Turboprop engine test bed simulation method, device and equipment and storage medium

Abstract

The invention relates to the technical field of engine testing, and discloses a turboprop engine test bed simulation method, device and equipment and a storage medium, and the method comprises the steps: obtaining a turboprop engine test bed geometric model, and replacing a real propeller geometric model with an equivalent disc model in the turboprop engine test bed geometric model; performing parameter setting on the geometric model, wherein the parameter setting comprises setting the boundary condition of the equivalent disc in the geometric model as a fan boundary condition and setting the pressure jump parameter of a fan as a propeller pressure jump value; and performing flow field simulation of the turboprop engine test bed based on the geometric model of the turboprop engine test bed after parameter setting to obtain a propeller air flow simulation value. According to the method, a complex real propeller geometric model with a large number of grid nodes is omitted, computing resources are saved, the evaluation efficiency is improved, and therefore optimization iteration of turboprop engine test bed design is accelerated.

Description

Technical Field

[0001] The present invention relates to the technical field of engine testing, and in particular to a turboprop engine test bench simulation method, device, equipment and storage medium. Background Art

[0002] The turboprop engine test bench (referred to as the propeller bench) is a necessary and key test equipment for the development and production of turboprop engines. A large number of turboprop engine-related test contents are specified in the General Specifications for Aviation Turboprop and Turboshaft Engines (GJB242A). The flow field characteristics inside the propeller bench are directly related to the safety, quality and accuracy of engine tests. The Design Specifications for Aviation Engine Test Benches (GB50454) stipulates the relevant flow fields and aerodynamic parameters. When designing and constructing a propeller bench, it is necessary to use the fluid dynamics (referred to as: CFD) method in advance to analyze and optimize the flow field inside the propeller bench.

[0003] In related technologies, such as Figure 1 As shown, the real propeller geometry model can be used to carry out the flow field analysis inside the propeller platform by using the fluid mechanics method. The specific method is to establish a 1:1 geometry model of the propeller platform (the model contains the real propeller geometry model), and then divide the entire calculation domain into a rotating domain 101 (including the propeller model) and a stationary domain (propeller platform model) to divide the CFD simulation grids respectively. The rotating domain simulates the rotation of the propeller, and the flow field characteristics inside the propeller platform are simulated by this method. When the internal flow field of different propeller working states is required, the propeller (rotating domain) geometry model is replaced and the calculation is iterated again.

[0004] However, the above-mentioned flow field analysis method inside the propeller platform requires drawing the propeller mesh. Due to the complex propeller surface and large changes in airflow, a denser mesh needs to be arranged for simulation, and the number of grid nodes is usually large. During the propeller platform flow field simulation process, the number of grid nodes accounts for more than 60% of the total, which consumes a lot of computing resources. When computing resources are insufficient, CFD simulation is very difficult to carry out. At the same time, in order to carry out a more comprehensive analysis and research, it is necessary to replace different propeller geometric models to repeatedly perform unsteady CFD verification simulations. Therefore, this method is very inefficient and cannot be quickly analyzed and optimized iteratively. Summary of the invention

[0005] In view of this, the present invention provides a turboprop engine test bench simulation method, device, equipment and storage medium to solve the problems of large computing resource consumption and low efficiency of the flow field analysis method inside the turboprop engine test bench.

[0006] In a first aspect, the present invention provides a turboprop engine test bench simulation method, the method comprising:

[0007] Acquire a turboprop engine test bench geometric model, wherein an equivalent disk model is used to replace a real propeller geometric model in the turboprop engine test bench geometric model;

[0008] Setting parameters for the geometric model, the parameter setting comprising: setting the boundary condition of the equivalent disk in the geometric model as the fan boundary condition, and setting the pressure jump parameter of the fan as the propeller pressure jump value;

[0009] The flow field simulation of the turboprop engine test bench is performed based on the geometric model of the turboprop engine test bench after parameter setting to obtain a propeller air flow simulation value.

[0010] In an optional embodiment, the propeller pressure jump value is determined based on the propeller thrust and the propeller disc area.

[0011] In an optional implementation, the calculation formula of the propeller pressure jump value is:

[0012]

[0013] Wherein, ΔP is the propeller pressure jump value, F is the propeller thrust, and A is the propeller disc area.

[0014] In an optional embodiment, after performing flow field simulation of the turboprop engine test bench based on the turboprop engine test bench geometric model after parameter setting and obtaining the propeller air flow simulation value, the method further includes:

[0015] Determine an estimate of propeller air flow based on propeller thrust, propeller disc area, and air density;

[0016] A deviation between the propeller air flow estimation value and the propeller air flow simulation value is obtained.

