CN113255068B - Modeling method of aero-engine blade blank and machining method of aero-engine blade - Google Patents
Modeling method of aero-engine blade blank and machining method of aero-engine blade Download PDFInfo
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Abstract
The invention relates to a modeling method of an aircraft engine blade blank and a machining method of an aircraft engine blade. The modeling method comprises the following steps: obtaining a blade model of a net-size blade of an aeroengine; dividing the blade model into a plurality of cross sections between the blade tip and the blade root; cutting the blade model in a mean camber line direction perpendicular to each cross section at a position which is a first preset distance away from the front edge and/or the tail edge of the blade along the chord direction of the blade model; taking the section of the blade model as a reference, and extending a second preset distance in the direction away from the blade along the normal direction of the section of each cross section to generate an extension section; the second preset distance is greater than the first preset distance; taking the section of the blade model as the initial end of the extension section, wherein the thickness of the blade part corresponding to the initial end of the extension section is greater than that of the blade part corresponding to the termination end of the extension section; and forming a blank model of the aero-engine blade. The invention is used for improving the processing precision of the blade.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a modeling method of an aero-engine blade blank and a machining method of an aero-engine blade.
Background
At present, a machining method without allowance is often adopted for the blade of the aero-engine, the machining efficiency can be improved, and the blade body part can achieve sufficient precision. However, with the development of the aircraft engine technology, the requirement of the designer for the machining precision is continuously increased, and the machining method completely without margin is slightly insufficient in the treatment of the leading edge and the trailing edge, which is embodied in the following two points:
on one hand, with the development of aviation technology, the single-stage pressure ratio of the compressor is continuously improved. The high load operating environment results in a significant increase in the aerodynamic sensitivity of the blade. Minor deviations introduced in the process can have a severe impact on aerodynamic performance. The influence of the shape of the front edge and the tail edge of the blade on the performance is the most obvious, and the complex geometry of the front edge and the tail edge which are machined at one time by a machining method without allowance forming has certain risks.
On the other hand, to realize lightweight design, composite blades are widely used in aircraft engines, and the RTM process of composite blades has edge effects, namely: after the blade is formed, due to the release of internal stress, the blade has certain deformation which is most obvious at the edge (blade tip and front and tail edges), and the forming method without allowance is difficult to ensure the processing precision requirement of the front and tail edges.
Disclosure of Invention
Some embodiments of the invention provide a modeling method of an aircraft engine blade blank and a machining method of an aircraft engine blade, which are used for improving the machining precision of the aircraft engine blade.
Some embodiments of the invention provide a method of modeling an aircraft engine blade blank, comprising:
obtaining a blade model of a net-size blade of an aeroengine;
dividing the blade model into a plurality of cross sections between the blade tip and the blade root, wherein two adjacent cross sections are arranged along the direction from the blade tip to the blade root or along the direction from the blade root to the blade tip;
cutting the blade model in a mean camber line direction perpendicular to each cross section at a position which is a first preset distance away from the front edge and/or the tail edge of the blade along the chord direction of the blade model;
taking the section of the blade model as a reference, and extending a second preset distance in the direction away from the blade along the normal direction of the section of each cross section to generate an extension section; the second preset distance is greater than the first preset distance;
taking the section of the blade model as the initial end of the extension section, wherein the thickness of the blade part corresponding to the initial end of the extension section is greater than that of the blade part corresponding to the termination end of the extension section;
and forming a blank model of the blade of the aircraft engine.
In some embodiments, a tangent line at the intersection of the extension section and the blade body is tangent to the blade body, and the extension direction of the termination end of the extension section is parallel to the normal direction of the section plane.
In some embodiments, the thickness of the blade portion corresponding to the extension section gradually decreases along the direction from the starting end to the terminating end of the extension section.
