CN116818339A - Method, device and equipment for determining heat insulation wall temperature of disc cavity - Google Patents
Method, device and equipment for determining heat insulation wall temperature of disc cavity Download PDFInfo
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Abstract
The embodiment of the disclosure provides a method, a device and equipment for determining the heat insulation wall temperature of a disc cavity. The method comprises the following steps: acquiring working condition information and attribute information of a disc cavity to be determined at a preset core position; according to the working condition information and the attribute information, determining the circumferential speed of the turntable to be determined at a preset core position; and determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judgment condition. The heat insulation wall temperature is determined by acquiring the working condition information and the attribute information of the disc cavity to be determined at the preset core position on the static casing, a foundation is provided for determining the heat insulation wall temperature, the operation is simple, the safety is high, and the technical difficulty of experiments is reduced. The heat insulation wall temperature is determined by combining the working condition information and the attribute information with a circumferential speed determination formula and an airflow temperature determination formula, so that the heat exchange coefficient and the heat insulation wall temperature are obtained simultaneously in one experiment, the time cost of the experiment is reduced, and the determination efficiency of the heat insulation wall temperature is improved.
Description
Technical Field
The invention relates to the technical field of rotating disc cavities of aeroengines, in particular to a method, a device and equipment for determining the heat insulation wall temperature of a disc cavity.
Background
The rotary disk cavity is an important component of an air system of the aero-engine, and a large number of rotary disk cavity structures exist in the pre-rotation air supply system, the rim seal and the air compressor. The research on the flow heat exchange characteristics in the rotating disc cavity of the aeroengine has important significance for improving the performance, the service life and the reliability of the engine.
Determining the heat exchange coefficient firstly obtains clear heat exchange temperature. In the experimental study of the flow heat exchange of the rotating disc cavity, the rotating disc drives the air flow to rotate together, and the rotating disc 'senses' the relative total temperature of the air flow. In prior studies of rotating disk cavities, the rotational speed of the disk was typically below 3000rpm, the relative speed of the air flow to the disk was low, and the main flow temperature and the relative total temperature of the disk and air flow were nearly equal. In the cavity of the high-speed rotating disc, the relative speed between the air flow and the rotating disc is high, and the relative total temperature is selected as the heat exchange temperature with the disc surface. At the same time, the temperature insulation wall temperature of the air flow stagnation to the disk surface is lower than the relative total temperature due to the viscous dissipation effect of the air flow. The current adiabatic wall temperature can be obtained by a method of irradiating an adiabatic wall surface by a thermal infrared imager.
However, the mode needs to perform a heat exchange coefficient experiment and a heat exchange temperature experiment respectively, a great deal of time and investment are needed, and meanwhile, the infrared thermal imager is used for measuring, so that the experiment cost is increased remarkably.
Disclosure of Invention
The invention aims to solve the problem that infrared thermal imaging equipment needs to be additionally arranged when the heat insulation wall temperature is determined in the prior art, and provides a method, a device and equipment for determining the heat insulation wall temperature of a disc cavity, wherein the heat insulation wall temperature of the disc cavity can be determined by combining working condition information and attribute information of the disc cavity.
In a first aspect, embodiments of the present disclosure provide a method of determining an adiabatic wall temperature of a disc cavity, the method comprising:
acquiring working condition information and attribute information of a disc cavity to be determined at a preset core position;
according to the working condition information and the attribute information, determining the circumferential speed of the turntable to be determined at a preset core position;
and determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judgment condition.
Optionally, determining, according to the working condition information and the attribute information, the circumferential speed of the turntable to be determined at the preset core position includes:
extracting a rotational flow total temperature value, a total pressure value and a static pressure value in the working condition information;
determining a rotation Mach number at a preset core position according to a preset adiabatic index, a rotational flow total temperature value, a total pressure value and a static pressure value; and determining the circumferential speed of the turntable to be determined at the preset core position according to the rotation Mach number, the preset gas constant and the preset circumferential speed determination formula.
Optionally, the preset core position is a preset radius position of a windward receiver in the turntable to be determined.
Optionally, the preset circumferential speed determination formula is:
wherein ,for circumferential speed +.>For rotational Mach number, k is the adiabatic index, R g Is a gas constant, and T is a static temperature.
