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Fuel injection and atomization combustion test device suitable for large-gradient shear flow

A technology of combustion test and shear flow, which is applied in the field of aviation, can solve the problems of difficult complete combustion of fuel, unstable flame, and difficult ignition, and achieve the effects of preventing coking, improving atomization effect, and solving ignition difficulties

Inactive Publication Date: 2021-01-01
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0004] In view of the above problems, the present invention proposes a method that can effectively prevent oil accumulation and coking, improve the atomization effect of liquid fuel, and solve the problems of difficult ignition, unstable flame, and difficulty in complete combustion of fuel, which is suitable for large gradient shear flow Fuel injection and atomization combustion test device

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  • Fuel injection and atomization combustion test device suitable for large-gradient shear flow
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  • Fuel injection and atomization combustion test device suitable for large-gradient shear flow

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Embodiment Construction

[0025] In order to clearly illustrate the technical characteristics of this patent, the following describes this patent in detail through specific implementation methods and in conjunction with the accompanying drawings.

[0026] The present invention as Figure 1-5 As shown, it includes a mixing chamber main body 5, a subsonic flow channel 1, a supersonic flow channel 2, a support plate 3, a Laval nozzle 6, a direct injection fuel injection rod 8 and a cover plate 7;

[0027] There is a rectangular channel in the mixing chamber main body 5, the head port of the rectangular channel is connected to the air inlet channel through the welding flange 4, and the tail port of the rectangular channel is connected to the subsequent channel through the mixing chamber end flange 13; The rectangular channel includes a mixing chamber and an observation chamber that communicate with each other, and the mixing chamber is divided into a subsonic flow channel 1 in the upper layer and a superso...

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Abstract

The invention discloses a fuel injection and atomization combustion test device suitable for large-gradient shear flow, and relates to the technical field of aviation. The fuel injection and atomization combustion test device suitable for large-gradient shear flow comprises a mixing chamber main body 5, a subsonic flow channel 1, a supersonic flow channel 2, a support plate 3, a Laval nozzle 6, adirect injection type oil injection rod 8 and a cover plate 7, and a side wall surface optical measurement window 10 and an upper wall surface optical measurement window 12 which are used for shootingan oil mist field after fuel oil atomization, and a side wall surface temperature and pressure measurement point 9 and a lower wall surface temperature and pressure measurement point 11 which are used for measuring the temperature and pressure of the inner wall of the observation cavity, are arranged in an observation cavity. According to the designed mixing chamber, oil accumulation and coking can be effectively prevented, the atomization effect of liquid fuel is improved, and the problems that ignition is difficult, flames are unstable, and fuel is difficult to completely burn are solved.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a test device suitable for fuel injection and atomization combustion in a large gradient shear flow. Background technique [0002] The embedded rocket ramjet has a high working height, which can meet the urgent needs of high-altitude space penetration, theater communication, rapid strike and long-range flight of anti-near space weapons, accelerated maneuvering, and space interception of high-speed space vehicles, which has greatly improved my country's aerospace industry. integrated combat capability. One of the key technologies of the embedded rocket engine combustor is the efficiency and stability of combustion in the sub-super-large velocity gradient shear mixed layer between the two. The velocity difference and The temperature difference is large, so a complex strong shear mixed layer composed of a nonlinear quasi-ordered vortex system is formed between the two. In the mixe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/14G01M15/02
CPCG01M15/02G01M15/14
Inventor 姚倩李建中金武胡阁汤朝伟李夏飞
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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