Gas compressor blade mean camber line design method, gas compressor blade, gas compressor and aero-engine

Abstract

The invention discloses a gas compressor blade mean camber line design method, a gas compressor blade, a gas compressor and an aero-engine, and the method comprises the steps: S1, obtaining known design data, including an inlet blade angle theta in, an outlet blade angle theta out, a mean camber line starting point coordinate, a mean camber line end point abscissa, and turning angles delta theta 1, delta theta 2 and delta theta 4 of a first section arc, a second section arc and a fourth section arc, and abscissas of all tangency points; and S2, each section of arc is calculated through a geometric analysis method, a mean camber line is constructed after circle center coordinates, arc radiuses and tangent point coordinates of each section of arc are calculated, and the mean camber line is formed by sequentially and tangentially connecting four sections of arcs according to the sequence of convex, concave, convex and concave. The gas compressor blade mean camber line design method is good in adaptability and multiple in controllable point in the high Mach number state; therefore, the requirements of an advanced compressor are met; design parameters are greatly reduced, the optimizing period is greatly shortened, the adjusting efficiency is high, and the time is short.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and in particular, to a method for designing the mean camber line of a compressor blade, a compressor blade, a compressor, and an aeroengine. Background Art

[0002] As Figure 1 shown, the compressor is one of the core components of an aeroengine, and its performance largely determines the performance of the engine. The blade design is the core content of the compressor design and determines the performance of the compressor. The design of the compressor blade is mainly divided into three parts: the mean camber line design, the thickness design, and the spatial position design of the blade profile centroid. The compressor blade needs to adapt to complex inlet conditions, guide and compress the air flow, and finally make the air flow out at a certain angle and speed at the outlet. It is required that the parameters of the gas do not change greatly during the whole flow process, and the gas needs to flow along the blade surface as much as possible. In addition, the inlet and outlet conditions of the compressor blade change at all times, and the change range is very large. The blade needs to adapt to the inlet and outlet conditions with a large range of changes to achieve a good working state. To achieve this goal, the design of the mean camber line at the inlet and outlet is very critical, and it is necessary to finely guide and control the air flow at the inlet and outlet.

[0003] Currently, the mean camber lines of compressor blades are mainly divided into analytical types and arbitrarily distributed types: among them, the analytical types are mainly composed of 1-2 simple geometric curves, such as circular arc mean camber lines, parabolic mean camber lines (see Figure 2 ), double circular arc mean camber lines (see Figure 3 ), etc. The design parameters of such mean camber lines are few, there are many application cases, and the design criteria and databases are relatively rich. However, the degree of freedom of guiding and controlling the air flow of such mean camber lines is also small, and it is increasingly difficult to meet the requirements of advanced compressors in terms of performance. Especially at high Mach numbers, the adaptability is poor and the number of controllable points is small; while the arbitrary mean camber line (see Figure 4 ) has no fixed geometric form, and the mean camber line is determined by specifying the slope from the inlet to the outlet (or the angle between the tangent and the coordinate axis). The design parameters of such mean camber lines are many, the design freedom is large, and theoretically, better compressor performance can be achieved. However, due to too many design parameters, the design cycle is long, and it is impossible to find a better design result in a short time. Even if parametric means are used to fit the arbitrary mean camber line, its design parameters are still many, and the optimization cost is high. It is usually only used for the optimization in the later stage of blade design. Summary of the Invention

[0004] On the one hand, the present application provides a method for designing the mean camber line of a compressor blade, which is used to solve the technical problems of poor adaptability, few controllable points, long design cycle, and high optimization cost of the existing mean camber line design method of compressor blades at high Mach numbers.

[0005] This application is implemented through the following solutions: A method for designing the mean camber line of a compressor blade, comprising the steps of: S1. Obtain known design data, including the inlet blade angle θ in , the outlet blade angle θ out , the coordinates of the starting point of the mean camber line, the abscissa of the ending point of the mean camber line, the turning angles Δ θ 1 of the first, second, and fourth circular arcs θ 2 , Δ θ 4 , and the abscissas of each tangent point; S2. Calculate each circular arc by geometric analysis method, including the center coordinates, radius of the circular arc, and tangent point coordinates of each circular arc, and then construct the mean camber line. The mean camber line is composed of 4 circular arcs tangent to each other in the order of convex, concave, convex, and concave in sequence.

