JP4013666B2 - Aerodynamic machine design method - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to an aerodynamic machine design method and design program. In particular, the present invention relates to an aerodynamic machine design method and a design program characterized by a procedure for planning an arrangement design around a gas flow path using a parametric design method.
[0002]
[Prior art]
To design a device that is a complex combination of parts with many different functions, such as aerodynamic machines (for example, jet engines), it meets the required specifications, conforms to strength and standards, and is maintained. Design with consideration of complex factors such as sex.
In general, the drawings are used based on the conventional design, and the dimensions of each part are finely adjusted and cut and pasted. This process involves many trial and error processes, and it took one to several months to create an overall layout plan.
[0003]
For example, in the design of a jet engine, design is proceeded in the order of conceptual design, basic design, detailed design, and manufacturing design. FIG. 7 is a side sectional view of the jet engine.
The procedure for producing an overall design drawing from passage data in the conceptual design process will be described as an example.
The passage data defines the shape of the gas flow path of the jet engine 1 and is two-dimensional data that defines the shape of the gas flow path connected to the compressor 2, the combustor 3, and the turbine 4 from the upstream. . This two-dimensional data represents the position of the wall surface of the gas flow path on the cut surface including the gas flow direction.
In conceptual design, based on the two-dimensional data of the passage data, each component device is roughly arranged, then the shape dimensions of each component device are determined, and an overall plan diagram showing the rough shape and arrangement of each component part is shown. create. Based on the passage data, a drawing from a conventional model is used and roughly arranged, and the overall plan is produced by changing the shape so as not to impair the passage data by adjusting fine inconsistencies.
However, since the component devices are arranged along the gas flow path and are connected to each other, if the shape of one component device is changed, the shape of the other component device must be changed. Work by mistake increases.
[0004]
[Problems to be solved by the invention]
As described above, the conventional aerodynamic machine design method has a problem that the time required for the aerodynamic machine design cannot be further shortened.
[0005]
The present invention has been devised in view of the above-described problems. Instead of a conventional aerodynamic machine design method, an aerodynamic machine capable of designing aerodynamic parts in a short time while effectively utilizing past design know-how. A design method and a design program for executing the method are provided.
[0006]
[Means for Solving the Problems]
In order to achieve the above object, a plurality of aerodynamic components having respective aerodynamic functions arranged along the gas flow path based on the passage data defining the shape of the gas flow path according to the present invention and some of the aerodynamic components. The design method of an aerodynamic machine for designing an aerodynamic machine having a disk that supports and rotates an aerodynamic component has dimension data of each part as a function including an indeterminate constant, and when a specific numerical value is given, An aerodynamic part template preparation step for preparing in advance an aerodynamic part template to which parametric part shape data, which is aerodynamic part shape data having specific dimensions by applying to constants, and functional data representing a predetermined aerodynamic function are provided, and passage data A first step of generating, for each aerodynamic part, aerodynamic part dimension data that is dimension data of each part of the aerodynamic part and aerodynamic part function data that defines the aerodynamic function A force component data generation step, selecting the aerodynamic component template to which function data matching the aerodynamic component function data is selected, and applying the aerodynamic component dimension data to the parametric component shape data of the aerodynamic component template And an aerodynamic part design process for generating aerodynamic part shape data having dimensions.
[0007]
According to the above configuration of the present invention, when the aerodynamic component template preparation process has the dimension data of each part as a function including an undetermined constant and is given a specific numerical value, it is applied to the undetermined constant and the aerodynamic having a specific dimension. Prepare an aerodynamic part template to which parametric part shape data as part shape data and functional data representing a predetermined aerodynamic function are assigned in advance, and from the passage data in the first step of the aerodynamic part data generation process, The aerodynamic part dimension data that is dimension data and the aerodynamic part function data that defines the aerodynamic function are generated for each aerodynamic part, and the aerodynamic part template to which functional data that matches the aerodynamic part functional data is assigned in the aerodynamic part design process And aerodynamic parts having specific dimensions by applying the aerodynamic part dimension data to the parametric part shape data of the aerodynamic part template Since product shape data is generated, aerodynamic part shape data having specific dimensions can be obtained by applying the aerodynamic part function data and aerodynamic part dimension data obtained from the passage data to the aerodynamic part template. The shape of a plurality of aerodynamic parts that can be adapted and perform a predetermined aerodynamic function can be determined promptly.
