JP4587527B2 - Blade surface design method, blade surface design program recording medium, and blade surface design apparatus - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
  The present invention relates to a blade curved surface design method for designing an axial flow type or a diagonal flow type impeller used for a domestic air conditioner or a ventilation fan,Blade surfaceDesign program recording medium, andBlade surfaceThe present invention relates to a design apparatus.
[0002]
[Prior art]
While air blowers are used throughout the life of home air conditioners, relatively low noise and large air flow are obtained, and because of low manufacturing costs, axial flow and mixed flow impellers Is often used. This kind of impeller is designed by a design method based on a carpet diagram, a hydrodynamic simulation, or an empirical design based on an enormous amount of experiments, like an airplane propeller. Then, several kinds of high-performance impellers obtained by repeating such design and correction design are prepared for each operating point, and thereafter, it is necessary to enlarge and reduce the blade shape almost similar to the basic shape. Designed impeller with various dimensions and operating point. For design of the blade curved surface, an apparatus which can design a wide range of blade shapes by arbitrarily giving parameters for determining the blade curved surface as described in Japanese Patent Publication No. 2827613 is used.
[0003]
[Problems to be solved by the invention]
However, the conventional design method as described above has a problem that the optimum design according to the use condition of the impeller cannot be performed. That is, unlike the sirocco fan and the turbo fan, the axial flow and diagonal flow type impellers do not have a casing covering the periphery, and thus are easily affected by mounting conditions and obstacles around the mounting portion. As a result, it often happens that an impeller that was very high performance in one device does not perform well in another device. In particular, the noise characteristics change greatly, and therefore, it is indispensable to make an optimum design according to the equipment so that high performance can be realized while maintaining low noise.
[0004]
In order to perform the optimum design of the impeller, a great variety of parameters that determine the three-dimensional shape of the blades are required. As general ones, there are the number of blades, distribution of blade inlet angles, outlet angles, meridian shapes, and the like, and the number of types of parameters becomes enormous if the three-dimensionality of the blade curved surface is taken into consideration. Recently, for the purpose of improving noise performance, wing-type wings with a streamlined cross-section, such as aircraft wings, and blades with a unique planar shape with a protruding part at the leading edge have been adopted. However, not only a variety of parameters are required, but also the parameters have become complicated, and it has become impossible to perform appropriate parameter studies with conventional design apparatuses.
[0005]
For example, the change in the planar shape due to the protrusion on the leading edge needs to be considered at the initial stage of the design as a change in the chord length of the blade, and this change in chord length is considered based on this. It also affects the maximum thickness of the airfoil. That is, there are many cases where parameters influence each other without functioning independently, and a very complicated work of blade curved surface design in consideration of all these relationships is required. In addition, many of these parameters cannot be discretely leveled and need to be treated as irregular shapes (meridian shape, blade warp shape, etc.) or distribution shapes (blade angle, airfoil shape, etc.) There is. Therefore, it is not easy to consider a wide range of combinations for finding the optimum value.
[0006]
In addition, the various design methods described above have the following problems, and it is difficult to design with combinations of various parameters from the viewpoint of the design technique. That is, the method based on the carpet diagram uses an existing airfoil whose performance is known, and a new airfoil cannot be designed or a new blade warp shape cannot be determined. The empirical design method based on experimental data cannot, of course, design a new impeller without experimental data, and there is a degree of freedom to study various impellers by freely changing design parameters. Too low. The simulation-based method predicts the performance and internal flow of the designed impeller, and the shape of the original impeller must be designed in a different way, creating a model for simulation. However, it takes a lot of time and the performance prediction accuracy is still insufficient.
[0007]
Therefore, the development of a design method and a design apparatus that can design an impeller having an optimum blade curved surface corresponding to each device by combining various parameters in a short time is an issue.
[0008]
[Means for Solving the Problems]
  In order to solve the above-described problem, the blade curved surface design method of the present invention includes a line segment L on the quadrilateral and line segments T, line segments T, and line segments b1, b2,. .., Bn are rotated around an arbitrary straight line X to form rotating curved surfaces s1, s2,..., Sn and Ls, Ts, and the rotating curved surface Ls on the rotating curved surfaces s1, s2,. , Cn are formed, and the end points of the warp line curves c1, c2,..., Cn coincide with an arbitrary curve portion le on the rotating curved surface Ls. The procedure of rotating around the straight line X is performed as described above, and thereafter, a circumferential protruding portion lex is provided on the curve portion le.WhenIn addition, the warp line curve cm is extended in a predetermined direction to define the protrusion end point lmx, or the airfoil curves cs1, cs2 constituting the airfoil shape with the warp line curves c1, c2,. ,..., Csn and the airfoil curves cp1, cp2,..., Cpn, and finally the warp curve c1, c2,..., Cn, or the airfoil curves cs1, cs2,. .., csn, cp1, cp2,..., Cpn are smoothly connected to define a curved surface. By doing so, it becomes possible to study the shape of the protrusion of the leading edge of the blade without changing the parameter for determining the curved surface shape of the entire blade, and to easily handle the irregular parameter of the airfoil.