[0006] Further, the turning angles Δ θ 1 of the first, second, and fourth circular arcs θ 2 , Δ θ 4 are respectively the included angles between the blade angles at the starting points and the ending points of the first, second, and fourth circular arcs, and are all functions of the flow field conditions felt at the inlet of the compressor blade. The optimal values are determined through design iteration. The flow field conditions include the Mach number.

[0007] Further, when obtaining the known design data, the coordinates of the starting point of the mean camber line are the origin, the abscissa of the ending point of the mean camber line is the unit axial distance 1, the abscissa x 1 of the first tangent point is 0.1 - 0.15, the abscissa x 2 of the second tangent point is 0.5 - 0.6, and the range of the abscissa x 3 of the third tangent point is 0.85 - 0.9; After calculating the center coordinates and tangent point coordinates of each circular arc by geometric analysis method and constructing the mean camber line, then multiply the constructed mean camber line by a scale factor to enlarge or reduce it according to the actual size of the compressor blade to obtain the mean camber line of the compressor blade.

[0008] Further, when calculating each circular arc by geometric analysis method, the first circular arc is calculated through the following steps: The first circular arc is the first part of the entire mean camber line, and its starting point A is the origin, and the blade angle is the blade angle at the starting point of the entire mean camber line θ in . According to the flow field conditions felt at the inlet of the blade, select an appropriate turning angle Δθ 1 , and the abscissa x of the end point B 1 , and then the center coordinates of the first arc are obtained by geometric analysis O 1 , the arc radius R c1 and the ordinate y of the end point B 1 , and then with O 1 as the center and R c1 as the radius, an arc passing through points A and B is made to obtain the first arc.

[0009] Furthermore, when calculating each arc by geometric analysis, the second arc is calculated through the following steps: The second arc is the second part of the entire middle arc. Its starting point is the end point B of the first arc, and the blade angle is the blade angle at the end point of the first arc , according to the flow field conditions felt at the inlet of the blade, a corresponding turning angle Δ θ 2 , and the abscissa x of the end point C 2 , and then the center coordinates of the second arc are obtained by geometric analysis O 2 , the arc radius R c2 and the ordinate y of the end point C 2 , and then with O 2 as the center and R c2 as the radius, an arc passing through points B and C is made to obtain the second arc.

[0010] Furthermore, when calculating each arc by geometric analysis, the third arc is calculated through the following steps: The third arc is the third part of the entire middle arc. Its starting point is the end point C of the second arc, and the blade angle is the blade angle at the end point of the second arc , according to the flow field conditions felt at the inlet of the blade, a corresponding turning angle Δ of the fourth arc is selected θ 4 , and the abscissa x of the end point D 3 , and then the center coordinates of the third arc are obtained by geometric analysis O 3 , the arc radius R c3 and the ordinate y of the end point D 3 , and then with O 3 as the center and R c3 as the radius, an arc passing through points C and D is made to obtain the second arc.

[0011] Further, when calculating each arc segment by the geometric analysis method, the fourth arc segment is calculated through the following steps: The fourth arc segment is the fourth part of the entire middle arc line, and its starting point is the end point D of the third arc segment, and the blade angle is the blade angle at the end point of the third arc segment , and the turning angle Δ of the fourth arc segment θ 4 has been determined during the design process of the third arc segment. The end point E of the fourth arc segment is the end point of the entire middle arc line, and the abscissa x of the end point E 4 is the abscissa of the end point of the middle arc line. Then, the center coordinates O 4 , the arc radius R c4 and the ordinate y of the end point E 4 of the fourth arc segment are obtained by the geometric analysis method. Then, with O 4 as the center and R c4 as the radius, an arc segment passing through points D and E is drawn to obtain the fourth arc segment.

[0012] On the other hand, the present application also provides a compressor blade, and the compressor blade includes the middle arc line obtained by the above-mentioned middle arc line design method of the compressor blade.

[0013] On the other hand, the present application also provides a compressor, including the above-mentioned compressor blade.

[0014] On the other hand, the present application also provides an aeroengine, including the above-mentioned compressor blade or the above-mentioned compressor.