[0008]
Furthermore, the aerodynamic machine design method according to the present invention preferably includes an aerodynamic component arrangement step of arranging the aerodynamic component shape data of a plurality of aerodynamic components and producing overall arrangement data.
According to the configuration of the present invention, the aerodynamic component shape data of a plurality of aerodynamic components is arranged in the aerodynamic component arrangement step to produce the entire arrangement data, so that the overall arrangement design is completed based on the aerodynamic component shape data for each aerodynamic component. Can do things quickly.
[0009]
Furthermore, in the aerodynamic machine design method according to the present invention, the aerodynamic part is composed of a plurality of small parts, and the function of the parametric part shape data satisfies a dimensional restriction condition based on the mutual functions of the small parts. Is preferred.
With the above-described configuration of the present invention, the parametric part shape data function satisfies the dimensional limit condition based on the mutual functions of the small parts, so a specific dimension is applied to the undetermined constant of the parametric part shape data function. The small parts constituting the aerodynamic part having the obtained aerodynamic part shape data can exhibit the mutual functions, and it is ensured that the aerodynamic parts can also exhibit the predetermined aerodynamic function.
[0010]
Furthermore, in the design method of the aerodynamic machine according to the present invention, the passage data represents the position of the wall surface of the gas flow path in the cut surface including the gas flow direction, the two-dimensional data corresponding to the arrangement of each aerodynamic component, and each It has a set of combinations with functional data corresponding to aerodynamic parts, and the first step of the aerodynamic part data generation process generates the aerodynamic part dimension data and the aerodynamic part functional data from the two-dimensional data and the functional data. It is preferable to do this.
According to the configuration of the present invention, the two-dimensional data represents the position of the wall surface of the gas flow path on the cut surface including the gas flow direction, corresponds to the arrangement of each aerodynamic component, and the function data corresponds to each aerodynamic component. Therefore, the functional data and the two-dimensional data are associated with each other, and it is ensured that the aerodynamic component having the aerodynamic component shape data derived from the two-dimensional data exhibits a predetermined aerodynamic function.
[0011]
Further, the aerodynamic machine design method according to the present invention includes a disk data generation step of generating disk shape data having specific dimensions of each part of the disk and disk position data which is position data of each part of the disk from the passage data. Preferably, the aerodynamic component data generation step includes a second step of generating, for each aerodynamic component, the aerodynamic component dimension data of the aerodynamic component supported by the disc from the disc shape data and the disc position data.
According to the configuration of the present invention, the disk data generation process generates disk shape data having specific dimensions of each part of the disk and disk position data which is position data of each part of the disk from the passage data, and generates an aerodynamic component data process. In the second step, aerodynamic part dimension data of the aerodynamic parts supported by the disk is generated for each aerodynamic part from the disk shape data and the disk position data, so the aerodynamic parts supported by the disk are designed by parametric design. Thus, the aerodynamic part shape data of the aerodynamic parts in which the relationship between the disk and the passage data is appropriate can be quickly determined, and the entire layout design of the aerodynamic machine in which these aerodynamic parts and the disk are properly arranged can be quickly performed.
[0012]
Further, in order to achieve the above object, a plurality of aerodynamic components and parts having respective aerodynamic functions arranged along the gas flow path based on the passage data defining the shape of the gas flow path according to the present invention. A design program for an aerodynamic machine for designing an aerodynamic machine having a disk that supports and rotates the aerodynamic parts of the machine has dimensional data of each part as a function including an undetermined constant and is given a specific numerical value. Aerodynamic part template preparation in which parametric part shape data, which is aerodynamic part shape data having specific dimensions, and functional data representing a predetermined aerodynamic function are assigned in advance to the undetermined constant The aerodynamic parts and the aerodynamic part dimension data that defines the aerodynamic functions and the aerodynamic part dimension data that is the dimension data of each part of the aerodynamic part An aerodynamic component data generation procedure having a first procedure to be generated, and an aerodynamic component template to which functional data matching the aerodynamic component functional data is selected, and the aerodynamic component dimension data is selected as the parametric component shape of the aerodynamic component template An aerodynamic component design procedure for generating aerodynamic component shape data having specific dimensions by applying to the data is executed.
