A device and method for temperature step experiment of an aero-engine intake total temperature sensor

Abstract

The present application relates to a kind of device and method for aero-engine intake total temperature sensor temperature step experiment, belong to total temperature sensor dynamic test field.The experimental table disclosed in the present application mainly includes high-pressure gas source storage tank, pressure stabilizing shunt valve, eddy current heater, cold and hot airflow pipeline, total temperature sensor, bidirectional rotating electromagnet, signal acquisition device, power supply, host computer and controller etc.One way airflow is heated after passing through eddy current heater and flows out through hot airflow pipeline outlet, another way unheated airflow flows out through cold airflow pipeline outlet, total temperature sensor placed at the pipeline outlet is driven by bidirectional rotating electromagnet, and rapidly switches between cold airflow and hot airflow pipeline outlet to realize the step change of measured airflow temperature.The present application realizes to carry out airflow velocity and temperature step amplitude adjustable positive and negative step experiment to total temperature sensor, and it has important significance for the test and error compensation research of aero-engine intake total temperature sensor dynamic characteristic.

Description

Technical Field

[0001] This invention relates to an apparatus and method for a temperature step test of an air intake total temperature sensor for aero-engines, belonging to the field of dynamic testing of total temperature sensors. Background Technology

[0002] In the field of aero-engine control and testing, the total temperature of the engine's multi-section intake air can directly affect the normal operation of the engine and is an important parameter that needs to be monitored. Therefore, the performance and accuracy of the total temperature sensor are crucial to the normal operation of the engine.

[0003] The total air temperature sensor for aero-engines mainly consists of a resistance temperature detector (RTD) probe and an airflow stagnation shield. It is primarily used to measure the total air temperature at the inlet of the aero-engine's air intake, fan inlet, and compressor inlet. However, during temperature measurement, the sensor introduces dynamic errors such as response delay, as well as steady-state errors including velocity error, thermal conductivity error, and radiation error. To analyze whether the total air temperature sensor can meet the requirements for high-precision real-time temperature measurement, dynamic characteristic experiments and research on dynamic error compensation are necessary. The dynamic performance of the total air temperature sensor is often evaluated using its time constant, which is typically obtained experimentally by acquiring the sensor's dynamic response under a step change in airflow temperature.

[0004] Temperature step change experiments typically employ a catapult device to rapidly transfer a sensor from a cold airflow to a hot airflow, thereby enabling the sensor to measure the step change in airflow temperature. However, this method demands extremely high stability, accuracy, and response speed from the catapult device. Patent CN201610879373.X discloses a step temperature field generator for measuring the time constant of a fiber optic grating; however, this device has high requirements for switching the type of electrical contacts and controlling the pulse current, and the device itself is relatively complex. Patent CN201711276686.7 discloses a high-temperature step method; however, this device uses laser heating, which requires high precision and is relatively expensive. Summary of the Invention

[0005] The purpose of this invention is to provide an apparatus and method for conducting temperature step experiments on the total temperature sensor of an aero-engine intake, aiming to carry out positive and negative step experiments on the total temperature sensor with adjustable airflow velocity and temperature step amplitude.

[0006] To achieve the above objectives, the present invention provides the following technical solution:

[0007] The present invention discloses an apparatus for a temperature step experiment of an air intake total temperature sensor for an aero-engine, comprising a high-pressure gas source storage tank, a pressure regulating and diverting valve, an eddy current heater, an airflow duct, a flange connection device, a bidirectional rotating electromagnet, an electromagnet actuator, a static pressure sensor, a total pressure sensor, a total temperature sensor, a reference thermal resistor, a signal acquisition device, a filter, a power supply, a host computer, and a controller.

[0008] The controller is connected to the electromagnet driver via a data transmitter. The electromagnet driver is connected to a bidirectional rotating electromagnet. The static pressure sensor, total pressure sensor, total temperature sensor, and reference RTD are connected to the signal acquisition device. The signal from the signal acquisition device is filtered and then sent to the host computer. The power supply provides power to the controller, filter, signal acquisition device, and electromagnet driver.

[0009] The outlet airflow of the high-pressure gas source storage tank is divided into two paths by a pressure-stabilizing and diverting valve. One path enters the eddy current heater to be heated to obtain a hot airflow with a static temperature of T1, and the other path is an unheated cold airflow with a static temperature of T2.

[0010] The pressure regulating and diverting valve can adjust the airflow pressure P at the outlet of the high-pressure gas source storage tank. out This changes the airflow velocity v at the pipe outlet, which ranges from 10 m / s to 70 m / s.

[0011] The electric eddy current heater can fully heat the airflow to a specified static temperature T1, with a temperature range between 100℃ and 350℃ and a temperature error of ±1℃.