[0009]
DETAILED DESCRIPTION OF THE INVENTION
  The blade curved surface design method according to claim 1 of the present invention includes:The computing means is set through the input means connected to the computing meansArbitrary four points on the plane are connected by a smooth closed curve to form a substantially quadrilateral. One of the opposite sides of the quadrilateral is defined as a line segment L, and the other as a line segment T. .., Ln and t1, t2,..., Tn equal in number to the minute T, and line segments b1, b2,. Rotate by rotating the line segments b1, b2,..., Bn, the line segment L, and the line segment T with an arbitrary straight line X on the same plane having no intersection with the closed curve as a rotation axis. Processing procedure 1 for constructing the curved surfaces s1, s2,..., Sn and Ls, Ts;The computing means isThe rotating curved surfaces Ls and Ts are connected on the rotating curved surfaces s1, s2,..., And the end points l1L, l2L,..., LnL on the rotating curved surface Ls and the end points t1T, t2T on the rotating curved surface Ts side are connected. , ..., at tnT, the angles formed with the circumferential direction in the rotation around the straight line X are respectivelyInput from the input means..., .alpha.n and .beta.1, .beta.2,..., .beta.n warp line curves c1, c2,..., cn are developed surfaces of the rotating curved surfaces s1, s2,. Processing procedure 2 expressed as a concatenation of a plurality of cubic curves above,The computing means isThe curved line curves c1, c2, c, c2, c, c2, c so that the end points l1L, l2L,..., LnL coincide with an arbitrary curve segment le set in a direction connecting the rotating curved surfaces s1 and sn on the rotating curved surface Ls. ..., processing procedure 3 for rotating cn around the straight line X;The computing means isIn the curve leCircumferential directionA process procedure 4 for extending the warp curve cm in the direction of the angle αm at the end point lmL corresponding to the projecting part lex, and defining the projecting part end point lmx on the extended warp line curve cm;The computing means isRotates in the processing procedure 3 and has the projecting end point lmx defined in the processing procedure 4BeforeAnd a processing procedure 5 for defining curved surfaces by smoothly connecting the warped curve curves c1, c2,..., Cn.
[0010]
The above configuration means that the protrusion of the leading edge of the blade is separated from the design of the entire blade curved surface, which is consistent with the conventional blade curved surface design method and facilitates the design of the blade curved surface, as well as aerodynamic performance. This makes it possible to examine the optimum shape of the protruding part, which has a large influence on the noise performance, separately from the blade curved surface, without greatly changing the curved surface of the entire blade having a large influence.
[0013]
  Claim2The blade surface design method described isThe computing means is set through the input means connected to the computing meansArbitrary four points on the plane are connected by a smooth closed curve to form a substantially quadrilateral. One of the opposite sides of the quadrilateral is defined as a line segment L, and the other as a line segment T. .., Ln and t1, t2,..., Tn equal in number to the minute T, and line segments b1, b2,. Rotate by rotating the line segments b1, b2,..., Bn, the line segment L, and the line segment T with an arbitrary straight line X on the same plane having no intersection with the closed curve as a rotation axis. Processing procedure 1 for constructing the curved surfaces s1, s2,..., Sn and Ls, Ts;The computing means isThe rotating curved surfaces Ls and Ts are connected on the rotating curved surfaces s1, s2,..., And the end points l1L, l2L,..., LnL on the rotating curved surface Ls and the end points t1T, t2T on the rotating curved surface Ts side are connected. , ..., at tnT, the angles formed with the circumferential direction in the rotation around the straight line X are respectivelyInput from the input means..., .alpha.n and .beta.1, .beta.2,..., .beta.n warp line curves c1, c2,..., cn are developed surfaces of the rotating curved surfaces s1, s2,. Processing procedure 2 expressed as a concatenation of a plurality of cubic curves above,The computing means isThe curved line curves c1, c2, c, c2, c, c2, c so that the end points l1L, l2L,..., LnL coincide with an arbitrary curve segment le set in a direction connecting the rotating curved surfaces s1 and sn on the rotating curved surface Ls. ..., processing procedure 3 for rotating cn around the straight line X;The computing means isOn the rotating curved surfaces s1, s2,..., Sn, the airfoil curves cs1, cs2 constituting the airfoil shape with the warp line curves c1, c2,. , ..., csn and airfoil curves cp1, cp2, ..., cpn;The computing means isIn the curve leCircumferential directionThe warp curve cm is extended in the direction of the angle αm at the end point lmL corresponding to the protrusion lex, the protrusion end point lmx is defined on the extended warp curve cm, and the airfoil curves csm and cpm are at least The process procedure 8 extends from the end point lmL to the protrusion end point lmx in accordance with the warp curve curve cm without changing the shape of the portion exceeding the distance Ym between the end point lmx and the end point lmL.The computing means isIn the processing procedure 8Has a defined protrusion end point lmx, Csn, and air flow curves cp1, cp2,..., Cpn are smoothly connected to each other to define a curved surface.
