阅读说明：本技术 一种航空制冷涡轮冷热介质混合结构 (Cold and hot medium mixed structure of aviation refrigeration turbine ) 是由 闫周易 张运瑞 冯有军 刘俊峰 刘芳芳 付旭东 袁庆燕 于 2020-10-30 设计创作，主要内容包括：本发明涉及飞行器环境控制技术领域,具体提供一种航空制冷涡轮冷热介质混合结构,所述航空制冷涡轮冷热介质混合结构包括环形壳体和中心管；所述环形壳体套装在中心管外环形成环形腔体,所述环形壳体开有热介质导入通孔；所述中心管用于流通冷介质；所述中心管位于所述环形腔体的管壁部分开有至少一个导气通孔；所述导气通孔为斜孔,所述斜孔在中心管内壁的开口方向与所述中心管的流通方向所呈空间夹角α为锐角。本发明的防冰热路混合结构,可以使航空环控系统在结冰工况下,提升防冰热路空气与冷空气混合后温度场的均匀性,降低下游控制反馈用的温度传感器周围的温度波动,提高混合温度控制精度,避免制冷涡轮出口空气结冰,提升涡轮和下游产品的使用寿命。(The invention relates to the technical field of aircraft environment control, and particularly provides an aviation refrigeration turbine cold and hot medium mixing structure which comprises an annular shell and a central tube, wherein the annular shell is arranged in the annular shell; the annular shell is sleeved outside the central pipe to form an annular cavity, and a heat medium leading-in through hole is formed in the annular shell; the central pipe is used for circulating a cold medium; the pipe wall part of the central pipe, which is positioned in the annular cavity, is provided with at least one air guide through hole; the air guide through holes are inclined holes, and the space included angle alpha formed by the opening direction of the inclined holes on the inner wall of the central tube and the flowing direction of the central tube is an acute angle. The anti-icing hot circuit mixing structure can improve the uniformity of a temperature field after air and cold air of an anti-icing hot circuit are mixed under the icing condition of an aviation environmental control system, reduce the temperature fluctuation around a temperature sensor for downstream control feedback, improve the control precision of mixed temperature, avoid the icing of the air at the outlet of a refrigeration turbine and prolong the service life of the turbine and downstream products.)

1. The utility model provides an aviation refrigeration turbine cold and hot medium mixed structure which characterized in that: the aviation refrigeration turbine cold and hot medium mixing structure comprises an annular shell (1) and a central pipe (2);

the annular shell 1 is sleeved outside the central tube (2) to form an annular cavity, and a heat medium leading-in through hole is formed in the annular shell; the central pipe is used for circulating a cold medium; the central pipe (2) is provided with at least one air guide through hole at the pipe wall part of the annular cavity; the air guide through hole is an inclined hole (3), and a space included angle alpha formed by the opening direction of the inclined hole on the inner wall of the central tube and the flowing direction of the central tube is an acute angle.

2. The aircraft refrigeration turbine cold and hot medium mixing structure as recited in claim 1, wherein: establishing a rectangular coordinate system by taking the opening central point of the inclined hole on the inner wall of the central tube as an origin, wherein an xy plane of the rectangular coordinate system is a section of the central tube, and a yz plane of the rectangular coordinate system is a plane passing through the opening central point and the tube central line; the y axis is the intersection line of the xy plane and the yz plane, the opening direction of the inclined hole on the inner wall of the central tube and the y axis of the coordinate system form an included angle beta of 20-89 degrees, and the projection angle gamma of the space included angle alpha on the yz plane is 1-89 degrees.

3. The aircraft refrigeration turbine cold and hot medium mixing structure as recited in claim 1, wherein: the number of the air guide through holes is a plurality of and the air guide through holes are distributed annularly.

4. An aviation refrigeration turbine cold and hot medium mixing structure as recited in claim 3, wherein: are distributed in a uniform ring shape.

5. An aviation refrigeration turbo-cooling heat medium mixing structure as recited in any one of claims 1 to 4, wherein: the sum of the open cross-sectional areas of the air guide through holes is smaller than the cross-sectional area of the heat medium introduction through hole.

6. An aviation refrigeration turbo-cooling heat medium mixing structure as recited in any one of claims 1 to 5, wherein: the number of the air guide through holes is a plurality of and the air guide through holes are distributed spirally.

7. An aviation refrigeration turbo-cooling heat medium mixing structure as recited in any one of claims 1 to 6, wherein: the thickness of the central tube 2 on the tube wall part of the annular cavity is more than 2 MM.

8. An aviation refrigeration turbo-cooling heat medium mixing structure as recited in any one of claims 1 to 7, wherein: the front end port of the central pipe is a refrigerating turbine outlet, and the annular shell and the refrigerating turbine volute are integrally formed.