[0013]
According to the configuration of the present invention described above, when the computer has the dimension data of each part as a function including an undetermined constant in the aerodynamic component template preparation procedure and given a specific numerical value, the computer has a specific dimension by applying the undetermined constant. Prepare aerodynamic part template to which parametric part shape data as aerodynamic part shape data and function data representing a predetermined aerodynamic function are assigned in advance, and from the passage data to each part of the aerodynamic part in the first step of the aerodynamic part data generation procedure Aerodynamic part dimension data and aerodynamic part function data defining aerodynamic functions are generated for each aerodynamic part, and the aerodynamic part template to which functional data matching the aerodynamic part functional data is given in the aerodynamic part design procedure And apply the aerodynamic part dimension data to the parametric part shape data of the aerodynamic part template to have specific dimensions. Since the aerodynamic component shape data is generated, the aerodynamic component function data and the aerodynamic component dimension data obtained from the passage data can be applied to the aerodynamic component template to obtain aerodynamic component shape data having specific dimensions. It is possible to quickly determine the shape of a plurality of aerodynamic components that conform to the above and can exhibit a predetermined aerodynamic function.
[0014]
Furthermore, the aerodynamic machine design program according to the present invention preferably causes a computer to execute an aerodynamic component arrangement procedure for arranging the aerodynamic component shape data of a plurality of aerodynamic components and producing overall arrangement data.
With the configuration of the present invention, the computer arranges the aerodynamic component shape data of a plurality of aerodynamic components in the aerodynamic component arrangement procedure and produces overall arrangement data. Therefore, the entire arrangement is made based on the aerodynamic component shape data for each aerodynamic component. The design can be completed quickly.
[0015]
Further, in the design program for an aerodynamic machine according to the present invention, the aerodynamic part is composed of a plurality of small parts, and the function of the parametric part shape data satisfies a dimensional restriction condition based on the mutual functions of the small parts. Is preferred.
With the above-described configuration of the present invention, the parametric part shape data function satisfies the dimensional limit condition based on the mutual functions of the small parts, so a specific dimension is applied to the undetermined constant of the parametric part shape data function. The small parts constituting the aerodynamic part having the obtained aerodynamic part shape data can exhibit the mutual functions, and it is ensured that the aerodynamic parts can also exhibit the predetermined aerodynamic function.
[0016]
Furthermore, the aerodynamic machine design program according to the present invention includes a passage data representing a position of a wall surface of a gas flow path in a cut surface including a gas flow direction and two-dimensional data corresponding to the arrangement of each aerodynamic component. It has a set of combinations with functional data corresponding to aerodynamic parts, and the first procedure of the aerodynamic part data generation procedure generates the aerodynamic part dimension data and the aerodynamic part functional data from the two-dimensional data and the functional data. It is preferable to do this.
According to the configuration of the present invention, the two-dimensional data represents the position of the wall surface of the gas flow path on the cut surface including the gas flow direction, corresponds to the arrangement of each aerodynamic component, and the function data corresponds to each aerodynamic component. Therefore, the function data and the two-dimensional data are associated with each aerodynamic part, and it is ensured that the aerodynamic part having the aerodynamic part shape data derived from the two-dimensional data exhibits a predetermined aerodynamic function.
[0017]
Further, the aerodynamic machine design program according to the present invention is a disc data for generating disc shape data having specific dimensions of each part of the disc and disc position data which is position data of each part of the disc from the passage data. A generation procedure is executed, and the aerodynamic component data generation step includes a second step of generating, for each aerodynamic component, the aerodynamic component dimension data of the aerodynamic component supported by the disk from the disk shape data and the disk position data. preferable.
With the configuration of the present invention, the computer generates disk shape data having specific dimensions of each part of the disk and disk position data which is position data of each part of the disk from the passage data in the disk data generation process, and aerodynamic components In the second step of the data generation process, aerodynamic part dimension data of the aerodynamic parts supported by the disk is generated for each aerodynamic part from the disk shape data and the disk position data, so the aerodynamic parts supported by the disk are parametrically designed. The aerodynamic component shape data of the aerodynamic parts that are designed according to the disc and passage data can be determined promptly, and the overall layout design of the aerodynamic machine in which those aerodynamic components and the disc are properly arranged can be quickly performed. .
