Aviation fuel oil heating system for high-temperature fuel oil dynamic seal test

Abstract

The utility model discloses an aviation fuel heating system for a high temperature fuel dynamic seal test, which comprises a dynamic seal test cavity, a water cooling device, a conduction oil mold temperature controller and a control terminal, a conduction oil heat exchange tube and aviation fuel are arranged in the dynamic seal test cavity, the top of the dynamic seal test cavity is provided with an air inlet valve and an exhaust valve, and the air inlet valve and the exhaust valve are communicated with the conduction oil mold temperature controller. A first temperature sensor is installed on the dynamic seal test cavity, the water cooling device is connected with the heat conduction oil mold temperature controller and used for cooling heat conduction oil in the heat conduction oil mold temperature controller, and the heat conduction oil mold temperature controller is connected with the heat conduction oil heat exchange pipe and used for adjusting the temperature of aviation fuel through the heat conduction oil. And the control terminal is connected with the water cooling equipment, the heat-conducting oil mold temperature controller and the first temperature sensor. The aviation fuel oil heating system for the high-temperature fuel oil dynamic seal test is high in safety, and long-term stable control over the temperature of high-temperature fuel oil can be achieved.

Description

Technical Field

[0001] This utility model relates to the field of high-temperature fuel dynamic sealing test technology, and in particular provides an aviation fuel heating system for high-temperature fuel dynamic sealing test. Background Technology

[0002] During high-temperature fuel dynamic sealing tests, it is necessary to ensure that the aviation fuel in the test chamber is in a stable high-temperature state. However, in the existing technology, aviation fuel is usually heated to a set temperature outside the test chamber before being introduced into the test chamber for testing. During the process of the high-temperature aviation fuel entering the test chamber, leakage may occur. If it comes into contact with an open flame, it may cause an explosion, which is extremely unsafe. In addition, the high-temperature aviation fuel entering the test chamber will lose heat over time and will also heat up due to the friction interface of high-speed rotation in the test chamber. As a result, it is impossible to ensure the long-term stability of the aviation fuel temperature and meet the requirements of stable high-temperature test conditions.

[0003] Therefore, how to structurally improve the aviation fuel heating system to ensure the safety requirements of the high-temperature fuel dynamic sealing test, while ensuring that the aviation fuel is under stable high-temperature conditions, has become an urgent problem to be solved. Utility Model Content

[0004] Therefore, the purpose of this utility model is to provide an aviation fuel heating system for high-temperature fuel dynamic sealing tests, so as to solve the problems existing in the prior art.

[0005] The technical solution provided by this utility model is: an aviation fuel heating system for high-temperature fuel dynamic sealing tests, comprising: a dynamic sealing test chamber, a water-cooling device, a heat transfer oil temperature controller, and a control terminal. The dynamic sealing test chamber is equipped with a heat transfer oil heat exchanger and aviation fuel for high-temperature fuel dynamic sealing tests. An inlet valve and an exhaust valve are provided on the top of the dynamic sealing test chamber. A first temperature sensor is installed on the dynamic sealing test chamber to monitor the temperature of the aviation fuel within the dynamic sealing test chamber. The water-cooling device is connected to the heat transfer oil temperature controller. A hot oil mold temperature controller is connected to the system for cooling the heat transfer oil inside the controller using cooling water. The controller is connected to the heat transfer oil heat exchange tube to form a closed-loop circuit. The heat transfer oil in the heat exchange tube is used to exchange heat with the aviation fuel in the dynamic sealing test chamber, thereby adjusting the temperature of the aviation fuel. The control terminal is connected to the water cooling equipment, the hot oil mold temperature controller, and the first temperature sensor, and is used to control the working status of the water cooling equipment and the hot oil mold temperature controller based on the aviation fuel temperature information monitored by the first temperature sensor.