[0015] Compared with the prior art, the present application has the following beneficial effects: The present invention provides a method for designing the mean camber line of a compressor blade, a compressor blade, a compressor, and an aeroengine. The method for designing the mean camber line of the compressor blade guides and controls the air flow by designing the concave and convex shapes of the inlet and outlet arcs. Due to the concave and convex shape at the inlet section of the mean camber line, there is a negative curvature pre-compression effect here, thereby effectively reducing the control of the peak Mach number and shock wave intensity on the suction surface. Therefore, at the same inlet Mach number, the compressor blade with the mean camber line designed by the present application has lower flow losses. At the same time, due to the concave and convex shape at the outlet section, the surface pressure distribution of the blade is adjusted at the outlet section, the aerodynamic load is reduced, and the flow separation at the trailing edge of the blade is suppressed, so the margin of the compressor is increased. In addition, compared with the ordinary analytical mean camber line, the mean camber line designed by the present application has a greater design freedom at the inlet and outlet of the blade, realizes more refined control of the air flow, and achieves better performance. Compared with the arbitrary mean camber line, the design parameters of the mean camber line designed by the present application are greatly reduced, and the optimization period is greatly shortened. The mean camber line designed by the present application can achieve better performance on the premise of significantly shortening the compressor design cycle, and is especially suitable for the design of high Mach number rotor blade profiles, so as to meet the requirements of advanced compressors.

[0016] In addition to the objectives, features, and advantages described above, the present application has other objectives, features, and advantages. The following will refer to the drawings for a further detailed description of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings forming a part of the present application are used to provide a further understanding of the present application. The schematic embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation of the present application. In the drawings: Figure 1 is a schematic diagram of a typical compressor blade; Figure 2 is a schematic diagram of a parabolic mean camber line; Figure 3 is a schematic diagram of a double circular arc mean camber line; Figure 4 is a schematic diagram of an arbitrary mean camber line; Figure 5 is the method for designing the mean camber line of the compressor blade according to the preferred embodiment of the present application; Figure 6 is a schematic diagram of the four-segment circular arc mean camber line according to the preferred embodiment of the present application; Figure 7 is a schematic diagram for solving the first circular arc; Figure 8 is a schematic diagram for solving the second and third circular arcs; Figure 9 is a schematic diagram for solving the fourth circular arc; Figure 10 is a schematic diagram for solving the blade angle of the mean camber line; Figure 11 It is a schematic diagram of the angular distribution of the mean camber line of the blade; Figure 12 It is a schematic diagram for comparing the cloud map effects of the mean camber line; Figure 13 It is a schematic diagram of the module of the mean camber line design device for the compressor blade in the preferred embodiment of the present application; Figure 14 It is a schematic block diagram of the entity of the electronic device in the preferred embodiment of the present application; Figure 15 It is the internal structure diagram of the computer device in the preferred embodiment of the present application. Detailed implementation manners

[0018] The embodiments of the present application will be described in detail below with reference to the accompanying drawings, but the present application can be implemented in many different ways defined and covered by the following.

[0019] As Figure 5 shown, the preferred embodiment of the present application provides a method for designing the mean camber line of a compressor blade, including the steps of: S1. Obtain known design data, including the inlet blade angle θ in , the outlet blade angle θ out , the starting point coordinates of the mean camber line, the abscissa of the end point of the mean camber line, the turning angles Δ θ 1 , Δ θ 2 , Δ θ 4 of the first, second and fourth arcs, and the abscissas of each tangent point; S2. Calculate and construct each arc through geometric analysis, including the center coordinates, arc radii, and tangent point coordinates of each arc, and then construct the mean camber line, which is formed by connecting 4 arcs in sequence in the order of convex, concave, convex, and concave (see Figure 6 ).