Optionally, determining the adiabatic wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judgment condition includes:
comparing the circumferential speed with a preset speed judgment condition;
if the circumferential speed meets the preset speed judging condition, determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity and the preset recovery coefficient;
otherwise, the total rotational flow temperature in the working condition information is used as the heat insulation wall temperature of the disc cavity to be determined.
Optionally, determining the adiabatic wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity and the preset recovery coefficient includes:
determining an air flow temperature according to a circumferential speed, a preset specific heat capacity of a preset pressure and a preset recovery coefficient and a preset air flow temperature determining formula;
and determining the heat insulation wall temperature according to the total rotational flow temperature and the air flow temperature in the working condition information.
Optionally, the airflow temperature determination formula is:
wherein ,Td The air flow temperature is represented, R represents a recovery coefficient, ω represents an angular velocity, R represents a preset radius, and C p Representing the specific heat capacity at constant pressure.
In a second aspect, embodiments of the present disclosure also provide an adiabatic wall temperature determination device for a disc cavity, the device comprising: the information acquisition module is used for acquiring working condition information and attribute information of the disc cavity to be determined at a preset core position;
the speed determining module is used for determining the circumferential speed of the turntable to be determined at the preset core position according to the working condition information and the attribute information;
and the wall temperature determining module is used for determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judging conditions.
In a third aspect, embodiments of the present disclosure further provide an electronic device, including:
at least one processor; and
a memory communicatively coupled to the at least one processor; wherein,
when the memory stores a computer program executable by the at least one processor, the computer program is executable by the at least one processor to enable the at least one processor to perform an adiabatic wall temperature determination device of a disc cavity as in any embodiment of the present disclosure.
In a fourth aspect, embodiments of the present disclosure provide a computer readable storage medium having stored thereon a computer program which when executed by a processor implements an adiabatic wall temperature determination device for a disc cavity as in any of the embodiments of the present disclosure.
It should be understood that the description in this section is not intended to identify key or critical features of the embodiments of the invention or to delineate the scope of the invention. Other features of the present invention will become apparent from the description that follows.
Therefore, the invention has the following beneficial effects:
1. the heat insulation wall temperature is determined by acquiring the working condition information and the attribute information of the disc cavity to be determined at the preset core position on the static casing, a foundation is provided for determining the heat insulation wall temperature, the operation is simple, the safety is high, and the technical difficulty of experiments is reduced.
2. The heat insulation wall temperature is determined by combining the working condition information and the attribute information with a circumferential speed determination formula and an airflow temperature determination formula, so that the heat exchange coefficient and the heat insulation wall temperature are obtained simultaneously in one experiment, the time cost of the heat exchange experiment is reduced, and the determination efficiency of the heat insulation wall temperature is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a method for determining the adiabatic wall temperature of a disc cavity according to a first embodiment of the present invention;
FIG. 2 is a schematic diagram of a rotating-stationary disc chamber experiment table in a method for determining a heat insulation wall temperature of a disc chamber according to an embodiment of the present invention;
FIG. 3 is a flow chart of a method for determining the adiabatic wall temperature of a disc cavity according to a second embodiment of the present invention;
FIG. 4 is a graph showing the experimental results of directly measuring the adiabatic wall temperature and the numerical calculation according to the second embodiment of the present invention;
FIG. 5 is a schematic view of a flow structure of a rotating-stationary disc chamber according to a second embodiment of the present invention;
FIG. 6 is an exemplary graph of velocity profile in a rotor-stator disc cavity provided in accordance with a second embodiment of the present invention;
FIG. 7 is a comparative graph of directly measuring adiabatic wall temperature obtained by measuring absolute parameters of air flow in accordance with a second embodiment of the present invention;
FIG. 8 is a schematic view showing a construction of a heat-insulating wall temperature determining apparatus for a disk chamber according to a third embodiment of the present invention;
fig. 9 is a schematic structural diagram of an electronic device according to a fourth embodiment of the present invention.
In the figure: 1. the device comprises a rotating shaft 2, a heat insulating material 3, a titanium alloy rotating disc 4, a static casing 5, a rotational flow total temperature measuring point, a rotational flow total pressure measuring point and a static pressure measuring point which are arranged at different circumferential positions with the same radius r.
