Device for improving jet flow precooling heat exchange effect by injecting incoming flow

Abstract

A device for improving jet flow pre-cooling heat exchange effect through incoming flow injection is based on a wing-shaped jet flow support, adopts the incoming flow injection technology, reduces the windward area by arranging a front edge opening at a standing point of the windward side of the support, avoids air pressure loss and air stagnation conditions, can introduce high-speed air flow at the front edge of the support into a cooling channel, and improves the jet flow pre-cooling heat exchange effect. The cooling fins in the cooling channel are used for cooling the high-speed air flow, and the cooled high-speed air flow can be guided to the two sides and the tail edge of the support respectively through three paths of shunting. Airflows on the two sides of the supports can be ejected in the direction perpendicular to the side wall faces of the supports, the jet flow can increase the spanwise speed and diffusion uniformity of cooling medium liquid drops, the liquid drops ejected oppositely between the adjacent supports collide, the particle size of the liquid drops can be reduced, and the jet flow precooling effect is further improved. And for airflow ejected from the tail edge of the support, backflow at the tail edge can be effectively reduced, generation of non-uniform wakes is further restrained, and the obvious improvement effect on reduction of support resistance and improvement of temperature distribution uniformity is achieved.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aero-engine inlet duct cooling technology, especially relates to a device for improving jet precooling heat exchange effect by inducing flow. BACKGROUND

[0002] Hypersonic aircraft has become one of the technical commanding heights in the field of aerospace, and high-speed aero-engine is the key to realize high Mach number flight of hypersonic aircraft. At present, the aero turbine engine mainly operates at 0~2 flight Mach numbers, and the sub-burning ramjet engine mainly operates at 3~6 flight Mach numbers. Therefore, any single engine cannot meet the power demand from low speed to super high speed.

[0003] Therefore, the concept of combining the aero turbine engine and the sub-burning ramjet engine to form a parallel engine (Turbine Based Combined Cycle, referred to as TBCC) is proposed. Although the TBCC engine integrates the advantages of the aero turbine engine and the sub-burning ramjet engine in their respective flight Mach ranges in technology, how to achieve the high Mach conversion point of the aero turbine engine and the sub-burning ramjet engine under the condition of flow matching has become the main problem of the aero turbine engine.

[0004] At present, the continuity of the TBCC engine mode conversion process still has defects, and it is necessary to improve the upper limit of the aero turbine engine to realize the smooth progress of the mode conversion. At present, the precooling of the flow air of the aero turbine engine is carried out, that is, the cooling medium is injected into the inlet duct, and the phase change heat absorption of the cooling medium is used to realize the jet precooling of the air, which is one of the effective means to improve the upper limit of the working performance of the aero turbine engine.

[0005] At present, in order to realize jet precooling, a plurality of jet supports with jet nozzles need to be arranged in the inlet duct, but the jet support will also have a hindering effect, which will directly cause the loss of air pressure and the stagnation of air, resulting in a low-speed high-temperature long tail in the tail of the jet support. This is obviously not conducive to the effect of jet precooling.

[0006] In addition, the particle size of the liquid droplets generated by the jet flow nozzle is small, so the following property of the liquid droplets is good, but this leads to a small spanwise velocity of the liquid droplets after being sprayed into the air intake, thereby leading to poor cooling uniformity, and since the traditional jet flow support does not consider the measure of increasing the penetration distance of the liquid droplets between the supports, the traditional jet flow support still has obvious deficiencies in dealing with air flow loss and heat exchange uniformity. In addition, the stagnation point on the windward surface of the traditional jet flow support will form a high temperature under the hindering effect, and this high temperature will also affect the service life and reliability of the jet flow support. Therefore, it is necessary to optimize the structure of the jet flow support to improve the jet flow precooling effect. Content of the utility model