[0012] The flange connection device isolates the heating section and the outlet section of the hot gas pipeline. A ceramic heat insulation gasket with a thermal conductivity of 0.035 W / (m·K) is placed in the middle of the flange to slow down the temperature rise of the pipeline in the outlet section, thereby ensuring the normal operation of pressure and temperature measurement.

[0013] The static pressure sensor and the total pressure sensor draw out the airflow for pressure measurement through the static pressure tapping pipe and the total pressure tapping pipe, respectively. The inlet of the static pressure tapping pipe and the inlet of the total pressure tapping pipe are fixedly installed at the same axial position at the outlet end of the pipe.

[0014] The static pressure of the airflow measured by the static pressure sensor is P. s The total pressure of the airflow measured by the total pressure sensor is P. t Then the airflow velocity can be calculated.

[0015] The bidirectional rotating electromagnet is characterized in that an external limiting method is used to ensure that the electromagnet spindle can only rotate 90°. When the polarity of the input voltage is changed, the electromagnet spindle reverses, and the execution time is less than 50ms.

[0016] The electromagnet driver is characterized in that its main structure is an H-bridge circuit composed of MOS transistors. By changing the polarity of the voltage output by the electromagnet driver through high and low level signals output by the lower-level machine, the motion control of the bidirectional rotating electromagnet is realized.

[0017] The total temperature sensor is fixed on the main shaft of a bidirectional rotating electromagnet. By controlling the rotation direction of the bidirectional rotating electromagnet, the total temperature sensor can be rapidly switched at the outlet of the hot and cold airflow pipe, thereby achieving a step change in the inlet temperature of the total temperature sensor.

[0018] The reference thermal resistor is characterized by its small size and thin thickness, superior dynamic performance, and a time constant much smaller than that of the total temperature sensor. The reference thermal resistor is installed at the top of the pipe outlet to test the temperature of the cold and hot air outlet pipe.

[0019] The data acquisition device is characterized in that it can simultaneously acquire signals from a static pressure sensor, a total pressure sensor, a total temperature sensor, and a reference thermistor, and the frequency of signal acquisition is not less than 100Hz.

[0020] The filter is characterized in that it can reduce noise interference with the acquired signal.

[0021] The controller is characterized in that it is specifically an embedded programmable development board, which can develop corresponding functions according to requirements to realize the control of the movement of the bidirectional rotating electromagnet.

[0022] The host computer is characterized by having a graphical human-computer interaction interface, receiving signals from the static pressure sensor, total pressure sensor, total temperature sensor and reference thermal resistor sent by the signal acquisition device via serial communication, and being able to process and record the received signals. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the experimental system structure of the present invention.

[0024] Figure 2 This is a schematic diagram of the main structure of the experimental platform of the present invention.

[0025] Figure 3 This is a schematic diagram showing the connection between the heating section and the outlet section of the hot airflow pipeline of the present invention.

[0026] Figure 4 This is a schematic diagram showing the connection between the total temperature sensor and the main shaft of the bidirectional rotating electromagnet of the present invention.

[0027] In the diagram: 1-Experimental platform, 2-Hot airflow pipe inlet, 3-Cold airflow pipe inlet, 4-Eddy current heater, 5-Cold airflow pipe, 6-Hot airflow pipe, 7-Flange connection device, 71-Heating section flange, 72-Ceramic heat insulation gasket, 73-Outlet section flange, 74-Bolt, 75-Flat gasket, 76-Spring gasket, 77-Nut, 8-Static pressure tapping pipe, 9-Reference RTD, 10-Total pressure tapping pipe, 11-Total temperature sensor, 12-Electromagnet mounting cover, 13-Bidirectional rotating electromagnet, 131-Electromagnet spindle, 14-Nut, 15-Spring gasket, 16-Flat gasket, 17-Bolt, 18-Fixing clamp, 19-Fixing screw. Detailed Implementation

[0028] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0030] Please see Figure 1 In this invention, the device for the temperature step experiment of the total temperature sensor of the aero-engine intake includes a high-pressure gas source storage tank, a pressure regulating and diverting valve, an eddy current heater 4, hot and cold airflow pipes 5 and 6, a bidirectional rotating electromagnet 13, an electromagnet driver, a static pressure sensor, a total pressure sensor, a total temperature sensor 11, a reference thermal resistor 9, a signal acquisition device, a filter, a power supply, a host computer, and a controller. The controller is connected to the electromagnet driver through a data transmission terminal. The electromagnet driver is connected to the bidirectional rotating electromagnet 13. The static pressure sensor, the total pressure sensor, the total temperature sensor 11, and the reference thermal resistor 9 are connected to the signal acquisition device. The signal from the signal acquisition device is filtered and then sent to the host computer. The power supply provides power to the controller, the filter, the signal acquisition device, and the electromagnet driver.