In some embodiments, in one cross section of the blade model, the thickness of the blade part corresponding to the starting end is represented by a straight line segment CD on the starting end of the extending segment; the thickness of the blade part corresponding to the termination end on the termination end of the extension section is represented by a straight line section AB, and the straight line section AB is parallel to the straight line section CD;
connecting a midpoint N of the straight-line segment CD with a midpoint M of the straight-line segment AB to obtain a straight-line segment MN, wherein the direction of the straight-line segment MN is the chord direction of the extension segment, and the straight-line segment MN is perpendicular to the straight-line segment CD;
the length of the straight line segment AB is less than that of the straight line segment CD;
the point A and the point D are positioned on the first side of the straight-line segment MN, the point B and the point C are positioned on the second side of the straight-line segment MN, and the first side and the second side of the straight-line segment MN are opposite;
connecting the point A and the point D to form an AD curve section; connecting point B and point C forms a BC curve segment.
In some embodiments, when a rectangular coordinate system is established with the N point as the origin of coordinates, the direction from the N point to the D point as the Y axis direction, and the direction from the N point to the M point as the X axis direction, the AD curve segment equation is:
y＝(1-t n )(a 1 x+a 2 )+t n (a 3 x 3 +a 4 x 2 +a 5 x+a 6 )
wherein the content of the first and second substances,
n is a selective input parameter for controlling the shape characteristics of the curve segment;
a i (i =1,2, · 6) is the coefficient to be determined;
obtain information about a i (i =1,2.., 6) to obtain a i (i =1,2,.., 6), and then obtaining the AD curve segment equation.
In some embodiments of the present invention, the,coordinate the point A (x) A ，y A ) And D point coordinates (x) D ，y D ) Respectively substituting the AD curve segment equation to obtain the A i Two of the equations of (i =1,2.
In some embodiments, the AD curve segment equation is derived to obtain a derivative function equation:
let the tangent at point A on the AD curve segment be parallel to the straight line segment MN, then y' (x) A )＝0；
Make the tangent line of point D on the AD curve segment tangent with the blade body, y' (x) D ) The value of (a) is determined by the slope of the blade body;
will (x) A ，y′(x A ) And (x) D ，y′(x D ) Substituting into the tangent equation of the AD curve segment to obtain the equation about a i (i =1,2.., 6).
In some embodiments, let cubic curve y = a 3 x 3 +a 4 x 2 +a 5 x+a 6 Passing through the point A and the point D to obtain the point A i Two more equations for (i =1,2.
In some embodiments, the first predetermined distance from the leading edge of the blade is 1 to 2.5 times the thickness of the leading edge of the blade; the first preset distance from the trailing edge of the blade is 1-2.5 times the thickness of the trailing edge of the blade.
In some embodiments, the second predetermined distance is 5% to 10% of the chord length of the blade.
In some embodiments, the ratio of the length of the straight line segment AB to the length of the straight line segment CD is a predetermined ratio, and the predetermined ratio ranges from 0.5 to 0.8.
In some embodiments, n ranges from 3.0 to 10.0.
Some embodiments of the invention provide a method of machining an aircraft engine blade comprising:
establishing an aero-engine blade blank model by adopting the modeling method of the aero-engine blade blank;
processing an aero-engine blade blank by using the aero-engine blade blank model;
and machining the extension section of the aircraft engine blade blank to form the blade leading edge and/or the blade trailing edge of the aircraft engine blade.