[0006] Preferably, the water-cooling device includes a water tank, a cooling fan, a second temperature sensor, and a water pump. The thermal oil mold temperature controller includes a water-cooled heat exchange chamber, a thermal oil heating chamber, a third temperature sensor, and a thermal oil pump. The water tank contains cooling water and forms a closed-loop circuit with the water-cooled heat exchange chamber of the thermal oil mold temperature controller through a first pipeline. The water pump is installed on the first pipeline. The cooling fan is used to cool the cooling water. The thermal oil heating chamber is connected to the thermal oil heat exchange tube through a second pipeline to form a thermal oil closed-loop circuit. The thermal oil pump is installed on the second pipeline. The second temperature sensor and the third temperature sensor are both connected to the control terminal and are used to detect the temperature information of the cooling water in the water tank and the temperature information of the thermal oil in the thermal oil heating chamber, respectively, and send them to the control terminal.

[0007] Further preferably, a first valve and a second valve are respectively installed on the first pipeline and the second pipeline, and both the first valve and the second valve are connected to the control terminal, which is used to control the opening and closing of the first valve and the second valve.

[0008] Further preferably, the aviation fuel heating system for the high-temperature fuel dynamic sealing test also includes a high-pressure nitrogen cylinder, which is connected to the air inlet valve through a third pipeline for inputting high-pressure nitrogen into the dynamic sealing test chamber.

[0009] Further preferably, a first pressure sensor is installed on the third pipeline to monitor the pressure of the nitrogen output from the high-pressure nitrogen cylinder.

[0010] Furthermore, the dynamic sealing test chamber is further equipped with a second pressure sensor for monitoring aviation fuel pressure.

[0011] The aviation fuel heating system for high-temperature fuel dynamic sealing tests provided by this utility model has high safety and can achieve long-term stable control of high-temperature fuel temperature. Attached Figure Description

[0012] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments:

[0013] Figure 1 A schematic diagram of the aviation fuel heating system for high-temperature fuel dynamic sealing test provided by this utility model. Detailed Implementation

[0014] The present invention will be further explained below with reference to specific implementation schemes, but it is not limited to the present invention.

[0015] To address the issues of low safety and poor temperature controllability in existing high-temperature fuel dynamic seal tests, such as... Figure 1As shown, this utility model provides an aviation fuel heating system for high-temperature fuel dynamic sealing tests, including: a dynamic sealing test chamber 1, a water-cooling device 2, a heat transfer oil mold temperature controller 3, and a control terminal 4. The dynamic sealing test chamber 1 is equipped with a heat transfer oil heat exchange pipe 11 and aviation fuel for high-temperature fuel dynamic sealing tests. An inlet valve 12 and an exhaust valve 13 are located on the top of the dynamic sealing test chamber 1. A first temperature sensor 14 is installed on the dynamic sealing test chamber 1 to monitor the temperature of the aviation fuel inside the dynamic sealing test chamber 1. The water-cooling device 2 is connected to the heat transfer oil mold temperature controller 3 for... Cooling water cools the heat transfer oil in the heat transfer oil mold temperature controller 3. The heat transfer oil mold temperature controller 3 is connected to the heat transfer oil heat exchange pipe 11 to form a closed-loop circuit for the heat transfer oil. The heat transfer oil in the heat transfer oil heat exchange pipe 11 is used to exchange heat with the aviation fuel in the dynamic sealing test chamber 1, thereby adjusting the temperature of the aviation fuel. The control terminal 4 is connected to the water cooling device 2, the heat transfer oil mold temperature controller 3 and the first temperature sensor 14. It is used to control the working status of the water cooling device 2 and the heat transfer oil mold temperature controller 3 according to the aviation fuel temperature information monitored by the first temperature sensor 14, so as to adjust the temperature of the aviation fuel and ensure its long-term temperature stability.