Detailed Description
In order that those skilled in the art will better understand the present invention, a technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in which it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present invention without making any inventive effort, shall fall within the scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and the claims of the present invention and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that the embodiments of the invention described herein may be implemented in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
Example 1
Fig. 1 is a flowchart of a method for determining a heat-insulating wall temperature of a disc cavity according to an embodiment of the present invention, where the embodiment is applicable to determining a heat-insulating wall temperature of a disc cavity during an experiment. The method may be performed by an adiabatic wall temperature determination device for a disc cavity provided by embodiments of the present disclosure, which may be implemented in software and/or hardware, and may be generally integrated in an electronic device. The method of the embodiment of the disclosure specifically comprises the following steps:
s110, acquiring working condition information and attribute information of the disc cavity to be determined at a preset core position.
In this embodiment, the disk cavity to be determined is understood to be a turntable comprising a rotor-stationary disk cavity, wherein the disk cavity to be determined comprises a rotor and a windward housing (stationary housing), the maximum radius r=250mm of the rotor. In the experimental process, the high-speed motor drives the rotating shaft to drive the turntable to rotate through the coupler. And (5) testing and pasting a heat insulation material on the back surface of the turntable and in the case of the windward side of the turntable for heat insulation treatment.
The preset core position is a position with a preset radius (r for example) of a windward receiver in the turntable to be determined. Static pressure measuring points, rotational flow total pressure measuring points and rotational flow total temperature measuring points are arranged at different circumferential positions of the radius r of the static casing. The distance between the probe of the rotational flow total temperature and total pressure measuring point and the inner surface of the static casing is 3mm, and the direction is opposite to the circumferential speed direction of the airflow.
In this embodiment, the operating condition information may be understood as being obtained by measurement, and includes, for example, a total rotational flow pressure value, a total pressure value, a static pressure value, and the like. The attribute information may include a disc cavity radius, etc.
Specifically, measuring points can be arranged at different circumferential positions at the same radius r on the static casing in advance, and the total temperature, total pressure and static pressure parameters of the rotational flow can be measured. The total temperature probe and the total pressure probe pass through a round hole with the diameter of 2mm on the static casing, so that the position of the hole coincides with the position of the measuring point, and the position of the probe is 3mm away from the inner surface of the static casing and faces the circumferential speed direction of the airflow. The processor can acquire rotational flow total pressure value, total pressure, static pressure value and the like of the disc cavity to be determined at a preset core position through the total temperature probe and the total pressure probe as working condition information, and can acquire disc cavity radius and the like input in advance by related personnel in corresponding storage media as attribute information.
In order to facilitate understanding of the test bed structure of the present solution, a schematic diagram of a rotating-static disc chamber test bed structure is provided, fig. 2 is a schematic diagram of a rotating-static disc chamber test bed structure in a method for determining a heat insulation wall temperature of a disc chamber according to an embodiment of the present invention, and as shown in fig. 2, 1 is a rotating shaft, 2 is a heat insulation material, 3 is a titanium alloy turntable, 4 is a static casing, 5 is a rotational flow total temperature measuring point, a rotational flow total pressure measuring point, and a static pressure measuring point which are installed at different circumferential positions with a radius r.
S120, according to the working condition information and the attribute information, determining the circumferential speed of the turntable to be determined at the preset core position.
Specifically, the processor can determine the circumferential speed of the turntable to be determined at the preset core position according to the working condition information and the attribute information through corresponding calculation formulas.
S130, determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judgment condition.
Specifically, the processor may compare the circumferential speed with a preset speed judgment condition, and when the airflow speed is low, the dynamic temperature is almost negligible, and when the airflow speed is high, the static temperature is equal to the total temperature, and when the airflow speed is high, the adiabatic wall temperature can be determined by the circumferential speed, the preset pressure specific heat capacity and the preset recovery coefficient through corresponding calculation formulas.