Based on the technical scheme, the invention at least has the following beneficial effects:
in some embodiments, the blade leading edge and/or the blade trailing edge of the blade model are/is cut off and then is generated into an extension section, and the blade blank model is processed to generate an aeroengine blade blank; and machining the front edge/the tail edge of the blank to form the aero-engine blade so as to solve the problem of poor machining quality of the front edge/the tail edge caused by factors such as edge effect and the like during the forming of the aero-engine blade.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention and do not constitute a limitation of the invention. In the drawings:
FIG. 1 is a schematic illustration of a partitioning of a blade model into cross-sections provided in accordance with some embodiments of the present invention;
FIG. 2 is a schematic view of a curvilinear configuration of a cross-sectional generating extension segment of a blade model provided in accordance with some embodiments of the invention;
fig. 3 is a schematic diagram illustrating the influence of the control parameter n on the curve of the stretch according to some embodiments of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without any inventive step, are within the scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
As shown in fig. 1, a pre-processed blade model 1 of an aircraft engine blade is provided for some embodiments, wherein the blade model 1 of the aircraft engine blade includes a blade body 15, a blade tip 11, a blade root 12, a blade leading edge 13 and a blade trailing edge 14. The direction from the blade leading edge 13 to the blade trailing edge 14 is the chord direction of the blade.
Some embodiments provide a method of modeling an aircraft engine blade blank, comprising:
a blade model 1 of a net size blade of an aircraft engine is obtained. The blade model 1 of an aircraft engine blade is formed when designing an aircraft engine blade.
The blade model 1 is divided into a plurality of cross sections 2 between a blade tip 11 and a blade root 12, and two adjacent cross sections 2 are arranged along the direction from the blade tip 11 to the blade root 12 or along the direction from the blade root 12 to the blade tip 11. Optionally, the cross section 2 of the blade model 1 is an airfoil profile.
Truncating the blade model 1 in a mean camber line direction perpendicular to each cross section 2 at a position which is a first preset distance away from the blade front edge 13 and/or the blade tail edge 14 along the chord direction of the blade model 1; since the first predetermined distance is much smaller than the chord length of the blade, the remaining part after truncation is the blade body 15.
And taking the section 2 of the blade model 1 as a reference, and extending a second preset distance in the direction away from the blade body 15 along the normal direction of each section to generate an extension section 3. The second preset distance is larger than the first preset distance. The blade leading edge 13 and the blade trailing edge 14 are both called extension sections 3 after being truncated.
The section of the blade model 1 is taken as the starting end of the extension section 3, and the thickness of the blade part corresponding to the starting end of the extension section 3 is larger than that of the blade part corresponding to the ending end of the extension section 3.
And forming a blank model of the aero-engine blade.
Processing the aero-engine blade blank model to generate an aero-engine blade blank; the extension section 3 of the blank of the blade of the aero-engine is machined to form the leading edge 13 and/or the trailing edge 14 of the blade of the aero-engine, so that the problem of poor processing quality of the leading edge and/or the trailing edge caused by factors such as edge effect and the like during forming of the blade of the aero-engine is solved.
Defining: the direction from the blade tip 11 to the blade root 12 or from the blade root 12 to the blade tip 11 of the blade is the height or length direction of the blade; the direction from the blade front edge 13 to the blade tail edge 14 or from the blade tail edge 14 to the blade front edge 13 is the chord direction of the blade; the direction from the pressure-side surface to the back-pressure-side surface or from the back-pressure-side surface to the pressure-side surface of the blade is the thickness direction of the blade.
In some embodiments, a tangent line where the extension 3 meets the blade airfoil 15 is tangent to the blade airfoil 15, so that the extension 3 and the blade airfoil 15 have a smooth transition. The terminating end of the extension 3 faces (in the direction of extension when continuing) parallel to the normal of the section plane. The terminating end face of the extension 3 is parallel to the section plane.
In some embodiments, the thickness of the blade portion corresponding to the extension section 3 gradually decreases along the direction from the starting end to the terminating end of the extension section 3, so that the thickness of the blade of the extension section is monotonously distributed along the chord direction.
In some embodiments, as shown in fig. 2, in a cross section 2 (a section formed by projecting from the blade tip 11 to the blade root 12) of the blade model 1, a straight line segment CD characterizing the thickness of the blade corresponding to the start end is on the start end of the extension 3; the thickness of the blade corresponding to the termination end represented on the termination end of the extension section 3 is a straight line section AB, and the straight line section AB is parallel to the straight line section CD.
