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A Low Infrared Characteristic Lobe Ejection and Mixing Device for Binary Nozzle Outlet

A binary nozzle and mixing device technology, applied in the direction of jet propulsion devices, machines/engines, etc., can solve the problems of limited cold air flow, no ejection channel for cold air flow, and limited suppression effect, so as to reduce resistance, The effect of reducing the intensity of infrared radiation and lowering the temperature

Inactive Publication Date: 2017-06-13
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Judging from the existing literature, the main profile characteristics of the current traditional binary injection nozzles (such as long casing binary injection nozzles, short casing binary injection nozzles, etc.) are The outlet is covered with a binary cylinder with a slightly larger equivalent diameter. The binary injection nozzle obtained in this way has very limited enhancement of the shielding effect on the high-temperature parts inside the nozzle, that is, the infrared radiation suppression effect on the solid wall is very limited. ; Secondly, the high-temperature gas flow of the nozzle and the cold air flow ejected from the nozzle begin to mix at the cross-sectional position of the nozzle outlet. Relatively large, resulting in a very limited amount of cold flow air outside the injection nozzle, so the traditional injection nozzle has a relatively limited suppression effect on jet infrared radiation

Method used

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  • A Low Infrared Characteristic Lobe Ejection and Mixing Device for Binary Nozzle Outlet
  • A Low Infrared Characteristic Lobe Ejection and Mixing Device for Binary Nozzle Outlet
  • A Low Infrared Characteristic Lobe Ejection and Mixing Device for Binary Nozzle Outlet

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Experimental program
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Effect test

Embodiment 1

[0044] Set the logarithm n of the outer expansion lobe to 6, then the logarithm of the inner expansion lobe is 5; the logarithm of the outer expansion lobe is 1.5 times the aspect ratio, then the aspect ratio AR is 4 and the width is L5 Take 1.44m; then the equivalent diameter of the entrance of the rectangular transition section 1 is 0.576, and the area A1 of the entrance section 5 is 0.5184m 2 .

[0045] The area A2 of the exit section of the lobe section 2 and the entrance area of ​​the rectangular transition section is equal to 0.5184m 2 , Lobe transition section 3 exit section 8 area A3 is twice the entrance area of ​​rectangular transition section, namely 1.0368m 2 , The area A4 of the outlet section 9 of the separated cold and hot flow passage section 4 is equal to it.

[0046] In terms of length dimension, the axial length L1 of the rectangular transition section 1 is 0.1 times the equivalent diameter of the entrance of the rectangular transition section 1, which is 0.0576m....

Embodiment 2

[0048] Set the logarithm n of the outer expansion lobe to 12 pairs, then the logarithm of the inner expansion lobe is 11; the inlet equivalent diameter of the rectangular transition section 1 is 0.576, the aspect ratio AR is 4, and the width L5 is 1.44m.

[0049] According to the above data, the area A1 of the entrance section 5 is 0.5184m 2 , The area A2 of the exit section 7 of the lobe section 2 is the same as that of 0.5184m 2 , The area of ​​the exit section of the lobe transition section 3 and 8 area A3 is 1.0368m 2 ,Separated cold and hot flow channel section 4 exit section 9 area A4 is 1.0368m 2 .

[0050] In terms of length dimensions, the axial length L1 of the rectangular transition section 1 is 0.144m, the axial length L2 of the lobe section 2 is 0.6912m, the axial length L3 of the lobe transition section 3 is 0.1152m, and the separated cold and hot flow channel section 4 The axial length L4 is taken as 0.3456m, the radius R1 at the end of the outer expansion lobe 11 is ...

Embodiment 3

[0052] Set the logarithm n of the outer expansion lobe to 9 pairs, then the logarithm of the inner expansion lobe is 8; the inlet equivalent diameter of the rectangular transition section 1 is taken as 0.576, and the area A1 of the inlet section 5 is taken as 0.5184m 2 , The aspect ratio AR is 4, and the width L5 is 1.44m.

[0053] Lobe section 2 exit section 7 area A2 is 0.5184m 2 , The area of ​​the exit section 8 of the lobe transition section 3 is 1.0368m 2 ,Separated cold and hot flow channel section 4 exit section 9 area A4 is 1.0368m 2 .

[0054] The axial length L1 of the rectangular transition section 1 is 0.103m, the axial length L2 of the lobe section 2 is 0.5042m, the axial length L3 of the lobe transition section 3 is 0.0808m, and the axial length L4 of the split cold and hot flow channel section 4 is taken 0.2882m, the radius R1 of the end of the outer expansion lobe 11 is 0.04m, the radius of the end of the inner expansion lobe 10 is R2 is 0.045m; the height of the lo...

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Abstract

The invention provides a low-infrared characteristic lobe ejection mixing device for the outlet of a binary nozzle, which includes a rectangular transition section, a wave section, a wave transition section and a separate cold and hot flow channel section. For the traditional two The high-temperature components inside the exhaust system (central cone, support plate, mixer) that cannot be effectively shielded by the nozzle profile can be effectively shielded by the special wave lobe profile of the device and the separate inner partition of the cold and hot flow channels. Reduce the detectable infrared radiation of these high-temperature components, and at the same time, the separate cold and hot flow channel sections separate the high-temperature gas flow from the ejected cold air flow, effectively reducing the resistance of the ejected cold air flow, It ensures that the amount of injected cold air flow is very considerable, and the cold and hot air are mixed at the outlet of the device, which greatly reduces the temperature of the jet flow, thereby reducing the infrared radiation of the jet flow.

Description

Technical field [0001] The patent of the present invention relates to the technical field of suppression of infrared radiation characteristics of aircraft, specifically, it mainly relates to a low-infrared characteristic lobe ejection mixing device used at the exit of a binary nozzle. Background technique [0002] Under the threat of the current complex electromagnetic search and detection environment and advanced ground-to-air and air-to-air weapons and equipment, the battlefield survival environment of aircraft is deteriorating day by day. How to improve the survivability of aircraft on the battlefield and carry out effective attacks against the enemy has become one of the key technologies urgently needed for development in modern warfare. According to statistics, in several air battles since the 1980s, aircraft shot down by infrared guided missiles accounted for 70-80% of all aircraft shot down in the war. Aircraft in various countries are facing the threat of close combat inf...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/38F02K1/46
Inventor 吉洪湖王丁黄伟
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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