[0020] The mean camber line designed in this embodiment is composed of four tangent arcs connected in sequence in the order of convex, concave, convex, and concave. The concave and convex shapes of the arcs form a negative curvature pre-compression effect in the inlet section to control the peak Mach number and shock wave intensity on the suction surface; in the outlet section, the aerodynamic load is reduced, and the flow separation at the blade trailing edge is decreased, which is particularly suitable for the design of high Mach number rotor blade profiles. The points where the arcs are tangent to each other are called tangent points, which are also the end points of the previous arc and the starting points of the next arc. The starting point of the entire mean camber line is located at the blade inlet, and the end point of the entire mean camber line is located at the outlet of the compressor blade. After determining the blade angles at the inlet and outlet (the angles between the tangents of the arcs and the abscissa), the main design parameters include the turning angles of the first, second, and fourth arcs (the angles between the blade angles at the starting points and the ending points of the arcs) and the abscissas of the arc tangent points. Usually, in order to reduce the design parameters and complexity, the relative axial positions of the arc tangent points can be set to a fixed value. At this time, the design parameters are reduced from six to three, and better performance can be achieved under the condition of significantly shortening the compressor design cycle.

[0021] In summary, the method for designing the mean camber line of the compressor blade in this embodiment guides and controls the air flow by designing the concave and convex shapes of the inlet and outlet arcs. Due to the concave and convex shapes in the inlet section of the mean camber line, there is a negative curvature pre-compression effect here, thus effectively reducing the control of the peak Mach number and shock wave intensity on the suction surface. Therefore, under the same inlet Mach number, the compressor blade with the mean camber line designed in this application has lower flow losses; at the same time, due to the concave and convex shapes in the outlet section, the surface pressure distribution of the blade is adjusted in the outlet section, the aerodynamic load is reduced, and the flow separation at the blade trailing edge is suppressed, so the margin of the compressor is increased. In addition, compared with the ordinary analytical mean camber line, the mean camber line designed in this application has a greater design freedom at the inlet and outlet of the blade, enabling more precise control of the air flow and better performance; compared with the arbitrary mean camber line, the design parameters of the mean camber line designed in this embodiment are significantly reduced, and the optimization cycle is greatly shortened; the mean camber line designed in this application can achieve better performance on the premise of significantly shortening the compressor design cycle, and is particularly suitable for the design of high Mach number rotor blade profiles, thus meeting the requirements of advanced compressors.

[0022] Preferably, the turning angles Δ θ 1 、Δ θ 2 、Δ θ 4 of the first, second, and fourth arcs are respectively the angles between the blade angles at the starting points and the ending points of the first, second, and fourth arcs, and are all functions of the flow field conditions sensed at the inlet of the compressor blade. The optimal values are determined through design iteration, and the flow field conditions include the Mach number.

[0023] Preferably, when obtaining the known design data, the starting point coordinates of the mean camber line are the origin, the abscissa of the end point of the mean camber line is the unit axial distance 1, and the abscissa x of the first tangent point 1 is 0.1 to 0.15, and the abscissa x of the second tangent point 2 is 0.5 to 0.6, and the abscissa x of the third tangent point 3 ranges from 0.85 to 0.9; After calculating the center coordinates and tangent point coordinates of each arc segment by the geometric analysis method and constructing the mean camber line, the constructed mean camber line is multiplied by a scale factor to enlarge or reduce it according to the actual size of the compressor blade, so as to obtain the mean camber line of the compressor blade.

[0024] In this embodiment, in order to adapt to the design of the mean camber line of compressor blades with different actual sizes but the same shape, this embodiment first designs the mean camber line of a standard-sized compressor blade. For example, first set the starting point coordinates of the mean camber line as the origin, the abscissa of the end point of the mean camber line as the unit axial distance 1, and the abscissas of each tangent point are set at a predetermined ratio between the origin and 1, so as to obtain the mean camber line of a standard-sized compressor blade. After the design is completed, for compressor blades with the same shape but different actual sizes, only the parameters of the mean camber line of the designed standard-sized compressor blade need to be enlarged or reduced proportionally, and the mean camber line of the compressor blade can be quickly obtained, meeting the design requirements of the mean camber line of various compressor blades with different actual sizes but the same shape, and improving the design efficiency and applicability.

[0025] In this application, the known variables include the inlet blade angle θ in , the outlet blade angle θ out , the starting point coordinates of the mean camber line, the abscissa of the end point of the mean camber line, the turning angles Δ θ 1 of the first, second, and fourth arc segments θ 2 , Δ θ 4 , Δ 1 , as well as the abscissas x 2 , x 3 of the tangent points. The entire mean camber line starts from the starting point A(0, 0), passes through a convex arc and is tangent to the second concave arc at B(x 1 , y 1 ), the second concave arc is tangent to the third convex arc at C(x 2 , y 2 ), the third convex arc is tangent to the fourth concave arc at D(x 3 , y 3 ), and finally ends at the end point E(x 4 , y 4); The geometric analysis of each arc will be illustrated below with reference to the attached drawings.