According to the technical scheme, the working condition information and the attribute information of the disc cavity to be determined at the preset core position are obtained; according to the working condition information and the attribute information, determining the circumferential speed of the turntable to be determined at a preset core position; and determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judgment condition. The heat insulation wall temperature is determined by acquiring the working condition information and the attribute information of the disc cavity to be determined at the preset core position on the static casing, a foundation is provided for determining the heat insulation wall temperature, the operation is simple, the safety is high, and the technical difficulty of experiments is reduced. The heat insulation wall temperature is determined by combining the working condition information and the attribute information with a circumferential speed determination formula and an airflow temperature determination formula, so that the heat exchange coefficient and the heat insulation wall temperature are obtained simultaneously in one experiment, the time cost of the experiment is reduced, and the determination efficiency of the heat insulation wall temperature is improved.
Example two
Fig. 3 is a flowchart of a method for determining a heat insulation wall temperature of a disc cavity according to a second embodiment of the present invention, where the method according to the embodiment of the present disclosure specifically includes:
s210, acquiring working condition information and attribute information of the disc cavity to be determined at a preset core position.
S220, extracting a rotational flow total temperature value, a total pressure value and a static pressure value in the working condition information.
S230, determining the rotation Mach number at the preset core position according to the preset adiabatic index, the rotational flow total temperature value, the total pressure value and the static pressure value.
Specifically, the rotational Mach number can be calculated by the following formula:
wherein, the total rotational flow pressure P * And static pressure P, the rotating Mach number of the radius position of the core region r of the disc cavity can be obtained through the following formula
wherein ,for circumferential speed +.>For rotational Mach number, k is the adiabatic index, R g Is a gas constant, and T is a static temperature.
S250, comparing the circumferential speed with a preset speed judgment condition.
In this embodiment, the preset speed judgment condition may be understood as a set air flow temperature determination condition, and judgment may be performed by means of a circumferential speed threshold.
Specifically, the processor may compare the circumferential speed with a preset speed judgment condition, and determine a comparison result.
And S260, if the circumferential speed meets the preset speed judging condition, determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity and the preset recovery coefficient.
Specifically, if the circumferential speed is greater than a preset circumferential speed threshold, the circumferential speed is considered to satisfy a preset speed judgment condition, and then the adiabatic wall temperature of the disc cavity to be determined is determined according to the circumferential speed, a preset pressure specific heat capacity and a preset recovery coefficient.
Further, the step of determining the adiabatic wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, and the preset recovery coefficient may include:
a1, determining an airflow temperature according to a circumferential speed, a preset pressure specific heat capacity and a preset recovery coefficient and a preset airflow temperature determining formula.
Wherein, the airflow temperature determination formula is:
wherein ,Td Represents the air flow temperature, ω represents the angular velocity, r represents the preset radius, C p Represents constant pressure specific heat capacity, R represents recovery coefficient, and under laminar flow condition, the recovery coefficient takes Pr 1/2 The method comprises the steps of carrying out a first treatment on the surface of the Under turbulent flow condition, pr is taken 1/3 。
b1, determining the heat insulation wall temperature according to the total rotational flow temperature and the air flow temperature in the working condition information.
It should be noted that the adiabatic wall temperature is the temperature closest to the wall air flow, i.e., the heat exchange temperature for convective heat exchange with the wall. The turntable drives the air flow to rotate together, and the turntable 'senses' the relative temperature of the air flow. The relative velocity of the gas stream may not be entirely converted to the relative total temperature of the gas stream. Therefore, the adiabatic wall temperature can be obtained by subtracting the total temperature of the air flow from the unrecovered air flow temperature.
Specifically, the processor may subtract the total temperature of the swirling flow from the moving temperature of the air flow to obtain the adiabatic wall temperature.
By way of example, the adiabatic wall temperature may be determined by the following equation:
wherein ,T* Is the total temperature of the rotational flow.
And S270, otherwise, taking the total rotational flow temperature in the working condition information as the heat insulation wall temperature of the disc cavity to be determined.
Specifically, when the wind direction speed does not meet the preset speed judgment condition, the processor can use the total rotational flow temperature in the working condition information as the heat insulation wall temperature of the disc cavity to be determined.
