CN113723017B - Method and device for determining temperature field of wall surface of rotary disk of aero-engine - Google Patents
Method and device for determining temperature field of wall surface of rotary disk of aero-engine Download PDFInfo
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Abstract
The application provides a method for determining a temperature field of a wall surface of a rotary disk of an aeroengine, which comprises the following steps: constructing a finite element model of the rotating disc assembly, and obtaining an initial temperature field under the conditions of given boundary conditions and initial parameters; dividing the solid wall surface of the disk center of the rotary disk into a plurality of micro-element nodes, and obtaining the temperature of each micro-element node of the solid wall surface of the disk center of the rotary disk and the area of each micro-element node of the solid wall surface; and constructing a first-order differential equation, bringing the temperature and the area of each infinitesimal node into the first-order differential equation for iterative computation, and obtaining the temperature of the solid wall surface of the rotating disk after iteration convergence. According to the method provided by the application, the temperature field of the wall surface of the rotary disk is accurately solved in a flow thermal coupling mode, CFD calculation is not carried out on the fluid, and the influence of thermal balance between the fluid and the solid can be considered, so that the aim of rapidly and iteratively solving the temperature field of the wall surface of the rotary disk is fulfilled, higher calculation accuracy can be ensured, and the aim of rapidly and iteratively solving the temperature field of the wall surface of the rotary disk of the engine can be fulfilled.
Description
Technical Field
The application belongs to the technical field of aero-engine design, and particularly relates to a method for determining a temperature field of a wall surface of a rotating disc of an aero-engine.
Background
The air compressor and the turbine of the aeroengine are both provided with multistage rotary disk structures, blades are arranged on the rotary disk structures, when the temperature of the rotary disks changes, the positions of the blades arranged on the rotary disks in the radial direction can be influenced, the blade tip gaps between the blades and the casing are changed, and the change of the blade tip gaps can lead to the change of the engine performance and influence the safety of the engine.
Important factors determining the temperature field of the wall surface of the rotating disk are the temperature variation of the air flow along the way and the heat balance between the air flow and the wall surface of the rotating disk. The heat balance between the air flow and the wall surface of the rotating disc means that a temperature difference exists between the air flow and the wall surface of the rotating disc along the process, and heat is transferred between the wall surface of the rotating disc and the air flow in a convection heat exchange mode, so that stable balance is finally achieved. This means that the wall of the rotating disk and the temperature of the air flow are simultaneously changing. In the calculation process, not only the change of the air flow temperature, but also the change of the wall surface temperature of the rotating disc are required to be considered, and the two are required to be synchronously changed.
The calculation method of the temperature field of the wall surface of the rotating disc mainly comprises two schemes at present:
one is to consider that there is no change in the temperature along the air flow near the wall of the rotating disk while ignoring the effect of the heat balance. The method is simple to process, the heat balance is not considered, the fluid temperature is directly used as the boundary condition of wall heat exchange to calculate the temperature field, and the method has obvious defects, namely poor calculation accuracy.
And secondly, adopting CFD flow thermal coupling simulation. And the temperature field of the wall surface of the rotating disc is obtained by coupling solving through numerical simulation calculation of the wall surface of the rotating disc and peripheral air flow and comprehensive flow and heat exchange influence. However, the scheme has large calculated amount and low calculation efficiency, is suitable for scientific research, and cannot meet the requirement of rapid iteration in engineering.
Disclosure of Invention
It is an object of the present application to provide a method, apparatus, computing processing device and readable storage medium for determining a temperature field of a rotating disk wall of an aeroengine, to solve or mitigate at least one problem in the background art.
In one aspect, the technical scheme provided by the application is as follows: a method of determining an aircraft engine rotating disk wall temperature field, comprising:
constructing a finite element model of the rotating disc assembly, and obtaining an initial temperature field under the conditions of given boundary conditions and initial parameters;
dividing the solid wall surface of the disk center of the rotary disk into a plurality of micro-element nodes, and obtaining the temperature of each micro-element node of the solid wall surface of the disk center of the rotary disk and the area of each micro-element node of the solid wall surface;
and constructing a first-order differential equation, bringing the temperature and the area of each micro-element node into the first-order differential equation for iterative computation, and obtaining the temperature of the solid wall surface of the rotating disk after iterative convergence.
Further, the initial parameters include an initial heat exchange coefficient and an initial heat exchange temperature.
