CN103136426A - 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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CN103136426A
CN103136426A CN2013100649328A CN201310064932A CN103136426A CN 103136426 A CN103136426 A CN 103136426A CN 2013100649328 A CN2013100649328 A CN 2013100649328A CN 201310064932 A CN201310064932 A CN 201310064932A CN 103136426 A CN103136426 A CN 103136426A
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blade
point
leading edge
circular arc
curve
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CN103136426B (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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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 comprised of a series of blades 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 has determined 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 manufacturing of aerial blade has mainly comprised 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 the process system that forms due to workpiece, cutter, fixture and lathe itself, can produce when blade processing cut or process less than phenomenon; If directly process based on the blade cad model, can cause the unmanageable problem of blade shape precision, thereby affect the crudy of blade.Prior art is based on the thought of reversible deformation the error in the blade forming process is carried out the reversible deformation compensation to the improvement of blade processing quality; The research of blade process modeling mainly is based on blade investment pattern precision casting forming method sets up the casting technique model.Digital control processing for the aviation thin wall vane, on the basis of blade cad model, consider the surplus distribution situation in blade blade position leaf basin, blade back, leading edge and trailing edge zone, set up the numerical control processing technology model of blade, for guaranteeing that the blade processing quality has important using value.
Summary of the invention
The deficiency that is difficult to set up 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 characteristics 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 informations such as leading edge point of blade, and according to the leading edge point of the leading edge process modeling of setting and the distance size of former cad model leading edge point, determine the leading edge process modeling that meets the demands.During engineering is used, the user only needs according to the actual requirements, sets the front and rear edge process allowance, can obtain fast circular arc front and rear edge blade process modeling accurately, in order to instruct the high-quality processing 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 1, read in the aerial blade cad model;
Step 2, along vertical Z to intercepting aerial blade a certain cross section, leading edge curve L and leaf basin, blade back point of contact is designated as respectively P 1, P 2, ask P 1, P 2The tangent line L of place 1, L 2And the intersection point O (O of two tangent lines x, O y);
The 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), (x wherein i, y i) be any point on curve, 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 2 tangent line L that locate 2Be respectively y=y 2+ k 2(x-x 2); Intersection point O (the 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
Figure BDA00002873435200022
Obtain the tangent slope k of angular bisector, 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 are with leading edge point P 0Be benchmark, along P 0The direction of O is asked a P 0Distance be that the straight line of δ is made L 4
Step 6, 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
Figure BDA00002873435200023
At first at L 3On look for center of circle M (m x, m y) to L 1, L 2, L 4Distance equate; And obtain this apart from d m, as the radius of tangent circle M; The point of contact is designated as respectively T 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 characteristics 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 informations such as leading edge point of blade, and according to the leading edge point of the leading edge process modeling of setting and the distance size of former cad model leading edge point, determine the leading edge process modeling that meets the demands.During engineering is used, the user only needs according to the actual requirements, sets the front and rear edge process allowance, can obtain fast circular arc front and rear edge blade process modeling accurately, in order to instruct the high-quality processing of aerial blade.
Below in conjunction with drawings and Examples, the present invention is elaborated.
Description of drawings
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 diagram 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 1, read in the aerial blade cad model;
Step 2, along vertical Z to intercepting aerial blade a certain cross section, leading edge curve L and leaf basin, blade back point of contact is designated as respectively P 1, P 2, ask P 1, P 2The tangent line L of place 1, L 2And the intersection point O (O of two tangent lines x, O y);
The 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), (x wherein i, y i) be any point on curve, 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 2 tangent line L that locate 2Be respectively y=y 2+ k 2(x-x 2); Intersection point O (the 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
Figure BDA00002873435200032
Obtain the tangent slope k of angular bisector, 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 are with leading edge point P 0Be benchmark, along P 0The direction of O is asked a P 0Distance be that the straight line of δ is made L 4
Step 6, 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
Figure BDA00002873435200033
At first at L 3On look for center of circle M (m x, m y) to L 1, L 2, L 4Distance equate; And obtain this apart from d m, as the radius of tangent circle M; The point of contact is designated as respectively T 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 is respectively P 1(32.77 ,-3.62), P 2(32.71 ,-3.06);
To being elaborated of circular arc front and rear edge process modeling generation method of the present invention, concrete steps are as follows in conjunction with the accompanying drawings and embodiments:
Step 1, read in the blade cad model;
Step 2, along vertical Z to intercepting aerial blade a certain cross section, leading edge curve L and leaf basin, blade back point of contact is designated as respectively P 1, P 2, ask P 1, P 2The tangent line L of place 1, L 2And the intersection point O (O of two tangent lines x, O y);
The 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), (x wherein i, y i) be any point on curve, 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 2 tangent line L that locate 2Be respectively y=y 2+ k 2(x-x 2); Intersection point O (the 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
Figure BDA00002873435200042
Obtain the tangent slope k of angular bisector, 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 are with leading edge point P 0Be benchmark, along P 0The O direction is asked a P 0Distance be the straight line L of δ 4
Step 6, 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
Figure BDA00002873435200051
At first at L 3On look for center of circle M (m x, m y) to L 1, L 2, L 4Distance equate; And obtain this apart from d m, as the radius of tangent circle M; The point of contact is designated as respectively T 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 the blade selected cross section circular arc front edge that generates by above-mentioned several steps as shown in Figure 3.Wherein, the arc section T of leading edge process modeling 1T 2The place 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 engineering is used, by importing cad model and setting fabrication error, can generate the process model of aerial blade, and then instruct the processing of aerial blade, can effectively avoid the mistake that front and rear edge in aerial blade process place may occur to cut problem, thereby guarantee the crudy of aerial blade.

