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Icing wind tunnel heat exchanger outlet airflow temperature control system and method

A temperature control method and temperature control system technology, applied in the direction of instruments, refrigerators, refrigeration components, etc., can solve the problems of large heat load changes, temperature control lag, long flow path, etc., to change heat transfer performance and improve stability , the effect of quick adjustment

Active Publication Date: 2022-04-15
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Operation experience shows that due to the large tube capacity and long flow path of the icing wind tunnel heat exchanger, there are many factors affecting the heat transfer effect during the test (such as wind speed, airflow density, etc.), and the refrigerant evaporation heat transfer process in the heat exchanger is complicated.
There is a large hysteresis in temperature control by using expansion valves to control the flow of liquid supply, which cannot meet the rapidity requirements of test temperature control
[0007] According to the test process flow, after the airflow temperature is stable, the spray system and the hot gas anti-icing test system are turned on. The hot gas injected will cause a large change in the heat load of the refrigeration system. Ice tests, especially the requirements for anti-icing airworthiness certification tests

Method used

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  • Icing wind tunnel heat exchanger outlet airflow temperature control system and method
  • Icing wind tunnel heat exchanger outlet airflow temperature control system and method
  • Icing wind tunnel heat exchanger outlet airflow temperature control system and method

Examples

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Effect test

Embodiment 1

[0042] The invention provides a temperature control system for the outlet air flow of the icing wind tunnel heat exchanger, please combine with the attached figure 1 As shown, the present invention includes: compressor, suction pressure sensor, condenser (evaporative condenser), liquid storage tank (high pressure liquid storage tank), refrigerant shielded pump, heat exchanger, liquid inlet regulating valve, return air Regulating valve, temperature sensor, low-pressure circulation barrel, controller (compressor controller) and host computer; it should be explained that, as a preferred embodiment, in the present invention, ammonia is used as the refrigerant, and in other embodiments Other refrigerants can be used, Freon refrigerants (such as: R12, R11, R114, R113, R22, R13, R14, etc.), saturated hydrocarbon refrigerants (such as: methane (R50), ethane (R170), propane (R290), butane (R600), isodifluoroethane (R152a) and isobutane (R601), etc.), azeotropic refrigerants and non-aze...

Embodiment 2

[0050] please combine figure 2 As shown, the system is roughly adjusted through the suction pressure of the compressor, and the specific steps are as follows:

[0051] Step S1: Input the test conditions, and the host computer calculates the ammonia saturation evaporation pressure P0 corresponding to the target temperature T0 of the test conditions based on the ammonia physical property fitting function (evaporation temperature - saturated evaporation pressure);

[0052] Step S2: Obtain the target suction pressure P1 of the compressor, where P1=P0+ΔP, ΔP1 is the empirical value of pressure change; in actual operation, ΔP1 is based on the pressure loss of the heat exchanger outlet pipeline and historical temperature control experience, ΔP1 In the actual experimental operation, ΔP1 is empirically set to 0.3 bar through repeated simulations; this difference can be modified in the host computer software according to the working conditions.

[0053] Step S3: Set the suction pressu...

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Abstract

The invention is suitable for the technical field of wind tunnel experiments, and provides an icing wind tunnel heat exchanger outlet airflow temperature control system and method, and the system comprises a compressor, a condenser, a liquid storage tank, a refrigerant shield pump, a heat exchanger, a low-pressure circulation barrel, a controller, and an upper computer. An air suction pressure sensor is arranged at the air suction end of the compressor; an inlet and an outlet of the heat exchanger are respectively provided with a liquid inlet regulating valve and an air return regulating valve; a downstream air outlet of the heat exchanger is provided with a temperature sensor, and the temperature sensor and the heat exchanger are both arranged in the icing wind tunnel; the controller is in control connection with the compressor; the upper computer is connected with the temperature sensor, the return air regulating valve and the controller; the air suction pressure sensor is directly arranged at the air suction end of the compressor, the air suction pressure of the compressor can be visually and sensitively obtained, and the problems that in the prior art, due to the large volume of a low-pressure circulation barrel, the load increasing and decreasing speed of a refrigerating system unit is low, and finally the heat exchanger outlet airflow temperature has large hysteresis quality are solved.

Description

technical field [0001] The invention belongs to the field of icing wind technology, and relates to a system for controlling the outlet airflow temperature of a heat exchanger in an icing wind tunnel, in particular to a method for controlling the outlet airflow temperature of a heat exchanger in an icing wind tunnel. Background technique [0002] When an aircraft passes through low-temperature clouds rich in supercooled liquid droplets, icing is prone to occur on the windward surface, which seriously threatens the flight safety of the aircraft. Aircraft icing wind tunnel test is an important means to obtain its icing characteristics, verify the performance of airborne anti-icing system and carry out airworthiness certification. The quality of the thermal flow field is an important technical index to evaluate the test capability of the icing wind tunnel, and the temperature control performance is one of the core technologies for the research of aircraft icing and anti-icing in...

Claims

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Application Information

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IPC IPC(8): F25B1/00F25B41/20F25B43/00F25B49/02B64F5/60G01M9/04G01M9/06
CPCY02T50/50
Inventor 张平涛倪章松张轲郭向东孙才国林伟
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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