[0014]
  The above configuration means that the blade warp line and the thickness distribution that forms the airfoil are handled separately, making it easy to handle the irregular parameters of the airfoil, and the experience of the design method mainly of the conventional warp line. It becomes possible to save. further,The above configuration means changing the blade thickness distribution only near the leading edge protrusion,FeathersIn this case, the curved surface shape of the entire blade and the shape of the protruding portion can be considered separately.
[0015]
  Claim3The blade curved surface design program recording medium described in claim 1Or 2ListedFeatherRoot surface design method processing procedureFor the calculation means to executeprogramTheRecordedA computer-readable recording medium.As a result, the program can be carried and moved, and can be used in a plurality of locations or at remote locations.
[0016]
  Claim4The described blade curved surface design apparatus isA blade curved surface design apparatus comprising processing means, input means connected to the processing means, and display means, wherein the processing means includes calculation means and storage means, and the storage means passes through the input means. Arbitrary four points on the set plane are connected by a smooth closed curve to form a substantially quadrilateral. One of the opposite sides of the quadrilateral is set as a line segment L and the other as a line segment T. .., And ln and t1, t2,..., Tn are provided, and line segments b1, b2,. , Bn, and the line segments b1, b2,..., Bn, the line segment L, and the line segment T are rotated about an arbitrary straight line X on the same plane having no intersection with the closed curve. , Rotate curved surfaces s1, s2, ..., sn and Ls, Ts , Sn, and the end points l1L, l2L,..., LnL, and the rotating curved surface Ls side are connected to the rotating curved surfaces Ls and Ts on the rotating curved surfaces s1, s2,. ..., TnT, the angles formed with the circumferential direction in the rotation around the straight line X are α1, α2,..., Αn and β1, β2, .., Βn warping line curves c 1, c 2,..., Cn are represented as a plurality of cubic curves connected on the developed surface of the rotating curved surfaces s 1, s 2,. The curve line curve so that the end points l1L, l2L,..., LnL coincide with an arbitrary curve portion le set in the direction connecting the rotating surfaces s1 and sn on the rotating surface Ls. c1, c2,..., c Is rotated around the straight line X, and the warp curve curve cm is extended in the direction of the angle αm at the end point lmL corresponding to the circumferential protrusion lex provided on the curve segment le, and the warpage line is extended. The process procedure 4 for determining the projecting end point lmx on the curve cm, and the warp line curves c1, c2,..., Cn rotated in the process procedure 3 and having the projecting end point lmx defined in the process procedure 4 A program for causing the calculation means to execute the processing procedure 5 for smoothly defining the curved surface is stored, and the calculation means follows the processing procedure 1, the processing procedure according to the program stored in the storage means. 2. The processing procedure 3, the processing procedure 4 and the processing procedure 5 are executed, and the processing means displays the curved surface defined in the processing procedure 5 on the display means. That.
  The blade curved surface design apparatus according to claim 5 is a blade curved surface design apparatus comprising processing means, input means connected to the processing means, and display means, wherein the processing means includes calculation means and storage means. The storage means connects an arbitrary four points on the plane set through the input means with a smooth closed curve to form a substantially quadrilateral, and one of a pair of opposite sides of the quadrilateral is a line segment L, With the other being a line segment T, the same number of dividing points l1, l2,..., Ln and t1, t2,. .., Bn are set, and the line segments b1, b2,..., Bn are set with an arbitrary straight line X on the same plane having no intersection with the closed curve as a rotation axis. The line segment L and the line segment T are rotated, respectively, to rotate the curved surfaces s1, s. ,..., Sn, and Ls and Ts, and the rotating curved surfaces Ls and Ts are connected to the rotating curved surfaces s1, s2,. , L2L,..., LnL and the rotation surface Ts side end points t1T, t2T,. ,..., .Alpha. And β1, .beta.2,..., .Beta.n warp line curves c1, c2,..., Cn on the development surface of the rotating curved surfaces s1, s2,. The processing procedure 2 expressed as connecting three cubic curves, and the end points l1L, l2L,... On an arbitrary curve segment le set in the direction connecting the rotating curved surfaces s1 and sn on the rotating curved surface Ls. , LnL before matching Process line 3 for rotating the warp line curves c1, c2,..., Cn around the straight line X, and the warp line curve rotated in the process step 3 on the rotating curved surfaces s1, s2,. , cpn and airfoil curves cs1, cs2,..., csn and airfoil curves cp1, cp2,..., cpn that form the airfoil shape with c1, c2,. The warp curve cm is extended in the direction of the angle αm at the end point lmL corresponding to the circumferential protrusion lex provided in the curve segment le, and the protrusion end point lmx is defined on the extended warp curve cm. The airfoil curves csm and cpm are projected in conformity with the warp curve curve cm without changing the shape of at least the distance Ym between the end point lmL and the protrusion end point lmx to the end point lmL. , Csn, and airfoil curves cp1, cp2,..., Csn, and airfoil curves cs1, cs2,..., Csn having the projecting end point lmx defined in the processing procedure 8. A program for causing the calculation means to execute the processing procedure 7 for smoothly defining cpn and defining a curved surface is stored. The calculation means follows the processing procedure 1, The processing procedure 2, the processing procedure 3, the processing procedure 6, the processing procedure 8, and the processing procedure 7 are executed, and the processing means displays the curved surface defined in the processing procedure 7 on the display means. Features.
