step one, read in aerial blade cad model;
Step 2, along vertical Z to intercepting a certain cross section of aerial blade, leading edge curve L and leaf basin, blade back point of contact are designated as P respectively 1, P 2, ask P 1, P 2place tangent line L 1, L 2and two intersection point O (O of tangent line x, O y);
Leading edge Curves at the equation of circle is: (x-x 0) 2+ (y-y 0) 2=r 2wherein, the center of circle is (x 0, y 0), radius is r; On calculated curve, the slope of any point is k i=(x i-x 0)/(y i-y 0), wherein (x i, y i) be any point on curve, then any point (x on curve i, y i) tangential equation: y=y i+ k i(x-x i);
By P 1the slope k at place 1try to achieve the tangent line L at this some place 1be respectively y=y 1+ k 1(x-x 1), by P 2the slope k at place 2try to achieve the tangent line L at 2 places 2be respectively y=y 2+ k 2(x-x 2); The then intersection point O (O of two tangent lines x, O y) coordinate be ( y 2 - k 2 x 2 - y 1 + k 1 x 1 k 1 - k 2 , k 1 k 2 ( x 1 - x 2 ) k 1 - k 2 ) .
The angular bisector L of two tangent line angles in step 3, calculation procedure two 3, utilize formula obtain the tangent slope k of angular bisector, then angular bisector is y 3=O y+ k (x 3-O x);
Angular bisector L in step 4, calculation procedure three 3with the intersection point of leading edge curve L, be the leading edge point P of circular arc front edge 0;
Step 5, setting process allowance δ, with leading edge point P 0for benchmark, along P 0the direction of O, asks a P 0distance be that the straight line of δ makes L 4;
Step 6, to obtain and L 1, L 2, L 4simultaneously tangent circle, utilizes point (x m, y m) to the range formula of straight line Ax+By+C=0 first at L 3on look for center of circle M (m x, m y) to L 1, L 2, L 4distance equal; And obtain this distance d m, as the radius of tangent circle M; Point of contact is designated as T respectively 1, T 2, T 3, intercept corresponding arc section, and smooth link line segment T 1p 1, T 2p 2and circular arc T 1t 2, segment of curve P 1t 3p 2be aerial blade circular arc front edge process modeling.
Application Example:
This embodiment is certain h type engine h circular arc front edge blade, and circular arc front edge place equation of a circle is (x-32.73) 2+ (y+3.34) 2=0.28 2, leading edge curve L and leaf basin, blade back point of contact are respectively P 1(32.77 ,-3.62), P 2(32.71 ,-3.06);
Being described in detail in conjunction with the accompanying drawings and embodiments to circular arc front and rear edge process modeling generation method of the present invention, concrete steps are as follows:
Step one, read in blade cad model;
Step 2, along vertical Z to intercepting a certain cross section of aerial blade, leading edge curve L and leaf basin, blade back point of contact are designated as P respectively 1, P 2, ask P 1, P 2place tangent line L 1, L 2and two intersection point O (O of tangent line x, O y);
Leading edge Curves at the equation of circle is: (x-x 0) 2+ (y-y 0) 2=r 2wherein, the center of circle is (x 0, y 0), radius is r; On calculated curve, the slope of any point is k i=(x i-x 0)/(y i-y 0), wherein (x i, y i) be any point on curve, then any point (x on curve i, y i) tangential equation: y=y i+ k i(x-x i);
By P 1the slope k at place 1try to achieve the tangent line L at this some place 1be respectively y=y 1+ k 1(x-x 1), by P 2the slope k at place 2try to achieve the tangent line L at 2 places 2be respectively y=y 2+ k 2(x-x 2); The then intersection point O (O of two tangent lines x, O y) coordinate be ( y 2 - k 2 x 2 - y 1 + k 1 x 1 k 1 - k 2 , k 1 k 2 ( x 1 - x 2 ) k 1 - k 2 ) .
The angular bisector L of two tangent line angles in step 3, calculation procedure two 3: utilize formula obtain the tangent slope k of angular bisector, then angular bisector is y 3=O y+ k (x 3-O x);
Angular bisector L in step 4, calculation procedure three 3with the intersection point of leading edge curve L, be the leading edge point P of circular arc front edge 0;
Step 5, setting process allowance δ=0.15mm, with leading edge point P 0for benchmark, along P 0o direction, asks a P 0distance be the straight line L of δ 4;
Step 6, to obtain and L 1, L 2, L 4simultaneously tangent circle: utilize point (x m, y m) to the range formula of straight line Ax+By+C=0 first at L 3on look for center of circle M (m x, m y) to L 1, L 2, L 4distance equal; And obtain this distance d m, as the radius of tangent circle M; Point of contact is designated as T respectively 1, T 2, T 3, intercept corresponding arc section, and smooth link line segment T 1p 1, T 2p 2and circular arc T 1t 2, segment of curve P 1t 3p 2be aerial blade circular arc front edge process modeling.
The process modeling of cross section circular arc front edge selected by the blade generated by above-mentioned several step as shown in Figure 3.Wherein, the arc section T of leading edge process modeling 1t 2place circle is (x-32.88) 2+ (y+3.32) 2=0.27 2, and T 1(32.93 ,-3.59), T 2(32.87 ,-3.05).
In sum, the inventive method is in engineer applied, by importing cad model and setting fabrication error, the process model of aerial blade can be generated, and then instruct the processing of aerial blade, the mistake that in aerial blade process, front and rear edge place may occur effectively can be avoided to cut problem, thus ensure the crudy of aerial blade.

