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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 hydrocarbon fuel and air, and the DDT is longer than the existing engine combustion chamber, so the axial distance between the turbine and the compressor will increase, which will lead to problems such as too long starting of the engine

Method used

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

Examples

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Embodiment approach 1

[0025] The diffuser structure 1 of the backflow pulse detonation combustor in this example can be changed according to the form of the compressor. In this embodiment, 15 radial triangular diffuser blades are evenly distributed on the diffuser disc, corresponding to The adjacent triangular diffuser blades are spaced at 24°. There are 40 rectifying blades evenly distributed in the circumferential direction of the diffuser disc, the inlet of the blade is 45° to the axial direction, and the outlet is parallel to the axial direction. The diffuser is linked with the casing through rectifying vanes, and there are 4 bolt holes on the diffuser disc for fixing the bearings.

[0026] The recirculation pulse detonation combustor 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 detonation straight section 11, and an exhaust curved section 12. The central axis of the detonation tube is even...

Embodiment approach 2

[0029] The recirculation pulse detonation combustor in this example contains 6 J-type recirculation detonation tubes B type 17 see image 3 , Type B is relatively with Type A, there is no angle between its intake mixing section 18 and detonation straight section 19, and its exhaust bend section 20 is 42.9% longer than Type A, which is more conducive to the formation of detonation waves. Different from the A-type detonation tube, the outlet of the B-type detonation tube exhaust bend 20 is installed on the outlet of the adjacent turbine guide 6, and the 6 tubes are distributed in a staggered manner as a whole. The central axis of the same B-type detonation tube is along the The circumferential direction is evenly distributed, and the central angles of the central axes of the two adjacent detonation tubes are the same as 60°. For the distribution, see Figure 6 .

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

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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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