According to the technical scheme, the working condition information and the attribute information of the disc cavity to be determined at the preset core position are obtained; according to the working condition information and the attribute information, determining the circumferential speed of the turntable to be determined at a preset core position; and determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judgment condition. The heat insulation wall temperature is determined by acquiring the working condition information and the attribute information of the disc cavity to be determined at the preset core position on the static casing, a foundation is provided for determining the heat insulation wall temperature, the operation is simple, the safety is high, and the technical difficulty of experiments is reduced. The heat insulation wall temperature is determined by combining the working condition information and the attribute information with a circumferential speed determination formula and an airflow temperature determination formula, so that the heat exchange coefficient and the heat insulation wall temperature are obtained simultaneously in one experiment, the time cost of the experiment is reduced, and the determination efficiency of the heat insulation wall temperature is improved.
For the convenience of understanding the flow field of the air flow in the disc cavity at different rotation speeds in this solution, an exemplary diagram is shown in fig. 5, and fig. 5 is a schematic flow structure diagram of the rotating-static disc cavity according to the second embodiment of the present invention, where fig. 5 is a flow field diagram of the air flow in the rotating-static disc cavity at 9000 rpm. It can be seen from the figure that after the air flow enters the disc cavity, a larger vortex is formed in the middle of the whole disc cavity, called the core region. In the core region, the airflow mainly flows in the circumferential direction, and the airflow circumferential velocity is large.
For the sake of convenience of understanding the speed distribution in the disc cavity of the present embodiment, an exemplary graph of speed distribution in the rotating-stationary disc cavity is shown in fig. 6, and the distribution of the non-dimensional circumferential speed, the non-dimensional radial speed, and the non-dimensional axial speed of the air flow at the radius r at 9000rpm in the axial direction of the disc cavity is shown in fig. 6. As can be seen from the figure, the radial and axial velocity of the air flow in the disc cavity is almost zero. In the experiment, static pressure is arranged by arranging the method described in fig. 2 at different radial positions, and the circumferential speed of the airflow is obtained by rotational flow total temperature and total pressure measuring points.
Illustratively, to verify the accuracy of the implementation described above. Fig. 6 is a graph comparing the experimental results of directly measuring the adiabatic wall temperature with the numerical calculation according to the second embodiment of the present invention, since there is no theoretical calculation formula of the adiabatic wall temperature in the turntable-stator plate cavity. Therefore, according to the definition of the adiabatic wall temperature, the adiabatic wall temperature of the turntable is directly measured by the thermal infrared imager on the basis of the existing experiment table and is compared with the CFD numerical calculation result. The comparison result is shown in fig. 6, and it can be seen from the graph that the deviation between the calculation result and the experimental result is small. At 9000rpm, the deviation of the two at radius r=240 mm is maximum, about 1.4k, and the deviation of the rest radius positions is within 1 k. The experimental results of the adiabatic wall temperature obtained by direct measurement are also reliable.
Fig. 7 is a comparative graph of directly measuring the insulation wall temperature obtained by measuring the absolute parameter of the air flow according to the second embodiment of the present invention, and the comparative result of the insulation wall temperature obtained by directly measuring the insulation wall temperature and the absolute parameter of the air flow is shown in fig. 7. As is clear from the figures, the adiabatic wall temperature at the two radii increases and tends to agree with each other as the experimental time progresses. The deviation between the two is small, and the deviation between the two is about 0.5 k.
Example III
Fig. 8 is a schematic structural diagram of a device for determining a heat insulation wall temperature of a disc cavity according to a third embodiment of the present invention. The apparatus may be implemented in software and/or hardware and may generally be integrated in an electronic device for performing the method. As shown in fig. 8, the apparatus includes: an information acquisition module 310, a speed determination module 320, and a wall temperature determination module 330.
The information obtaining module 310 is configured to obtain working condition information and attribute information of the disc cavity to be determined at a preset core position; the speed determining module 320 is configured to determine, according to the working condition information and the attribute information, a circumferential speed of the turntable to be determined at a preset core position; the wall temperature determining module 330 is configured to determine an adiabatic wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient, and the preset speed judging condition.