Claims (1)

1. an aerial blade circular arc front and rear edge process modeling generation method, is characterized in that comprising the following steps:
Step one, read in aerial blade cad model;
Step 2, along vertical Z to intercepting a certain cross section of aerial blade, leading edge curve L and leaf basin, blade back point of contact are designated as P respectively 1, P 2, ask P 1, P 2place tangent line L 1, L 2and two intersection point O (O of tangent line x, O y);
Leading edge Curves at the equation of circle is: (x-x 0) 2+ (y-y 0) 2=r 2wherein, the center of circle is (x 0, y 0), radius is r; On calculated curve, the slope of any point is k i=(x i-x 0)/(y i-y 0), wherein (x i, y i) be any point on curve, then any point (x on curve i, y i) tangential equation: y=y i+ k i(x-x i);
By P 1the slope k at place 1try to achieve the tangent line L at this some place 1be respectively y=y 1+ k 1(x-x 1), by P 2the slope k at place 2try to achieve the tangent line L at 2 places 2be respectively y=y 2+ k 2(x-x 2); The then intersection point O (O of two tangent lines x, O y) coordinate be ( y 2 - k 2 x 2 - y 1 + k 1 x 1 k 1 - k 2 , k 1 k 2 ( x 1 - x 2 ) k 1 - k 2 ) ;
The angular bisector L of two tangent line angles in step 3, calculation procedure two 3, utilize formula obtain the tangent slope k of angular bisector, then angular bisector is y 3=O y+ k (x 3-O x);
Angular bisector L in step 4, calculation procedure three 3with the intersection point of leading edge curve L, be the leading edge point P of circular arc front edge 0;
Step 5, setting process allowance δ, with leading edge point P 0for benchmark, along P 0the direction of O, asks a P 0distance be that the straight line of δ makes L 4;
Step 6, to obtain and L 1, L 2, L 4simultaneously tangent circle, utilizes point (x m, y m) to the range formula of straight line Ax+By+C=0 first at L 3on look for center of circle M (m x, m y) to L 1, L 2, L 4distance equal; And obtain this distance d m, as the radius of tangent circle M; Point of contact is designated as T respectively 1, T 2, T 3, intercept corresponding arc section, and smooth link line segment T 1p 1, T 2p 2and circular arc segment of curve P 1t 3p 2be aerial blade circular arc front edge process modeling.
CN201310064932.8A 2013-03-01 2013-03-01 Aviation blade circular arc leading-trailing edge process model generation method Expired - Fee Related CN103136426B (en)

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CN110110414B (en) * 2019-04-26 2022-08-16 西北工业大学 Thin-wall blade machining error compensation geometric modeling method
CN112197922B (en) * 2020-08-25 2022-03-25 中国航发湖南动力机械研究所 Turbine blade vibration fatigue simulation piece and design method thereof
CN116900808B (en) * 2023-09-14 2023-12-26 成都航空职业技术学院 Error compensation method and system for numerical control milling deformation of aero-engine blade

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