Further, the first-order differential equation is:
wherein: t (T) f To the local fluid temperature, T s For boundary surface temperature, s is the relative distance along the boundary surface, T pu To raise the temperature, H pu For the absorbed heat, A is the heat exchange area, W is the mass flow rate of the disk core airflow, C p And h is the heat capacity and h is the heat exchange coefficient.
On the other hand, the technical scheme provided by the application is as follows: an apparatus for determining a temperature field of a wall surface of a rotating disk of an aircraft engine, comprising:
the initial calculation module is used for constructing a finite element model of the rotating disc assembly and obtaining an initial temperature field under the condition of given boundary conditions and initial parameters;
the parameter acquisition module is used for dividing the solid wall surface of the disc center of the rotary disc into a plurality of micro-element nodes and acquiring the temperature of each micro-element node of the solid wall surface of the disc center of the rotary disc and the area of each micro-element node of the solid wall surface;
and the iterative calculation module is used for constructing a first-order differential equation, bringing the temperature and the area of each micro-element node into the first-order differential equation for iterative calculation, and obtaining the temperature of the solid wall surface of the rotating disk after iteration convergence.
Further, the initial parameters include an initial heat exchange coefficient and an initial heat exchange temperature.
Further, the first-order differential equation is:
wherein: t (T) f To the local fluid temperature, T s For boundary surface temperature, s is the relative distance along the boundary surface, T pu To raise the temperature, H pu For the absorbed heat, A is the heat exchange area, W is the mass flow rate of the disk core airflow, C p And h is the heat capacity and h is the heat exchange coefficient.
In a third aspect, the present application provides a technical solution that: a computing processing device, comprising:
at least one processor; and
a memory communicatively coupled to the at least one processor;
the memory stores computer instructions executable by the at least one processor, and the at least one processor is capable of implementing the method for determining the temperature field of the rotating disk wall surface of the aeroengine when the computer instructions are executed by the at least one processor.
In a final aspect, the present application provides the following technical solutions: a readable storage medium storing computer instructions for causing the computer to perform the method of determining the aeroengine rotating disk wall temperature field of any of the above.
According to the method provided by the application, the influence of heat balance is considered, the temperature field of the wall surface of the rotary disk is accurately solved in a flow-heat coupling mode, CFD calculation is not carried out on the fluid, and the influence of heat balance between the fluid and the solid can be considered, so that the aim of rapidly and iteratively solving the temperature field of the wall surface of the rotary disk is fulfilled, higher calculation accuracy can be ensured, calculation amount can be saved, and the aim of rapidly and iteratively solving the temperature field of the wall surface of the rotary disk of the engine is fulfilled.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a flow chart of a method of determining the temperature of a rotating disk wall of an aircraft engine according to the present application.
FIG. 2 is a schematic illustration of a typical flow scenario of an aircraft engine rotating disk core position temperature field.
Fig. 3 is a schematic diagram of an apparatus for determining a temperature field of a rotating disk wall surface of an aeroengine according to the present application.
Fig. 4 is a schematic structural diagram of a computer system of a server according to an embodiment of the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
As shown in fig. 1, the method for determining the temperature field of the wall surface of the rotating disk of the aero-engine provided by the application comprises the following steps:
firstly, establishing a finite element model of a rotating disc assembly, and obtaining an initial temperature field under initial parameters and boundary conditions of a preliminarily given rotating disc.
Boundary conditions are heat exchange coefficient and heat exchange temperature, and the parts of the rotating disc assembly, which are contacted with the gas, are respectively arranged. According to the overall temperature level of the rotating disc, an initial value (initial value, namely heat exchange coefficient and heat exchange temperature under boundary conditions, which are determined by test or prior art methods according to the prior art engine with similar structure) is given.
And then dividing the solid wall surface of the disk center of the rotary disk into a plurality of micro-element nodes, and obtaining the temperature of each micro-element node of the solid wall surface of the disk center of the rotary disk and the area of each micro-element node of the solid wall surface.
And finally, constructing a first-order differential equation, bringing the temperature and the area of each micro-element node into the first-order differential equation for iterative computation, and obtaining the temperature of the solid wall surface of the rotating disk after iterative convergence.
A typical flow profile of the temperature field at the center of the rotating disk of the engine is shown in fig. 1, where arrows characterize the flow direction of the gas.
