Composite material fan blade cold state blade profile parallel extraction method and device

Abstract

The invention provides a composite material fan blade cold state blade profile parallel extraction method and device. The method comprises the following steps: S1, inputting a guide node and a cold state finite element model surface unit; s2, according to the number of the guide nodes, determining the number of parallel computing cores, equally dividing the guide nodes, and sending the equally divided guide nodes and surface nodes to each sub-process by the host process; s3, executing a search algorithm by each sub-process, and determining all nodes of a cross section where each guide node is located; and S4, each sub-process sends the node of each section of the sub-process to the host process, and the host process outputs a cold-state leaf profile according to the sections after merging. According to the cold-state leaf profile parallel extraction method and device, cold-state leaf profile extraction can be automatically executed, the calculation efficiency is improved, the error probability is reduced, and the design efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of engine strength design technology, specifically to a method and apparatus for parallel extraction of cold-state blade profile of composite fan blades. Background Technology

[0002] Fan blades are designed as hot blades under centrifugal force and aerodynamic loads, i.e., temperature loads. However, blade manufacturing requires a cold blade profile. Therefore, fan blades need to be converted from hot to cold to obtain a cold blade profile, thus enabling the manufacture of fan blades.

[0003] Composite fan blades have complex structures, including polyurethane films, adhesive layers, composite bodies, and metal reinforcing edges. The transition between hot and cold states needs to be calculated using finite element methods. However, due to the presence of adhesive layers and reinforcing edges, the nodes on the surface of the finite element model are discontinuous. The challenge lies in extracting the nodes of the cold-state blade profile to form the cold-state blade profile and then using 3D CAD software to build the cold-state model.

[0004] The common method is to manually create a finite element node set and output the coordinates of the points in the set. However, due to the complexity of the composite material fan blade structure, this process is tedious and prone to errors.

[0005] In view of this, the inventors of this application have designed a method and apparatus for parallel extraction of cold-state blade profile of composite material fan blades in order to overcome the above-mentioned technical problems. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to overcome the defect that it is difficult to extract the cold blade profile of composite material fan blades in the prior art, and to provide a method and apparatus for parallel extraction of the cold blade profile of composite material fan blades.

[0007] The present invention solves the above-mentioned technical problems through the following technical solution:

[0008] This invention provides a parallel extraction method for cold-state blade profiles of composite material fan blades. The method comprises the following steps: S1, inputting guiding nodes and surface elements of the cold-state finite element model; S2, determining the number of parallel computation cores based on the number of guiding nodes, evenly distributing the guiding nodes, and having the main process send the evenly distributed guiding nodes and surface nodes to each subprocess; S3, each subprocess executing a search algorithm to determine all nodes in the cross-section of each guiding node; S4, each subprocess sending the nodes of each cross-section of its own process to the main process, which then merges them and outputs the cold-state blade profile according to the cross-section.

[0009] According to one or more embodiments of the present invention, step S1 includes the following steps: S 11 1. Determine the engine analysis state point for cold and hot state analysis; S12 Regarding step S 11 Based on the determined analysis state points, computational fluid dynamics aerodynamic and thermal analyses are performed to obtain the aerodynamic and thermal loads acting on the blades; S 13 Regarding step S 11 The analysis state point determined in the process and the step S 12 Based on the obtained aerodynamic and temperature loads, a cold-to-hot state transition analysis was conducted to obtain a finite element model of the cold-state airfoil; S 14 Select a series of points along the radial direction as guide nodes to form a node set ψ; the guide nodes are selected from nodes on a continuous surface; S 15 The surface units are realized by extracting the outer surface units of the volume units, forming a surface unit set Φ and an exclusion unit set Ω.

[0010] According to one or more embodiments of the present invention, step S 11 The economic cycle state is used as the design point for the transition between hot and cold states.

[0011] According to one or more embodiments of the present invention, step S2 includes the following steps: S 21 1. Determine the parallel computing subprocesses based on the number of bootstrap nodes; S 22 The main process distributes the bootstrap node and surface node to each child process through the information transfer interface.

[0012] According to one or more embodiments of the present invention, step S 22 The boot nodes are stored in an array. The main process packages the node numbers according to the array's storage order and then sends them to each child process. The child processes form a boot node set Ψ. k k = 1, 2, 3, ...; At the same time, surface nodes and surface cells are sent directly to each child process without being split, and all surface nodes are also sent to each child process.