  According to the present inventionNot only can each processing procedure be performed without fail, but also cooperation with computer simulation and CAD can be strengthened, and work efficiency can be improved.
[0017]
Hereinafter, embodiments of the present invention will be specifically described with reference to the drawings.
First, the configuration of the blade curved surface design apparatus will be described with reference to FIG. In the figure, reference numeral 1 denotes a processing means, which uses a so-called personal computer or workstation, a CPU as the arithmetic means 2, and a storage means 3 for storing a program or data for performing calculation processing by the arithmetic means 2. It has. The storage means 3 has a recording medium on which a processing procedure according to at least one blade curved surface design method, which will be described later, for designing the blade curved surface shape of the turbo machine is programmed and recorded. Specifically, the recording medium is a floppy disk, a compact disk, a magneto-optical disk, a magnetic tape, a flash memory, or the like.
[0018]
Reference numeral 4 denotes an input means connected to the processing means 1, which is used to input basic data for calculating the blade curved surface and to input execution instructions for various processes. Generally, a keyboard or a mouse is used. It is. Reference numeral 5 denotes display means connected to the processing means 1 and has a function of displaying numerical values inputted or outputted and the shape of the calculation result as a figure, and is generally a CRT or a liquid crystal display. Reference numeral 6 denotes output means connected to the processing means 1, and a plotter or hard copy machine for outputting the final contour shape and numerical table of the impeller, or removable storage for retrieving them as digital data. A device such as a floppy disk drive or a CD-R device.
[0019]
Next, the blade curved surface design method using the blade curved surface design apparatus will be described with reference to examples.
Example 1
FIG. 2 shows a processing procedure of the blade curved surface design method according to the first embodiment of the present invention. The entire processing is performed in processing procedure 1 to processing procedure 5 and will be described sequentially.
[0020]
In step # 1, processing procedure 1 for forming a rotating curved surface is performed. As shown in FIGS. 3 to 4, arbitrary four points A, B, C, and D on the plane and a straight line X are input and set using coordinate values (step # 11), and then a set of opposite sides, here Then, the line segment L and the line segment T are designated (step # 12). After that, division points l1, l2, ..., ln and t1, t2, ..., tm, ..., tn are respectively set on the line segment L and line segment T by calculation automatically (step # 13). , Bm,..., Bn connecting the division points opposite to each other on the line segment are obtained (step # 14), and these line segments and the above-described line segment L and line segment T are connected to a straight line X. , Sm,..., Sn obtained by rotating around (step # 15), and accordingly, rotated surfaces Ls and Ts are formed (step # 16). FIG. 5 shows sm of the created rotating curved surfaces s1, s2,..., Sm,..., And sn and rotating curved surfaces Ls and Ts obtained from the line segments L and T. FIG.
[0021]
In step # 2, processing procedure 2 for forming a warped curve with a cubic curve is performed. As shown in FIG. 6, with respect to the rotating curved surface sm, an angle αm formed with the circumferential direction in the rotation around the straight line X is specified for the end point lmL on the rotating curved surface Ls side and the end point tmT on the rotating curved surface Ts side (step # 21). ), Βm is designated (step # 22). As a result, a plurality of cubic curves are connected between the end points lmL and tmT by calculation so that the specified value is obtained, thereby forming a warped curve cm (step # 23).
[0022]
In this procedure, the end point lmL on the rotating curved surface Ls side and the end point tmT on the rotating curved surface Ts side are parameters related to the planar shape of the blade, and what is required in this processing procedure is the distance between the two points. This can be given arbitrarily, but in general, the most basic arc wing is assumed based on the values input in procedure 1 and the angles αm and βm given in procedure 2. Determined automatically. It is also possible to input the distance between two points in order to increase the degree of design freedom.
[0023]
The curve connecting the end point lmL and tmT can also be defined in a three-dimensional space, but to reduce the dimensions handled and simplify the definition of design specifications, and to make use of the know-how of conventional design methods In addition, the method of defining on the development surface of the rotating curved surface sm is taken. As shown in FIG. 7, this process is performed for all of the rotating curved surfaces s1, s2,... Sn, and warp curve curves c1, c2,. At this time, α1, α2,..., Αn and β1, β2,..., Βn may all be input to the rotating curved surfaces from s1 to s2, but here, representative values of 5 and 6 points are used. By giving a value, it is automatically interpolated based on that value.
