Reverse-flow type pulse detonation combustor

A technology of pulse detonation and combustion chamber, which is applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of the length of the whole engine, the increase of the axial distance between the turbine and the compressor, etc., and achieve shortening of the axial distance, The effect of improving work stability and prolonging the use time

Active Publication Date: 2016-09-28
NORTHWESTERN POLYTECHNICAL UNIV
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AI-Extracted Technical Summary

Problems solved by technology

[0003] However, in the actual application process, the deflagration to detonation transition (Deflagration to Detonation Transition, referred to as "DDT") distance exists in the straight tube detonation chamber of the detonable mixture of...
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Method used

[0030] In this example, the detonation tubes are distributed in a staggered manner. Under the same axial distance, the overall le...
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Abstract

The invention provides a reverse-flow type pulse detonation combustor. The reverse-flow type pulse detonation combustor comprises a diffusion case, an outer combustor case, an inner combustor case, a combustor head case, a vortex guide unit, an oil nozzle, an electric spark, a fuel gas shaping chamber, a J-type reverse-flow detonation tube and a Shchelkin threaded strengthening device. An axial main air intake hole and a radial auxiliary air intake hole are formed in the air intake mixing section of the head portion of the J-type reverse-flow detonation tube, and the air intake mixing section is connected with the outer combustor case through an ignition base. The bent air exhaust section on the tail of the J-type reverse-flow detonation tube is fixed in a mounting hole in the inner combustor case and connected with the fuel gas shaping chamber. The vortex guide unit is installed behind the fuel gas shaping chamber. The axial distance of the detonation combustor can be decreased through the bent air exhaust section, the influence of detonation feedback is reduced through the volume between an inner sleeve and an outer sleeve of the combustor, air is preheated through the bent exhaust section so that combustible materials are mixed more sufficiently, and detonation combustion is made to be organized more easily.

Application Domain

Technology Topic

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  • Reverse-flow type pulse detonation combustor
  • Reverse-flow type pulse detonation combustor
  • Reverse-flow type pulse detonation combustor

Examples

  • Experimental program(2)

Example Embodiment

[0024] Embodiment 1:
[0025] The diffuser structure 1 of the recirculation pulse detonation combustion chamber in this example can be changed according to the form of the compressor. In this embodiment, 15 radial triangular diffuser vanes are evenly distributed on the diffuser disc. Adjacent triangular diffuser vanes are spaced 24° apart. There are 40 rectifying vanes evenly distributed in the circumferential direction of the diffuser disc, the vane inlet is 45° to the axial direction, and the outlet is parallel to the axial direction. The diffuser is connected to the casing through the rectifying vanes, and there are 4 bolt holes on the diffuser disc for fixing the bearings.
[0026] The recirculation pulse detonation combustion chamber in this example contains 6 J-type recirculation detonation tubes A type 9, see figure 2 , each detonation tube is composed of a mixing section 10, a detonating straight section 11, and an exhaust bend section 12. The central axis of the detonation tube is evenly distributed along the circumferential direction, and the central angles of the central axes of the two adjacent detonation tubes are the same. is 60°, its distribution see figure 2. Outside the mixing section 10 of each detonation tube, there is an axially mounted fuel nozzle 8, and the fuel nozzle 8 extends from the outer casing of the combustion chamber into the main air intake hole 13 of the mixing section.
[0027]When the recirculation pulse detonation combustion chamber in this example works, the high-pressure air from the compressor first enters the combustion chamber after being diffused and decelerated by the diffuser. The air intake hole 13 and the auxiliary air intake hole 14 enter the detonation pipe, and at the same time, the fuel nozzle 8 injects fuel into the main air intake hole 13, and mixes with the air to form a uniform explosive mixture, and then the fully mixed explosive mixture is filled with J Type recirculation detonation tube 9 is then ignited by spark plug 7 to form detonation, and the detonation wave gradually increases in intensity after passing through the detonation enhancement device in the detonation straight section, forming many high temperature and high pressure points locally. These high temperature and high pressure points develop backward into a stable detonation wave, and the detonation wave turns 180° along the exhaust elbow and then spreads out of the detonation pipe. Due to the effect of detonation and supercharging, part of the gas in the J-type return detonation tube 9 will flow out from the main and auxiliary air intake holes in the reverse direction, and the reversed air flow will gradually weaken in the volume space between the detonation tube and the outer casing of the combustion chamber, making the The influence of backpropagation on the compressor is weakened. When the pressure in the J-type return detonation tube 9 is reduced to the incoming pressure, the detonation tube begins to refill the detonable mixture, and the above process is repeated. The six J-type return detonation tubes 9 can perform the above process at the same time, or they can perform the above process in time-sharing. During the time-sharing operation, the six J-type return detonation tubes are sequentially fueled and ignited.

Example Embodiment

[0028] Embodiment 2:
[0029] The recirculation pulse detonation combustion chamber in this example contains 6 J-type recirculation detonation tubes B type 17 See image 3 , Compared with the A-type, the B-type has no angle between the intake mixing section 18 and the detonating straight section 19, and its exhaust curved section 20 is 42.9% longer than the A-type, which is more conducive to the formation of the knock wave. Different from the A-type detonation pipe, the outlet of the exhaust bend 20 of the B-type detonation pipe is installed on the outlet of the adjacent turbine guide 6, and the 6 pipes are generally staggered. The central axis of the same B-type detonation pipe is along the It is evenly distributed in the circumferential direction, and the central angles of the central axes of the two adjacent detonation tubes are the same as 60°. Image 6.
[0030] In this example, the detonation tubes are distributed in a staggered manner. Under the same axial distance, the overall length of the detonation tubes increases, which can make the detonation wave more fully formed and generate greater thermal power.
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Description & Claims & Application Information

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