[0013] According to one or more embodiments of the present invention, step S3 includes the following steps: S 31 Each child process traverses its own process's bootstrap node set Ψ k According to node number n yd_i If i = 1, 2, 3, ..., the face element f is determined in reverse order. yd_j j = 1, 2, 3, 4, with a maximum value of 4, and the corresponding surface elements are quadrilateral elements; S 32 For the starting node n yd_1 In surface element f yd_j By arbitrarily selecting a cell, the two edges e passing through that point can be determined. yd_1 and e yd_2Determine if the other node of the two edges is in the set of guiding nodes Ψ; if not, keep the node; if so, exclude the node and move the other node n. yd_i Add to the set of cross-section points m = 1, 2, 3, ...; S 33 For any subsequent node n yd_i Determine the quadrilateral cell containing the node, and based on the quadrilateral cell, determine the edges containing that node, excluding those containing n. yd_i and The nodes corresponding to the edges of the quadrilateral are defined, and the endpoints of the remaining edge are the set of points to be added to the cross-section. node n yd_i+1 .

[0014] According to one or more embodiments of the present invention, each subprocess in step S3 is performed independently, and there is no communication between the subprocesses.

[0015] According to one or more embodiments of the present invention, step S4 includes the following steps: S 41 The main process communicates with each slave process through an information transmission interface and collects the node sets of each cross-section formed by each slave process. S 42 The main process aggregates the nodes of each section into a cold airfoil node set. And output it.

[0016] This invention also provides a parallel extraction device for cold-state blade profiles of composite material fan blades. The device employs the parallel extraction method for cold-state blade profiles of composite material fan blades as described above. The parallel extraction device includes: an input module for inputting guiding nodes and surface elements of the cold-state finite element model; an allocation module for determining the number of parallel computing cores based on the number of guiding nodes, evenly distributing the guiding nodes, and having the main process send the evenly distributed guiding nodes and surface nodes to each subprocess; a calculation module for running each subprocess to execute a search algorithm and determine all nodes in the cross-section where each guiding node is located; and an output module for running each subprocess to send the nodes of each cross-section of its own process to the main process, which then merges them and outputs the cold-state blade profile according to the cross-section.

[0017] The present invention also provides an electronic device, characterized in that the electronic device includes: a processor and a memory, the memory storing a program or instructions that can run on the processor, the program or instructions being executed by the processor to implement the parallel extraction method for cold-state blade profile of composite material fan blades as described above.

[0018] The positive and progressive effects of this invention are as follows:

[0019] The method and apparatus for parallel extraction of cold-state blade profile of composite material fan blades of the present invention have at least the following advantages:

[0020] The cold-state blade profile parallel extraction method and apparatus of the present invention are designed based on the characteristics of composite material fan blades with metal reinforcement edges. The method can automatically perform cold-state blade profile extraction, improves computational efficiency, reduces the probability of errors, and improves design efficiency. Attached Figure Description

[0021] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features, wherein:

[0022] Figure 1 This is a schematic flowchart of the parallel extraction method for cold-state blade profile of composite material fan blades according to the present invention.

[0023] Figure 2 This is a schematic diagram of the guiding node for the cold air profile in the parallel extraction method of cold air profile of composite material fan blades in this invention.

[0024] Figure 3 This is a schematic diagram of some surface units in the parallel extraction method of cold-state blade profile of composite material fan blades of the present invention.

[0025] Figure 4 This is a schematic diagram from one perspective of the partial exclusion unit in the parallel extraction method for cold-state blade profile of composite material fan blades of the present invention.

[0026] Figure 5 This is a schematic diagram of some surface units in the parallel extraction method of cold-state blade profile of composite material fan blades of the present invention.

[0027] Figure 6 This is a schematic diagram illustrating the discontinuity of the metal reinforcing edge and adhesive layer in the transition region with the body in the parallel extraction method of cold-state blade profile of composite material fan blades of the present invention.