[0018]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. In each figure, common portions are denoted by the same reference numerals, and redundant description is omitted.
[0019]
An aerodynamic machine design method according to an embodiment of the present invention will be described. The aerodynamic machine design method is a method of designing an aerodynamic machine from passage data.
The passage data is data defining the shape of the gas flow path.
An aerodynamic machine is a machine having a plurality of aerodynamic parts arranged along a gas flow path and having respective aerodynamic functions and a disk that rotates while supporting some of the aerodynamic parts. , Axial compressors, turbines and the like.
Hereinafter, a jet engine will be described as an example of an aerodynamic machine, and a joint portion between a disk and a stationary blade will be described as an example of an aerodynamic part.
[0020]
FIG. 1 is a procedure diagram of the first embodiment of the present invention. FIG. 2 is a conceptual diagram of passage data according to the embodiment of the present invention. FIG. 3 is a partial cross-sectional view of an embodiment of the present invention. FIG. 4 is a parametric design diagram of the embodiment of the present invention.
[0021]
First, the joint portion 5 between the disk and the stationary blade will be briefly described with reference to the drawings. FIG. 3 shows a cross-sectional view of the engaging portion 5 between the disk and the stationary blade.
The disk / stator vane connecting portion 5 is a base portion structure of a compressor stator vane, and is an aerodynamic member including an inner band 7, a seal outer peripheral member 8, and a seal inner peripheral member 9. The inner band 7 is a member constituting a part of the circumference of the annular structure, and the outer peripheral surface forms the wall surface of the gas flow path (gas duct). The seal outer peripheral member 8 and the seal inner peripheral member 9 are members that constitute a labyrinth seal integrally. The gap between the seal outer peripheral member 8 and the seal inner peripheral member 9, which is the fixed side where the seal outer peripheral member engages with the inner band 7 and the seal inner peripheral member is the rotating side supported by the disk, forms a labyrinth seal. The gas pressure in the gas duct is prevented from lowering due to gas leakage.
[0022]
The aerodynamic machine design method according to the first embodiment of the present invention will be described below.
The aerodynamic machine design method is a method of designing an aerodynamic machine from passage data, and includes an aerodynamic component template preparation step P10, an aerodynamic component data generation step (first procedure) P20, a disk data generation step P30, and an aerodynamic component data generation step. (Second procedure) P40, an aerodynamic component design process P50, and an aerodynamic component arrangement process P60 are provided.
The passage data defines the shape of the gas flow path of the jet engine 1, and is position data that defines the shape of the gas flow path connected to the compressor 2, the combustor 3, and the turbine 4 from the upstream. Further, the passage data defines the function of each space by dividing the flow path into short spaces by function from the front. The function is what number of stator blades or what number of stator blades is in the case of a compressor or a turbine.
The passage data does not define the fine dimensions of the parts arranged around the flow path.
In particular, the passage data represents the position of the wall surface of the gas flow path on the cut surface including the gas flow direction, and a combination of two-dimensional data corresponding to the arrangement of each aerodynamic component and functional data corresponding to each aerodynamic component. It is preferable to have a set of FIG. 2 shows an example of passage data. Functional data is composed of a combination of blade row number constants, and two-dimensional data is defined by coordinate data for each position represented by blade point number constants associated with blade row number constants.
In the figure, “SV” represents a compressor vane, “RB” represents a compressor blade, “NZL” represents a turbine vane, “BKT” represents a turbine blade, and the numbers represent the compressor or turbine. Represents the number of steps.
[0023]
The aerodynamic component template preparation step P10 is a step of preparing an aerodynamic component template in advance. The aerodynamic part template is given parametric part shape data and function data.
The parametric part shape data has dimension data of each part as a function including an undetermined constant, and when given a specific numerical value, it is applied to the undetermined constant and has a specific dimension. The function data is data representing a predetermined aerodynamic function.
The aerodynamic function is a function in an aerodynamic component jet engine (aerodynamic equipment), and is defined by, for example, a compressor stationary blade, a compressor moving blade, a turbine nozzle, or the number of stages.