Further, the speed determining module 320 is specifically configured to:
extracting a rotational flow total temperature value, a total pressure value and a static pressure value in the working condition information;
determining a rotation Mach number at a preset core position according to a preset adiabatic index, a rotational flow total temperature value, a total pressure value and a static pressure value; and determining the circumferential speed of the turntable to be determined at the preset core position according to the rotation Mach number, the preset gas constant and the preset circumferential speed determination formula.
The preset circumferential speed determination formula is as follows:
wherein ,for circumferential speed +.>For rotational Mach number, k is the adiabatic index, R g Is a gas constant, and T is a static temperature.
Further, the wall temperature determination module 330 includes:
a first determination unit configured to;
the condition comparison unit is used for comparing the circumferential speed with a preset speed judgment condition;
the second determining unit is used for determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity and the preset recovery coefficient if the circumferential speed meets the preset speed judging condition;
and the third determining unit is used for taking the total rotational flow temperature in the working condition information as the heat insulation wall temperature of the disc cavity to be determined.
Further, the second determining unit may be specifically configured to:
determining an air flow temperature according to a circumferential speed, a preset specific heat capacity of a preset pressure and a preset recovery coefficient and a preset air flow temperature determining formula;
and determining the heat insulation wall temperature according to the total rotational flow temperature and the air flow temperature in the working condition information.
Wherein, the airflow temperature determination formula is:
wherein ,Td The air flow temperature is represented, R represents a recovery coefficient, ω represents an angular velocity, R represents a preset radius, and C p Representing the specific heat capacity at constant pressure.
According to the technical scheme, the working condition information and the attribute information of the disc cavity to be determined at the preset core position are obtained; according to the working condition information and the attribute information, determining the circumferential speed of the turntable to be determined at a preset core position; and determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judgment condition. The heat insulation wall temperature is determined by acquiring the working condition information and the attribute information of the disc cavity to be determined at the preset core position on the static casing, a foundation is provided for determining the heat insulation wall temperature, the operation is simple, the safety is high, and the technical difficulty of experiments is reduced. The heat insulation wall temperature is determined by combining the working condition information and the attribute information with a circumferential speed determination formula and an airflow temperature determination formula, so that the heat exchange coefficient and the heat insulation wall temperature are obtained simultaneously in one experiment, the time cost of the experiment is reduced, and the determination efficiency of the heat insulation wall temperature is improved.
The device for determining the heat-insulating wall temperature of the disc cavity provided by the embodiment of the invention can be used for executing the method for determining the heat-insulating wall temperature of the disc cavity provided by any embodiment of the invention, and has the corresponding functional modules and beneficial effects of the executing method.
Example IV
Fig. 9 is a schematic structural diagram of an electronic device 400 according to a fourth embodiment of the present invention. The electronic device in the embodiment of the disclosure may be a device corresponding to a back-end service platform of an application program, and may also be a mobile terminal device on which an application program client is installed. In particular, the electronic device may include, but is not limited to, mobile terminals such as mobile phones, notebook computers, digital broadcast receivers, PDAs (personal digital assistants), PADs (tablet computers), PMPs (portable multimedia players), car terminals (e.g., car navigation terminals), and the like, and stationary terminals such as digital TVs, desktop computers, and the like. The electronic device shown in fig. 9 is merely an example, and should not impose any limitations on the functionality and scope of use of embodiments of the present disclosure.
As shown in fig. 9, the electronic device 400 may include a processing means (e.g., a central processing unit, a graphics processor, etc.) 401, which may perform various appropriate actions and processes according to a program stored in a Read Only Memory (ROM) 402 or a program loaded from a storage means 408 into a Random Access Memory (RAM) 403. In the RAM 403, various programs and data necessary for the operation of the electronic device 400 are also stored. The processing device 401, the ROM 402, and the RAM 403 are connected to each other by a bus 404. An input/output (I/O) interface 405 is also connected to bus 404.
In general, the following devices may be connected to the I/O interface 405: input devices 406 including, for example, a touch screen, touchpad, keyboard, mouse, camera, microphone, accelerometer, gyroscope, etc.; an output device 407 including, for example, a Liquid Crystal Display (LCD), a speaker, a vibrator, and the like; storage 408 including, for example, magnetic tape, hard disk, etc.; and a communication device 409. The communication means 409 may allow the electronic device 400 to communicate with other devices wirelessly or by wire to exchange data. While fig. 3 shows an electronic device 400 having various means, it is to be understood that not all of the illustrated means are required to be implemented or provided. More or fewer devices may be implemented or provided instead.