[0028] Figure 7 This is a schematic diagram illustrating the determination of the next node based on the initial node in the parallel extraction method of cold-state blade profile of composite material fan blades according to the present invention. Detailed Implementation

[0029] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0030] Embodiments of the invention will now be described in detail with reference to the accompanying drawings. Preferred embodiments of the invention will now be described in detail, examples of which are illustrated in the drawings. Wherever possible, the same reference numerals will be used in all the drawings to denote the same or similar parts. Furthermore, although the terminology used herein is selected from commonly known and used terminology, some terms mentioned in this specification may have been chosen by the applicant at his or her discretion, and their detailed meanings are explained in the relevant sections of the description herein. Moreover, the invention should be understood not only by the actual terms used, but also by the meaning implied by each term.

[0031] like Figure 1 As shown, this invention provides a method for parallel extraction of cold-state blade profile of composite fan blades, comprising the following steps:

[0032] Step S1: Input the guiding node and surface elements of the cold finite element model;

[0033] Step S2: Determine the number of computing cores and allocate data. That is, determine the number of parallel computing cores based on the number of boot nodes, distribute the boot nodes equally, and have the main process send the equally distributed boot nodes and surface nodes to each child process.

[0034] Step S3: Each subprocess executes the search algorithm to determine all nodes in the section where each guiding node is located;

[0035] Step S4: The main process receives data from each child process and outputs the cold air profile. That is, each child process sends the nodes of each section of its process to the main process. The main process merges the data and outputs the cold air profile according to the section.

[0036] The present invention provides a parallel extraction method for cold-state blade profiles of composite material fan blades, which can automatically perform cold-state blade profile extraction, improve computational efficiency, reduce the probability of errors, and enhance design efficiency.

[0037] In a preferred embodiment of the parallel extraction method for cold-state blade profile of composite material fan blades of the present invention, step S1 includes the following steps:

[0038] Step S 11 Determine the engine analysis state point for cold and hot state analysis;

[0039] Step S 12 Regarding step S 11 Based on the determined analysis state point, computational fluid dynamics (CFD) aerodynamic and thermal analyses are performed to obtain the aerodynamic and temperature loads on the blade.

[0040] Step S 13 Regarding step S 11 The analysis state point determined in the process and the step S12 The aerodynamic and temperature loads obtained are used to conduct cold-hot state transformation analysis and obtain the finite element model of the cold airfoil.

[0041] Step S 14 Select a series of points along the radial direction as guide nodes to form a node set Ψ, such as Figure 2 As shown; the guiding node selects nodes on a continuous surface;

[0042] Step S 15 The surface units are realized by extracting the outer surface units of the volume units, forming a surface unit set Φ and an exclusion unit set Ω; Figure 3 This is a schematic diagram of some surface units. Figure 4 This is a perspective from which a partial unit diagram is excluded; due to the discontinuity between the metal reinforcing edge and the adhesive layer in the transition area with the body, such as... Figure 5 As shown, the aerodynamic blade profile of each section needs to be continuous, so overlapping point sets need to be removed from the section point set.

[0043] As a preferred embodiment of the parallel extraction method for cold-state blade profile of composite fan blades of the present invention, step S 11 The economic cycle state is used as the design point for the transition between hot and cold states.

[0044] In a preferred embodiment of the parallel extraction method for cold-state blade profile of composite material fan blades of the present invention, step S2 includes the following steps:

[0045] Step S 21 The number of parallel computing subprocesses is determined based on the number of bootstrap nodes. To minimize the communication volume between each subprocess and improve the efficiency of parallel computing, eight subprocesses are usually used.

[0046] Step S 22 The main process (process 0) distributes the boot node and surface node to each child process through the message passing interface (MPI).

[0047] As a preferred embodiment of the parallel extraction method for cold-state blade profile of composite fan blades of the present invention, step S 22 The boot nodes are stored in an array. The main process packages the node numbers according to the array's storage order and then sends them to each child process. The child processes form a boot node set Ψ. k k = 1, 2, 3, ...; At the same time, surface nodes and surface cells are sent directly to each child process without being split, and all surface nodes are also sent to each child process.

[0048] In a preferred embodiment of the parallel extraction method for cold-state blade profile of composite fan blades of the present invention, step S3 includes the following steps:

[0049] Step S 31 Each child process traverses its own process's bootstrap node set Ψ k According to node number n yd_i If i = 1, 2, 3, ..., the face element f is determined in reverse order. yd_j j = 1, 2, 3, 4, with a maximum value of 4. Since hexahedral elements are used when analyzing composite materials, the corresponding surface elements are all quadrilateral elements.

