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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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI 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

Method used

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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
Comparison scheme
Effect test

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 de...

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, ...

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PUM

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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.

Description

technical field [0001] The invention belongs to the technical field of engines, in particular to a backflow pulse detonation combustion chamber. Background technique [0002] Pulse detonation engine (PDC) is a new concept engine that uses high-temperature and high-pressure gas generated by periodic detonation waves to generate thrust. This engine has been favored by researchers at home and abroad because of its high cycle thermal efficiency and simple structure. widespread attention. According to whether it has its own oxidant, the pulse detonation engine can work in two modes: air-breathing and rocket. The air-breathing pulse detonation engine is divided into basic pulse detonation engine, pulse detonation turbine engine and combined Pulse detonation engine. The basic pulse detonation engine is mainly composed of an intake port, a detonation combustion chamber and a tail nozzle. The high-temperature, high-speed detonation gas is directly discharged from the detonation comb...

Claims

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Application Information

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IPC IPC(8): F23R3/00
CPCF23R3/00
Inventor 郑龙席王凌羿
Owner NORTHWESTERN POLYTECHNICAL UNIV
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