Claims (1)

1. aerial blade circular arc front and rear edge process modeling generation method is characterized in that comprising the following steps:
Step 1, read in the aerial blade cad model;
Step 2, along vertical Z to intercepting aerial blade a certain cross section, leading edge curve L and leaf basin, blade back point of contact is designated as respectively P 1, P 2, ask P 1, P 2The tangent line L of place 1, L 2And the intersection point O (O of two tangent lines x, O y);
The 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), (x wherein i, y i) be any point on curve, 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 2 tangent line L that locate 2Be respectively y=y 2+ k 2(x-x 2); Intersection point O (the 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
Figure FDA00002873435100012
Obtain the tangent slope k of angular bisector, 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 are with leading edge point P 0Be benchmark, along P 0The direction of O is asked a P 0Distance be that the straight line of δ is made L 4
Step 6, 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 At first at L 3On look for center of circle M (m x, m y) to L 1, L 2, L 4Distance equate; And obtain this apart from d m, as the radius of tangent circle M; The point of contact is designated as respectively T 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.
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CN104331561A (en) * 2014-11-06 2015-02-04 西北工业大学 Method for building blade rolling process model
CN109214032A (en) * 2017-12-07 2019-01-15 中国航空制造技术研究院 A kind of adaptive machining method of hollow blade
CN110110414A (en) * 2019-04-26 2019-08-09 西北工业大学 Thin wall vane mismachining tolerance compensates Geometric Modeling Method
CN112197922A (en) * 2020-08-25 2021-01-08 中国航发湖南动力机械研究所 Turbine blade vibration fatigue simulation piece and design method thereof
CN116900808A (en) * 2023-09-14 2023-10-20 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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CN102728880A (en) * 2012-07-12 2012-10-17 西北工业大学 Cutter shaft control method of leading line yielding track in blade helical milling process

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104331561A (en) * 2014-11-06 2015-02-04 西北工业大学 Method for building blade rolling process model
CN109214032A (en) * 2017-12-07 2019-01-15 中国航空制造技术研究院 A kind of adaptive machining method of hollow blade
CN109214032B (en) * 2017-12-07 2019-06-21 中国航空制造技术研究院 A kind of adaptive machining method of hollow blade
CN110110414A (en) * 2019-04-26 2019-08-09 西北工业大学 Thin wall vane mismachining tolerance compensates Geometric Modeling Method
CN110110414B (en) * 2019-04-26 2022-08-16 西北工业大学 Thin-wall blade machining error compensation geometric modeling method
CN112197922A (en) * 2020-08-25 2021-01-08 中国航发湖南动力机械研究所 Turbine blade vibration fatigue simulation piece and design method thereof
CN116900808A (en) * 2023-09-14 2023-10-20 成都航空职业技术学院 Error compensation method and system for numerical control milling deformation of aero-engine blade
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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