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Film evaporation type flame stabilizer and combustion chamber

A flame stabilizer, evaporative technology, applied in combustion chambers, continuous combustion chambers, combustion methods, etc., can solve the problems of lean fuel ignition and flame stabilization capability difficult to meet the working requirements of wide flight envelopes, and achieve improved ignition performance and Flame stabilization capability, increased gas phase fuel concentration, and the effect of widening operating range

Active Publication Date: 2020-12-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Purpose of the invention: In order to solve the problem that the concave cavity flame stabilizer which plays the role of on-duty ignition in the existing concave cavity / support plate flame stabilizer is easily affected by the radial support plate flame stabilizer, which leads to the lean ignition and flame stabilization ability of the flame stabilizer It is difficult to meet the working requirements of the wide flight envelope. The present invention provides a thin-film evaporation flame stabilizer, which uses a thin-film covering plate to partially block the concave cavity to weaken the impact of the radial support plate flame stabilizer on the concave cavity flame stabilizer. Disruption of the flow field and improved ignition performance and flame stability

Method used

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  • Film evaporation type flame stabilizer and combustion chamber
  • Film evaporation type flame stabilizer and combustion chamber
  • Film evaporation type flame stabilizer and combustion chamber

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Embodiment 1

[0027] Embodiment 1: as figure 1 As shown, the direction of X in the figure is the axial direction described in this embodiment, which is also the front-to-back direction, and the direction in which the Z-axis extends in the figure is the radial direction described in this embodiment, which is also the direction from top to bottom , the direction in which the Y axis extends in the figure is the horizontal direction described in this embodiment, which is also the direction from left to right. The horizontal direction described in this embodiment is the direction parallel to the plane formed by the X-Y axis. The vertical direction of is the direction parallel to the plane formed by the Z-Y axis.

[0028] Such as figure 1 with figure 2 As shown, the thin film evaporative flame holder of the present invention includes a concave cavity flame holder 1 and a horizontally extending first distributor plate 2 arranged at the front end of the concave cavity flame holder 1, and the con...

Embodiment 2

[0033] Embodiment 2: as Image 6 As shown, the thin-film evaporative flame stabilizer of embodiment 1 is applied in the rectangular combustion chamber, and the ignition nozzle 7 of the combustion chamber is opened on the main board 12, and the trailing edge of the liquid film covering plate 4 is preferably no more than the opening of the ignition nozzle 7 Location. The concave cavity flame stabilizer 1, the first splitter plate 2 and the second splitter plate 8 are affixed to the side wall surface of the rectangular combustion chamber 9 through both sides; The lower end surface of the plate flame stabilizer 3 is affixed to the lower wall of the rectangular combustion chamber 9, the support plate flame stabilizer 3 is a thin-walled hollow part, the outer shell 32 forms a triangular blunt body structure, and the ignition nozzle 7 is welded or mechanically fitted. The method is fixed on the upper wall surface of the rectangular combustion chamber 9, and passes through the main b...

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Abstract

The invention discloses a film evaporation type flame stabilizer and a combustion chamber. The film evaporation type flame stabilizer comprises a concave cavity flame stabilizer and a first splitter plate which is arranged at the front end of the concave cavity flame stabilizer and extends horizontally. The concave cavity flame stabilizer comprises a front edge plate extending vertically, a main plate extending backwards horizontally along the upper end face of the front edge plate and a rear edge plate arranged at the tail end of the main plate and extending downwards obliquely, and a supporting plate flame stabilizer is fixed to the lower wall face of the first splitter plate. A plurality of liquid film covering plates extending horizontally are fixed to the lower end of the front edge plate. According to the film evaporation type flame stabilizer and the combustion chamber, the damage of the radial supporting plate flame stabilizer to the flow field of the concave cavity flame stabilizer is weakened in a manner of partially shielding a concave cavity by the film covering plates, and the gas-phase fuel oil concentration in an on-duty area is increased in a film evaporation oil supply manner, so that the working range of the conventional concave cavity / supporting plate flame stabilizer is widened.

Description

technical field [0001] The invention relates to a turbofan engine afterburner combustion chamber, a sub-combustion ramjet engine combustion chamber and a turbofan / ramjet combined cycle engine multi-mode combustion chamber, in particular to a thin-film evaporation flame stabilizer and a combustion chamber. Background technique [0002] Turbine-based combined cycle (TBCC) as an air-breathing engine has the advantages of wide flight range, conventional take-off and landing, and reusability, and is considered to be the most promising hypersonic vehicle power at this stage. device. Due to the large variation of the bypass ratio in the whole working range, the low temperature of the incoming flow inside the TBCC combustion chamber and the excessive local flow velocity bring difficulties to the ignition and flame stability inside the multi-mode combustion chamber. [0003] With the increase of the airflow velocity in the modern high-performance afterburner chamber, in order to ens...

Claims

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Application Information

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IPC IPC(8): F23R3/18
CPCF23R3/18
Inventor 范育新缪俊杰赵世龙吴伟秋刘琛姜凯琳
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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