CN107223003A - A kind of cold cooling device of liquid of the high-power self coupling vertoro of civil aircraft - Google Patents

Abstract

The invention relates to the technical field of aircraft transformer rectifier cooling, and provides a liquid-cooled cooling device for a high-power autotransformer rectifier of a civil aircraft, including a liquid-cooled back plate and a liquid-cooled flow channel; Including autotransformer, rectifier bridge, capacitors, resistors; heat-generating components are set on one side of the liquid-cooled backplane; liquid-cooled channels are set on the other side of the liquid-cooled backplane opposite to the heat-generating components, and the liquid-cooled channels include transformers connected in sequence Section, rectifier bridge section, capacitor section, resistance section; the liquid inlet and outlet of the liquid cooling channel are integrated together to form a liquid cooling interface. The beneficial effects of the present invention are: high heat dissipation efficiency, reducing the weight of the entire autotransformer rectifier; eliminating the influence of noise, increasing the power-to-weight ratio, and helping to improve the economy of large civil aircraft; the input and output nozzles are integrated in a liquid-cooled On the interface, it is more conducive to the integrated installation of the autotransformer rectifier and other liquid cooling equipment; the structure is simple and the application prospect is broad.

Description

A liquid cooling device for a high-power autotransformer rectifier of a civil aircraft

technical field

The invention relates to the technical field of cooling of aircraft transformer rectifiers, in particular to a liquid cooling device for high-power autotransformer rectifiers of civil aircraft.

Background technique

With the continuous development of multi-power technology, the power supply capacity and voltage level of large civil aircraft continue to increase. With the increasing number of electrical equipment on the aircraft, the capacity of the power conversion device that converts the primary power supply and supplies power to the load has increased significantly. , and the corresponding heat dissipation is also increasing.

Traditional narrow-body civil aircraft power conversion devices have low power. For example, the C919 airliner has two power conversion devices, the transformer rectifier (TRU) and the static converter (INV). The power of the transformer rectifier is 9.8kW, and the heat dissipation is 1470W. The static converter has a capacity of 1kVA and a heat dissipation of 200W, all of which adopt forced air cooling for heat dissipation, while the high-power electric energy conversion device autotransformer rectifier (ATRU) used in civil multi-electric aircraft has a power of 165kW and a heat dissipation requirement of 3300W , which is far greater than the heat dissipation requirements of traditional narrow-body civil aircraft power conversion devices. If the traditional forced air cooling method is adopted, not only the volume and weight of the designed autotransformer rectifier will be larger, but the weight of the aircraft will be increased to increase the design difficulty. The fan noise will also be loud, affecting passenger comfort.

In addition, judging from the current patent retrieval and technical paper research, it is still blank to use liquid cooling for the heat dissipation of high-power autotransformer rectifiers on domestic civil aircraft. In foreign countries, there are similar high-power autotransformer rectifiers, which use uniformly distributed micro-channels for fluid circulation and heat dissipation. Please refer to the patent application WO2016134230A1, which discloses an ATRU liquid cooling, including a liquid cooling backplane and a liquid cooling interface. There are some deficiencies in the heat dissipation device: no design and calculation of hot spots will lead to an increase in the volume of the internal liquid cooling pipes, which will not be able to effectively dissipate heat from the hot spots, will increase the volume of the radiator, and then increase the volume and weight of the device; application In the field of civil aircraft, the different positions of the liquid inlet and outlet in the device will increase the volume occupied by the external liquid cooling pipe; the microchannel design increases the difficulty of design and processing.

Contents of the invention

The purpose of the present invention is to overcome the deficiencies of the prior art and provide a liquid-cooled cooling device for a high-power autotransformer rectifier of a civil aircraft. , so that the heat generated is effectively taken away by the coolant.

The present invention is a liquid-cooled cooling device for a high-power autotransformer rectifier of a civil aircraft, comprising a liquid-cooled backplane and a liquid-cooled flow channel; the heating components of the autotransformer rectifier include an autotransformer, a rectifier bridge, a capacitor, Resistance; the heating component is arranged on one side of the liquid-cooled backplane; the liquid-cooled channel is arranged on the other side of the liquid-cooled backplane opposite to the heating component, and the liquid-cooled channel includes sequentially connected The transformer section, the rectifier bridge section, the capacitor section, and the resistor section; the liquid inlet and outlet of the liquid cooling channel are integrated together to form a liquid cooling interface.