For a rotating disk hub boundary, it is defined herein as a "heat balance line," which means that along the direction of airflow flow of the boundary, fluid may absorb heat from one point on the boundary surface and then transport to another point on the boundary surface. Variation T of fluid temperature along contact boundary f (s) can be solved with a first order differential equation:
wherein: t (T) f To the local fluid temperature, T s Is the solid boundary surface temperature, s is the relative distance along the boundary surface, T pu For (absorbed) temperature rise, H pu For the absorbed heat, A is the heat exchange area, W is the mass flow rate of the disk core airflow, C p And h is the heat capacity and h is the heat exchange coefficient. The heat exchange coefficient is calculated by a heat exchange coefficient criterion formula, and the mass flow of the disc center airflow is given by an air system calculated value. Firstly, calculating the temperature rise dT of the air flow between adjacent microcell units f The total temperature rise (T) of the air flow is obtained after gradual path superposition out -T in )。
The solid boundary surface temperature T is used in the above s An iterative calculation between the solid temperature and the fluid temperature is required.
Taking the local fluid temperature T f And (3) when the average temperature of the inlet and the outlet of the heat balance line is the heat exchange temperature of the disk center of the new round of rotating disk, keeping the heat exchange coefficient unchanged, calculating a temperature field, comparing with the temperature field of the previous round, and judging whether convergence exists or not. If the iteration is converged, the final solid temperature can be obtained after the iteration is converged after the calculation is finished; if the wall temperature is not converged, returning to the previous step, and re-extracting the wall temperature to carry out the next round of calculation.
Referring to fig. 3, there is also provided a device for determining a temperature field of a wall surface of a rotary disk of an aero-engine, including:
the initial calculation module 101 is used for constructing a finite element model of the rotating disc assembly, and giving initial parameters under boundary conditions to obtain an initial temperature field;
the parameter obtaining module 102 is configured to divide a solid wall surface of a disk core of the rotating disk into a plurality of infinitesimal nodes, and obtain a temperature of each infinitesimal node of the solid wall surface of the disk core of the rotating disk and an area of each infinitesimal node of the solid wall surface;
and the iterative computation module 103 is used for constructing a first-order differential equation, bringing the temperature and the area of each micro-element node into the first-order differential equation for iterative computation, and obtaining the temperature of the solid wall surface of the rotating disk after the iteration converges.
In the application, the above-mentioned processes are all implemented in Ansys software, specifically, the initial heat exchange coefficient and the initial heat exchange temperature are input to perform calculation in Ansys, so as to obtain an initial temperature field.
And for the temperature and the area of the micro-element nodes, the configuration files of the temperature calculation formula and the area calculation formula are compiled through APDL language, so that the temperature of each micro-element node of the solid wall surface on the boundary of the heat balance line and the area of a unit between adjacent micro-elements of the solid wall surface on the boundary of the heat balance line can be extracted in ANSYS, and the flow heat coupling iterative solution can be realized by loading the configuration files into Ansys and repeatedly calling the Ansys.
The method and the device provided by the application consider the influence of heat balance, accurately solve the temperature field of the wall surface of the rotary disk in a flow-heat coupling mode, do not perform CFD calculation on the fluid, and can consider the influence of heat balance between the fluid and the solid, so that the aim of quickly and iteratively solving the temperature field of the wall surface of the rotary disk is fulfilled, higher calculation accuracy can be ensured, the calculated amount can be saved, and the aim of quickly and iteratively solving the temperature field of the wall surface of the rotary disk of the engine is fulfilled.
With continued reference to FIG. 4, a schematic diagram of a computer system 600 suitable for use in implementing the server of an embodiment of the present application is shown. The server illustrated in fig. 4 is merely an example, and should not be construed as limiting the functionality and scope of use of the embodiments herein.
As shown in fig. 4, the computer system 200 includes a Central Processing Unit (CPU) 201, which can perform various appropriate actions and processes according to a program stored in a Read Only Memory (ROM) 202 or a program loaded from a storage section 608 into a Random Access Memory (RAM) 203. In the RAM 203, various programs and data required for the operation of the system 600 are also stored. The CPU 201, ROM 202, and RAM 203 are connected to each other through a bus 204. An input/output (I/O) interface 205 is also connected to bus 204.
