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Control method of turbo-based twin-chamber ram combined cycle engine

A technology of ramjet and dual combustion chambers, which is applied in combined engines, ramjet engines, machines/engines, etc., can solve the problems of engines not being able to relay, reduce the demand for high-temperature dynamic seals, expand the range of working Mach numbers, and average The effect of high thrust-to-weight ratio

Active Publication Date: 2018-06-12
BEIJING POWER MACHINERY INST +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to overcome the deficiencies of the prior art, provide a control method for a turbo-based dual-combustion chamber ramjet combined cycle engine, and solve the problems that the existing turboramjet combined engine cannot relay at a lower Mach number.

Method used

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  • Control method of turbo-based twin-chamber ram combined cycle engine
  • Control method of turbo-based twin-chamber ram combined cycle engine
  • Control method of turbo-based twin-chamber ram combined cycle engine

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Embodiment 1

[0056] This embodiment provides a turbo-based dual combustion chamber ramming combined cycle engine. figure 1 Its cross-sectional structure is shown, and its structure includes an intake port 1, a turbine engine 2, a double-combustion chamber ramjet engine 3, and an exhaust pipe 4, wherein the turbine engine 2 is located between the intake port 1 and the exhaust pipe 4 The channel of the channel constitutes a low-speed channel, and the channel where the dual-chamber ramjet 3 is located between the intake port 1 and the tail nozzle 4 forms a high-speed channel.

[0057] The low-speed channel and the high-speed channel are connected in parallel. This parallel relationship can be parallel connection up and down, or parallel connection left and right. figure 1 It shows a parallel mode in which the low-speed channel is on the top and the high-speed channel is on the bottom.

[0058] further, figure 2 A schematic diagram of the structure of a dual-combustion chamber ramjet is sho...

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Abstract

The invention aims at overcoming the defects in the prior art and provides a control method for a turbine-based double-combustion-chamber punching combined cycle engine to solve the problem that relay of an existing turbine punching combined engine cannot be achieved under the low Mach number. By means of the control method, the double-combustion-chamber punching engine is improved firstly, and combustion chambers arranged in a rectangular parallel connection manner; an air inlet way of the engine is improved, the two-dimensional air inlet way configuration is adopted in the air inlet way, the air inlet way is divided into at least one subsonic combustion runner and at least two supersonic runners through supporting plates, wherein the supersonic runners are evenly arranged on the two sides of the subsonic combustion runner; and inner contraction section adjusting molded surfaces and expansion section adjusting molded surfaces are additionally arranged in the design of all the runners so that the size of the area of a throat of the air inlet way can be controlled, the requirement for air with different compression degrees of the combustion chambers is met, the Mach number range of work of the engine is enlarged, and the performance of the engine is improved.

Description

technical field [0001] The invention belongs to the technical field of combined engines, and in particular relates to a control method for a turbo-based double combustion chamber ramming combined cycle engine. Background technique [0002] Near-space hypersonic flight missions, aerospace missions, etc. have put forward an urgent demand for high-performance new engines with wide airspace and wide-speed operating capabilities. Technically mature rocket engines, turbine engines, and ramjet engines have their own advantages, but they all have their own advantages. The above tasks cannot be accomplished alone. In order to meet the needs of this task, a new thermodynamic cycle scheme can be formed based on the above three engine technologies, thereby broadening the working range, and thus evolved combined engine schemes such as Turbo-Based Combined Cycle (TBCC) and TRIJET. [0003] The above-mentioned TBCC and TRIJET combination engine still has the following defects: TBCC is res...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K7/16F02K1/16F02C7/057F02C7/042F02C6/00F02C9/16
CPCF02C6/00F02C7/042F02C7/057F02C9/16F02K1/165F02K7/16
Inventor 侯金丽赵文胜郭金鑫李亭鹤凌文辉
Owner BEIJING POWER MACHINERY INST
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