CN117108399A - Novel thermal management layout of aviation air-cooled engine - Google Patents

Abstract

The technical scheme adopted for solving the technical problems is as follows: the utility model provides a novel thermal management overall arrangement of aviation forced air cooling engine which characterized in that: the engine comprises an engine body, a water tank, a water mist generator, an engine controller and a diversion channel; the invention has the beneficial effects that: the present invention designs a water mist generating system on current air (air) cooled engines. In the environment of the ground take-off, low-altitude accelerated flight or high-temperature operation of the aircraft, the water mist generating system generates water mist, and the water mist reaches a high-temperature part under the guidance of an air duct. The water mist is evaporated and gasified at the high temperature part to take away a large amount of heat, so that high-efficiency cooling is realized. Meanwhile, the water mist system belongs to weight reduction for the engine, the more the water mist system is used, the ground high-temperature enhanced cooling can be realized through accurate calculation, and no extra load is caused in a high-altitude cold environment. Thereby not only solving the requirement of intensified cooling, but also adding extra load to the minimum.

Description

Novel thermal management layout of aviation air-cooled engine

Technical Field

The invention belongs to the technical field of aero-engines, and particularly relates to a novel thermal management layout of an aero-air cooled engine.

Background

Because the aero-engine is complicated in climate environment, the ground at normal temperature is used to a cold high altitude, the environment temperature has a great influence on the reliable operation of the aero-engine from summer to winter and from a tropical zone to a cold zone, cooling needs to be enhanced at high temperature and the ground, and cooling needs to be limited at the high-cold high altitude, so how to realize effective thermal management is a great problem in the industry all the time.

The development trend of the aircraft is that the operation load is continuously increased, the aircraft and the aeroengine are continuously designed in a lightweight mode, and the wind (air) cooled engine is configured on the current aircraft in a large quantity due to simple structure and light weight. The air-cooled engine takes heat away by air flowing over the engine surface to cool. The fatal disadvantage of air cooling is that the cooling efficiency is low, and the cooling requirement of the engine under the high-temperature working condition is difficult to meet. Because the specific heat capacity of water is 4 times of that of air under the same mass condition, a liquid cooling mode is generally adopted for closed circulation cooling in other industries. However, if the liquid cooling system is added, the size and weight of the power pack structure are greatly changed, a liquid storage structure, a conveying structure, a heat dissipation structure and a large amount of cooling liquid are required to be added, the complexity of the engine is increased, the weight is greatly increased, and the layout design and the weight of the hanging aircraft are seriously affected. Meanwhile, in the high-altitude cruising environment without enhanced cooling, the liquid cooling system is a heavy burden.

Therefore, a more efficient cooling and controllable thermal management layout solution is needed for the use characteristics of air-cooled aeroengines.

Disclosure of Invention

The invention aims to provide a novel thermal management layout for an aero-air-cooled engine, which can realize thermal management control of high-temperature enhanced cooling and low-temperature air cooling according to the heat load characteristics of the aero-engine, and has the advantage of minimizing the influence on the design of an aircraft.

The design of the aviation air-cooled small engine thermal management scheme realizes the purposes of forced cooling in a high-temperature state and air cooling in a low-temperature state, controls the engine body temperature of the air-cooled engine in different environments, ensures the reliability of the engine and prolongs the service life.

The technical scheme adopted for solving the technical problems is as follows: the utility model provides a novel thermal management overall arrangement of aviation forced air cooling engine which characterized in that: the engine comprises an engine body, a water tank, a water mist generator, an engine controller and a diversion channel;

the water tank is a cooling water filling and storing structure, and the capacity of the water tank is calculated and determined according to the heat dissipation capacity of the engine. A liquid level sensor is arranged inside the water tank for monitoring the residual water quantity. When the water quantity is insufficient, the ECU outputs an alarm signal to remind the timely completion of water supplementing operation;

the water mist generator is a core structure for generating water mist and mainly comprises an electronic water pump, a water pipe and a high-pressure nozzle, wherein a controller is arranged in the electronic water pump, a required flow is input by an ECU (electronic control Unit), the electronic water pump calculates a required rotating speed based on the required flow so as to control a motor in the oil pump to rotate so as to pump cooling water in a water tank, the water pipe is pressurized, the pressurized high-pressure water is sprayed into air from a small hole of the nozzle to form water mist, and detailed size and performance parameters of each structure in the generator are determined through calculation and test according to an actual use scene;

the engine controller obtains the water capacity in the current water tank through a liquid level sensor and a temperature signal channel, judges whether the cooling is needed to be intensified and the required flow of the cooling is needed based on the current engine temperature ECU, when the engine temperature is higher than the required opening temperature, the electronic water pump operates based on the minimum flow, when the engine temperature is continuously increased, the closed-loop control based on the engine required temperature is performed based on the required flow, the higher the temperature is, the higher the required flow is, the higher the rotating speed of the electronic water pump is, the water quantity in the current water tank is calculated by the engine controller based on the liquid level sensor signal, the real-time feedback is fed to the flight control to monitor whether the water is needed to be added,

the flow guide channel is a ventilation channel under the condition of normal air cooling, air flows through the channel to dissipate heat of the surface of the engine, and water mist enters the channel to flow through the surface of the engine along with air flow after the water mist occurs, so that vaporization and heat dissipation are carried out.