[0031] Please see Figure 2 The hot and cold airflow pipes 5 and 6, as well as the electromagnet mounting cover 12, are fixedly installed on the experimental platform 1. One airflow enters the hot airflow pipe 6, is heated by the eddy current heater 4, and then flows out of the hot airflow pipe 6 outlet, with a static airflow temperature of T1. The other airflow flows out of the cold airflow pipe 5 outlet, with a static airflow temperature of T2. The bidirectional rotating electromagnet 13 drives the total temperature sensor 11 to quickly switch between the hot and cold airflow pipe outlets, realizing a step change in the inlet temperature of the total temperature sensor 11.

[0032] Please see Figure 3 The flange connection device 7 mainly consists of a heating section flange 71, a ceramic heat insulation gasket 72, an outlet section flange 73, bolts 74, a flat gasket 75, a spring gasket 76, and nuts 77. The thermal conductivity of the ceramic heat insulation gasket is only 0.035 W / (m·K), which can effectively prevent the heat of the heating section pipeline from being transferred to the outlet section through heat conduction, thereby ensuring that the temperature of the outlet section pipeline does not affect the normal operation of the temperature and pressure measuring devices.

[0033] Please see Figure 4 The fixing clamp 18 is fixed to the rotating electromagnet spindle 131 by fixing screws 19. The total temperature sensor 11 is fixed in the fixing clamp 18 by nuts 14, spring washers 15, flat washers 16 and bolts 17. The total temperature sensor 11 swings as the bidirectional rotating electromagnet 13 rotates.

[0034] This embodiment discloses a method for a device used in a temperature step experiment of an air intake total temperature sensor for an aero-engine, and its operation flow has the following logical steps:

[0035] Step 1: Turn on the high-pressure gas source storage tank switch, set the pressure value of the pressure regulating and diverting valve, and obtain two uniform airflows;

[0036] Step 2: Turn on the eddy current heater so that the airflow in the hot airflow pipe 6 is heated to the specified temperature T1;

[0037] Step 3: Control the inlet of the total temperature sensor 11 to be directly opposite the center of the outlet of the cold air duct 5. After the pressure and temperature values ​​at the outlets of the cold and hot air ducts 5 and 6 stabilize, control the electromagnet driver to change the voltage polarity of the bidirectional rotating electromagnet 13, so that the total temperature sensor 11 quickly switches to the center of the outlet of the hot air duct 6.

[0038] Step 4: After the output of the total temperature sensor 11 stabilizes, control the electromagnet driver again to change the voltage polarity of the bidirectional rotating electromagnet 13, so that the total temperature sensor 11 quickly switches to the center of the outlet of the cold air duct 5.

[0039] Step 5: Change the power of the eddy current heater 4 and the pressure value of the pressure regulating and diverting valve, and repeat the above operation;

[0040] Step 6: Real-time acquisition of signals from the static pressure sensor, total pressure sensor, total temperature sensor 11, and reference RTD 9; observation of signal changes and data processing.

[0041] This invention is not limited to the above embodiments. Based on the technical solutions disclosed in this invention, those skilled in the art can make some simple modifications, equivalent changes and alterations to some of the technical features without creative effort, all of which fall within the scope of the technical solutions of this invention.

Claims

1. A device for a temperature step experiment of an aero-engine intake air total temperature sensor, characterized in that, The system includes a high-pressure gas storage tank, a pressure regulating and diverting valve, an eddy current heater (4), hot and cold air flow pipes (5) and (6), a flange connection device (7), a bidirectional rotating electromagnet (13), an electromagnet driver, a static pressure sensor, a total pressure sensor, a total temperature sensor (11), a reference thermal resistor (9), a signal acquisition device, a filter, a power supply, a host computer, and a controller. The controller is connected to the electromagnet driver via a data transmission terminal. The electromagnet driver is connected to the bidirectional rotating electromagnet (13). The static pressure sensor, total pressure sensor, total temperature sensor (11), and reference thermal resistor (9) are connected to the signal acquisition device. The signal from the signal acquisition device is filtered and then sent to the host computer. The power supply provides power to the controller, the filter, the signal acquisition device, and the electromagnet driver. The outlet airflow of the high-pressure gas source storage tank is divided into two paths by the pressure regulating and diverting valve. One path enters the electric eddy current heater (4) to be heated to obtain a hot airflow with a static temperature of T1, and the other path is an unheated cold airflow with a static temperature of T2. The pressure regulating and diverting valve can adjust the airflow pressure P at the inlet of the hot and cold airflow pipes (5) and (6). out This changes the airflow velocity v at the outlet of the hot and cold airflow pipes (5) and (6), with the airflow velocity v at the outlet ranging from 10 m / s to 70 m / s. The electric eddy current heater (4) can fully heat the airflow to a specified static temperature T1, with a temperature range of 100°C to 350°C and a temperature error of ±1°C. The flange connection device (7) is located between the heating section and the outlet section of the hot air duct (6). The flange connection device (7) consists of a heating section flange (71), a ceramic heat insulation gasket (72), an outlet section flange (73), bolts (74), a flat gasket (75), a spring gasket (76), and a nut (77). The thermal conductivity of the ceramic heat insulation gasket (72) is 0.035 W / (m·K).

