CN220305687U - Automatic control device for air supply temperature of ground test bed of aero-engine - Google Patents
Automatic control device for air supply temperature of ground test bed of aero-engine Download PDFInfo
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- CN220305687U CN220305687U CN202321218433.5U CN202321218433U CN220305687U CN 220305687 U CN220305687 U CN 220305687U CN 202321218433 U CN202321218433 U CN 202321218433U CN 220305687 U CN220305687 U CN 220305687U
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Abstract
The utility model provides an automatic control device for air supply temperature of an aeroengine ground test bed, which comprises the following components: the temperature measuring element is used for collecting the inlet temperature of the aeroengine; the PLC thermocouple expansion module is connected with the temperature measuring element and is used for carrying out A/D conversion on the millivolt signal converted by the temperature measuring element and transmitting the converted digital quantity signal to the PLC CPU module; the PLC CPU module is used for calculating a given value of the thyristor voltage regulating power supply according to the temperature given signal of the upper computer and the digital quantity signal converted by the PLC thermocouple expansion module, and transmitting the given value to the thyristor trigger controller; and the thyristor trigger controller is used for controlling the output power of the electric heater of the aero-engine according to the given value. According to the utility model, the PLC automatic control technology is adopted to realize closed-loop control of the inlet gas temperature of the aeroengine ground test bed engine, so that disturbance caused by external interference and structural parameter change is shielded, and the temperature control precision of the test bed is improved.
Description
Technical Field
The utility model relates to the technical field of automatic control, in particular to an automatic control device for air supply temperature of an aeroengine ground test bed.
Background
The aeroengine is a power device for pushing the aircraft to fly, and different from a power device for a ground and water transport means, the working position of the aeroengine is in the air of thousands of meters. Once a problem occurs in the air, the aircraft loses power, the flying height and speed cannot be maintained, the aircraft cannot complete the task due to light weight, and serious accidents of the aircraft, such as destruction and death, can be caused.
The development and development of aeroengines is a complex comprehensive system project involving multiple disciplines of aerodynamics, engineering thermophysics, heat and mass transfer, mechanical, strength, transmission, sealing, electronics, automatic control, and the like. The aerodynamic, thermal and structural material characteristics inside an aeroengine are so complex that so far a detailed and accurate description cannot be given theoretically, only by means of experiments with actual engines.
The ground test bed of the aero-engine is used as an effective means of an aero-engine working environment simulation experiment, and provides gas with certain temperature and pressure for the aero-engine in a pipeline gas supply mode to simulate the working environment of the engine in different flight states. The heating and pressurizing air inlet system is an important component of the test bed. In order to ensure the test environment, very high requirements are put on the air supply temperature, pressure, flow and the like of the air inlet system.
At present, a ground test bed for the whole machine experiment of the aero-engine is independently researched and developed in China, and can provide an air inlet and exhaust environment for the whole machine of the aero-engine in a high-altitude simulation state, but the temperature and pressure regulation precision is low, and the real-time performance is poor; the quality of the experiment is directly affected, and the development of the ground experiment of the aero-engine is limited.
Disclosure of Invention
In order to solve the problems, the utility model aims to provide an automatic control device for the air supply temperature of an aeroengine ground test bed.
An aeroengine ground test bed air feed temperature automatic control device, includes:
the temperature measuring element is used for collecting the inlet temperature of the aeroengine and converting a temperature signal into a millivolt signal of thermal electromotive force;
the PLC thermocouple expansion module is connected with the temperature measuring element and is used for carrying out A/D conversion on the millivolt signal converted by the temperature measuring element and transmitting the converted digital quantity signal to the PLCCPU module;
the PLCCPU module is respectively connected with the PLC thermocouple expansion module and the thyristor trigger controller, and is used for calculating a given value of the thyristor voltage regulating power supply according to the received upper computer temperature given signal and the digital quantity signal converted by the PLC thermocouple expansion module, and transmitting the given value to the thyristor trigger controller;
the thyristor trigger controller is connected with a thyristor voltage-regulating power supply of the power supply device of the electric heater of the aeroengine through an optical fiber, and is used for converting a given value into a pulse signal for phase control and controlling the output power of the electric heater of the aeroengine by utilizing the pulse signal.
Preferably, the temperature measuring element is a thermocouple.