Further, the transformer section, the rectifier bridge section, the capacitor section, and the resistor section are sequentially connected in series.

Further, the transformer section, rectifier bridge section, capacitor section, and resistor section are all single or multi-branched.

Further, the liquid-cooled flow channel is an internal flow channel of the liquid-cooled backplane, and the material is aluminum alloy.

Further, the liquid-cooled backplane is made of aluminum alloy.

The beneficial effects of the present invention are:

1. By designing the hot spot distribution of heat dissipation components, heat dissipation can be carried out in a more targeted manner. Reasonable design of the flow channel of the liquid-cooled backplane inside the high-power autotransformer rectifier can improve the heat exchange efficiency of heat-generating components and cooling liquid , effectively take away the heat, reduce the size of the liquid cooling pipe used, and reduce the weight of the entire autotransformer rectifier;

2. Compared with forced air cooling, the introduction of liquid cooling can reduce or even eliminate the impact of noise, improve the power-to-weight ratio, and help improve the economy of large civil aircraft;

3. Different from the input interface and output interface of the general ground civilian liquid cooling equipment located in different positions of the radiator, the input and output nozzles of the present invention are integrated on one liquid cooling interface, which is more conducive to the connection between the autotransformer rectifier and other liquid cooling devices. The integrated installation of equipment is conducive to reducing the volume of the switchboard box and supporting its optimized design;

4. The structure is simple and the application prospect is broad.

Description of drawings

Figure 1 shows a schematic diagram of the distribution of heating components in an autotransformer rectifier.

Fig. 2 is a schematic diagram showing the principle of the flow path of the liquid-cooled backplane of the autotransformer rectifier.

Fig. 3 is a diagram of the internal liquid-cooling flow path of the autotransformer rectifier in the embodiment of the present invention.

Among them: 1-autotransformer, 2-rectifier bridge, 3-capacitor, 4-resistor, 5-liquid-cooled backplane, 6-liquid-cooled runner, 61-transformer section, 62-rectifier bridge section, 63-capacitor section , 64-resistance section, 65-liquid cooling interface.

detailed description

Specific embodiments of the present invention will be described in detail below in conjunction with specific drawings. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be regarded as isolated, and they can be combined with each other to achieve better technical effects. In the drawings of the following embodiments, the same reference numerals appearing in each drawing represent the same features or components, which can be applied in different embodiments.

As shown in Figures 1-3, an embodiment of the present invention is a liquid-cooled cooling device for a high-power autotransformer rectifier of a civil aircraft, including a liquid-cooled backplane 5 and a liquid-cooled flow channel 6; the autotransformer rectifier The heating components include an autotransformer 1, a rectifier bridge 2, a capacitor 3, and a resistor 4; the heating components are arranged on one side of the liquid-cooled backplane 5; the liquid-cooled flow channel 6 is arranged on the liquid-cooled backplane 5 On the other side opposite to the heat-generating components, the liquid-cooled flow channel 6 is the internal flow channel of the liquid-cooled back plate 5, which is milled out of the entire aluminum alloy according to the direction of the flow channel designed at the power generation point, and then used The aluminum alloy 2A12 of the same material is covered above the flow channel, and the two aluminum alloys are joined by friction stir welding to form a closed flow channel. The reason for using aluminum alloy is that the airborne liquid cooling equipment generally requires a normal working pressure of 1MPa , a safe working pressure of 2 MPa, this type of aluminum alloy can meet the strength requirements through simulation verification, the liquid cooling channel 6 includes a transformer section 61, a rectifier bridge section 62, a capacitor section 63, and a resistor section 64 connected in sequence; The liquid inlet port and the liquid outlet port of the liquid cooling channel 6 are integrated together to form a liquid cooling interface 65 .

The transformer section 61 , the rectifier bridge section 62 , the capacitor section 63 and the resistor section 64 are sequentially connected in series. The transformer section 61, the rectifier bridge section 62, the capacitor section 63, and the resistor section 64 are all single or multi-branched.

The heat dissipation area of the high-power autotransformer is the hot spots such as the autotransformer 1, the rectifier bridge 2, the capacitor 3, and the resistor 4. The flow channel path principle of the liquid-cooled backplane 5 of the autotransformer rectifier is shown in FIG. 2 .

