Binary plug nozzle of turbofan engine with afterburning

A turbofan engine and afterburning technology, applied in the direction of machines/engines, jet propulsion devices, etc., can solve the problems of increased weight, increased flow resistance of the nozzle, and the influence of the aerodynamic performance of the nozzle, so as to achieve the reduction of metal solid radiation, mixed The effect of mixed enhancement and good thrust performance

Inactive Publication Date: 2012-07-04
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, there are three main problems in the use of the plug nozzle: first, the plug cone increases the flow resistance in the nozzle, changes the flow conditions in the nozzle, and has...

Method used

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  • Binary plug nozzle of turbofan engine with afterburning
  • Binary plug nozzle of turbofan engine with afterburning
  • Binary plug nozzle of turbofan engine with afterburning

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Embodiment Construction

[0025] Below in conjunction with accompanying drawing and embodiment the patent of the present invention is described further.

[0026] figure 1 with figure 2 The structural schematic diagrams of the A-A section and the B-B section of the binary plug nozzle are shown respectively. The front part of the nozzle has an outer channel 14 and an inner channel 1. A central cone 12 is installed in the inner channel through a support plate 13, and a flame stabilizer 3 is installed downstream of the central cone 12; the middle part of the nozzle is an afterburner; The rear portion is successively a transition section 6 and a convergent expansion section 7, and the convergent expansion section 7 is equipped with a plug cone. The plug cone is prismatic, including the front part 10 of the plug cone and the rear part 9 of the plug cone. The diameter of the defined connotation channel is D1, the diameter of the central cone is D2, the diameter of the entrance of the transition section is ...

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Abstract

The invention relates to a binary plug nozzle of a turbofan engine with afterburning, and belongs to the field of suppressing an infrared radiation characteristic of an aircraft. The front part of the nozzle is provided with an external channel (14) and an internal channel (1), a central cone (12) is arranged in the internal channel (1) through a support plate (13), and a flame holder (3) is also arranged at the downstream of the central cone (12); the middle part of the nozzle is provided with an afterburning chamber, the rear part of the nozzle is sequentially provided with a transitional section (6) and a retracting and expanding section (7), and a tapered plug which is of a prism shape is arranged in the retracting and expanding section (7), and the tapered plug comprises a front part (10) of the tapered plug and a rear part (9) of the tapered plug. In the invention, while the pneumatic performance is maintained to be high, the infrared radiation characteristic of an engine exhaust emission system is remarkably reduced, and the tracking distance of an infrared detection system is shortened, so that the battlefield survival ability of the aircraft is effectively improved.

Description

technical field [0001] The patent of the present invention relates to the suppression of infrared radiation characteristics of aircraft, specifically, it mainly relates to the turbofan engine power exhaust system. Background technique [0002] With the development of modern military science and technology, various ground-air and air-to-air weapons and equipment are increasingly threatening aircraft, especially fighter jets that play the role of penetration tactics. The problem of how to improve the survivability of aircraft battlefields has become increasingly prominent. In view of the target signal characteristics of the aircraft itself, countries all over the world have developed advanced detection, search and tracking devices. At present, the vast majority of medium and short-range surface-to-air and air-to-air missiles use infrared and microwave radar composite guidance technology. Relevant data show that in several air battles since the 1980s, the number of aircraft sho...

Claims

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Application Information

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IPC IPC(8): F02K1/78
Inventor 吉洪湖陈俊
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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