9. An aviation refrigeration turbo-cooling heat medium mixing structure as recited in any one of claims 1 to 8, wherein: the annular shell is a volute shell.

10. An aviation refrigeration turbo-cooling heat medium mixing structure as recited in any one of claims 1 to 9, wherein: the annular shell and the central tube are made of aluminum alloy, titanium alloy or stainless steel.

Technical Field

The invention relates to the technical field of aircraft environment control, in particular to a cold and hot medium mixing structure of an aviation refrigeration turbine.

Background

In the refrigeration subsystem of the aircraft environmental control system, in order to prevent the air at the outlet of the refrigeration turbine from freezing and damaging products, hot air needs to be introduced under the freezing working condition for mixing, so that ice is melted. The temperature of the used anti-icing hot air is above 300 ℃, and in order to prevent the performance of a refrigeration subsystem from being reduced, passengers from being scalded or the introduced hot air from being insufficient due to the introduction of excessive hot air, the system is frozen to damage products, and the flow of the anti-icing hot air is adjusted in an automatic control mode. The anti-icing hot air flow automatic control device adopts temperature signal feedback adjustment, the temperature sensor is arranged at the downstream of the hot air mixing device at the outlet of the refrigeration turbine, the temperature of a medium at the temperature sensor fluctuates due to uneven temperature mixing, a control system based on the temperature feedback of the sensor cannot stably work, the anti-icing hot air flow fluctuates, the outlet of the refrigeration turbine is frequently frozen and blocked, and the product failure rate is high. The situation of uneven temperature mixing can be improved by adding the mechanical cyclone at the downstream of the hot air mixing device, but the aircraft has high requirements on weight and space, and the mechanical cyclone is not arranged in space, so technical innovation is needed.

Disclosure of Invention

The purpose of the invention is as follows: the technical problems that the turbine outlet of the aviation environmental control system is at a low-temperature working condition, the working condition near a temperature sensor fluctuates, the control of the air supply amount of anti-icing hot air is not accurate, air is frequently iced, and a turbine and a downstream product are damaged are solved.

Technical scheme

The aviation refrigeration turbine cold and hot medium mixing structure comprises an annular shell 1 and a central pipe 2;

the annular shell 1 is sleeved outside the central tube 2 to form an annular cavity, and a heat medium leading-in through hole is formed in the annular shell; the central pipe is used for circulating a cold medium; the part of the central tube 2, which is positioned on the tube wall of the annular cavity, is provided with at least one air guide through hole; the air guide through holes are inclined holes, and the space included angle alpha formed by the opening direction of the inclined holes on the inner wall of the central tube and the flowing direction of the central tube is an acute angle.

Further, a rectangular coordinate system is established by taking the opening center point of the inclined hole on the inner wall of the central tube as an origin, the xy plane of the rectangular coordinate system is the section of the central tube, and the yz plane is the plane passing through the opening center point and the tube center line; the y axis is the intersection line of the xy plane and the yz plane, the opening direction of the inclined hole on the inner wall of the central tube and the y axis of the coordinate system form an included angle beta of 20-89 degrees, and the projection angle gamma of the space included angle alpha on the yz plane is 1-89 degrees. The projection angle beta is not less than 20 degrees, so that the blending track of the heat medium entering the central tube 2 is spiral and used for enhancing the blending effect, and the projection angle gamma is less than 90 degrees, so that the flow resistance generated by blending is reduced.

Furthermore, the number of the air guide through holes is multiple and the air guide through holes are distributed annularly. Preferably, in a uniform annular distribution.

Furthermore, the sum of the open cross-sectional areas of the air guide through holes is smaller than the cross-sectional area of the heat medium leading-in through hole. The purpose is to improve the flow velocity of the heat medium entering the central tube at the air guide through hole and strengthen the mixing effect.

Furthermore, the number of the air guide through holes is multiple and the air guide through holes are distributed spirally.

Further, the thickness of the pipe wall part of the central pipe 2 positioned in the annular cavity is more than 2 MM. The sufficient wall thickness can realize the direction of the air current, and the sufficient wall thickness can make the inclined hole form an oblique direction passageway.

Further, the front end port of the central pipe is a refrigerating turbine outlet, and the annular shell and the refrigerating turbine volute are integrally formed. Preferably, the annular housing is a volute housing.