And connecting the midpoint N of the straight line segment CD with the midpoint M of the straight line segment AB to obtain a straight line segment MN, wherein the direction of the straight line segment MN is the chord direction of the extension segment 3, and the straight line segment MN is vertical to the straight line segment CD.
The length of straight line segment AB is less than the length of straight line segment CD.
The point A and the point D are located on the first side of the straight-line segment MN, the point B and the point C are located on the second side of the straight-line segment MN, and the first side and the second side of the straight-line segment MN are opposite.
Connecting point a and point D forms an AD curve segment. Connecting point B and point C forms a BC curve segment.
Because the quality of the blade leading edge 13 and/or the blade trailing edge 14 generated directly by means of precision forging, RTM forming and the like is poor, when a blank is designed, the blade leading edge 13 and/or the blade trailing edge 14 are/is extended, and for the design of an extension section, a curve is required to be smooth and straight, the thickness is required to be monotonously distributed along the chord direction, and the part of the extension section is in smooth transition with the blade body 15. In order to meet the above requirements, the extension section 3 is constructed by using a combined polynomial curve, which has the characteristics of smooth transition and easy control and can generate a high-quality extension section profile.
In some embodiments, taking the point N as the origin of coordinates, the direction from the point N to the point D is the Y-axis direction (the thickness direction of the blade), and the direction from the point N to the point M is the X-axis direction, and a rectangular coordinate system is established, then the AD curve segment equation is:
y＝(1-t n )(a 1 x+a 2 )+t n (a 3 x 3 +a 4 x 2 +a 5 x+a 6 )
wherein the content of the first and second substances,
n is a selective input parameter for controlling the shape characteristics of the curve segment;
a i (i =1,2,. 6) is the coefficient to be determined;
obtain information about a i Six equations of (i =1,2,.., 6) to obtain a i (i =1,2.., 6), and then obtaining the AD curve segment equation.
In some embodiments, the A point coordinate (x) A ，y A ) And D point coordinates (x) D ，y D ) Respectively substituting the AD curve segment equation to obtain the A i Two of the equations of (i =1,2.
In some embodiments, the AD curve segment equation is derived to obtain a derivative function equation:
let the tangent direction at point A on the AD curve segment be parallel to the straight line segment MN, then y' (x) A )＝0；
The tangent line of the point D on the AD curve segment is tangent to the part of the blade body 15, y' (x) D ) The value of (d) is determined by the slope of the main blade 15 portion;
will (x) A ，y′(x A ) And (x) D ，y′(x D ) Substituting into the tangent equation of the AD curve segment to obtain the equation about a i (i =1,2.., 6).
In some embodiments, let cubic curve y = a 3 x 3 +a 4 x 2 +a 5 x+a 6 Passing through the point A and the point D to obtain the point A i Two more equations for (i =1,2.
Similarly, the BC curve segment equation is:
y＝(1-t n )(a 1 x+a 2 )+t n (a 3 x 3 +a 4 x 2 +a 5 x+a 6 )
wherein, the first and the second end of the pipe are connected with each other,
n is a selective input parameter for controlling the shape characteristics of the curve segment;
a i (i =1,2,. 6) is the coefficient to be determined;
obtain information about a i (i =1,2.., 6) to obtain a i (i =1,2.., 6), and thereby obtain the BC curve segment equation.
Coordinate point B (x) B ，y B ) And C point coordinate (x) C ，y C ) Respectively substituting into the equation of BC curve segment to obtain the equation of a i Two of the equations of (i =1,2.
And (3) carrying out derivation on the equation of the BC curve segment to obtain a derivative function equation:
let the tangent direction at point B on the curve segment BC be parallel to the straight line segment MN, then y' (x) B )＝0；
The tangent line of point C on the BC curve segment is tangent to the part of the blade body 15, y' (x) C ) The value of (d) is determined by the slope of the main blade 15 portion;
will (x) B ，y′(x B ) And (x) C ，y′(x C ) Substituting the tangent equation of the BC curve segment to obtain the equation about a i (i =1,2.., 6).