[0050] Step S 32 For the starting node n yd_1 In surface element f yd_j By arbitrarily selecting a cell, the two edges e passing through that point can be determined. yd_1 and e yd_2 Determine if the other node of the two edges is in the set of guiding nodes Ψ; if not, keep the node; if so, exclude the node and move the other node n. yd_i Add to the set of cross-section points m = 1, 2, 3, ..., such as Figure 6 As shown;

[0051] Step S 33 For any subsequent node n yd_i Determine the quadrilateral cell containing the node, and based on the quadrilateral cell, determine the edges containing that node, excluding those containing n. yd_i and The nodes corresponding to the edges of the quadrilateral are defined, and the endpoints of the remaining edge are the set of points to be added to the cross-section. The node nyd_i+1, such as Figure 7 As shown.

[0052] In a preferred embodiment of the parallel extraction method for cold-state blade profile of composite material fan blades of the present invention, each subprocess in step S3 is performed independently and there is no communication between the subprocesses.

[0053] Since each subprocess runs independently and there is no communication between them, communication time is reduced and parallel efficiency is improved.

[0054] In a preferred embodiment of the parallel extraction method for cold-state blade profile of composite material fan blades of the present invention, step S4 includes the following steps:

[0055] Step S 41 The main process communicates with each slave process through the Message Passing Interface (MPI) and collects the node sets of each cross-section formed by each slave process.

[0056] Step S 42 The main process aggregates the nodes of each section into a cold airfoil node set. And output it.

[0057] The parallel extraction method for cold-state blade profile of composite fan blades of the present invention is designed based on the characteristics of composite fan blades with metal reinforcing edges. It can automatically perform cold-state blade profile extraction, improves computational efficiency, reduces the probability of errors, and improves design efficiency.

[0058] The parallel extraction method for cold-state blade profile of composite material fan blades of the present invention utilizes parallel computing technology, which can process multiple computing tasks simultaneously and significantly shorten the computing time. Since the calculation of cold-state blade profile involves a large amount of finite element analysis and data processing, parallel processing can effectively utilize computing resources and improve overall computing efficiency.

[0059] The present invention also provides a parallel extraction device for cold-state blade profiles of composite material fan blades. The parallel extraction device employs the parallel extraction method for cold-state blade profiles of composite material fan blades as described above. The parallel extraction device includes:

[0060] The input module is used to input the guide nodes and surface elements of the cold finite element model;

[0061] The allocation module is used to determine the number of parallel computing cores based on the number of boot nodes, distribute the boot nodes equally, and have the main process send the equally distributed boot nodes and surface nodes to each child process.

[0062] The calculation module is used to run various subprocesses to execute search algorithms and determine all nodes in the section where each guiding node is located;

[0063] The output module is used to run each subprocess to send the nodes of each section of its own process to the main process. The main process then merges them and outputs the cold air profile according to the section.

[0064] The present invention also provides an electronic device, comprising: a processor and a memory, wherein the memory stores a program or instructions executable on the processor, the program or instructions being executed by the processor to implement the parallel extraction method for cold-state blade profiles of composite material fan blades as described above.

[0065] The present invention relates to a parallel extraction method, apparatus, and electronic device for cold-state blade profiles of composite material fan blades. These methods and devices are designed based on the characteristics of composite material fan blades with metal-reinforced edges. They can automatically perform cold-state blade profile extraction, improve computational efficiency, reduce the probability of errors, and enhance design efficiency.

[0066] The present invention relates to a parallel extraction method, apparatus, and electronic device for cold-state blade profile of composite material fan blades. By utilizing parallel computing technology, it is possible to process multiple computing tasks simultaneously, significantly shortening the computing time. Since the calculation of the cold-state blade profile involves a large amount of finite element analysis and data processing, parallel processing can effectively utilize computing resources and improve overall computing efficiency.

[0067] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A method for parallel extraction of cold-state blade profile of composite fan blades, characterized in that, The parallel extraction method includes the following steps: S1, Input guide node and surface elements of cold finite element model; S2. Based on the number of boot nodes, determine the number of parallel computing cores, distribute the boot nodes equally, and have the main process send the equally distributed boot nodes and surface nodes to each child process; S3. Each subprocess executes the search algorithm to determine all nodes in the section where each guiding node is located; S4. Each child process sends the nodes of each section of its own process to the main process. The main process merges them and outputs the cold air profile according to the section.