Working principle of the invention

When the refrigeration turbine works under the icing condition, the anti-icing hot gas enters the annular cavity from the heat medium leading-in through hole and then enters the central tube from the air guide through hole, the anti-icing hot gas entering the central tube flows along a spiral track and is mixed with cold air in the central tube, the flow area of the air guide through hole is smaller than that of the heat medium leading-in through hole, the anti-icing hot gas can accelerate when passing through the air guide through hole, and a stronger mixing effect is generated; after the mixing effect of the cold air and the hot air is improved, the uniformity of the mixed air temperature field is improved, the temperature fluctuation around a temperature sensor for downstream control feedback can be reduced, the control precision of the mixed temperature is improved, the air at the outlet of a refrigeration turbine is prevented from being frozen, and the service lives of the refrigeration turbine and downstream products are prolonged; the annular cavity can be combined with the outlet shell of the refrigeration turbine into a double-layer shell, so that the axial length of the airborne equipment can be shortened, and the weight of the airborne equipment can be reduced.

Advantageous effects

By adopting the anti-icing hot circuit mixing structure, the uniformity of a temperature field after the air of the anti-icing hot circuit and the cold air are mixed can be improved under the icing condition of an aviation environmental control system, the temperature fluctuation around a temperature sensor for downstream control feedback is reduced, the mixed temperature control precision is improved, the air at the outlet of a refrigeration turbine is prevented from being iced, and the service lives of the turbine and downstream products are prolonged. Meanwhile, after the annular cavity and the rear shell of the refrigeration turbine are combined into a double-layer shell, the axial length of the airborne equipment can be shortened, the weight of the airborne equipment is reduced, and the fuel consumption condition of the airplane is improved.

Drawings

FIG. 1 is a schematic diagram of a mixed structure of a cold and hot medium of an aviation refrigeration turbine of the invention;

FIG. 2 is a cross-sectional view of FIG. 1;

FIG. 3 is a schematic view of example 1;

FIG. 4 is a schematic view of example 2;

wherein: the heat medium cooling system comprises a 1-annular shell, a 2-central tube, a 3-heat medium leading-in through hole, a 4-air guide through hole, a 5-cold medium flowing direction, a 6-heat medium flowing direction, a 7-air guide through hole axis, an 8-included angle alpha, a 9-rectangular coordinate system xy plane, a 10-yz plane, an 11-included angle beta and a 12-projection angle gamma.

Detailed Description

Embodiment 1, referring to fig. 1 and 3, there is provided an aviation refrigeration turbo-cooling and heating medium mixing structure, which includes an annular housing 1 and a central tube 2;

the annular shell 1 is sleeved outside the central tube 2 to form an annular cavity, and a heat medium leading-in through hole is formed in the annular shell; the central pipe is used for circulating a cold medium; the part of the central tube 2, which is positioned on the tube wall of the annular cavity, is provided with at least one air guide through hole; the air guide through holes are inclined holes, and the space included angle alpha formed by the opening direction of the inclined holes on the inner wall of the central tube and the flowing direction of the central tube is an acute angle.

Establishing a rectangular coordinate system by taking the opening central point of the inclined hole on the inner wall of the central tube as an origin, wherein an xy plane of the rectangular coordinate system is a section of the central tube, and a yz plane of the rectangular coordinate system is a plane passing through the opening central point and the tube central line; the y axis is an intersection line of the xy plane and the yz plane, an included angle beta between the opening direction of the inclined hole on the inner wall of the central tube and the y axis of the coordinate system is 45 degrees, and a projection angle gamma of the space included angle alpha on the yz plane is 30 degrees.

The number of the air guide through holes is 8, and the air guide through holes are uniformly and annularly distributed.

The thickness of the central tube 2 on the tube wall part of the annular cavity is 3 MM.

Embodiment 2, referring to fig. 1 and 4, there is provided an aviation refrigeration turbo-cooling and heating medium mixing structure, which includes an annular housing 1 and a central tube 2;

the annular shell 1 is sleeved outside the central tube 2 to form an annular cavity, and a heat medium leading-in through hole is formed in the annular shell; the central pipe is used for circulating a cold medium; the part of the central tube 2, which is positioned on the tube wall of the annular cavity, is provided with at least one air guide through hole; the air guide through holes are inclined holes, and the space included angle alpha formed by the opening direction of the inclined holes on the inner wall of the central tube and the flowing direction of the central tube is an acute angle.

Establishing a rectangular coordinate system by taking the opening central point of the inclined hole on the inner wall of the central tube as an origin, wherein an xy plane of the rectangular coordinate system is a section of the central tube, and a yz plane of the rectangular coordinate system is a plane passing through the opening central point and the tube central line; the y axis is an intersection line of the xy plane and the yz plane, an included angle beta between the opening direction of the inclined hole on the inner wall of the central tube and the y axis of the coordinate system is 60 degrees, and a projection angle gamma of the space included angle alpha on the yz plane is 45 degrees.

The number of the air guide through holes is 10, and the air guide through holes are uniformly and annularly distributed.

The central tube 2 is located in the wall part thickness 4MM of the annular cavity.

The front end port of the central pipe is a refrigerating turbine outlet, and the annular shell and the refrigerating turbine volute are integrally formed. The annular shell is a volute shell.