[0026] Preferably, as Figure 7 shown, when calculating each arc by the geometric analysis method, the first arc is calculated through the following steps: The first arc is the first part of the entire middle arc. Its starting point A is the origin, and the blade angle is the blade angle at the starting point of the entire middle arc θ in , according to the flow field conditions felt at the inlet of the blade, a suitable turning angle Δ θ 1 , and the abscissa x 1 of the end point B are selected. Then, the center coordinates O 1 , the arc radius R c1 and the ordinate y 1 of the end point B of the first arc are obtained by the geometric analysis method. Then, with O 1 as the center and R c1 as the radius, an arc passing through points A and B is drawn to obtain the first arc. The detailed calculation process is as follows: Assume that the starting point of the first arc is the coordinate origin A( , the center of the first arc is ( , the starting blade angle is , the coordinate of the end point is B( , and the end blade angle is .

[0027] Then, the first arc has the following geometric relationships: ; Since and are known, then can be calculated. To construct a convex arc, is taken as a positive value here.

[0028] is the angle between the chord line at the starting point of the first arc and the abscissa, is the angle between the chord line at the end point of the first arc and the radius. There are the following geometric relationships: ; ; There are only , two unknowns in the above two equations, and their specific numerical solutions can be obtained.

[0029] Also, since is known: ; ; The radius of the first arc can be solved .

[0030] Combine geometric relationships: ; ; ; Can be solved , It is worth noting that the first arc is a convex arc passing through the origin, so a negative sign is added in front of its y value. At this point, the first arc has been completely determined.

[0031] Preferably, if Figure 8 As shown in the figure, when calculating each arc segment by geometric analysis method, the second arc segment is calculated by the following steps: The second arc is the second part of the entire middle arc line. Its starting point is the end point B of the first arc, and the blade angle is the blade angle of the end point of the first arc. , according to the flow field conditions felt by the blade inlet, select the corresponding turning angle Δ θ 2 , and the abscissa x of the end point C 2 , and then the coordinates of the center of the second arc are obtained by geometric analysis. O 2 、Arc radius R c2 and the ordinate y of the end point C 2 , and then O 2 is the center of the circle, R c2 Draw an arc passing through points B and C for the radius to get the second arc. The detailed calculation process is as follows: The center of the second arc is , because it is tangent to the first arc, the starting blade angle is , the end point coordinate is C( , the blade angle is .

[0032] The second arc has the following geometric relationship: ; because and the second arc turning angle It is known that the exit angle of the second arc is The solution can be found.

[0033] From the geometric relationship, we get; ; ; It can be seen from the combination that , .

[0034] because , , and are all known quantities, then , It can be seen that: ; ; because It is known that the above equations can be combined to solve and , so far, the second arc has been completely determined.

[0035] Preferably, if Figure 8 As shown in the figure, when calculating each arc segment by geometric analysis method, the third arc segment is calculated by the following steps: The third arc is the third part of the entire mid-arc line. Its starting point is the end point C of the second arc, and the blade angle is the blade angle of the end point of the second arc. , according to the flow field conditions felt by the blade inlet, select the corresponding fourth arc turning angle Δ θ 4 , and the abscissa x of the end point D 3 , and then the coordinates of the center of the third arc are obtained by geometric analysis. O 3 、Arc radius R c3 and the ordinate y of the end point D 3 , and then O 3 is the center of the circle, R c3 Draw an arc with radius passing through points C and D to obtain the second arc.

[0036] Preferably, if Figure 9 As shown in the figure, when calculating each arc segment by geometric analysis method, the fourth arc segment is calculated by the following steps: The fourth arc is the fourth part of the entire middle arc line. Its starting point is the end point D of the third arc, and the blade angle is the blade angle of the end point of the third arc. , the turning angle of the fourth arc Δ θ 4 It has been determined in the design process of the third arc that the end point E of the fourth arc is the end point of the entire mid-arc line. The horizontal coordinate x 4is the abscissa of the end point of the middle arc, and then the center coordinates of the fourth arc are obtained by geometric analysis method O 4 , the arc radius R c4 and the ordinate y of the end point E 4 , then with O 4 as the center and R c4 as the radius, an arc passing through points D and E is made to obtain the fourth arc.