In particular, according to embodiments of the present disclosure, the processes described above with reference to flowcharts may be implemented as computer software programs. For example, embodiments of the present disclosure include a computer program product comprising a computer program embodied on a non-transitory computer readable medium, the computer program comprising program code for performing the method shown in the flow chart. In such an embodiment, the computer program may be downloaded and installed from a network via communications device 409, or from storage 408, or from ROM 402. The above-described functions defined in the methods of the embodiments of the present disclosure are performed when the computer program is executed by the processing device 401.
It should be noted that the computer readable medium described in the present disclosure 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 disclosure, 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 disclosure, however, the computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, with the 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: electrical wires, fiber optic cables, RF (radio frequency), and the like, or any suitable combination of the foregoing.
In some implementations, the clients, servers may communicate using any currently known or future developed network protocol, such as HTTP (HyperText Transfer Protocol ), and may be interconnected with any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include a local area network ("LAN"), a wide area network ("WAN"), the internet (e.g., the internet), and peer-to-peer networks (e.g., ad hoc peer-to-peer networks), as well as any currently known or future developed networks.
The computer readable medium may be contained in the electronic device; or may exist alone without being incorporated into the electronic device.
The computer readable medium carries one or more programs which, when executed by the electronic device, cause the electronic device internal process to perform: when the state of the cutter in the cutting process meets the recording condition, changing the control mode of the cutter, and generating a first G1 code block in a preset G code file; controlling the cutter to move according to a control mode, and determining special point position information of the cutter in the moving process; generating a corresponding G1 code block in the G code file according to the special point location information; when the moving state of the cutter meets the ending condition, acquiring the generated G code file to complete the track record of the cutter; and when the cutter meets the position recovery condition, controlling the cutter to recover the position according to the generated G code file.
Computer program code for carrying out operations of the present disclosure may be written in one or more programming languages, including, but not limited to, an object oriented programming language such as Java, smalltalk, C ++ and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The program code may execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer or entirely on the remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any kind of network, including a Local Area Network (LAN) or a Wide Area Network (WAN), or may be connected to an external computer (for example, through the Internet using an Internet service provider).
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 disclosure. 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 units involved in the embodiments of the present disclosure may be implemented by means of software, or may be implemented by means of hardware. Wherein the names of the units do not constitute a limitation of the units themselves in some cases.
The functions described above herein may be performed, at least in part, by one or more hardware logic components. For example, without limitation, exemplary types of hardware logic components that may be used include: a Field Programmable Gate Array (FPGA), an Application Specific Integrated Circuit (ASIC), an Application Specific Standard Product (ASSP), a system on a chip (SOC), a Complex Programmable Logic Device (CPLD), and the like.
In the context of this disclosure, a machine-readable medium may be a tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. The machine-readable medium may be a machine-readable signal medium or a machine-readable storage medium. The machine-readable medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. More specific examples of a machine-readable storage medium would include an electrical connection based on 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.
The foregoing description is only of the preferred embodiments of the present disclosure and description of the principles of the technology being employed. It will be appreciated by persons skilled in the art that the scope of the disclosure referred to in this disclosure is not limited to the specific combinations of features described above, but also covers other embodiments which may be formed by any combination of features described above or equivalents thereof without departing from the spirit of the disclosure. Such as those described above, are mutually substituted with the technical features having similar functions disclosed in the present disclosure (but not limited thereto).
Moreover, although operations are depicted in a particular order, this should not be understood as requiring that such operations be performed in the particular order shown or in sequential order. In certain circumstances, multitasking and parallel processing may be advantageous. Likewise, while several specific implementation details are included in the above discussion, these should not be construed as limiting the scope of the present disclosure. Certain features that are described in the context of separate embodiments can also be implemented in combination in a single embodiment. Conversely, various features that are described in the context of a single embodiment can also be implemented in multiple embodiments separately or in any suitable subcombination.
Although the subject matter has been described in language specific to structural features and/or methodological acts, it is to be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or acts described above. Rather, the specific features and acts described above are example forms of implementing the claims.