[0007] In view of the problems existing in the prior art, the utility model provides a device for improving jet flow precooling heat exchange effect by ejecting incoming flow, which is based on a wing type jet flow support, adopts the ejecting incoming flow technology, and realizes a large reduction of the windward area of the wing type jet flow support by arranging a leading edge opening at the stagnation point on the windward surface of the wing type jet flow support, effectively avoids air pressure loss and air stagnation, and can introduce the high-speed airflow on the leading edge of the wing type jet flow support into the cooling channel, further cools the high-speed airflow by means of the cooling fins in the cooling channel, and the cooled high-speed airflow can be introduced into two sides of the wing type jet flow support and the trailing edge through three-way distribution. The airflow ejected from the two sides of the wing type jet flow support is perpendicular to the side wall surface of the support, and the jet flow can effectively increase the spanwise velocity of the liquid droplets, thereby effectively enhancing the diffusion uniformity of the liquid droplets, and the liquid droplets ejected from the adjacent wing type jet flow supports will collide due to the increase of the spanwise velocity, so that the liquid droplet size is further reduced through high-speed collision between the liquid droplets, and the further reduction of the liquid droplet size can effectively improve the jet flow precooling effect. The airflow ejected from the trailing edge of the wing type jet flow support can effectively reduce the backflow at the trailing edge, further inhibit the generation of non-uniform wake, and has obvious improvement effect on reducing the support resistance and improving the temperature distribution uniformity.

[0008] In order to achieve the above-mentioned purpose, the utility model adopts the following technical scheme: a device for improving jet flow precooling heat exchange effect by ejecting incoming flow, comprising a wing type jet flow support and an air intake, the number of wing type jet flow supports is several, and the several wing type jet flow supports are uniformly arranged along a straight line in the air intake; the spanwise ends of the wing type jet flow support are fixedly connected with the air intake through bolt fastening assemblies, a cooling medium channel is arranged in the wing type jet flow support, a plurality of jet flow nozzles are distributed on the two side walls of the wing type jet flow support, and the jet flow nozzles are in communication with the cooling medium channel; a cooling medium inlet is arranged at the spanwise end of the wing type jet flow support, and the cooling medium inlet is in communication with the cooling medium channel; and an ejecting incoming flow structure is arranged on the wing type jet flow support.

[0009] The ejecting flow structure comprises a leading edge opening, lateral openings and a trailing edge opening; the leading edge opening is arranged at the windward stagnation point of the leading edge of the airfoil jet support; the lateral openings are two in number and symmetrically arranged on the two side walls of the airfoil jet support, and jet nozzles are distributed on the front and rear sides of the lateral openings; and the trailing edge opening is arranged at the trailing edge of the airfoil jet support.

[0010] A cooling channel, a jet side channel and a jet tail channel are arranged inside the airfoil jet support; the leading edge opening is located at the air inlet side of the cooling channel and communicates with the same; the lateral openings are located at the air outlet side of the jet side channel and communicate with the same; the trailing edge opening is located at the air outlet side of the jet tail channel and communicates with the same; and the air outlet side of the cooling channel communicates with the air inlet sides of the jet side channel and the jet tail channel.

[0011] A plurality of cooling fins are arranged inside the cooling channel, the cooling fins are of a hollow structure, the internal cavities of the cooling fins are connected to the cooling medium, and the internal cavities of the cooling fins communicate with the cooling medium inlet through a hose.

[0012] The cooling fins are equidistantly and sequentially staggered along the chord length direction of the airfoil jet support.

[0013] The upper and lower ends of the cooling fins are connected to the airfoil jet support through springs, and the cooling fins have a rotational degree of freedom around the central axis of the spring.

[0014] A lateral flow adjusting baffle is arranged at the air inlet side of the jet side channel, and a lateral flow control motor is arranged at the spanwise end of the airfoil jet support, and the motor shaft of the lateral flow control motor is connected to the lateral flow adjusting baffle.

[0015] A trailing edge flow adjusting baffle is arranged at the air inlet side of the jet tail channel, and a trailing edge flow control motor is arranged at the spanwise end of the airfoil jet support, and the motor shaft of the trailing edge flow control motor is connected to the trailing edge flow adjusting baffle.

[0016] The length of the leading edge opening is 1% to 99% of the spanwise height of the airfoil jet support, and the width of the leading edge opening is 10% to 90% of the maximum width of the leading edge of the airfoil jet support; the length of the trailing edge opening is 1% to 99% of the spanwise height of the airfoil jet support, and the width of the trailing edge opening is 10% to 90% of the width of the trailing edge of the airfoil jet support.