[0017] In an optional implementation, the propeller air flow estimation value is calculated as follows:

[0018]

[0019] Among them, q m0 is the estimated value of the propeller air flow, ρ is the air density, A is the propeller disc area, and F is the propeller thrust.

[0020] In an optional implementation, the equivalent disk model is an equivalent disk sheet model or an equivalent disk body model.

[0021] In an optional implementation, the parameter setting further includes: setting a rotation speed and a radial speed.

[0022] In a second aspect, the present invention provides a turboprop engine test bench simulation device, the device comprising:

[0023] A model acquisition module, used for acquiring a geometric model of a turboprop engine test bench, wherein an equivalent disk model is used to replace a real propeller geometric model in the turboprop engine test bench geometric model;

[0024] A parameter setting module, used for setting parameters of the turboprop engine test bench geometric model, wherein the parameter setting includes: setting the boundary condition of the equivalent disk in the turboprop engine test bench geometric model as the fan boundary condition, and setting the pressure jump parameter of the fan as the propeller pressure jump value;

[0025] The simulation module is used to simulate the flow field of the turboprop engine test bench based on the geometric model of the turboprop engine test bench after parameter setting, so as to obtain the propeller air flow simulation value.

[0026] In a third aspect, the present invention provides a computer device, comprising: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, and the processor executing the turboprop engine test bench simulation method of the first aspect or any corresponding embodiment thereof by executing the computer instructions.

[0027] In a fourth aspect, the present invention provides a computer-readable storage medium having computer instructions stored thereon, the computer instructions being used to enable a computer to execute the turboprop engine test bench simulation method of the first aspect or any corresponding embodiment thereof.

[0028] In a fifth aspect, the present invention provides a computer program product, comprising computer instructions for causing a computer to execute the turboprop engine test bench simulation method of the first aspect or any corresponding embodiment thereof.

[0029] The turboprop engine test bench simulation method, device, equipment and storage medium provided in the embodiment of the present invention proposes a simulation method for a turboprop engine test bench (referred to as: propeller bench) that can quickly evaluate the propeller bench flow field without the need for a real propeller geometric model. The embodiment of the present invention uses a propeller equivalent disk to simulate the aerodynamic characteristics of the propeller to achieve flow field evaluation inside the propeller bench. The embodiment of the present invention omits the complex real propeller geometric model with a large number of grid nodes, saves computing resources, improves evaluation efficiency, and thus accelerates the optimization iteration of the turboprop engine test bench design. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the related technologies, the drawings required for use in the specific embodiments or the related technical descriptions will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0031] Figure 1 It is a schematic diagram of the propeller platform flow field simulation with a real propeller geometry model;

[0032] Figure 2 is a schematic flow chart of a turboprop engine test bench simulation method according to an embodiment of the present invention;

[0033] Figure 3 is a schematic diagram of a turboprop engine test bench geometric model after a real propeller geometric model is replaced by a propeller equivalent disk model according to an embodiment of the present invention;

[0034] Figure 4 is a schematic diagram of the internal flow field of the propeller platform obtained by using propeller equivalent disk simulation according to an embodiment of the present invention;

[0035] Figure 5 is a schematic diagram of propeller air flow estimation parameters according to an embodiment of the present invention;

[0036] Figure 6 is a structural block diagram of a turboprop engine test bench simulation device according to an embodiment of the present invention;

[0037] Figure 7 It is a schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0038] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0039] According to an embodiment of the present invention, a turboprop engine test bench simulation method embodiment is provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of executable computer instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0040] In this embodiment, a turboprop engine test bench simulation method is provided, which can be used for various computer devices. The turboprop engine test bench (referred to as the turboprop test bench) can be an indoor turboprop engine test bench. Figure 2 is a flow chart of a turboprop engine test bench simulation method according to an embodiment of the present invention. Figure 2 As shown, the process includes the following steps:

[0041] Step S201, obtaining a turboprop engine test bench geometric model, such as Figure 3 As shown, the equivalent disk model 301 is used in the turboprop engine test bench geometric model to replace the real propeller geometric model. The turboprop engine test bench geometric model is a 1:1 fluid mechanics geometric model. The diameter of the equivalent disk model 301 is consistent with the propeller diameter.

[0042] The geometric model of the turboprop engine test bench can be found in the related art and will not be described in detail here. The equivalent disk model is an equivalent disk sheet model or an equivalent disk body model.