Preferably, the PLC thermocouple extension module is an SM1231TC extension module.
Preferably, the PLCCPU module model is CPU1214C.
Preferably, the CPU1214C receives the upper computer temperature given value through the ethernet interface; the CPU1214C is connected with the SM1231TC extension module through a connection terminal and receives the digital quantity signal converted by the SM1231 TC; the CPU1214C is connected with the thyristor trigger controller through an RS485 interface and is used for transmitting a given value to the thyristor trigger controller through a standard MODBUS SRTU communication protocol.
The automatic control device for the air supply temperature of the ground test bed of the aero-engine has the beneficial effects that: compared with the prior art, the utility model realizes the closed-loop control of the inlet gas temperature of the ground test bed engine of the aeroengine by adopting the PLC automatic control technology, shields disturbance caused by external interference and structural parameter change, and improves the temperature control precision and the real-time performance of temperature response of the test bed.
In order to make the above objects, features and advantages of the present utility model more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 shows a schematic diagram of an automatic control device for air supply temperature of an aero-engine ground test bed provided by an embodiment of the utility model;
FIG. 2 shows a schematic diagram of automatic control of air supply temperature of an aircraft engine ground test bed provided by an embodiment of the utility model; (indicating how the control device shields external disturbances)
FIG. 3 shows a schematic diagram of a heating and pressurizing air inlet system of an aircraft engine ground test bed provided by an embodiment of the utility model (showing the position and the function of a heater in the ground test bed).
Detailed Description
In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present utility model, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the present utility model, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.
Referring to fig. 1-3, an automatic control device for air supply temperature of an aeroengine ground test bed includes: the device comprises a PLCCPU module (1), a PLC thermocouple expansion module (2), a thyristor trigger controller (3) and a temperature measuring element (4).
The temperature measuring element (4) is arranged at the inlet of the tested engine of the ground test bed of the aeroengine by adopting a thermocouple, acquires the inlet temperature of the tested engine, converts an inlet temperature signal into a millivolt signal of thermoelectromotive force and transmits the millivolt signal to the PLC thermocouple expansion module (2); the PLC thermocouple expansion module (2) is used for carrying out A/D conversion (analog quantity conversion) on the acquired temperature signals and transmitting digital quantity signals to the PLCCPU module (1); the PLCCPU module (1) is respectively connected with the PLC thermocouple expansion module and the thyristor trigger controller and is used for automatically controlling the inlet temperature of the engine, calculating a given value of the thyristor voltage regulating power supply through a PID algorithm according to a received upper computer temperature given signal, and transmitting the given value to the thyristor trigger controller; and the thyristor trigger controller (3) converts a given value into a pulse signal with phase control, is connected with a thyristor voltage regulating power supply device of the electric heater of the aeroengine through an optical fiber and is used for controlling the output power of the electric heater of the aeroengine according to the given value.
It should be noted that the temperature measuring element in the utility model is a thermocouple (4), the common types are J, K, T and E, and the thermocouple includes R, S and C. The PLC thermocouple expansion module is an SM1231TC expansion module (2). The model of the PLCCPU module is CPU1214C (1), and CPU1214C is connected to the thyristor trigger controller (3) by a standard MODBUSRTU communication protocol.
The utility model is further described below with reference to specific embodiments, where CPU1214C is a CPU module of an S7-1200 series PLC manufactured by siemens corporation, and as a control core of the utility model, the self-equipped industrial ethernet interface is connected to an upper computer, receives a given temperature sent by the upper computer as an input, and is connected to SM1231TC extension module (2) through a connection terminal, and receives a signal after a/D conversion thereof as a feedback; the CPU1214C (1) calculates the given value of the thyristor voltage-regulating power supply by adopting a PID algorithm according to the direct difference value of the input quantity and the feedback quantity, the given value is transmitted to the thyristor trigger controller (3) through a standard MODBUS SRTU communication protocol, and the thyristor trigger controller converts the given value into a phase-shifting pulse signal and transmits the phase-shifting pulse signal to the thyristor voltage-regulating power supply through an optical fiber, so that the output power of the power supply is controlled, and the constant temperature control is realized.