[0024]
In step # 3, process procedure 3 for rotating the rotating curved surface is performed. FIG. 8 is an enlarged plan view of a main part when the rotating curved surfaces s1, s2,... Sn are viewed from the rotating curved surface Ls side in the direction along the straight line X, and FIG. As shown in the figure, an arbitrary curve segment le in the direction connecting s1 and sn (substantially in the radial direction centered on the straight line X) is set on the rotating curved surface Ls (step # 31), and thereby automatically calculated. , And the curved surfaces le so that the intersections l1L, l2L,..., LnL of the curved lines c1, c2,. (c1, c2,..., cn) are rotated around the straight line X (step # 32). Here, the curve portion le determines the shape of the leading edge of the blade, and therefore, in this processing procedure 3, the warp curve of the blade is arranged on the basis of the leading edge.
[0025]
Next, in step # 3A, it is selected whether or not to provide a protrusion on an arbitrary curve portion le on the rotating curved surface Ls.
When providing a protrusion part, in step # 4, the process procedure 4 which forms a protrusion part is performed. When the protrusion lex is formed on a part of the leading edge of the blade as shown in the plan view of FIG. 10, the warp line curve cm is changed to the rotation curved surface Ls on the development surface of the rotation curved surface sm as shown in FIG. 11. The process is automatically performed with the point lmx extending in the direction of the angle αm at the intersection lmL and the point lmx overlapping with the protrusion lex in the plan view. The position of the end point lmx of the warp line curve cm corresponds to the angle αm. Similar processing is performed on the warped curve c1, c2,..., Cn in the range where the protruding portion lex exists, and the respective end points are determined.
[0026]
Next, in step # 5, the processing procedure 5 for forming the blade curved surface is performed. The curved lines c1, c2,..., Cn on the rotational curved surfaces s1, s2,..., Sn determined as described above are designated α1, α2,..., Αn and β1, β2,. Furthermore, since it is determined by the protruding portion lex of the curve portion le set on the rotating curved surface Ls, the process of stacking these warp line curves c1, c2,..., Cn is automatically performed. The blade curved surface l1L-t1T-tnT-lnT is uniquely determined.
[0027]
As described above, the blade curved surface other than the projecting portion lex is fixed by taking the procedure of additionally forming the shape of the projecting portion lex later, and the blade curved surface due to the provision of the projecting portion lex is fixed. No change will occur. Accordingly, when variously examining the shape of the protruding portion for reasons such as considering noise characteristics, the influence of only the protruding portion may be considered. This is also effective when designing a new blade shape provided with a protrusion based on the existing blade curved surface.
(Example 2)
FIG. 12 shows a processing procedure of the blade curved surface design method according to the second embodiment of the present invention. The entire process is performed in process procedure 1 to process procedure 7, and will be described sequentially.
[0028]
In the same manner as in the first embodiment, in Step # 1 (Processing Procedure 1), rotating curved surfaces s1, s2,..., Sm,..., Sn, Ls, Ts are configured, and in Step # 2 (Processing Procedure 2), Contour lines c1, c2,..., Cn are formed, and in step # 3 (processing procedure 3), the intersections l1L, l2L,..., LnL of the warp lines c1, c2,. The rotation curved surfaces s1, s2,..., Sn are rotated around the straight line X so as to ride on the minute le.
[0029]
Next, in step # 6, processing procedure 6 for obtaining the airfoil curve is performed. That is, as shown in FIG. 13, the airfoil curves csm and cpm are obtained on both sides of the warp curve cm on the development surface of the rotating curved surface sm. These airfoil curves csm and cpm share the end points lmL and tmT with the warp curve cm, and the shape between the end points gives the blade cross-sectional shape, that is, the airfoil shape. There are various methods for determining the airfoil curves csm and cpm. Here, the airfoil curves are automatically determined by designating the same thickness distribution on both sides of the warp curve cm. This method has a low degree of freedom as a parameter and is convenient to handle. At first glance, it seems that the degree of freedom such as asymmetry of the airfoil shape is reduced, but it has a degree of freedom in the method of determining the warp curve cm. It is possible to cope with it. A similar process is performed on the warped curve lines c1, c2,..., Cn, and the respective airfoil curves cs1, cs2,..., Csn and cp1, cp2,.
[0030]
Finally, in step # 7, processing procedure 7 for forming the blade curved surface is performed. That is, the process of connecting the airfoil curves cs1, cs2,..., Csn and cp1, cp2,..., Cpn is automatically performed to form front and back blade curved surfaces having thick airfoil cross sections.
[0031]
As described above, by using the warp line curves c1, c2,..., Cn as a reference line and providing a thickness distribution on both sides thereof to configure the airfoil, while utilizing the design method and design parameters of a thin blade with no thickness, Regardless of the airfoil performance given by the so-called carpet diagram, a new airfoil can be easily designed and studied. In addition, since the warp curve c1, c2,..., Cn are composed of a plurality of cubic curves, the degree of freedom of the warp line shape is high, and even if the thickness distribution of the airfoil is limited to the back and front target, the design The degree of freedom of the shape of the wing shape itself can be kept high.