[0043] Step S202, setting parameters for the geometric model of the turboprop engine test bench, the parameter setting includes: setting the boundary conditions of the equivalent disk in the geometric model of the turboprop engine test bench to the fan boundary conditions, and setting the pressure jump parameter of the fan to the propeller pressure jump value. The propeller pressure jump value, also known as the propeller pressure jump value, is the pressure jump value after the airflow passes through the propeller. The above-mentioned fan boundary conditions refer to the limitations on the performance and working conditions of the fan under a specific working environment. In an embodiment of the present invention, these limitations mainly involve multiple parameters in fluid dynamics, including pressure, flow, speed, etc. Specifically, in ANSYS Fluent (fluid mechanics simulation software), the fan boundary condition is to achieve the simulation of the fan by a pressure jump without thickness.

[0044] Initial technical indicators such as propeller thrust F, propeller diameter D or flow rate are proposed in the early stage of turboprop engine development. Based on the technical indicators proposed in the early stage, the propeller pressure jump value can be determined. Specifically, the propeller pressure jump value can be determined based on the propeller thrust and the propeller disk area (also called the propeller disk rotation area).

[0045] The calculation formula of the propeller pressure jump value is:

[0046]

[0047] Wherein, ΔP is the propeller pressure jump value, F is the propeller thrust, and A is the propeller disc area.

[0048] In addition, the parameter setting also includes: setting the rotation speed and radial speed as needed. In the embodiment of the present invention, the equivalent disk mainly simulates the axial speed of the propeller. The axial speed refers to the speed at which the propeller pushes the air along the propeller axis. It is one of the key factors in the generation of propeller thrust. When the propeller rotates, it "bites" the surrounding fluid and pushes it backwards, thereby generating forward thrust. In order to accurately simulate the work of the propeller, the embodiment of the present invention also sets the rotation speed and radial speed as needed.

[0049] Step S203, based on the geometric model of the turboprop engine test bench after parameter setting, the flow field simulation of the turboprop engine test bench is performed to obtain the propeller air flow simulation value (such as Figure 4 shown).

[0050] The turboprop engine test bench simulation method provided in this embodiment proposes a simulation method for the turboprop engine test bench (referred to as the propeller bench) that can quickly evaluate the propeller bench flow field without the need for a real propeller geometric model. This method uses a propeller equivalent disk to simulate the propeller aerodynamic characteristics and realize the flow field evaluation inside the propeller bench. This method omits the complex real propeller geometric model with a large number of grid nodes, saves computing resources, improves evaluation efficiency, and thus speeds up the optimization iteration of the turboprop engine test bench design.

[0051] In addition, in the early stages of turboprop engine demonstration and development, when there is no specific propeller model, the turboprop engine test bench simulation method provided in the embodiment of the present invention can be used to analyze and study the propeller flow field and conduct feasibility demonstration in advance, so that the demonstration design and construction of the turboprop engine test bench can be carried out in parallel with the propeller, thereby improving the development efficiency of the turboprop engine.

[0052] In some other optional specific implementations, after performing flow field simulation of the turboprop engine test bench based on the turboprop engine test bench geometric model after parameter setting and obtaining the propeller air flow simulation value, the method further includes:

[0053] like Figure 5 As shown (V0 is the air velocity), the estimated value of propeller air flow is determined based on the propeller thrust F, propeller disc area A and air density;

[0054] A deviation between the propeller air flow estimation value and the propeller air flow simulation value is obtained.

[0055] Specifically, the calculation formula of the propeller air flow estimation value is:

[0056]

[0057] Among them, q m0is the estimated value of the propeller air flow, ρ is the air density (in kg / m 3 ), A is the propeller disc area (m 2 ), F is the propeller thrust (in N).

[0058] Since the velocity field flowing through the propeller disk is not uniform, the actual flow rate may be smaller, and the error is about 10% compared with the simulation of the real propeller geometry model.

[0059] In an embodiment of the present invention, the propeller air flow is estimated based on parameters such as propeller thrust and propeller disc area. The estimated propeller air flow estimation value is then used to check the propeller air flow simulation value simulated by the turboprop engine test bench geometric model. If the deviation is within a certain range, such as 12%, it is considered to be an acceptable deviation. If the deviation exceeds 12%, the propeller air flow simulation value simulated by the test bench geometric model can be corrected based on the propeller air flow estimation value (if the simulated air flow is large, the propeller pressure jump value is reduced; vice versa).

[0060] The embodiments of the present invention have been successfully applied to multiple propeller platforms. By comparing the aerodynamic parameters inside the propeller platforms, the error is within 10%, and the method is practicable.