Claims (10)
1. A method for determining the adiabatic wall temperature of a disc cavity, comprising the steps of:
acquiring working condition information and attribute information of a disc cavity to be determined at a preset core position;
according to the working condition information and the attribute information, determining the circumferential speed of the turntable to be determined at the preset core position;
and determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judging condition.
2. The method for determining the adiabatic wall temperature of a disc cavity according to claim 1, wherein determining the circumferential speed of the turntable to be determined at the preset core position according to the operating condition information and the attribute information includes:
extracting the rotational flow total temperature value, the total pressure value and the static pressure value in the working condition information;
determining a rotational Mach number at the preset core position according to a preset adiabatic index, the rotational flow total temperature value, the total pressure value and the static pressure value;
and determining the circumferential speed of the turntable to be determined at the preset core position according to the rotation Mach number, a preset gas constant and a preset circumferential speed determination formula.
3. The method for determining the adiabatic wall temperature of a disc cavity as claimed in claim 1, wherein the preset core position is a preset radius position of a windward receiver in the turntable to be determined.
4. A method of determining the adiabatic wall temperature of a disc cavity as claimed in claim 2, wherein the predetermined circumferential velocity determination formula is:
wherein ,for the peripheral speed +.>For the rotational Mach number, k is the adiabatic index, R g And T is the static temperature for the gas constant.
5. The method according to claim 1, wherein determining the adiabatic wall temperature of the disc chamber to be determined based on the circumferential velocity, a preset pressure specific heat capacity, a preset recovery coefficient, and a preset velocity judgment condition comprises:
comparing the circumferential speed with the preset speed judgment condition;
if the circumferential speed meets the preset speed judging condition, determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity and the preset recovery coefficient;
otherwise, taking the total rotational flow temperature in the working condition information as the heat insulation wall temperature of the disc cavity to be determined.
6. The method according to claim 5, wherein determining the adiabatic wall temperature of the disc chamber to be determined based on the circumferential velocity, a preset pressure specific heat capacity, and a preset recovery coefficient comprises:
determining an airflow temperature according to the circumferential speed, the preset pressure specific heat capacity and the preset recovery coefficient and a preset airflow temperature determining formula;
and determining the heat insulation wall temperature according to the rotational flow total temperature and the airflow temperature in the working condition information.
7. The method of claim 6, wherein the airflow temperature determination formula is:
wherein ,Td The air flow temperature is represented, R represents a recovery coefficient, ω represents an angular velocity, R represents a preset radius, and C p Representing the specific heat capacity at constant pressure.
8. An adiabatic wall temperature determination device for a disc cavity, comprising:
the information acquisition module is used for acquiring working condition information and attribute information of the disc cavity to be determined at a preset core position;
the speed determining module is used for determining the circumferential speed of the turntable to be determined at the preset core position according to the working condition information and the attribute information;
and the wall temperature determining module is used for determining the heat insulation wall temperature of the disc cavity to be determined according to the circumferential speed, the preset pressure specific heat capacity, the preset recovery coefficient and the preset speed judging conditions.
9. An electronic device, the electronic device comprising:
at least one processor; and
a memory communicatively coupled to the at least one processor; wherein,
the memory stores a computer program executable by the at least one processor to enable the at least one processor to perform the method of claims 1-7.
10. A computer storage medium storing computer instructions for causing a processor to perform the method of claims 1-7 when executed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310639480.5A CN116818339A (en) | 2023-05-31 | 2023-05-31 | Method, device and equipment for determining heat insulation wall temperature of disc cavity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310639480.5A CN116818339A (en) | 2023-05-31 | 2023-05-31 | Method, device and equipment for determining heat insulation wall temperature of disc cavity |
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|---|---|
| CN116818339A true CN116818339A (en) | 2023-09-29 |
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| CN202310639480.5A Pending CN116818339A (en) | 2023-05-31 | 2023-05-31 | Method, device and equipment for determining heat insulation wall temperature of disc cavity |
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| Country | Link |
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| CN (1) | CN116818339A (en) |
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- 2023-05-31 CN CN202310639480.5A patent/CN116818339A/en active Pending
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