Combustion chamber of wide speed range ramjet engine and working method thereof

Abstract

The invention provides a combustion chamber of a wide speed range ramjet engine and a working method thereof, wherein the combustion chamber comprises an air inlet connecting section (1), a forward-inclined concave combustion chamber (2) and a tail nozzle (3), wherein the air inlet connecting section (1), the forward-inclined concave combustion chamber (2) and the tail nozzle (3) are arranged successively; the air inlet connecting section (1) is a bridge component, through which a variable supersonic air inlet outlet is connected with the combustion chamber inlet, the area of the forward-inclined concave combustion chamber (2) is larger than that of the air inlet connecting section (1); the air inlet connecting section (1), the forward-inclined concave combustion chamber (2) and the tail nozzle (3) as well as the structure of the combination of the air inlet connecting section (1), the forward-inclined concave combustion chamber (2) and the tail nozzle (3) is symmetrical with a centralplane, or rotationally symmetrical with a central axis.

Description

technical field [0001] The present invention relates to the field of power technology, in particular, to a wide-speed range ramjet combustion chamber and its working method, in particular to the design of a combined engine, ramjet and scramjet combustion chamber, which is essentially a combination of free jet and The heat release distribution coupling control technology of the combustion chamber of the ramjet engine realizes the wide speed range operation; the wide speed range refers to the speed range covering at least flight Mach number 2.5-8. Background technique [0002] The ramjet intake uses the change in cross-sectional area to quickly decelerate the supersonic airflow to subsonic speed on the windward side, so that the fuel and air in the combustion chamber can be ignited and burned. However, as the flight speed increases, the huge pressure loss seriously affects the efficiency and energy consumption. [0003] In addition, during the multiple flight stages of the air...

AI Technical Summary

Problems solved by technology

[0006] But similar to the prior art mentioned above, in the first aspect, the working range of the ramjet engine is limited by the combustion mode of dual-mode supercombustion and supercombustion, and it is difficult to ignite under the low flight Mach number, and the minimum working flight Mach number is usually greater than 4, while The working upper limit of the turbojet engine is around 2.5, which is difficult to meet the combined needs of the actual combined cycle

In the second aspect, the existing technology uses a small concave cavity or a progressively expanding geometric channel without a cavity, which has severe wall thermal protection problems at high flight Mach numbers

In the third aspect, the front wall of the concave cavity structure is a right-angled sudden expansion configuration, and the flow will experience a very large loss of kinetic energy, causing resistance, which will partially offset the thrust of the engine

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