[0061] In this embodiment, a turboprop engine test bench simulation device is also provided, which is used to implement the above-mentioned embodiments and preferred implementation modes, and the descriptions that have been made will not be repeated. As used below, the term "module" can implement a combination of software and / or hardware of a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceivable.

[0062] This embodiment provides a turboprop engine test bench simulation device, such as Figure 6 As shown, including:

[0063] A model acquisition module 601 is used to acquire a turboprop engine test bench geometric model, in which an equivalent disk model is used to replace a real propeller geometric model;

[0064] A parameter setting module 602 is used to set parameters for the turboprop engine test bench geometric model, wherein the parameter setting includes: setting the boundary condition of the equivalent disk in the turboprop engine test bench geometric model as the fan boundary condition, and setting the pressure jump parameter of the fan as the propeller pressure jump value;

[0065] The simulation module 603 is used to simulate the flow field of the turboprop engine test bench based on the geometric model of the turboprop engine test bench after parameter setting, and obtain a propeller air flow simulation value.

[0066] In some optional embodiments, the propeller pressure jump value is determined based on the propeller thrust and the propeller disc area.

[0067] In some optional implementations, the propeller pressure jump value is calculated as follows:

[0068]

[0069] Wherein, ΔP is the propeller pressure jump value, F is the propeller thrust, and A is the propeller disc area.

[0070] In some optional embodiments, the turboprop engine test bench simulation device further includes:

[0071] an estimation module for determining an estimated value of propeller air flow based on propeller thrust, propeller disc area, and air density;

[0072] The deviation acquisition module is used to obtain the deviation between the propeller air flow estimation value and the propeller air flow simulation value.

[0073] In some optional embodiments, the propeller air flow estimation value is calculated as follows:

[0074]

[0075] Among them, q m0 is the estimated value of the propeller air flow, ρ is the air density, A is the propeller disc area, and F is the propeller thrust.

[0076] In some optional embodiments, the equivalent disk model is an equivalent disk sheet model or an equivalent disk body model.

[0077] In some optional implementations, the parameter setting further includes: setting the rotation speed and the radial speed.

[0078] The further functional description of each of the above modules is the same as that of the above corresponding embodiments and will not be repeated here.

[0079] The turboprop engine test bench simulation device in this embodiment is presented in the form of a functional unit, where the unit refers to an ASIC (Application Specific Integrated Circuit) circuit, a processor and memory that executes one or more software or fixed programs, and / or other devices that can provide the above functions.

[0080] The embodiment of the present invention also provides a computer device having the above Figure 6 The turboprop engine test bench simulation device shown.

[0081] See also Figure 7 , Figure 7 is a schematic diagram of the structure of a computer device provided by an optional embodiment of the present invention, such as Figure 7 As shown, the computer device includes: one or more processors 10, a memory 20, and interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. Various components are connected to each other using different buses for communication, and can be installed on a common mainboard or installed in other ways as needed. The processor can process the instructions executed in the computer device, including instructions stored in or on the memory to display the graphical information of the GUI on an external input / output device (such as, a display device coupled to the interface). In some optional embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories and multiple memories. Similarly, multiple computer devices can be connected, and each device provides some necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Figure 7 A processor 10 is taken as an example.

[0082] The processor 10 may be a central processing unit, a network processor or a combination thereof. The processor 10 may further include a hardware chip. The hardware chip may be a dedicated integrated circuit, a programmable logic device or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general purpose array logic or any combination thereof.

[0083] The memory 20 stores instructions executable by at least one processor 10, so that the at least one processor 10 executes the method shown in the above embodiment.

[0084] The memory 20 may include a program storage area and a data storage area, wherein the program storage area may store an operating system, an application required for at least one function; the data storage area may store data created according to the use of the computer device, etc. In addition, the memory 20 may include a high-speed random access memory, and may also include a non-transient memory, such as at least one disk storage device, a flash memory device, or other non-transient solid-state storage device. In some optional embodiments, the memory 20 may optionally include a memory remotely arranged relative to the processor 10, and these remote memories may be connected to the computer device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0085] The memory 20 may include a volatile memory, such as a random access memory; the memory may also include a non-volatile memory, such as a flash memory, a hard disk or a solid state drive; the memory 20 may also include a combination of the above types of memory.

[0086] The computer device also includes an input device 30 and an output device 40. The processor 10, the memory 20, the input device 30 and the output device 40 may be connected via a bus or other means. Figure 7 The example of connecting through bus is taken in the following.