[0037] The detailed calculation processes of the third arc and the fourth arc are as follows: The center of the third arc is , the starting blade angle is , the end point coordinates are , the blade angle is . The center of the fourth arc is , the starting blade angle is , the end point coordinates are , the blade angle is . Among them, this analysis method is defined on the unit axial distance. Therefore, .

[0038] First, consider the fourth arc. There are: ; Since the former is known, then can solve .

[0039] Since the starting point coordinates of the fourth arc and the end point coordinates are known, there are: ; ; Combining them can obtain , from which can calculate .

[0040] In the third arc, there are the following geometric relationships: ; ; Combining them can obtain , and can calculate

[0041] Since ; ; ; Combining them can solve

[0042] At this point, the third and fourth arc segments have been determined. It is worth noting that the above calculation of the turning angle position transformation based on geometric relationships needs to pay attention to the positive and negative signs of the angles.

[0043] In summary, through the combination and iteration of the above formulas, a definite middle arc line consisting of four arcs can be obtained, and the required inlet and outlet angles can be controlled.

[0044] The coordinates of the mid-arc can also be obtained by solving differential equations, such as Figure 10 As shown, the angle between the tangent line of the curve and the horizontal axis is Derivative of the curve There is the following relationship:

[0045] For arcs, there are the following characteristics: The value is plotted on the graph according to the horizontal axis from the starting point to the end point, and its distribution is a straight line, the slope of the convex arc is less than 0, and the slope of the concave arc is greater than 0. Therefore, the middle arc line in the present invention The values ​​are plotted on the graph from the starting point to the end point according to the horizontal axis, and their distribution is four straight lines connected at the first position: The starting point of the first straight line has a horizontal coordinate of 0 and a vertical coordinate of The abscissa of the end point is , the vertical axis is ; The horizontal coordinate of the starting point of the second straight line is , the vertical axis is The abscissa of the end point is , the vertical axis is ; The abscissa of the starting point of the third straight line is , the vertical axis is The abscissa of the end point is , the vertical axis is ; The abscissa of the starting point of the fourth straight line is , the vertical axis is The abscissa of the end point is , the vertical axis is .

[0046] , is a known quantity, and the main design parameters are also the turning angles of the first, second, and fourth arcs. , , , and the horizontal coordinate of the tangent point , , , and the following relationships exist: ; ; ;

[0047] The blade angle distribution of the four circular arcs is shown in Figure 11 , and there are: ; ; ; ; ;

[0048] The coordinates of all 4 circular arcs can be obtained by numerically solving the differential equation to determine the entire center line. The Runge-Kutta method is introduced for inverse solution. Its main principle is to take some specific points near a certain point t, and then use the function values of these points for linear combination so that the combined value replaces the derivative value at point t in the Taylor expansion: Expand y in Taylor series:

[0049] Let , according to the derivative rule of multivariate functions, there are: ;

[0050] And so on, there are:

[0051] The formal solution of the Taylor expansion:

[0052] Among them, ; ; ;

[0053] Its general term is:

[0054] The iterative use of the fourth-order Runge-Kutta in the present invention can meet the accuracy: ; ; ; ; ; Through the combination and iteration of the above formulas, a definite middle arc composed of four circular arcs can be solved, and the required inlet and outlet blade angles can be controlled. During the solution process, the concave and convex characteristics of each arc segment are controlled by the positive and negative characteristics of the angle.

[0055] Use a compressor to test the effect, such as Figure 13 The compressor designed by the compressor blade camber design method provided by the above embodiment can effectively reduce the separation of the trailing edge and reduce the high Mach number area in the blade flow channel area, thereby reducing the loss.

[0056] Another preferred embodiment of the present application further provides a compressor blade, wherein the compressor blade includes a center camber line obtained by the compressor blade center camber line design method.

[0057] Another preferred embodiment of the present application further provides a compressor, comprising the compressor blades described above.

[0058] Another preferred embodiment of the present application also provides an aircraft engine, including the compressor blades or the compressor.