Let cubic curve y = a 3 x 3 +a 4 x 2 +a 5 x+a 6 Passing through points B and C to obtain the point A i (i =1,2.., 6).
In some embodiments, the first predetermined distance is 1 to 2.5 times the thickness of the leading edge 13 or the trailing edge 14 of the blade. Wherein, the first preset distance from the front edge 13 of the blade is 1 to 2.5 times of the thickness of the front edge 13 of the blade. The first predetermined distance from the trailing edge 14 of the blade is 1 to 2.5 times the thickness of the trailing edge 14 of the blade.
In some embodiments, the second predetermined distance is 5% to 10% of the chord length of the blade.
In some embodiments, the ratio of the length of the straight line segment AB to the length of the straight line segment CD is a predetermined ratio, and the predetermined ratio ranges from 0.5 to 0.8.
In some embodiments, n ranges from 3.0 to 10.0.
As shown in fig. 3, the value of n is used to control the radian of the curve, for example: n is n1 and n2, and n1< n2, then when n = n1, a real line segment in fig. 3 is generated correspondingly, and when n = n2, a dashed line segment in fig. 3 is generated correspondingly. The curvature of the real line segment is smaller than the curvature of the imaginary line segment.
Some embodiments provide a method of machining an aircraft engine blade, comprising:
the modeling method of the aero-engine blade blank provided by the embodiment is adopted to establish the aero-engine blade blank model. Optionally, the blade body part of the aircraft engine blade blank adopts a zero-allowance design, and the machining efficiency is ensured.
And processing the aero-engine blade blank by using the aero-engine blade blank model.
The extension section 3 of the aircraft engine blade blank is machined to form a blade leading edge 13 and/or a blade trailing edge 14 of the aircraft engine blade so as to ensure the machining accuracy of the blade leading edge 13 and/or the blade trailing edge 14.
The blade processed by the processing method of the aero-engine blade provided by the embodiment of the disclosure has the following advantages:
1) Through the design of the blank extension section, the influence of the edge effect on the machining precision is reduced, and the machining quality of the blade is improved.
2) The extension section constructed by adopting the combined polynomial curve has smooth and straight surface and monotonous thickness distribution along the chord direction, and can complete smooth and natural transition with the blade body 15 part, so that the manufacturability of a blade blank is improved, and the product percent of pass is improved.
The following is a description of a method for modeling an aircraft engine blade blank provided by an embodiment of the present disclosure, in which the method for modeling an aircraft engine blade blank includes:
1. firstly, dividing an original blade model 1 (a blade model 1 of a net-size blade of an aircraft engine) into a plurality of cross sections 2 according to the blade height, as shown in figure 1;
2. taking the blade leading edge 13 as an example, the leading edge of each cross section 2 is cut off along the mean camber line direction perpendicular to the cross sections 2, and a cut-off straight line segment CD is obtained in one of the cross sections 2, as shown in fig. 2.
The position of truncation is at about twice the blade leading edge thickness from the blade leading edge 13.
3. Taking a midpoint N of a straight line segment CD, passing the midpoint N and making an extension line MN along the outer normal direction of the cutting line, wherein the extension length is about 5 percent of the chord length of the blade, and the smoothness of the front end of the extension section is ensured;
4. taking M as a middle point as a parallel straight-line segment AB of the straight-line segment CD, wherein the length ratio of the straight-line segment AB to the straight-line segment CD is 0.5-0.8;
5. and constructing the AD curve segment and the BC curve segment by adopting a combined polynomial curve. The following description will take an AD curve segment as an example.