2. The method for parallel extraction of cold-state blade profile of composite fan blades as described in claim 1, characterized in that, Step S1 includes the following steps: S 11 Determine the engine analysis state point for cold and hot state analysis; S 12 Regarding step S 11 Based on the determined analysis state point, computational fluid dynamics aerodynamic and thermal analyses are performed to obtain the aerodynamic and temperature loads on the blade. S 13 Regarding step S 11 The analysis state point determined in the process and the step S 12 The aerodynamic and temperature loads obtained are used to conduct cold-hot state transformation analysis and obtain the finite element model of the cold airfoil. S 14 Select a series of points along the radial direction as guide nodes to form a node set Ψ; the guide nodes are selected from nodes on a continuous surface; S 15 The surface units are realized by extracting the outer surface units of the volume units, forming a surface unit set Φ and an exclusion unit set Ω.

3. The method for parallel extraction of cold-state blade profile of composite fan blades as described in claim 2, characterized in that, The step S 11 The economic cycle state is used as the design point for the transition between hot and cold states.

4. The method for parallel extraction of cold-state blade profile of composite fan blades as described in claim 1, characterized in that, Step S2 includes the following steps: S 21 Determine the parallel computing subprocesses based on the number of bootstrap nodes; S 22 The main process distributes the bootstrap node and surface node to each child process through the information transfer interface.

5. The method for parallel extraction of cold-state blade profile of composite fan blades as described in claim 4, characterized in that, The step S 22 The boot nodes are stored in an array. The main process packages the node numbers according to the array's storage order and then sends them to each child process. The child processes then form a boot node set. Ψ k k = 1, 2, 3, ...; At the same time, surface nodes and surface cells are sent directly to each child process without being split, and all surface nodes are also sent to each child process.

6. The method for parallel extraction of cold-state blade profile of composite fan blades as described in claim 1, characterized in that, Step S3 includes the following steps: S 31 Each child process traverses its own process's bootstrap node set Ψ k According to node number n yd_i i = 1, 2, 3, ..., determine the face element f in reverse order. yd_j j = 1, 2, 3, 4, with a maximum value of 4, and the corresponding surface element is a quadrilateral element; S 32 For the starting node n yd_1 In surface element f yd_j By arbitrarily selecting a cell, the two edges e passing through that point can be determined. yd_1 and e yd_2 Determine if the other node of the two edges is in the set of guiding nodes Ψ; if not, keep the node; if so, exclude the node and move the other node n. yd_i Add to the set of cross-section points m＝1,2,3,…； S 33 For any subsequent node n yd_i Determine the quadrilateral cell containing the node, and based on the quadrilateral cell, determine the edges containing that node, excluding those containing n. yd_i and The nodes corresponding to the edges of the quadrilateral are defined, and the endpoints of the remaining edge are the set of points to be added to the cross-section. node n yd_i+1 .

7. The method for parallel extraction of cold-state blade profile of composite fan blades as described in claim 1 or 6, characterized in that, In step S3, each subprocess operates independently, and there is no communication between the subprocesses.

8. The method for parallel extraction of cold-state blade profile of composite fan blades as described in claim 1, characterized in that, Step S4 includes the following steps: S 41 The main process communicates with each slave process through an information transmission interface and collects the node sets of each cross-section formed by each slave process. S 42 The main process aggregates the nodes of each section into a cold airfoil node set. And output it.

9. A parallel extraction device for cold-state blade profile of composite material fan blades, characterized in that, The parallel extraction device employs the parallel extraction method for cold-state blade profiles of composite fan blades as described in any one of claims 1-8, and the parallel extraction device comprises: The input module is used to input the guide nodes and surface elements of the cold finite element model; The allocation module is used to determine the number of parallel computing cores based on the number of boot nodes, evenly distribute the boot nodes, and have the main process send the evenly distributed boot nodes and surface nodes to each child process. The calculation module is used to run various subprocesses to execute search algorithms and determine all nodes in the section where each guiding node is located; The output module is used to run each subprocess to send the nodes of each section of its own process to the main process. The main process then merges them and outputs the cold air profile according to the section.

10. An electronic device, characterized in that, The electronic device includes a processor and a memory, the memory storing programs or instructions that can run on the processor, the programs or instructions being executed by the processor to implement the parallel extraction method for cold-state blade profiles of composite material fan blades as described in any one of claims 1-8.

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