[0017] A method for improving the jet precooling heat exchange effect by ejecting flow, which adopts the device for improving the jet precooling heat exchange effect by ejecting flow, specifically comprises the following steps:

[0018] The high-speed airflow in the inlet passage first enters the cooling channel through the leading edge opening, and further contacts the cooling fins to realize heat exchange cooling, and the cooling fins will be deflected under the impact of the high-speed airflow, thereby enabling the high-speed airflow to smoothly pass through the cooling channel; when the high-speed airflow moves to the air outlet side of the cooling channel, three-way flow separation is formed, two of which pass through the opened lateral flow regulating baffle into the jet side channel, and finally are ejected from the air outlet side of the jet side channel to the wing type jet support, at this time, the cooling medium liquid drops ejected from the jet nozzle will increase the spanwise velocity under the action of the airflow ejected from the jet side channel, so as to enhance the diffusion uniformity of the cooling medium liquid drops, and the cooling medium liquid drops ejected from the adjacent wing type jet supports will collide, so as to reduce the particle size of the cooling medium liquid drops, thereby further improving the jet precooling effect; for the last one of the three-way flow separation, it passes through the opened trailing edge flow regulating baffle into the jet tail channel, and finally is ejected from the air outlet side of the jet tail channel to the wing type jet support, so as to reduce the backflow at the trailing edge and further inhibit the generation of uneven wake.

[0019] The device has the advantages that:

[0020] The device for improving jet precooling heat exchange effect by ejecting incoming airflow is based on the wing type jet support, adopts the ejecting incoming airflow technology, realizes a large reduction of the windward area of the wing type jet support by arranging the leading edge opening at the stagnation point of the windward surface of the wing type jet support, effectively avoids the loss of air pressure and the air stagnation, and can introduce the high-speed airflow at the leading edge of the wing type jet support into the cooling channel, further cools the high-speed airflow by the cooling fins in the cooling channel, and the cooled high-speed airflow can be introduced to the two sides and the trailing edge of the wing type jet support through three-way flow separation; the airflow ejected from the two sides of the wing type jet support is perpendicular to the direction of the support side wall surface, which can effectively increase the spanwise velocity of the jet liquid drops, thereby effectively enhancing the diffusion uniformity of the liquid drops, and the liquid drops ejected from the adjacent wing type jet supports will collide due to the increase of the spanwise velocity, thereby further reducing the liquid drop size through the high-speed collision between the liquid drops, and the further reduction of the liquid drop size can effectively improve the jet precooling effect; the airflow ejected from the trailing edge of the wing type jet support can effectively reduce the backflow at the trailing edge and further inhibit the generation of uneven wake, which has obvious improvement effect on reducing the support resistance and improving the temperature distribution uniformity. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is a structural schematic view of the device for improving jet precooling heat exchange effect by ejecting incoming airflow.

[0022] Figure 2 It is a front view of the leading edge side of the wing type jet support.

[0023] Figure 3 For Figure 2 A-A sectional view in the middle;

[0024] In the figure, 1 - airfoil jet support, 2 - air inlet, 3 - bolt fastening assembly, 4 - jet nozzle, 5 - cooling medium inlet, 6 - leading edge opening, 7 - lateral opening, 8 - trailing edge opening, 9 - cooling channel, 10 - jet side channel, 11 - jet tail channel, 12 - cooling fin, 13 - spring, 14 - lateral flow regulating baffle, 15 - trailing edge flow regulating baffle, 16 - cooling medium channel. DETAILED DESCRIPTION

[0025] The utility model will be made further detailed explanation in combination with the drawings and specific embodiment.

[0026] As Figures 1 to 3 shown, a device for improving jet precooling heat exchange effect by ejecting incoming flow, comprising airfoil jet support 1 and air inlet 2, the airfoil jet support 1 is several, and several airfoil jet supports 1 are evenly arranged in air inlet 2 along a straight line;The airfoil jet support 1 is fixedly connected with air inlet 2 by bolt fastening assembly 3 at both ends of the span, and cooling medium channel 16 is formed in the airfoil jet support 1, and several jet nozzles 4 are distributed on the two side walls of the airfoil jet support 1, and the jet nozzle 4 is communicated with the cooling medium channel 16;Cooling medium inlet 5 is arranged at the spanwise end of the airfoil jet support 1, and the cooling medium inlet 5 is communicated with the cooling medium channel 16;The airfoil jet support 1 is provided with ejecting incoming flow structure.

[0027] The ejecting incoming flow structure comprises leading edge opening 6, lateral opening 7 and trailing edge opening 8;The leading edge opening 6 is arranged at the windward point of the leading edge of the airfoil jet support 1;The lateral opening 7 is two, and the two lateral openings 7 are symmetrically arranged on the two side walls of the airfoil jet support 1, and jet nozzles 4 are distributed on the front and rear sides of the lateral opening 7;The trailing edge opening 8 is arranged at the trailing edge of the airfoil jet support 1.