[0087] The input device 30 can receive input digital or character information, and generate key signal input related to the user settings and function control of the computer device, such as a touch screen, a keypad, a mouse, a track pad, a touch pad, an indicator bar, one or more mouse buttons, a trackball, a joystick, etc. The output device 40 may include a display device, an auxiliary lighting device (e.g., an LED) and a tactile feedback device (e.g., a vibration motor), etc. The above-mentioned display device includes but is not limited to a liquid crystal display, a light emitting diode, a display and a plasma display. In some optional embodiments, the display device can be a touch screen.

[0088] The computer device also includes a communication interface, which is used for the computer device to communicate with other devices or a communication network.

[0089] The embodiment of the present invention also provides a computer-readable storage medium. The method according to the embodiment of the present invention can be implemented in hardware, firmware, or can be implemented as a computer code that can be recorded in a storage medium, or can be implemented as a computer code that is originally stored in a remote storage medium or a non-temporary machine-readable storage medium and will be stored in a local storage medium through a network download, so that the method described herein can be stored in such software processing on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only storage memory, a random access memory, a flash memory, a hard disk or a solid-state hard disk, etc.; further, the storage medium can also include a combination of the above types of memories. It can be understood that a computer, a processor, a microprocessor controller, or programmable hardware includes a storage component that can store or receive software or computer code. When the software or computer code is accessed and executed by a computer, a processor, or hardware, the method shown in the above embodiment is implemented.

[0090] A part of the present invention may be applied as a computer program product, such as a computer program instruction, which, when executed by a computer, can call or provide the method and / or technical solution according to the present invention through the operation of the computer. Those skilled in the art should understand that the existence of the computer program instruction in a computer-readable medium includes, but is not limited to, a source file, an executable file, an installation package file, etc., and accordingly, the way in which the computer program instruction is executed by the computer includes, but is not limited to: the computer directly executes the instruction, or the computer compiles the instruction and then executes the corresponding compiled program, or the computer reads and executes the instruction, or the computer reads and installs the instruction and then executes the corresponding installed program. Here, the computer-readable medium may be any available computer-readable storage medium or communication medium accessible to the computer.

[0091] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A turboprop engine test bench simulation method, characterized in that: The method comprises: Acquiring a turboprop engine test bench geometric model, wherein an equivalent disk model is used to replace a real propeller geometric model in the turboprop engine test bench geometric model; Setting parameters for the geometric model, the parameter setting comprising: setting the boundary condition of the equivalent disk in the geometric model as the fan boundary condition, and setting the pressure jump parameter of the fan as the propeller pressure jump value; The flow field simulation of the turboprop engine test bench is performed based on the geometric model of the turboprop engine test bench after parameter setting to obtain a propeller air flow simulation value.

2. The method according to claim 1, characterized in that: The propeller pressure jump value is determined based on the propeller thrust and the propeller disc area.

3. The method according to claim 2, characterized in that The calculation formula of the propeller pressure jump value is: Wherein, ΔP is the propeller pressure jump value, F is the propeller thrust, and A is the propeller disc area.

4. The method according to claim 1, characterized in that: After the flow field simulation of the turboprop engine test bench is performed based on the turboprop engine test bench geometric model after parameter setting and the propeller air flow simulation value is obtained, the method further includes: Determine an estimate of propeller air flow based on propeller thrust, propeller disc area, and air density; A deviation between the propeller air flow estimation value and the propeller air flow simulation value is obtained.

5. The method according to claim 4, characterized in that The propeller air flow estimation value is calculated as follows: Among them, q m0 is the estimated value of the propeller air flow, ρ is the air density, A is the propeller disc area, and F is the propeller thrust.

6. The method according to claim 1, characterized in that The equivalent disk model is an equivalent disk sheet model or an equivalent disk body model.

7. The method according to claim 1, characterized in that The parameter setting also includes: setting the rotation speed and radial speed.

8. A turboprop engine test bench simulation device, characterized in that: The device comprises: A model acquisition module, used for acquiring a geometric model of a turboprop engine test bench, wherein an equivalent disk model is used to replace a real propeller geometric model in the turboprop engine test bench geometric model; A parameter setting module, used for setting parameters of the turboprop engine test bench geometric model, wherein the parameter setting includes: setting the boundary condition of the equivalent disk in the turboprop engine test bench geometric model as the fan boundary condition, and setting the pressure jump parameter of the fan as the propeller pressure jump value; The simulation module is used to simulate the flow field of the turboprop engine test bench based on the geometric model of the turboprop engine test bench after parameter setting, so as to obtain the propeller air flow simulation value.

9. A computer device, characterized in that: include: A memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the method according to any one of claims 1 to 7 by executing the computer instructions.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a computer to execute the method according to any one of claims 1 to 7.

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