In particular, the aerodynamic function preferably corresponds to the blade number constant of the passage data.
The parametric part shape data has a function for determining dimension data of a part that is a basic dimension in designing and manufacturing an aerodynamic device.
For example, when the aerodynamic part is a part that joins the disk and the stationary blade, the front and rear support points (P3, P4) supported by the disk of the inner peripheral channel 9 and the front and rear portions (P1, P2) and the seal inner peripheral member 9 , P5, P6) is set as an undetermined constant of the function, and each data of P1, P2, P3, P4, P5, P6 is applied to the undetermined constant, whereby the inner band 7 having a specific size and the outer circumference of the seal The member 8 and the seal inner peripheral member 9 are preferably determined.
The function of the parametric part shape data satisfies the dimensional limit condition based on the mutual functions of the inner band 7, the seal outer peripheral member 8, and the seal inner peripheral member 9 (corresponding to small parts). The dimensional restriction condition is that the gap between the seal outer peripheral member 8 and the seal inner peripheral member 9 maintains a predetermined value, and the inner peripheral surface of the seal outer peripheral member 8 forms a plane parallel to the rotation center of the disk. And so on.
[0024]
The aerodynamic component data generation step (first procedure) P20 is a step of generating aerodynamic component dimension data that is dimension data of each part of the aerodynamic component and aerodynamic component function data that defines the aerodynamic function from the passage data.
In the aerodynamic component data generation step (first procedure) P20, aerodynamic component position data that is position data of each part of the aerodynamic component and aerodynamic component function data that defines the aerodynamic function are extracted from the passage data for each aerodynamic component, Next, the aerodynamic component position data is converted for each aerodynamic component into aerodynamic component dimension data which is dimension data of each part of the aerodynamic component.
When the passage data represents the position of the wall surface of the gas flow path on the cut surface including the gas flow direction and has two-dimensional data corresponding to the arrangement of each aerodynamic component, the two-dimensional data corresponding to the arrangement of the aerodynamic component is used. Extracting the aerodynamic component position data;
The aerodynamic component position data is subjected to coordinate conversion based on the design origin of the aerodynamic component to generate aerodynamic component dimension data.
For example, the aerodynamic component data generated in the aerodynamic component data generation step (first procedure) S20 is two-dimensional data applied to P1 and P2.
[0025]
The disk data generation process P30 is a process of generating disk shape data having specific dimensions of each part of the disk and disk position data that is position data of each part of the disk from the passage data.
Disc shape data and disc position data are generated from the relative relationship with the passage data and the strength condition.
[0026]
The aerodynamic component data generation step (second procedure) P40 is a step of generating, for each aerodynamic component, aerodynamic component dimension data of the aerodynamic component supported by the disc from the disc shape data and the disc position data.
In the aerodynamic component data generation step (second procedure) P40, disk support point position data, which is position data of a support point of a disk that supports the aerodynamic component, is extracted from the disk shape data and the disk position data. The support point position data is converted into aerodynamic component dimension data of aerodynamic components for each aerodynamic component.
For example, two-dimensional data (position data in the XY coordinates) of the point at which the disk supports the aerodynamic component is generated from the disk support point position data, and the two-dimensional data of the corresponding point of the aerodynamic component (in consideration of the mutual relationship between the components) (Position data in XY coordinates) is determined and aerodynamic component dimension data is created.
For example, the aerodynamic component data generated in the aerodynamic component data generation step (second procedure) S40 is two-dimensional data applied to P3, P4, P5, and P5.
[0027]
In the aerodynamic part design process P50, an aerodynamic part template to which functional data matching the aerodynamic part functional data is selected is selected, and the aerodynamic part dimension data is applied to an undetermined constant of a parametric part shape data function of the aerodynamic part template. This is a step of generating aerodynamic component shape data having specific dimensions. FIG. 4 illustrates a state where aerodynamic part shape data is generated from parametric part shape data.
From the aerodynamic component function data, the number of stages is confirmed whether it is a compressor or turbine, a stationary blade or a moving blade, and an aerodynamic component template that matches the aerodynamic component function data is selected. The parametric part shape data of the selected aerodynamic part template is called, and the aerodynamic part dimension data is applied to the parameters to create aerodynamic part shape data having specific dimensions.