2. The apparatus for a temperature step experiment of an aero-engine intake air total temperature sensor as described in claim 1, characterized in that, The flange connection device (7) isolates the heating section and the outlet section of the hot air flow pipeline (6), which can slow down the rise of the pipeline temperature in the outlet section to ensure the normal operation of pressure measurement and temperature measurement. The static pressure sensor and the total pressure sensor draw out the airflow for pressure measurement through the static pressure tap (8) and the total pressure tap (10) respectively. The inlet of the static pressure tap (8) and the inlet of the total pressure tap (10) are fixedly installed at the same axial position at the outlet end of the pipeline. The static pressure sensor measures the static pressure of the airflow as P. s If the total pressure of the airflow is measured by the total pressure sensor as Pt, then the airflow velocity can be calculated. The bidirectional rotating electromagnet (13) uses an external limiting method to ensure that the electromagnet spindle (131) can only rotate 90°. When the polarity of the input voltage is changed, the electromagnet spindle (131) reverses, and the execution time is less than 50ms. The main structure of the electromagnet driver is an H-bridge circuit composed of MOS transistors. By changing the polarity of the voltage output by the electromagnet driver through the high and low level signals output by the lower computer, the motion control of the bidirectional rotating electromagnet (13) is realized. The total temperature sensor (11) is fixed on the main shaft (131) of the bidirectional rotating electromagnet. By controlling the rotation direction of the main shaft (131) of the bidirectional rotating electromagnet, the total temperature sensor (11) is controlled to switch rapidly at the outlet of the hot and cold airflow pipes (5) and (6), thereby realizing a step change in the inlet temperature of the total temperature sensor (11). The reference thermal resistor (9) is small in size and thin in thickness, and has excellent dynamic performance. Its time constant is much smaller than that of the total temperature sensor. The reference thermal resistor (9) is installed on the top of the pipe outlet to test the temperature of the outlet of the hot and cold air flow pipes (5) and (6). The signal acquisition device described above can simultaneously acquire signals from the static pressure sensor, total pressure sensor, total temperature sensor (11), and reference thermistor (9), and the signal acquisition frequency is not less than 100Hz. The filter can reduce noise interference with the acquired signal; The controller is specifically an embedded programmable development board, which can develop corresponding functions according to requirements and realize the control of the movement of the bidirectional rotating electromagnet (131); The host computer has a graphical human-machine interface, receives signals from the static pressure sensor, total pressure sensor, total temperature sensor (11) and reference thermal resistor (9) sent by the signal acquisition device through serial communication, and can process and record the received signals.

3. The method for a device used in a temperature step experiment of an aero-engine intake air total temperature sensor as described in claim 1, characterized in that, The experimental procedure follows the following logic: Step 1: Turn on the high-pressure gas source storage tank switch, set the pressure value of the pressure regulating and diverting valve, and obtain two uniform airflows; Step 2: Turn on the eddy current heater so that the airflow in the hot airflow pipe (6) is heated to the specified temperature T1; Step 3: Control the inlet of the total temperature sensor (11) to be directly opposite the center of the outlet of the cold air duct (5). After the pressure and temperature values ​​of the outlets of the cold and hot air ducts (5) and (6) stabilize, control the electromagnet driver to change the voltage polarity of the bidirectional rotating electromagnet (13) so that the total temperature sensor (11) quickly switches to the center of the outlet of the hot air duct (6). Step 4: After the output of the total temperature sensor (11) stabilizes, control the electromagnet driver again to change the voltage polarity of the bidirectional rotating electromagnet (13), so that the total temperature sensor (11) quickly switches to the center of the outlet of the cold air duct (5). Step 5: Change the power of the eddy current heater (4) and the pressure value of the pressure regulating and diverting valve, and repeat the above operation; Step 6: Real-time acquisition of signals from static pressure sensor, total pressure sensor, total temperature sensor (11) and reference thermal resistor (9), observation of signal changes and data processing.

Images