[0059] like Figure 13 As shown, another preferred embodiment of the present application further provides a compressor blade mid-camber design device, comprising the steps of: Parameter acquisition module, obtains known design data, including inlet blade angle θ in , outlet blade angle θ out , the coordinates of the starting point of the middle arc, the horizontal coordinates of the end point of the middle arc, the turning angles Δ of the first, second and fourth arcs θ 1 , Δ θ 2 , Δ θ 4 , and the horizontal coordinates of each tangent point; The center arc construction module calculates each arc segment through geometric analysis method, including the coordinates of the center point, arc radius and tangent point of each arc segment, and then constructs the center arc line. The center arc line is composed of 4 arc segments connected tangently in the order of convex, concave, convex and concave.

[0060] like Figure 14 As shown, a preferred embodiment of the present application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the compressor blade mid-arc design method in the above-mentioned embodiment when executing the computer program.

[0061] like Figure 15As shown, a preferred embodiment of the present application further provides a computer device, which may be a terminal or a living body detection server, and its internal structure diagram may be as shown in Figure 15 shown. The computer device includes a processor, a memory, and a network interface connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with other external computer devices through a network connection. When the computer program is executed by the processor, it realizes the steps of the above-mentioned mid-arc design method for compressor blades.

[0062] Those skilled in the art can understand that Figure 15 the structure shown in is only a block diagram of some structures related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0063] A preferred embodiment of the present application further provides a storage medium. The storage medium includes a stored program, and when the program runs, it controls the device where the storage medium is located to execute the steps of the mid-arc design method for compressor blades in the above embodiment.

[0064] It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. And although the logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in a different order than here.

[0065] If the functions of the method in this embodiment are implemented in the form of software function units and sold or used as independent products, they can be stored in one or more computer-readable storage media. Based on such an understanding, the part that contributes to the prior art or the part of the technical solution of the present application can be embodied in the form of a software product. The software product is stored in a storage medium and includes several instructions for causing a computing device (which may be a personal computer, a server, a mobile computing device, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present application. And the foregoing storage medium includes: various media such as USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks, or optical discs that can store program codes.

[0066] Those skilled in the art should understand that the embodiments of the present application can be provided as methods, systems, or computer program products. Therefore, the present application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Moreover, the present application can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of the present application can be implemented in various computer languages. For example, object-oriented programming languages such as Java and interpreted scripting languages such as JavaScript, etc.

[0067] The present application is described with reference to the flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each flow and / or block in the flowchart and / or block diagram, as well as the combination of flows and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing devices generate a device for implementing the functions specified in Figure 1 one flow or multiple flows and / or blocks Figure 1 one block or multiple blocks.

[0068] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer-readable memory generate a manufactured article including an instruction device, and the instruction device implements the functions specified in Figure 1 one flow or multiple flows and / or blocks Figure 1 one block or multiple blocks.

[0069] These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to generate a computer-implemented process. Thus, the instructions executed on the computer or other programmable device provide steps for implementing the functions specified in Figure 1 one flow or multiple flows and / or blocks Figure 1 one block or multiple blocks.

[0070] Although the preferred embodiments of the present application have been described, those skilled in the art can make additional changes and modifications once they know the basic creative concepts. Therefore, the appended claims are intended to be interpreted to include the preferred embodiments as well as all changes and modifications falling within the scope of the present application.

[0071] Obviously, those skilled in the art can make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalent technologies, this application is also intended to include these changes and modifications.

Claims

1. A method for designing the mean camber line of a compressor blade, characterized in that: Includes steps: S1. Obtain known design data, including inlet blade angle θ in , outlet blade angle θ out , the coordinates of the starting point of the middle arc, the horizontal coordinates of the end point of the middle arc, the turning angles Δ of the first, second and fourth arcs θ 1. Δ θ 2. Δ θ 4, and the horizontal coordinates of each tangent point; S2. Calculate each arc segment by geometric analysis method, including the coordinates of the center of each arc segment, the arc radius, and the coordinates of the tangent point, and then construct the middle arc line. The middle arc line is formed by 4 arc segments connected tangently in the order of convex, concave, convex, and concave.