(Example 3)
FIG. 14 shows a processing procedure of the blade curved surface design method according to the third embodiment of the present invention. The entire processing is performed in processing procedure 1 to processing procedure 8, and will be described sequentially.
[0032]
In the same manner as in the second embodiment, in step # 1 (processing procedure 1), the rotational curved surfaces s1, s2,..., Sm,..., Sn, Ls, Ts are configured, and in step # 2 (processing procedure 2), Contour lines c1, c2,..., Cn are formed, and in step # 3 (processing procedure 3), the intersections l1L, l2L,..., LnL of the warp lines c1, c2,. The rotation curved surfaces s1, s2,..., Sn are rotated around the straight line X so as to ride on the minute le, and in step # 6 (processing procedure 6), the airfoil curves cs1, cs2, ..., csn and cp1, cp2, ..., find cpn.
[0033]
Next, in step # 8, a process procedure 8 for forming a thick protrusion is performed. As shown in FIG. 15, on the development surface of the rotational curved surface sm, the end point lmL of the warp curve curve cm is extended in the direction of the angle αm to obtain a point lmx corresponding to the end point of the protruding portion lex, and accordingly, the airfoil The end points of the curves csm and cpm are also moved from the original point lmL to the new point lmx, so that the extended portion, that is, the point lmx and the original airfoil curves csm and cpm are smoothly connected to the airfoil curve near the point lmL. The process of changing the shape of is automatically performed. At this time, it is assumed that a range is provided from the point lmL to the point tmT side by the same distance as the extension length Ym of the warp line curve cm, and at least the shape of the airfoil curve on the point tmT side from the range is not changed. As long as this condition is satisfied, the airfoil curve shape from the vicinity of the point lmL to the protruding portion lex is free, but the airfoil curve on the adjacent rotating curved surface is smoothly connected.
[0034]
Finally, in step # 7, processing procedure 7 for forming the blade curved surface is performed. That is, the process of connecting the airfoil curves cs1, cs2,..., Csn and cp1, cp2,..., Cpn is automatically performed, and the front and back blade curved surfaces having a thick airfoil cross section including the protruding portion lex are formed. To do.
[0035]
As described above, the warp line curves c1, c2,..., Cn are used as reference lines, thickness distribution is provided on both sides thereof to form the airfoil, and the shape of the protrusion is additionally formed later, By correcting the airfoil curve partially and connecting it smoothly, the blade surface of the airfoil does not change due to the provision of protrusions while utilizing the design method and design parameters of thin thin wings. Design considerations are possible.
[0036]
【The invention's effect】
  As explained above, according to the blade curved surface calculation method of the present invention,On a computer system,A wide range of blade shapes can be designed by arbitrarily giving parameters for determining the blade curved surface, and the following effects can be obtained.
[0037]
By taking the procedure of additionally forming the protrusion provided on the blade leading edge later, the shape of the various protrusions can be designed while fixing the blade curved surface other than the protrusion.
[0038]
By creating a warp line curve and using it as a reference line and providing a thickness distribution on both sides of the airfoil, a new airfoil can be created while taking advantage of the design method and design parameters of thin airfoils. Easy design review.
[0039]
A warp line curve is used as a reference line, thickness distribution is provided on both sides to form an airfoil, and the shape of the protrusion is additionally formed later, and the airfoil curve is partially corrected and connected smoothly. This makes it possible to study the design of an airfoil wing that does not cause a change in the blade curved surface due to the provision of the protrusion, while utilizing the design method and design parameters of a thin wing with no thickness.
[0040]
Furthermore, by programming the blade curved surface design method as described above into a recording medium, the program can be carried and moved, and can be used at a plurality of locations.
[0041]
  Also,eachNot only can the processing procedure be performed without fail, but also cooperation with computer simulation, CAD, etc. can be strengthened, and work efficiency can be improved.
[Brief description of the drawings]
FIG. 1 is an explanatory diagram showing a configuration of a blade curved surface design apparatus according to an embodiment of the present invention.
FIG. 2 is a flowchart showing a processing procedure of a blade curved surface design method according to the first embodiment of the present invention.
FIG. 3 is an explanatory diagram for explaining calculation design in processing procedure 1 of the method
FIG. 4 is a flowchart of processing procedure 1 of the method.
FIG. 5 is a schematic diagram showing a rotating curved surface created in processing procedure 1 of the method.
FIG. 6 is a development view of a rotating curved surface for explaining calculation design in processing procedure 2 of the same method.
FIG. 7 is a flowchart of processing procedure 2 of the method.
FIG. 8 is a plan view for explaining calculation design in processing procedure 3 of the method
FIG. 9 is a flowchart of processing procedure 3 of the method.
FIG. 10 is a plan view for explaining calculation design in process procedure 4 of the method
FIG. 11 is a development view of a rotating curved surface for explaining calculation design in processing procedure 4 of the same method.
FIG. 12 is a flowchart showing a processing procedure of a blade curved surface design method in Embodiment 2 of the present invention.