The thyristor trigger controller (3) is used as a control unit of a phase-shifting pulse signal of the thyristor voltage-regulating power supply, and is used for calculating the position generated by the trigger pulse after receiving a given value output by the CPU1214C to form a pulse signal, sending the signal to the thyristor voltage-regulating power supply through an optical fiber, and driving the thyristor through a photoelectric conversion and shaping amplifying circuit to regulate the output power of the power supply.
According to the utility model, by adopting an industrial communication network technology, the data communication among the upper computer, the CPU1214C and the thyristor trigger controller is realized, the inlet temperature of the tested engine is changed in real time along with the temperature setting signal of the upper computer, and the real-time performance of temperature response is improved.
As shown in fig. 3, the electric heater is a core part of the heating control system of the ground test bed of the aero-engine. The part mainly comprises an electric heater body and a power supply. The test bed heating control is mainly that a thyristor AC voltage-regulating power supply provides set electric power to an electric heater body. The electric heater body converts electric energy into heat energy to heat the flowing gas to a certain temperature, the temperature is kept constant under a certain pressure, and finally the gas with specific pressure, flow and temperature required by the experiment is injected into the engine.
According to the utility model, the PLC automatic control technology is adopted to realize closed-loop control of the inlet gas temperature of the aeroengine ground test bed engine, so that disturbance caused by external interference and structural parameter change is shielded, and the temperature control precision of the test bed is improved.
The foregoing is merely illustrative of the present utility model, and the present utility model is not limited thereto, and any person skilled in the art can easily think about variations or alternatives within the scope of the present utility model. Therefore, the protection scope of the present utility model shall be subject to the protection scope of the claims.
Claims (5)
1. The utility model provides an aeroengine ground test bed air feed temperature automatic control device which characterized in that includes:
the temperature measuring element is used for collecting the inlet temperature of the aeroengine and converting a temperature signal into a millivolt signal of thermal electromotive force;
the PLC thermocouple expansion module is connected with the temperature measuring element and is used for carrying out A/D conversion on the millivolt signal converted by the temperature measuring element and transmitting the converted digital quantity signal to the PLC CPU module;
the PLC CPU module is respectively connected with the PLC thermocouple expansion module and the thyristor trigger controller, and is used for calculating a given value of the thyristor voltage regulating power supply according to the received upper computer temperature given signal and the digital quantity signal converted by the PLC thermocouple expansion module, and transmitting the given value to the thyristor trigger controller;
the thyristor trigger controller is connected with a thyristor voltage-regulating power supply of the power supply device of the electric heater of the aeroengine through an optical fiber, and is used for converting a given value into a pulse signal for phase control and controlling the output power of the electric heater of the aeroengine by utilizing the pulse signal.
2. The automatic control device for the air supply temperature of the ground test bed of the aeroengine according to claim 1, wherein the temperature measuring element is a thermocouple.
3. The automatic control device for the air supply temperature of the ground test bed of the aeroengine according to claim 2, wherein the PLC thermocouple expansion module is an SM1231TC expansion module.
4. An automatic control device for air supply temperature of an aircraft engine ground test bed according to claim 3, wherein the PLC CPU module is of the CPU1214C type.
5. The automatic control device for air supply temperature of ground test bed of aero-engine according to claim 4, wherein the CPU1214C receives the upper computer temperature given value through ethernet interface; the CPU1214C is connected with the SM1231TC extension module through a connection terminal and receives the digital quantity signal converted by the SM1231 TC; the CPU1214C is connected with the thyristor trigger controller through an RS485 interface and is used for transmitting a given value to the thyristor trigger controller through a standard MODBUS RTU communication protocol.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321218433.5U CN220305687U (en) | 2023-05-19 | 2023-05-19 | Automatic control device for air supply temperature of ground test bed of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321218433.5U CN220305687U (en) | 2023-05-19 | 2023-05-19 | Automatic control device for air supply temperature of ground test bed of aero-engine |
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| Publication Number | Publication Date |
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| CN220305687U true CN220305687U (en) | 2024-01-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202321218433.5U Active CN220305687U (en) | 2023-05-19 | 2023-05-19 | Automatic control device for air supply temperature of ground test bed of aero-engine |
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| Country | Link |
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| CN (1) | CN220305687U (en) |
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2023
- 2023-05-19 CN CN202321218433.5U patent/CN220305687U/en active Active
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