The following components are connected to the I/O interface 205: an input section 206 including a keyboard, a mouse, and the like; an output portion 207 including a Cathode Ray Tube (CRT), a Liquid Crystal Display (LCD), and the like, and a speaker, and the like; a storage section 208 including a hard disk or the like; and a communication section 209 including a network interface card such as a LAN card, a modem, and the like. The communication section 609 performs communication processing via a network such as the internet. The drive 210 is also connected to the I/O interface 205 as needed. A removable medium 211 such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, or the like is installed on the drive 210 as needed, so that a computer program read out therefrom is installed into the storage section 208 as needed.
In particular, according to embodiments of the present application, the processes described above with reference to flowcharts may be implemented as computer software programs. For example, embodiments of the present application include a computer program product comprising a computer program embodied on a computer readable medium, the computer program comprising program code for performing the method shown in the flowcharts. In such an embodiment, the computer program may be downloaded and installed from a network via the communication portion 209, and/or installed from the removable medium 211. The above-described functions defined in the method of the present application are performed when the computer program is executed by a Central Processing Unit (CPU) 201. It should be noted that the computer readable medium of the present application may be a computer readable signal medium or a computer readable storage medium, or any combination of the two. The computer readable storage medium can be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or a combination of any of the foregoing. More specific examples of the computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the context of this document, a computer readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. In the present application, however, a computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, with computer-readable program code embodied therein. Such a propagated data signal may take any of a variety of forms, including, but not limited to, electro-magnetic, optical, or any suitable combination of the foregoing. A computer readable signal medium may also be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code embodied on a computer readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, fiber optic cable, RF, etc., or any suitable combination of the foregoing.
The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A method of determining a temperature field of a wall surface of a rotating disk of an aircraft engine, comprising:
constructing a finite element model of the rotating disc assembly, and giving initial parameters under boundary conditions to obtain an initial temperature field;
dividing the solid wall surface of the disk center of the rotary disk into a plurality of micro-element nodes, and obtaining the temperature of each micro-element node of the solid wall surface of the disk center of the rotary disk and the area of each micro-element node of the solid wall surface;
construction of first order differential equationT in f To the local fluid temperature, T s For boundary surface temperature, s is the relative distance along the boundary surface, T pu To raise the temperature, H pu For the absorbed heat, A is the heat exchange area, W is the mass flow rate of the disk core airflow, C p And taking the heat capacity, h as a heat exchange coefficient, bringing the temperature and the area of each micro-element node into the first-order differential equation for iterative computation, and obtaining the temperature of the solid wall surface of the rotating disc after iterative convergence.
2. The method for determining a wall temperature field of a rotating disk of an aircraft engine according to claim 1, wherein the initial parameters include an initial heat exchange coefficient and an initial heat exchange temperature.
3. An apparatus for determining a temperature field of a wall surface of a rotating disk of an aircraft engine, comprising:
the initial calculation module is used for constructing a finite element model of the rotating disc assembly, and giving initial parameters under boundary conditions to obtain an initial temperature field;
the parameter acquisition module is used for dividing the solid wall surface of the disc center of the rotary disc into a plurality of micro-element nodes and acquiring the temperature of each micro-element node of the solid wall surface of the disc center of the rotary disc and the area of each micro-element node of the solid wall surface;
an iterative calculation module for constructing a first-order differential equationWherein: t (T) f To the local fluid temperature, T s For boundary surface temperature, s is the relative distance along the boundary surface, T pu To raise the temperature, H pu For the absorbed heat, A is the heat exchange area, W is the mass flow rate of the disk core airflow, C p And h is a heat exchange coefficient, the temperature and the area of each micro-element node are brought into the first-order differential equation for iterative computation, and the temperature of the solid wall surface of the rotating disk is obtained after the iterative convergence.
4. The apparatus for determining a wall temperature field of an aircraft engine rotating disk according to claim 1, wherein the initial parameters include an initial heat exchange coefficient and an initial heat exchange temperature.
5. A computing processing device, wherein the computing processing device comprises:
at least one processor; and
a memory communicatively coupled to the at least one processor;
wherein the memory stores computer instructions executable by the at least one processor, which when executed by the at least one processor, implement the method of determining a temperature field of a rotating disk wall of an aircraft engine as claimed in any one of claims 1-2.
6. A readable storage medium, characterized in that the readable storage medium stores computer instructions for causing the computer to implement the method of determining the temperature field of the wall surface of the rotating disk of an aeroengine according to any of claims 1-2 when executed.
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