For example, aerodynamic component shape data is expanded and contracted by applying aerodynamic component dimension data to P1, P2, P3, P4, P5 and P5, and aerodynamic component shape data is automatically generated.
[0028]
The aerodynamic component arrangement step P60 is a step of arranging the aerodynamic component shape data of a plurality of aerodynamic components and producing overall arrangement data.
In the aerodynamic component arrangement step S60, the aerodynamic component shape data of each aerodynamic component is arranged based on the aerodynamic component position data, and this step is applied to the compression unit, the combustor unit, the turbine unit, and the disk, thereby Overall layout data that is the basis of the overall layout plan is completed.
[0029]
Next, an aerodynamic machine design program according to the second embodiment of the present invention will be described.
FIG. 5 is a conceptual diagram of a computer according to the second embodiment of this invention. FIG. 6 is a flowchart of the second embodiment of the present invention.
[0030]
First, the computer 10 will be described. FIG. 5 shows the configuration of the computer. The computer 10 is a device that executes a predetermined procedure using a design program, and includes an operation unit 11, a storage unit 12, a calculation unit 13, a display unit 14, and a printing unit 15.
The operation unit 11 is used to input various types of information serving as a basis for designing a jet engine (corresponding to an aerodynamic machine) to the calculation unit, and is, for example, a keyboard. Such information includes, for example, a target jet engine (corresponding to an aerodynamic machine) design specifications, strength conditions, aerodynamic conditions, and the like.
The storage unit 12 stores passage data and a design program, outputs the stored information to the calculation unit 13 in response to a request from the calculation unit, and stores the calculation result sent from the calculation unit 13.
The calculation unit 13 executes a predetermined procedure according to the design program for the aerodynamic machine, determines the overall layout design of the aerodynamic machine, outputs the calculation result to the storage unit 12, the display unit 14, or the printing unit 15, for example, a personal computer or Engineering center.
The display unit 14 is a device that displays the display data sent from the calculation unit 13 and is, for example, a monitor.
The printing unit 15 is a device that prints the printing data sent from the calculation unit 13, and is a plotter, for example. The whole design drawing data generated by the design program is plotted as a design drawing.
[0031]
An aerodynamic machine design program will be described by taking a case where the aerodynamic machine is a jet engine as an example.
[0032]
The aerodynamic machine design program includes an aerodynamic part template preparation program S10, an aerodynamic part data generation program (part 1) S20, a disk data generation program S30, an aerodynamic part data generation program (part 2) S40, an aerodynamic part design program S50, and an aerodynamic part. An arrangement program S60.
[0033]
The aerodynamic component template preparation program S10 is a program that causes a computer to execute an aerodynamic component template preparation procedure for preparing an aerodynamic component template in advance.
Since the aerodynamic component template preparation procedure is the same as the procedure described in the aerodynamic component template preparation step in the first embodiment, the description thereof is omitted.
[0034]
The aerodynamic component data generation program (first procedure) S20 generates, for each aerodynamic component, aerodynamic component dimension data that is dimension data of each part of the aerodynamic component and aerodynamic component function data that defines the aerodynamic function from the passage data. A program for causing a computer to execute a data generation procedure.
Since the aerodynamic component data generation procedure is the same as the procedure described in the aerodynamic component data generation step in the first embodiment, the description thereof is omitted.
[0035]
The disk data generation program S30 is a program that causes a computer to execute a disk data generation procedure for generating disk shape data having specific dimensions of each part of the disk from disk data and disk position data that is position data of each part of the disk. is there.
The disc data generation procedure is the same as the procedure described in the disc data generation step in the first embodiment, and thus description thereof is omitted.
[0036]
The aerodynamic component data generation program (second procedure) S40 is a computer that generates an aerodynamic component data generation procedure for generating, for each aerodynamic component, the aerodynamic component dimension data of the aerodynamic component supported by the disc from the disc shape data and the disc position data. This is a program to be executed.
Since the aerodynamic component data generation procedure is the same as the procedure described in the aerodynamic component data generation step in the first embodiment, the description thereof is omitted.