FIG. 13 is a rotation curved surface development view for explaining calculation design in processing procedure 6 of the same method;
FIG. 14 is a flowchart showing a processing procedure of a blade curved surface design method in Embodiment 3 of the present invention.
FIG. 15 is a development view of a rotating curved surface for explaining calculation design in processing procedure 8 of the same method.
[Explanation of symbols]
1 Processing means
2 Calculation means
3 storage means
4 input means
5 display means
6 Output means
# 1 Procedure 1
# 2 Processing procedure 2
# 3 Procedure 3
# 4 Procedure 4
# 5 Procedure 5
# 6 Procedure 6
# 7 Procedure 7
# 8 Procedure 8

Claims (5)

The computing means connects an arbitrary four points on the plane set through the input means connected to the computing means with a smooth closed curve to form a substantially quadrilateral, and one side of a set of opposite sides of the quadrilateral is drawn as a line The segment L and the other segment T are provided with the same number of division points l1, l2,..., Ln and t1, t2,. Line segments b1, b2,..., Bn connecting the dividing points are set, and the line segments b1, b2,... Are set with an arbitrary straight line X on the same plane having no intersection with the closed curve as a rotation axis. , Bn and the line segment L and the line segment T, respectively, to form the rotation curved surfaces s1, s2,..., Sn and Ls, Ts;
The calculation means connects the rotation curved surfaces Ls and Ts on the rotation curved surfaces s1, s2,..., Sn, and the end points l1L, l2L,. endpoint t1T, t2T, ···, in TNT, [alpha] 1 angle between the circumferential direction of rotation about the line X is inputted from each of said input means, α2, ···, αn and β1, β2, ·· Process procedure 2 representing warp line curves c1, c2,..., Cn to be βn as a result of connecting a plurality of cubic curves on the development surface of the rotating curved surfaces s1, s2,. When,
The warp line so that the end points l1L, l2L,..., LnL coincide with an arbitrary curve segment le set in the direction connecting the rotating curved surfaces s1 and sn on the rotating curved surface Ls. Processing procedure 3 for rotating the curves c1, c2,..., Cn around the straight line X;
The computing means extends the warp curve curve cm in the direction of the angle αm at the end point lmL corresponding to the circumferential protrusion lex provided on the curve segment le, and the protrusion end point lmx on the extended warp line curve cm. Processing procedure 4 for determining
Defining a curved surface the arithmetic unit, the procedure 3 is rotated in the processing procedure SL before having a protrusion end point lmx defined by 4 camber line curves c1, c2, · · ·, concluded smoothly the cn And a blade curved surface design method. The computing means connects an arbitrary four points on the plane set through the input means connected to the computing means with a smooth closed curve to form a substantially quadrilateral, and one side of a set of opposite sides of the quadrilateral is drawn as a line The segment L and the other segment T are provided with the same number of division points l1, l2,..., Ln and t1, t2,. Line segments b1, b2,..., Bn connecting the dividing points are set, and the line segments b1, b2,... Are set with an arbitrary straight line X on the same plane having no intersection with the closed curve as a rotation axis. , Bn and the line segment L and the line segment T, respectively, to form the rotation curved surfaces s1, s2,..., Sn and Ls, Ts;
The calculation means connects the rotation curved surfaces Ls and Ts on the rotation curved surfaces s1, s2,..., Sn, and the end points l1L, l2L,. endpoint t1T, t2T, ···, in TNT, [alpha] 1 angle between the circumferential direction of rotation about the line X is inputted from each of said input means, α2, ···, αn and β1, β2, ·· Process procedure 2 representing warp line curves c1, c2,..., Cn to be βn as a result of connecting a plurality of cubic curves on the development surface of the rotating curved surfaces s1, s2,. When,
The warp line so that the end points l1L, l2L,..., LnL coincide with an arbitrary curve segment le set in the direction connecting the rotating curved surfaces s1 and sn on the rotating curved surface Ls. Processing procedure 3 for rotating the curves c1, c2,..., Cn around the straight line X;
The blades forming the airfoil shape with the warp line curves c1, c2,..., Cn rotated in the processing procedure 3 on the rotating curved surfaces s1, s2,. , Csn and airfoil curves cp1, cp2,..., Cpn to obtain mold curves cs1, cs2,.