[0016] This aviation fuel heating system for high-temperature dynamic seal testing pre-injects aviation fuel for the test into the dynamic seal test chamber. Through the coordination of a first temperature sensor, water-cooling equipment, a thermal oil mold temperature controller, and a control terminal, the system can monitor and regulate the aviation fuel temperature (water-cooling equipment for cooling, thermal oil mold temperature controller for heat source compensation), ensuring long-term stability of the aviation fuel temperature during the test. Heating the aviation fuel within the dynamic seal test chamber improves test safety. Furthermore, before heating the aviation fuel, nitrogen can be introduced into the dynamic seal test chamber through the intake valve, allowing the air inside the chamber to be vented through the exhaust valve. Then, nitrogen is added... Using heated aviation fuel further ensures the safety of the experiment. The specific method for controlling the aviation fuel temperature is as follows: A first temperature sensor monitors the aviation fuel temperature in real time and sends it to the control terminal. If the aviation fuel temperature is high, the control terminal activates the water cooling equipment and / or reduces the heating power of the thermal oil mold temperature controller to lower the thermal oil temperature. The cooled thermal oil lowers the aviation fuel temperature. If the aviation fuel temperature is low, the control terminal shuts off the water cooling equipment and increases the heating power of the thermal oil mold temperature controller to raise the thermal oil temperature. The heated thermal oil raises the aviation fuel temperature. In summary, by controlling the thermal oil temperature, the aviation fuel temperature can be controlled to maintain a stable temperature over a long period.

[0017] As an improvement to the technical solution, the water-cooling device 2 includes a water tank, a cooling fan, a second temperature sensor, and a water pump. The thermal oil mold temperature controller 3 includes a water-cooled heat exchange chamber, a thermal oil heating chamber, a third temperature sensor, and a thermal oil pump. The water tank contains cooling water and forms a closed-loop circuit with the water-cooled heat exchange chamber of the thermal oil mold temperature controller 3 through a first pipe 5. The water pump is installed on the first pipe 5. The cooling fan is used to cool the cooling water. The thermal oil heating chamber is connected to the thermal oil heat exchange tube through a second pipe 6 to form a closed-loop circuit. The thermal oil pump is installed on the second pipe 6. The second temperature sensor and the third... All three temperature sensors are connected to the control terminal 4, and are used to detect the temperature information of the cooling water in the water tank and the temperature information of the heat transfer oil in the heat transfer oil heating chamber, respectively, and send them to the control terminal 4. When the water temperature in the water tank is too high, the control terminal controls the water cooling equipment to start the cooling fan to cool down, thereby improving the heat exchange efficiency between the cooling water and the heat transfer oil and realizing rapid cooling of the heat transfer oil. When the temperature of the heat transfer oil is too high, the control terminal controls the heat transfer oil mold temperature controller to reduce the heating power and / or start the water cooling equipment to cool down the heat transfer oil. When the temperature of the heat transfer oil is too low, the control terminal shuts down the water cooling equipment and controls the heat transfer oil mold temperature controller to increase the heating power to raise the temperature of the heat transfer oil.

[0018] As an improvement to the technical solution, a first valve 51 and a second valve 61 are respectively provided on the first pipeline 5 and the second pipeline 6. The first valve 51 and the second valve 61 are both connected to the control terminal 4. The control terminal 4 is used to control the opening and closing of the first valve 51 and the second valve 61.

[0019] As an improvement to the technical solution, the aviation fuel heating system for the high-temperature fuel dynamic sealing test also includes a high-pressure nitrogen cylinder 7. The high-pressure nitrogen cylinder 7 is connected to the air inlet valve 12 through a third pipeline 8, and is used to input high-pressure nitrogen into the dynamic sealing test chamber 1. The high-pressure nitrogen cylinder can both purge the air in the dynamic sealing test chamber before heating the aviation fuel and adjust the pressure in the dynamic sealing test chamber to realize the pressurized high-temperature fuel dynamic sealing test. Preferably, the high-pressure nitrogen cylinder 7 is connected to a control terminal, and the control terminal is used to control the opening and closing of the high-pressure nitrogen cylinder.

[0020] As an improvement to the technical solution, a first pressure sensor 81 is provided on the third pipeline 8 to monitor the pressure of nitrogen output from the high-pressure nitrogen cylinder 7. The first pressure sensor 81 can be connected to a control terminal.