[0037]
The aerodynamic component design program S50 selects an aerodynamic component template to which functional data matching the aerodynamic component functional data is selected, and applies the aerodynamic component dimension data to an undetermined constant of the function of the parametric component shape data of the aerodynamic component template. This is a program for causing a computer to execute an aerodynamic part design procedure for generating aerodynamic part shape data having specific dimensions.
Since the aerodynamic component design procedure is the same as the procedure described in the aerodynamic component design process in the first embodiment, the description thereof is omitted.
[0038]
The aerodynamic component arrangement program S60 is a program for causing a computer to execute an aerodynamic component arrangement procedure for arranging the aerodynamic component shape data of a plurality of aerodynamic components and producing overall arrangement data.
Since the aerodynamic component arrangement procedure is the same as the procedure described in the aerodynamic component arrangement step in the first embodiment, the description thereof is omitted.
[0039]
By using the jet engine design method and design program of the above-described embodiment, it is possible to design the entire arrangement of the jet engine from the passage data without trial and error.
Predetermining the aerodynamic part model, substituting the aerodynamic part dimension data obtained from the passage data into the aerodynamic part model, and obtaining the aerodynamic part shape data. The overall layout design of the jet engine is performed smoothly.
Also. Since the passage data is configured as a set of a set of two-dimensional data and functional data of the aerodynamic parts, the correspondence between the two-dimensional data of the aerodynamic parts and the aerodynamic function can be easily obtained.
In addition, since the parts dimensions of a plurality of aerodynamic parts arranged along the gas flow path are obtained from the passage data of the jet engine, respectively, and assembled into the overall layout design again, the overall layout design can be made smoothly without trial and error.
[0040]
The present invention is not limited to the embodiments described above, and various modifications can be made without departing from the scope of the invention.
Although the aerodynamic machine has been described as being a jet engine, the present invention is not limited thereto, and may be another aerodynamic machine having a disk and an aerodynamic component.
[0041]
【The invention's effect】
As described above, based on the passage data defining the shape of the gas flow path of the present invention, a plurality of aerodynamic parts arranged along the gas flow path and having respective aerodynamic functions and some of the aerodynamic parts An aerodynamic machine design method and design program for designing an aerodynamic machine having a disk that supports and rotates has the following effects depending on its configuration.
Since the aerodynamic parts are designed from the passage data using the aerodynamic part template prepared in advance, the aerodynamic part functional data and the aerodynamic part dimension data obtained from the passage data are applied to the aerodynamic part template and the aerodynamic parts have specific dimensions. Shape data can be obtained, and the shape of a plurality of aerodynamic components that can be adapted to passage data and exhibit a predetermined aerodynamic function can be determined promptly.
In addition, since the function of the parametric part shape data satisfies the dimensional restriction condition based on the mutual functions of the small parts, the aerodynamic part obtained by applying a specific dimension to the undetermined constant of the function of the parametric part shape data The small parts constituting the aerodynamic parts having the shape data can exhibit mutual functions, and it is ensured that the aerodynamic parts can also exhibit a predetermined aerodynamic function.
In addition, since the function data and the two-dimensional data correspond to each aerodynamic component, the function data and the two-dimensional data are associated with each other, and the aerodynamic component having the aerodynamic component shape data derived from the two-dimensional data is a predetermined aerodynamic function. It is guaranteed to demonstrate.
Therefore, it is possible to provide an aerodynamic machine design method capable of designing aerodynamic parts in a short time while effectively utilizing past design know-how and a design program for executing the method.
[0042]
[Brief description of the drawings]
FIG. 1 is a procedure diagram of a first embodiment of the present invention.
FIG. 2 is a conceptual diagram of passage data according to the embodiment of this invention.
FIG. 3 is a model of an aerodynamic component according to an embodiment of the present invention.
FIG. 4 is a parametric design diagram of an embodiment of the present invention.
FIG. 5 is a conceptual diagram of a computer according to a second embodiment of this invention.
FIG. 6 is a flowchart of the second embodiment of the present invention.
FIG. 7 is a side sectional view of the jet engine.