The heat dissipation method of the autotransformer rectifier of the high-power electric energy conversion device adopts a liquid-cooled cooling method. The cooling liquid flows in from the liquid cooling source through the liquid inlet, and flows through the hot spot area in the autotransformer rectifier calculated by design. Then flow out from the outlet. Among them, the heat-generating components in the autotransformer rectifier are installed on the liquid-cooled backplane 5, and one liquid inlet and one liquid outlet are integrated together to form the liquid-cooled interface 65 of the high-power autotransformer rectifier. The key is to reasonably design the flow channel of the liquid-cooled backplane 5 inside the autotransformer rectifier.

The coolant enters the inlet of the liquid-cooled backplane 5 of the autotransformer rectifier, flows through the heating area of the capacitor 3, the heating area of the resistor 4, the heating area of the autotransformer 1, the heating area of the rectifier bridge 2, and the heating area of the capacitor 3, and then flows from the liquid Outflow from outlet 5 of the cold backplane. This cycle is repeated to take away the heat of the autotransformer rectifier.

An embodiment is proposed for the device of the present invention. Aiming at the distribution of heating points of the autotransformer rectifier in FIG. 1 , the designed liquid-cooled flow channel 6 of the liquid-cooled backplane 5 is shown in FIG. 3 .

The coolant enters the liquid-cooled backplane 5 inlet of the autotransformer rectifier, flows through the heating area of the capacitor 3, and enters the heating area of the resistor 4 in two ways. After summarizing, it enters the heating area of the autotransformer 1, the rectifier bridge 2, the capacitor 3 heat-generating area, and then flow out from outlet 5 of the liquid-cooled backplane.

The liquid-cooled realization process of the autotransformer rectifier described in the present invention is the embodiment of the invention, and the liquid-cooled backplane 5 and the liquid-cooled flow channel 6 finally realized are designed as an example, because of the necessary technical characteristics of the flow channel design Extensive, so the embodiment described above is only a product of the technical solution applied for protection, and all liquid-cooled cooling methods for autotransformer rectifiers using the above ideas should be included in the protection.

The beneficial effects of the present invention are:

1. By designing the hot spot distribution of heat dissipation components, heat dissipation can be carried out in a more targeted manner. Reasonable design of the flow channel of the liquid-cooled backplane inside the high-power autotransformer rectifier can improve the heat exchange efficiency of heat-generating components and cooling liquid , effectively take away the heat, reduce the size of the liquid cooling pipe used, and reduce the weight of the entire autotransformer rectifier;

2. Compared with forced air cooling, the introduction of liquid cooling can reduce or even eliminate the impact of noise, improve the power-to-weight ratio, and help improve the economy of large civil aircraft;

3. Different from the input interface and output interface of the general ground civilian liquid cooling equipment located in different positions of the radiator, the input and output nozzles of the present invention are integrated on one liquid cooling interface, which is more conducive to the connection between the autotransformer rectifier and other liquid cooling devices. The integrated installation of equipment is conducive to reducing the volume of the switchboard box and supporting its optimized design;

4. The structure is simple and the application prospect is broad.

Although several embodiments of the present invention have been given herein, those skilled in the art should understand that the embodiments herein can be changed without departing from the spirit of the present invention. The above-mentioned embodiments are only exemplary, and the embodiments herein should not be used as limitations on the scope of rights of the present invention.

Claims (5)

1. A liquid-cooled cooling device for a civil aircraft high-power autotransformer rectifier, characterized in that it comprises a liquid-cooled backboard and a liquid-cooled runner; the heating parts of the autotransformer rectifier include autotransformers, rectifiers bridges, capacitors, and resistors; the heat-generating components are arranged on one side of the liquid-cooled backplane; the liquid-cooled flow channels are arranged on the other side of the liquid-cooled backplane The channel includes a transformer section, a rectifier bridge section, a capacitor section, and a resistor section connected in sequence; the liquid inlet and outlet of the liquid cooling channel are integrated together to form a liquid cooling interface. 2. The liquid cooling device according to claim 1, wherein the transformer section, the rectifier bridge section, the capacitor section, and the resistor section are sequentially connected in series. 3. The liquid cooling device according to claim 1, wherein the transformer section, the rectifier bridge section, the capacitor section, and the resistor section are all single or multiple. 4. The liquid-cooled cooling device according to any one of claims 1-3, wherein the liquid-cooled flow channel is an internal flow channel of a liquid-cooled backplane, and the material is aluminum alloy. 5. The liquid cooling device according to any one of claims 1-3, wherein the material of the liquid cooling back plate is aluminum alloy.