The invention has the beneficial effects that: the present invention designs a water mist generating system on current air (air) cooled engines. In the environment of the ground take-off, low-altitude accelerated flight or high-temperature operation of the aircraft, the water mist generating system generates water mist, and the water mist reaches a high-temperature part under the guidance of an air duct. The water mist is evaporated and gasified at the high temperature part to take away a large amount of heat, so that high-efficiency cooling is realized. Meanwhile, the water mist system belongs to weight reduction for the engine, the more the water mist system is used, the ground high-temperature enhanced cooling can be realized through accurate calculation, and no extra load is caused in a high-altitude cold environment. Thereby not only solving the requirement of intensified cooling, but also adding extra load to the minimum.

The invention will be described in more detail below with reference to the drawings and examples.

Drawings

Fig. 1 is a schematic view of the structure of the invention.

In the figure: 1-a water tank 2-a water mist generator 3-an ECU control unit 4-a diversion channel 5-an engine body.

Detailed Description

The terms "upper," "lower," "inner," "outer," "front," "rear," "both ends," "one end," "the other end," and the like in this application are used in an orientation or positional relationship based on that shown in the drawings, merely to facilitate the description of the invention and to simplify the description, and do not indicate or imply that the devices or elements being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "provided," "connected," and the like are to be construed broadly, and may be fixedly connected, detachably connected, or integrally connected, for example; 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 invention will be understood in specific cases by those of ordinary skill in the art.

In the embodiment 1, as shown in fig. 1, a liquid level sensor is installed in a water tank 1, so that the water level in the water tank can be fed back to an engine controller, and the current water quantity is fed back in real time to prompt an operator whether water needs to be added.

The electronic water pump is used for pumping water in the water tank and delivering the water to the high-pressure nozzle through the water pipe, when the electronic water pump works, the water pressure in the water pipe of the water mist generator is increased, and when the water pressure is higher than the opening pressure of the high-pressure nozzle, the high-pressure nozzle is opened to spray water mist to the diversion channel;

the ECU receives a temperature signal transmitted by an engine temperature sensor, judges whether the cooling needs to be intensified and the required flow of the cooling needs to be intensified or not based on the current engine temperature, and when the engine temperature is higher than the required starting temperature, the electronic water pump operates based on the minimum flow, and when the engine temperature is continuously increased, closed-loop control is performed based on the required flow, and when the temperature is higher, the required flow is higher, and the rotating speed of the electronic water pump is higher;

the diversion channel 4 is designed based on an external flow field of the engine, and the design principle is that the contact surface of the diversion channel is maximum based on the contact of water mist with the engine body 5. The water mist flows along with the air, reaches the high-temperature part (cylinder) of the engine along the diversion channel 4, and fully contacts and gasifies with the air cooling radiating fins of the cylinder to absorb a large amount of heat, thereby completing heat exchange.

The present invention designs a water mist generating system on current air (air) cooled engines. In the environment of the ground take-off, low-altitude accelerated flight or high-temperature operation of the aircraft, the water mist generating system generates water mist, and the water mist reaches a high-temperature part under the guidance of an air duct. The water mist is evaporated and gasified at the high temperature part to take away a large amount of heat, so that high-efficiency cooling is realized. Meanwhile, the water mist system belongs to weight reduction for the engine, the more the water mist system is used, the ground high-temperature enhanced cooling can be realized through accurate calculation, and no extra load is caused in a high-altitude cold environment. Thereby not only solving the requirement of intensified cooling, but also adding extra load to the minimum.

The above examples are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art to the technical solution of the present invention should fall within the scope of protection defined by the claims of the present invention without departing from the spirit of the design of the present invention.

The invention is not related in part to the same as or can be practiced with the prior art.

Claims (1)

1. The utility model provides a novel thermal management overall arrangement of aviation forced air cooling engine which characterized in that: the engine comprises an engine body, a water tank, a water mist generator, an engine controller and a diversion channel;

the water tank is a cooling water filling and storing structure, and the capacity of the water tank is calculated and determined according to the heat dissipation capacity of the engine. A liquid level sensor is arranged inside the water tank for monitoring the residual water quantity. When the water quantity is insufficient, the ECU outputs an alarm signal to remind the timely completion of water supplementing operation;

the water mist generator is a core structure for generating water mist and mainly comprises an electronic water pump, a water pipe and a high-pressure nozzle, wherein a controller is arranged in the electronic water pump, a required flow is input by an ECU (electronic control Unit), the electronic water pump calculates a required rotating speed based on the required flow so as to control a motor in the oil pump to rotate so as to pump cooling water in a water tank, the water pipe is pressurized, the pressurized high-pressure water is sprayed into air from a small hole of the nozzle to form water mist, and detailed size and performance parameters of each structure in the generator are determined through calculation and test according to an actual use scene;

the engine controller obtains the water capacity in the current water tank through a liquid level sensor and a temperature signal channel, judges whether the cooling is needed to be intensified and the required flow of the cooling is needed based on the current engine temperature ECU, when the engine temperature is higher than the required opening temperature, the electronic water pump operates based on the minimum flow, when the engine temperature is continuously increased, the closed-loop control based on the engine required temperature is performed based on the required flow, the higher the temperature is, the higher the required flow is, the higher the rotating speed of the electronic water pump is, the water quantity in the current water tank is calculated by the engine controller based on the liquid level sensor signal, the real-time feedback is fed to the flight control to monitor whether the water is needed to be added,

the flow guide channel is a ventilation channel under the condition of normal air cooling, air flows through the channel to dissipate heat of the surface of the engine, and water mist enters the channel to flow through the surface of the engine along with air flow after the water mist occurs, so that vaporization and heat dissipation are carried out.