[0028] Cooling channel 9, jet side channel 10 and jet tail channel 11 are formed in the airfoil jet support 1;The leading edge opening 6 is located at the air inlet side of the cooling channel 9 and is communicated with the cooling channel 9;The lateral opening 7 is located at the air outlet side of the jet side channel 10 and is communicated with the jet side channel 10;The trailing edge opening 8 is located at the air outlet side of the jet tail channel 11 and is communicated with the jet tail channel 11;The air outlet side of the cooling channel 9 is communicated with the air inlet side of the jet side channel 10 and the jet tail channel 11.

[0029] A plurality of cooling fins 12 are arranged inside the cooling channel 9, the cooling fins 12 are hollow structures, the internal cavities of the cooling fins 12 are connected with the cooling medium inlet 5 through a hose.

[0030] The cooling fins 12 are equidistantly and sequentially staggered along the chord length direction of the airfoil jet support 1.

[0031] The upper and lower ends of the cooling fins 12 are connected with the airfoil jet support 1 through springs 13, and the cooling fins 12 have a rotational degree of freedom around the central axis of the spring 13.

[0032] A lateral flow adjusting baffle 14 is arranged at the air inlet side of the jet side channel 10, and a lateral flow adjusting motor is arranged at the spanwise end of the airfoil jet support 1, and the motor shaft of the lateral flow adjusting motor is connected with the lateral flow adjusting baffle 14.

[0033] A trailing edge flow adjusting baffle 15 is arranged at the air inlet side of the jet tail channel 11, and a trailing edge flow adjusting motor is arranged at the spanwise end of the airfoil jet support 1, and the motor shaft of the trailing edge flow adjusting motor is connected with the trailing edge flow adjusting baffle 15.

[0034] The length of the leading edge opening 6 is 1% to 99% of the spanwise height of the airfoil jet support 1, and the width of the leading edge opening 6 is 10% to 90% of the maximum width of the leading edge of the airfoil jet support 1; the length of the trailing edge opening 8 is 1% to 99% of the spanwise height of the airfoil jet support 1, and the width of the trailing edge opening 8 is 10% to 90% of the width of the trailing edge of the airfoil jet support 1.

[0035] In this embodiment, the length of the leading edge opening 6 is 85% of the spanwise height of the airfoil jet support 1, and the width of the leading edge opening 6 is 20% of the maximum width of the leading edge of the airfoil jet support 1; the length of the trailing edge opening 8 is 90% of the spanwise height of the airfoil jet support 1, and the width of the trailing edge opening 8 is 20% of the width of the trailing edge of the airfoil jet support 1; the cooling medium introduced by the cooling medium inlet 5 is water, and the particle size of the cooling medium droplets sprayed by the jet nozzle 4 is 30 μm; the opening of the lateral flow adjusting baffle 14 is adjusted to make the real-time flow of the jet side channel 10 reach 10% of the maximum flow of the jet side channel 10; the opening of the trailing edge flow adjusting baffle 15 is adjusted to make the real-time flow of the jet tail channel 11 reach 10% of the maximum flow of the jet tail channel 11.

[0036] A method for improving the jet precooling heat exchange effect by inducing the flow, which adopts the device for improving the jet precooling heat exchange effect by inducing the flow, specifically comprising:

[0037] The high-speed airflow in the air inlet channel 2 first enters the cooling channel 9 through the leading edge opening 6, and further contacts the cooling fin 12 to realize heat exchange cooling, and the cooling fin 12 is deflected under the impact of the high-speed airflow, so that the high-speed airflow smoothly passes through the cooling channel 9; when the high-speed airflow moves to the air outlet side of the cooling channel 9, three-way flow separation is formed, two of which pass through the opened lateral flow regulating baffle 14 into the jet side channel 10, and finally are ejected from the airfoil jet support 1 through the air outlet side of the jet side channel 10; at this time, the cooling medium droplets ejected from the jet ejection port 4 will increase the spanwise velocity under the action of the airflow ejected from the jet side channel 10, so as to enhance the diffusion uniformity of the cooling medium droplets, and the cooling medium droplets ejected from the adjacent airfoil jet supports 1 will collide with each other, so as to reduce the particle size of the cooling medium droplets, thereby further improving the jet pre-cooling effect; for the last one of the three-way flow separation, it will pass through the opened trailing edge flow regulating baffle 15 into the jet tail channel 11, and finally be ejected from the airfoil jet support 1 through the air outlet side of the jet tail channel 11, so as to reduce the backflow at the trailing edge and further suppress the generation of uneven wake.