2. The method for designing the mean camber line of a compressor blade according to claim 1, characterized in that: The turning angles Δ of the first, second and fourth arcs θ 1. Δ θ 2. Δ θ 4 are the included angles of the blade angles at the starting points of the first, second and fourth arcs and the blade angles at the end points of the arcs, respectively, and are all functions of the flow field conditions felt by the compressor blade inlet. The optimal values ​​are determined through design iterations, and the flow field conditions include the Mach number.

3. The method for designing the mean camber line of a compressor blade according to claim 1, characterized in that: When obtaining known design data, the starting coordinate of the middle arc line is the origin, the horizontal coordinate of the end point of the middle arc line is the unit axial distance 1, the horizontal coordinate x1 of the first tangent point is 0.1~0.15, the horizontal coordinate x2 of the second tangent point is 0.5~0.6, and the horizontal coordinate x3 of the third tangent point is 0.85~0.9; after the center coordinates and tangent point coordinates of each arc are calculated by the geometric analysis method to construct the middle arc line, the constructed middle arc line is multiplied by the proportional coefficient according to the actual size of the compressor blade to enlarge or reduce it, so as to obtain the middle arc line of the compressor blade.

4. The method for designing the mean camber line of a compressor blade according to any one of claims 1 to 3, characterized in that: When calculating each arc segment by geometric analysis, the first arc segment is calculated by the following steps: The first arc is the first part of the entire mid-arc line, its starting point A is the origin, and the blade angle is the blade angle at the starting point of the entire mid-arc line θ in , according to the flow field conditions felt by the blade inlet, select the appropriate turning angle Δ θ 1, and the horizontal coordinate x1 of the end point B, and then the coordinates of the center of the first arc are obtained by geometric analysis. O 1 、Arc radius R c1 and the ordinate y1 of the end point B, and then O 1 is the center of the circle, R c1 Draw an arc with radius passing through points A and B to obtain the first arc.

5. The method for designing the mean camber line of a compressor blade according to claim 4, characterized in that: When calculating each arc segment by geometric analysis, the second arc segment is calculated by the following steps: The second arc is the second part of the entire middle arc line. Its starting point is the end point B of the first arc, and the blade angle is the blade angle of the end point of the first arc. , according to the flow field conditions felt by the blade inlet, select the corresponding turning angle Δ θ 2, and the horizontal coordinate x2 of the end point C, and then the coordinates of the center of the second arc are obtained by geometric analysis. O 2 、Arc radius R c2 and the ordinate y2 of the end point C, and then O 2 is the center of the circle, R c2 Draw an arc with radius passing through points B and C to obtain the second arc.

6. The method for designing the mean camber line of a compressor blade according to claim 5, characterized in that: When calculating each arc segment by geometric analysis, the third arc segment is calculated by the following steps: The third arc is the third part of the entire mid-arc line. Its starting point is the end point C of the second arc, and the blade angle is the blade angle of the end point of the second arc. , according to the flow field conditions felt by the blade inlet, select the corresponding fourth arc turning angle Δ θ 4, and the horizontal coordinate x3 of the end point D, and then the coordinates of the center of the third arc are obtained by geometric analysis. O 3 、Arc radius R c3 and the ordinate y3 of the end point D, and then O 3 is the center of the circle, R c3 Draw an arc with radius passing through points C and D to obtain the second arc.

7. The method for designing the mean camber line of a compressor blade according to claim 6, characterized in that: When calculating each arc segment by geometric analysis, the fourth arc segment is calculated by the following steps: The fourth arc is the fourth part of the entire middle arc line. Its starting point is the end point D of the third arc, and the blade angle is the blade angle of the end point of the third arc. , the turning angle of the fourth arc Δ θ 4 has been determined in the design process of the third arc. The end point E of the fourth arc is the end point of the entire middle arc line. The abscissa x4 of the end point E is the abscissa of the end point of the middle arc line. Then, the center coordinates of the fourth arc are obtained by geometric analysis. O 4 、Arc radius R c4 and the ordinate y4 of the end point E, and then O 4 is the center of the circle, R c4 Draw an arc with radius passing through points D and E to obtain the fourth arc.

8. A compressor blade, characterized in that: The compressor blade comprises a camber line obtained by the compressor blade camber line design method according to any one of claims 1 to 7.

9. A compressor, characterized in that: Comprising the compressor blade according to claim 8.

10. An aircraft engine, characterized in that: It comprises the compressor blade according to claim 8, or the compressor according to claim 9.

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