Wide-range working RBCC variable geometry full flow passage

Abstract

The invention discloses a wide-range working RBCC variable geometry full flow passage comprising an isolation section, a first combustion chamber, a second combustion chamber and a spray pipe sectionwhich are sequentially communicated from front to rear. A first supporting plate is horizontally arranged in the first combustion chamber in the length direction of the first combustion chamber, the first combustion chamber is divided into two independent channels which are an upper channel and a lower channel respectively, and a plurality of first injection rockets are longitudinally arranged atintervals at the rear end of the inside of the first supporting plate. The first supporting plate has a hollow cavity which is communicated with fuel. The plurality of first injection rockets are communicated with the fuel. The wide-range working RBCC variable geometry full flow passage has a wider working mach number range and can achieve efficient combustion.

Description

technical field [0001] The invention belongs to the technical field of engines, and in particular relates to an RBCC variable-geometry full-flow passage with wide-ranging operation. Background technique [0002] The rocket ramjet combined cycle (RBCC) engine organically combines the rocket engine and the ramjet engine in the same flow channel, so that it can enable the optimal working mode at different flight altitudes and Mach numbers, and give full play to the respective advantages of the rocket engine and the ramjet engine. The characteristics of the RBCC engine not only have high specific impulse and high thrust-to-weight ratio, but also have the advantages of zero-speed start and reusability. Compared with the existing power system, which only needs to work in a narrow range, the characteristics of rocket ramming combination (RBCC) propulsion in large airspace and wide speed range bring great challenges to the full channel design of rocket ramming combined power. The k...

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Problems solved by technology

[0003] RBCC engines usually only use the main support plate for single-stage rocket ejection. When the engine is working in ejection mode, the contact area between the single-stage rocket plume and the air is small, and the ability to work on the air is weak, resulting in the engine ejection and suction air capacity. Insufficient, the fixed-structure combustor configuration cannot adapt to the change of incoming flow conditions with a wide Mach number, nor can it keep the flow channel area of ​​the combustor matching the combustion heat release, so that it cannot combust the tissue efficiently. Therefore, the RBCC engine under different modes cannot Stable and efficient work

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