Firstly, a rectangular coordinate system shown in fig. 2 is established, wherein an N point is a coordinate origin, an MN direction is an X-axis direction, an ND direction is a Y-axis direction, and an equation of an AD curve segment is as follows:
y＝(1-t n )(a 1 x+a 2 )+t n (a 3 x 3 +a 4 x 2 +a 5 x+a 6 )。
wherein t is the relative position from A to D, expressed as:
a i the undetermined coefficient (i =1,2, ·, 6) can be obtained by the boundary condition between two end points of A, D.
n is an input parameter given by a designer and used for controlling the shape characteristics of the curve, and the recommended value range is between 3.0 and 10.0. n is a real number.
The curve is composed of two parts of a straight line and a cubic curve, and t is the part close to the end point A n The value is small, and the curve is close to a straight line; conversely, for portions close to end point D, t n The values are larger and the curve approaches a cubic curve.
The larger the value of n is, the same t is due to (0. Ltoreq. T. Ltoreq.1) n The larger the value of t corresponds to, the larger the range of influence of the straight part will be, as shown in fig. 3.
The curve can be adjusted by changing the value of n. Different leaf types have different thickness distribution requirements. The fullness degree of the curve can be controlled by changing the n value, so that the applicability of the curve structure is improved, the larger the n value is, the fuller the curve is, the smaller the n value is, and the sharper the curve is.
The curve equation has six waiting coefficients, and six equations need to be established for solving. Firstly, two equations can be established by the coordinate information of A, D; namely, two equations can be established by respectively substituting the coordinates of the two points A, D into the curve equation.
Then, two equations can be established by making the tangent line at point a on the curve AD parallel to the straight line segment MN and the tangent line at point D tangent to the blade body 15. Namely, a first derivative is obtained for x to obtain y '(x), and two equations can be established by substituting the equation y' (x) because the first derivatives at the two points A and D are known.
Finally, to close the equation and ensure good stability of the curve, let the cubic curve y = a 3 x 3 +a 4 x 2 +a 5 x+a 6 Two more equations can be established by crossing A, D.
Thus, the AD curve segment equation can be obtained.
In the same way, the equation of BC curve segment can be obtained.
In the description of the present invention, it should be understood that the terms "first", "second", "third", etc. are used to define the components, and are used only for the convenience of distinguishing the components, and if not otherwise stated, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present invention.
Furthermore, the technical features of one embodiment may be combined with one or more other embodiments advantageously without explicit negatives.
Finally, it should be noted that the above examples are only used to illustrate the technical solutions of the present invention and not to limit the same; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the invention as defined by the appended claims.
Claims (8)
1. A method of modeling an aircraft engine blade blank, comprising:
obtaining a blade model (1) of a net-size blade of an aircraft engine;
dividing the blade model (1) into a plurality of cross sections (2) between the blade tip (11) and the blade root (12), wherein two adjacent cross sections (2) are arranged along the direction from the blade tip (11) to the blade root (12) or along the direction from the blade root (12) to the blade tip (11);
truncating the blade model (1) in a mean camber line direction perpendicular to each cross section (2) at a position a first preset distance from the blade leading edge (13) and/or the blade trailing edge (14) along the chord direction of the blade model (1); the direction from the front edge (13) to the tail edge (14) of the blade is the chord direction of the blade model (1);
taking the section of the blade model (1) as a reference, and extending a second preset distance in the direction away from the blade along the normal direction of the section of each cross section (2) to generate an extension section (3); the second preset distance is greater than the first preset distance;
taking the section of the blade model (1) as the starting end of the extension section (3), wherein the thickness of the blade part corresponding to the starting end of the extension section (3) is greater than that of the blade part corresponding to the ending end of the extension section (3);
forming a blank model of the aero-engine blade;