The computing means extends the warp curve curve cm in the direction of the angle αm at the end point lmL corresponding to the circumferential protrusion lex provided on the curve segment le, and the protrusion end point lmx on the extended warp line curve cm. The airfoil curves csm and cpm are projected in accordance with the warp curve cm without changing the shape of at least the distance Ym between the end point lmx and the end point lmL from the end point lmL. Processing procedure 8 for extending to the end point lmx,
Said computing means, said processing airfoil curve cs1 having protrusions endpoint lmx defined in Step 8, cs2, · · ·, csn, and airfoil curve cp1, cp2, · · ·, smooth the cpn A blade curved surface design method including processing procedure 7 for connecting and defining a curved surface. A computer-readable blade curved surface design program recording medium recorded with a program for causing a computing means to execute the processing procedure of the blade curved surface design method according to claim 1 . A blade curved surface design apparatus comprising processing means, input means connected to the processing means, and display means,
The processing means includes a calculation means and a storage means,
The storage means
Arbitrary four points on the plane set through the input means are connected by a smooth closed curve to form a substantially quadrilateral, and one of the opposite sides of this quadrilateral set is a line segment L and the other is a line segment T. .., Ln and t1, t2,..., Tn are provided in equal numbers to each of the line segment L and line segment T, and the line segments b1 and b2 connecting the aforementioned division points. ,..., Bn are set, and the line segments b1, b2,..., Bn, the line segment L, and the line segment are set with an arbitrary straight line X on the same plane having no intersection with the closed curve as a rotation axis. Processing procedure 1 for rotating T respectively to form rotating curved surfaces s1, s2,..., Sn and Ls, Ts;
The rotating curved surfaces Ls and Ts are connected on the rotating curved surfaces s1, s2,..., Sn, and the end points l1L, l2L,. ,..., TnT, the angles formed with the circumferential direction in the rotation around the straight line X are α1, α2,..., Αn and β1, β2,. Process sequence 2 representing warp line curves c1, c2,..., Cn as a plurality of cubic curves connected on the development surface of the rotating curved surfaces s1, s2,.
The curved line curves c1, c2, c, c2, c, c2, c so that the end points l1L, l2L,..., LnL coincide with an arbitrary curve segment le set in a direction connecting the rotating curved surfaces s1 and sn on the rotating curved surface Ls. ..., processing procedure 3 for rotating cn around the straight line X;
Processing procedure 4 for extending the warp curve curve cm in the direction of the angle αm at the end point lmL corresponding to the circumferential protrusion lex provided on the curve segment le and determining the protrusion end point lmx on the extended warp curve cm. When,
Process procedure 5 for defining a curved surface by smoothly connecting the warp line curves c1, c2,..., Cn that rotate in the process procedure 3 and have the protrusion end point lmx defined in the process procedure 4.
Stores a program for causing the computing means to execute
The calculation means executes the processing procedure 1, the processing procedure 2, the processing procedure 3, the processing procedure 4 and the processing procedure 5 according to the program stored in the storage unit,
The processing means displays the curved surface defined in the processing procedure 5 on the display means.
A blade curved surface design apparatus characterized by that . A blade curved surface design apparatus comprising processing means, input means connected to the processing means, and display means,
The processing means includes a calculation means and a storage means,
The storage means
Arbitrary four points on the plane set through the input means are connected by a smooth closed curve to form a substantially quadrilateral, and one of the opposite sides of this quadrilateral set is a line segment L and the other is a line segment T. .., Ln and t1, t2,..., Tn are provided in equal numbers to each of the line segment L and line segment T, and the line segments b1 and b2 connecting the aforementioned division points. ,..., Bn are set, and the line segments b1, b2,..., Bn, the line segment L, and the line segment are set with an arbitrary straight line X on the same plane having no intersection with the closed curve as a rotation axis. Processing procedure 1 for rotating T respectively to form rotating curved surfaces s1, s2,..., Sn and Ls, Ts;
The rotating curved surfaces Ls and Ts are connected on the rotating curved surfaces s1, s2,..., Sn, and the end points l1L, l2L,. ,..., TnT, the angles formed with the circumferential direction in the rotation around the straight line X are α1, α2,..., Αn and β1, β2,. Process sequence 2 representing warp line curves c1, c2,..., Cn as a plurality of cubic curves connected on the development surface of the rotating curved surfaces s1, s2,.
The curved line curves c1, c2, c, c2, c, c2, c so that the end points l1L, l2L,..., LnL coincide with an arbitrary curve segment le set in a direction connecting the rotating curved surfaces s1 and sn on the rotating curved surface Ls. ..., processing procedure 3 for rotating cn around the straight line X;
On the rotating curved surfaces s1, s2,..., Sn, the airfoil curves cs1, cs2 constituting the airfoil shape with the warp line curves c1, c2,. ,..., Csn and airfoil curves cp1, cp2,.
The warp curve curve cm is extended in the direction of the angle αm at the end point lmL corresponding to the circumferential protrusion lex provided on the curve segment le, and the protrusion end point lmx is defined on the extended warp line curve cm. The airfoil curves csm and cpm are extended to the protrusion end point lmx in accordance with the warp curve curve cm without changing the shape of at least the distance Ym between the end point lmL and the end point lmL from the end point lmL. Processing procedure 8
A process of defining a curved surface by smoothly connecting the airfoil curves cs1, cs2,..., Csn and the airfoil curves cp1, cp2,. Step 7
Stores a program for causing the computing means to execute
The arithmetic means executes the processing procedure 1, the processing procedure 2, the processing procedure 3, the processing procedure 6, the processing procedure 8 and the processing procedure 7 according to the program stored in the storage means,
The processing means displays the curved surface defined in the processing procedure 7 on the display means.
A blade curved surface design apparatus characterized by that .

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