[0038] The scheme in the embodiment is not used to limit the protection scope of the utility model, and any equivalent implementation or change without departing from the utility model is included in the protection scope of the utility model.

Claims

1. A device for improving the heat exchange effect of a jet precooling by means of an ejector, characterized in that: The air inlet channel comprises airfoil jet support frames and an air inlet channel, the airfoil jet support frames are uniformly arranged along a straight line in the air inlet channel, the airfoil jet support frames are fixedly connected with the air inlet channel through bolt fastening assemblies at both spanwise ends of the airfoil jet support frames, a cooling medium channel is formed in the airfoil jet support frames, a plurality of jet nozzles are arranged on the two side walls of the airfoil jet support frames and are in communication with the cooling medium channel, a cooling medium inlet is arranged at the spanwise end of the airfoil jet support frame and is in communication with the cooling medium channel, and an ejecting incoming flow structure is arranged on the airfoil jet support frame.

2. The device for improving the heat exchange effect of a jet flow by pre-cooling according to claim 1, characterized in that: The ejecting incoming flow structure comprises a leading edge opening, lateral openings and a trailing edge opening, the leading edge opening is arranged at the windward point of the leading edge of the airfoil jet support frame, the lateral openings are arranged symmetrically on the two side walls of the airfoil jet support frame, and jet nozzles are arranged on the front and rear sides of the lateral openings, and the trailing edge opening is arranged at the trailing edge of the airfoil jet support frame.

3. The device for improving the heat exchange effect of a jet flow by pre-cooling according to claim 2, characterized in that: A cooling channel, a jet side channel and a jet tail channel are formed in the airfoil jet support frame, the leading edge opening is arranged at the air inlet side of the cooling channel and is in communication with the cooling channel, the lateral openings are arranged at the air outlet side of the jet side channel and are in communication with the jet side channel, the trailing edge opening is arranged at the air outlet side of the jet tail channel and is in communication with the jet tail channel, and the air outlet side of the cooling channel is in communication with the air inlet sides of the jet side channel and the jet tail channel.

4. The device for improving the heat exchange effect of a jet flow by pre-cooling according to claim 3, characterized in that: A plurality of cooling fins are arranged in the cooling channel, the cooling fins are hollow structures, the internal cavities of the cooling fins are in communication with the cooling medium, and the internal cavities of the cooling fins are in communication with the cooling medium inlet through a hose.

5. The device for improving the heat exchange effect of a jet flow by pre-cooling according to claim 4, characterized in that: The cooling fins are equidistantly and sequentially staggered in the chord direction of the airfoil jet support frame.

6. The device for improving the heat exchange effect of a jet flow by pre-cooling according to claim 4, characterized in that: The upper and lower ends of the cooling fins are connected with the airfoil jet support frame through springs, and the cooling fins have a rotational degree of freedom around the central axis of the spring.

7. The device for improving the heat exchange effect of a jet flow by pre-cooling according to claim 3, characterized in that: A lateral flow adjusting baffle is arranged at the air inlet side of the jet side channel, and a lateral flow control motor is arranged at the spanwise end of the airfoil jet support frame, and the motor shaft of the lateral flow control motor is connected with the lateral flow adjusting baffle.

8. The device for improving the heat exchange effect of a jet flow by pre-cooling according to claim 3, characterized in that: A trailing edge flow adjusting baffle is arranged at the air inlet side of the jet tail channel, and a trailing edge flow control motor is arranged at the spanwise end of the airfoil jet support frame, and the motor shaft of the trailing edge flow control motor is connected with the trailing edge flow adjusting baffle.

9. The device for improving the heat exchange effect of a jet flow by pre-cooling according to claim 2, characterized in that: The length of the leading edge opening is 1% to 99% of the spanwise height of the airfoil jet support frame, and the width of the leading edge opening is 10% to 90% of the maximum width of the leading edge of the airfoil jet support frame, the length of the trailing edge opening is 1% to 99% of the spanwise height of the airfoil jet support frame, and the width of the trailing edge opening is 10% to 90% of the width of the trailing edge of the airfoil jet support frame.

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