[0021] As an improvement to the technical solution, the dynamic sealing test chamber 1 is also equipped with a second pressure sensor 15 for monitoring aviation fuel pressure. The second pressure sensor 15 can also be connected to a control terminal. Preferably, the control terminal can control the opening and closing of the high-pressure nitrogen cylinder through the pressure monitored by the second pressure sensor so that the oil pressure reaches the preset value.

[0022] The specific embodiments of this utility model are written in a progressive manner, emphasizing the differences between each implementation scheme, and the similar parts can be referred to each other.

[0023] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.

Claims

1. An aviation fuel heating system for high-temperature fuel dynamic sealing tests, characterized in that, include: The test chamber includes a dynamic sealing test chamber (1), a water-cooling device (2), a heat transfer oil mold temperature controller (3), and a control terminal (4). The dynamic sealing test chamber (1) contains a heat transfer oil heat exchange pipe (11) and aviation fuel for high-temperature dynamic sealing tests. An inlet valve (12) and an exhaust valve (13) are located on the top of the dynamic sealing test chamber (1). A first temperature sensor (14) is installed on the dynamic sealing test chamber (1) to monitor the temperature of the aviation fuel inside the dynamic sealing test chamber (1). The water-cooling device (2) is connected to the heat transfer oil mold temperature controller (3) and is used to cool the fuel. Water cools the heat transfer oil in the heat transfer oil mold temperature controller (3). The heat transfer oil mold temperature controller (3) is connected to the heat transfer oil heat exchange tube (11) to form a closed loop circuit for heat transfer oil. The heat transfer oil in the heat transfer oil heat exchange tube (11) is used to exchange heat with the aviation fuel in the dynamic sealing test chamber (1) to adjust the temperature of the aviation fuel. The control terminal (4) is connected to the water cooling device (2), the heat transfer oil mold temperature controller (3) and the first temperature sensor (14) to control the working status of the water cooling device (2) and the heat transfer oil mold temperature controller (3) according to the temperature information of the aviation fuel monitored by the first temperature sensor (14).

2. The aviation fuel heating system for high-temperature fuel dynamic sealing test according to claim 1, characterized in that: The water-cooling device (2) includes a water tank, a cooling fan, a second temperature sensor, and a water pump. The thermal oil mold temperature controller (3) includes a water-cooled heat exchange chamber, a thermal oil heating chamber, a third temperature sensor, and a thermal oil pump. The water tank is filled with cooling water and forms a closed loop with the water-cooled heat exchange chamber of the thermal oil mold temperature controller (3) through a first pipeline (5). The water pump is installed on the first pipeline (5). The cooling fan is used to cool the cooling water. The thermal oil heating chamber is connected to the thermal oil heat exchange tube through a second pipeline (6) to form a thermal oil closed loop. The thermal oil pump is installed on the second pipeline (6). The second temperature sensor and the third temperature sensor are both connected to the control terminal (4) and are used to detect the temperature information of the cooling water in the water tank and the temperature information of the thermal oil in the thermal oil heating chamber, respectively, and send them to the control terminal (4).

3. The aviation fuel heating system for high-temperature fuel dynamic sealing test according to claim 2, characterized in that: A first valve (51) and a second valve (61) are respectively provided on the first pipeline (5) and the second pipeline (6). The first valve (51) and the second valve (61) are both connected to the control terminal (4). The control terminal (4) is used to control the opening and closing of the first valve (51) and the second valve (61).

4. The aviation fuel heating system for high-temperature fuel dynamic sealing test according to claim 1, characterized in that: It also includes a high-pressure nitrogen cylinder (7), which is connected to the air inlet valve (12) through a third pipeline (8) for inputting high-pressure nitrogen into the dynamic sealing test chamber (1).

5. The aviation fuel heating system for high-temperature fuel dynamic sealing test according to claim 4, characterized in that: A first pressure sensor (81) is installed on the third pipeline (8) to monitor the pressure of nitrogen output from the high-pressure nitrogen cylinder (7).

6. The aviation fuel heating system for high-temperature fuel dynamic sealing test according to claim 1, characterized in that: The dynamic sealing test chamber (1) is also equipped with a second pressure sensor (15) for monitoring aviation fuel pressure.

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