[Explanation of symbols]
1 Aerodynamic machine (jet engine)
2 Compressor section
3 Combustor
4 Turbine part
5 Aerodynamic parts
6 discs
7 Inner band
8 Seal peripheral member
9 Seal inner member
10 Computer
11 Operation unit
12 Storage unit
13 Calculation unit
14 Display section
15 Printing department
P1 Passage point
P2 passage point
P3 disc point
P4 disc point
P5 disc point
P6 disc point
P10 Aerodynamic part template preparation process
P20 Aerodynamic parts data generation process
P30 Disc data generation process
P40 Aerodynamic parts data generation process
P50 Aerodynamic component design process
P60 Aerodynamic component placement design process
S10 Aerodynamic parts template preparation program
S20 Aerodynamic parts data generation program
S30 Disk data generation program
S40 Aerodynamic parts data generation program
S50 Aerodynamic parts design program
S60 Aerodynamic component placement design program

Claims (6)

A plurality of aerodynamic parts arranged along the gas flow path based on passage data defining the shape of the gas flow path and having respective aerodynamic functions and a disk that supports and rotates some of the aerodynamic parts. A computer-implemented aerodynamic machine design method for designing an aerodynamic machine having:
Parametric part shape data and predetermined aerodynamics, which have dimension data of each part as a function including an undetermined constant and are applied to the undetermined constant to provide aerodynamic part shape data having a specific dimension. An aerodynamic part template preparation step for preparing in advance an aerodynamic part template to which function data representing a function is assigned;
An aerodynamic component data generation step having a first step of generating, for each aerodynamic component, aerodynamic component dimension data that is dimension data of each part of the aerodynamic component from the passage data and aerodynamic component function data that defines the aerodynamic function;
Aerodynamic part shape data having specific dimensions is selected by selecting the aerodynamic part template to which functional data matching the aerodynamic part functional data is assigned, and applying the aerodynamic part dimension data to the parametric part shape data of the aerodynamic part template Aerodynamic part design process to generate
A method for designing an aerodynamic machine, comprising: 2. The aerodynamic machine according to claim 1, wherein the aerodynamic part is composed of a plurality of small parts, and the function of the parametric part shape data satisfies a dimensional restriction based on the mutual functions of the small parts. Design method. The passage data represents the position of the wall surface of the gas flow path on the cut surface including the gas flow direction, and a set of combinations of two-dimensional data corresponding to the arrangement of each aerodynamic component and functional data corresponding to each aerodynamic component. Have
The first step of the aerodynamic component data generation step generates the aerodynamic component dimension data and the aerodynamic component functional data from the two-dimensional data and the functional data.
The method for designing an aerodynamic machine according to claim 1, wherein the design method is an aerodynamic machine. A plurality of aerodynamic parts arranged along the gas flow path based on passage data defining the shape of the gas flow path and having respective aerodynamic functions and a disk that supports and rotates some of the aerodynamic parts. An aerodynamic machine design program for designing an aerodynamic machine having
On the computer,
Parametric part shape data and predetermined aerodynamics, which have dimension data of each part as a function including an undetermined constant and are applied to the undetermined constant to provide aerodynamic part shape data having a specific dimension. An aerodynamic component template preparation procedure for preparing in advance an aerodynamic component template to which function data representing a function is assigned;
An aerodynamic component data generation procedure having a first procedure for generating, for each aerodynamic component, aerodynamic component dimension data that is dimension data of each part of the aerodynamic component from the passage data and aerodynamic component function data that defines the aerodynamic function;
The aerodynamic part model data having specific dimensions is selected by selecting an aerodynamic part model to which function data matching the aerodynamic part function data is assigned, and applying the aerodynamic part dimension data to the parametric part shape data of the aerodynamic part model. Aerodynamic component design procedure to generate,
A design program for an aerodynamic machine characterized in that 5. The aerodynamic machine according to claim 4, wherein the aerodynamic part is composed of a plurality of small parts, and the function of the parametric part shape data satisfies a dimensional restriction based on the mutual functions of the small parts. Design program. The passage data represents the position of the wall surface of the gas flow path on the cut surface including the gas flow direction, and a set of combinations of two-dimensional data corresponding to the arrangement of each aerodynamic component and functional data corresponding to each aerodynamic component. Have
The first procedure of the aerodynamic component data generation procedure generates the aerodynamic component dimension data and the aerodynamic component functional data from the two-dimensional data and the functional data.
The design program for an aerodynamic machine according to claim 4 or 5, wherein:

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