in one cross section (2) of the blade model (1), the starting end of the extension section (3) represents the thickness of a blade part corresponding to the starting end and is a straight line segment CD; the thickness of the blade part corresponding to the termination end represented on the termination end of the extension section (3) is a straight line section AB, and the straight line section AB is parallel to a straight line section CD;
connecting the midpoint N of the straight-line segment CD with the midpoint M of the straight-line segment AB to obtain a straight-line segment MN, wherein the direction of the straight-line segment MN is the chord direction of the extension segment (3), and the straight-line segment MN is perpendicular to the straight-line segment CD;
the length of the straight line segment AB is less than that of the straight line segment CD;
the point A and the point D are positioned on the first side of the straight-line segment MN, the point B and the point C are positioned on the second side of the straight-line segment MN, and the first side and the second side of the straight-line segment MN are opposite;
connecting the point A and the point D to form an AD curve section; connecting the point B and the point C to form a BC curve segment;
and (3) establishing a rectangular coordinate system by taking the N point as a coordinate origin, taking the direction from the N point to the D point as a Y-axis direction, and taking the direction from the N point to the D point as an X-axis direction, wherein the AD curve segment equation is as follows:
y＝(1-t n )(a 1 x+a 2 )+t n (a 3 x 3 +a 4 x 2 +a 5 x+a 6 )
wherein the content of the first and second substances,
n is a selective input parameter for controlling the shape characteristics of the curve segment;
a i (i =1,2, …, 6) is the coefficient to be determined;
obtain information about a i (i =1,2, …, 6) to obtain a i (i =1,2, …, 6) to obtain an AD curve segment equation;
coordinate (x) of point A A ，y A ) And D point coordinates (x) D ，y D ) Respectively substituting the AD curve segment equation to obtain the A i Two of the equations of (i =1,2, …, 6);
and (3) derivation is carried out on the AD curve segment equation to obtain a derivative function equation:
let the tangent at point A on the curve segment AD be parallel to the straight line segment MN, then y' (x) A )＝0；
The tangent line of the point D on the AD curve segment is tangent to the blade body (15), y' (x) D ) Is determined by the slope of the blade airfoil (15);
will (x) A ，y′(x A ) And (x) D ，y′(x D ) Substitution intoTangent equation of AD curve segment to obtain a i (i =1,2, …, 6);
let cubic curve y = a 3 x 3 +a 4 x 2 +a 5 x+a 6 Passing through the point A and the point D, obtaining the point A i (i =1,2, …, 6).
2. A method of modelling an aircraft engine blade blank according to claim 1, wherein a tangent at the intersection of the extension (3) and the main blade portion (15) is tangent to the main blade portion (15), the direction of extension of the terminating end of the extension (3) being parallel to the normal of the section.
3. A method of modelling an aircraft engine blade blank according to claim 1, wherein the thickness of the blade portion corresponding to the extension (3) is gradually reduced in the direction from the start to the end of the extension (3).
4. A method of modelling an aircraft engine blade blank according to claim 1, wherein the first predetermined distance from the leading edge (13) of the blade is between 1 and 2.5 times the thickness of the leading edge (13) of the blade; the first preset distance from the blade trailing edge (14) is 1-2.5 times the thickness of the blade trailing edge (14).
5. A method of modelling an aircraft engine blade blank as claimed in claim 1, wherein the second predetermined distance is in the range 5% to 10% of the chord length of the blade.
6. A method of modelling an aircraft engine blade blank as claimed in claim 1, wherein the ratio of the length of the straight line segment AB to the length of the straight line segment CD is a predetermined ratio, the predetermined ratio being in the range 0.5 to 0.8.
7. A method of modelling an aircraft engine blade blank as claimed in claim 1, wherein n is between 3.0 and 10.0.
8. A machining method for an aircraft engine blade is characterized by comprising the following steps:
establishing an aircraft engine blade blank model using the aircraft engine blade blank modeling method of claim 1;
processing an aero-engine blade blank by using the aero-engine blade blank model;
machining the extension section (3) of the aircraft engine blade blank to form a blade leading edge (13) and/or a blade trailing edge (14) of the aircraft engine blade.
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