Survey on key techniques of rocket-based combined-cycle engine in ejector mode

Experimental study on ejector-to-ramjet mode transition in a divergent kerosene-fueled RBCC combustor with low total temperature inflow

Research progress on ejector mode of rocket-based combined-cycle engines

Rocket-based combined-cycle (RBCC) engines are known as the most promising type of engine with the potential to realize ‘single stage to orbit’ (SSTO). This will dramatically reduce the cost of space round trips and improve the physical experience of astronauts. However, sixty years after this concept was first proposed, no RBCC engine has completed a real flight. The challenges in RBCC development include ejector, scramjet, mode transition, and thermal protection technologies. However, great progress has been made in recent years, suggesting a bright future for these engines. In this paper, we review worldwide progress in the overall layout of RBCC engines. The working process of RBCC engines is introduced to show their distinctiveness among traditional engines. RBCC engines are classified as rectangular section or axisymmetric configuration engines and the development of both types in different countries is reviewed. The engine-airframe integration design and mission planning of RBCC powered aircraft systems are analyzed separately. Even though RBCC powered aircraft and their missions remain conceptual, the design and planning processes are important for RBCC development and space round trips in the future. RBCC study is a typical multi-disciplinary design process. Research addressing the problems encountered by RBCC studies will promote the development of a range of disciplines relevant to aerospace science.

The overall layout of rocket-based combined-cycle engines: a review

Effect of the heat release on the component coordination in the rocket-based combined cycle engine

A rocket-based combined-cycle engine prototype demonstrating comprehensive component compatibility and effective mode transition

Numerical analysis of flow features and operation characteristics of a rocket-based combined-cycle inlet in ejector mode

The invention discloses a double-channel variable geometry rocket base combined cycle engine. A double-channel structure is adopted; the excellent work in wide flight range is realized through a partitioned combustion mode; double channels synchronously work in low-speed flight state to finish work of low-speed section in an ejecting mode and a sub-combustion mode; and in high-speed flight state, the high-speed channel singly works to finish work of high-speed section in the sub-combustion mode and a ultra-combustion mode. The adjustment of low shrinkage rate in low-speed flight state and high shrinkage rate in high-speed flight state is realized by a variable geometry mode of rotating an ejection plate around a rotating shaft, so that the air capturing and airflow compression demands under different flight Mach numbers in wide engine range are satisfied. A binary mixed-pressure intake way is adopted, and the ejection plate is highly bonded with a side plate of the intake way, so that the mechanical dynamic seal is easy to realize, the engineering application is adapted to, and the power demands of aircraft in different working modes are satisfied. The ejection plate and a conversion plate are respectively connected with the rotating shaft with a double-fulcrum structure, so that the structure rigidity is good, and the high-temperature seal is easy to realize.

Double-channel variable geometry rocket base combined cycle engine

The invention discloses an efficient supercritical kerosene condenser for an active cooling test. The efficient supercritical kerosene condenser comprises at least two rows of heat exchange modules arranged side by side and in parallel, wherein each row of heat exchange modules comprise a plurality of horizontally arranged heat exchange tubes. Each heat exchange tube comprises an outer heat exchange shell and an inner heat exchange shell which are coaxially sleeved together and have the same length, wherein an annular cooling channel with two closed ends is formed between the outer heat exchange shell and the inner heat exchange shell. In the same row, the end parts of every two adjacent inner heat exchange shells are sequentially connected so that the inner heat exchange shells can form acommunicating S-shaped fluid channel; the end parts of the adjacent outer heat exchange shells are connected in sequence so that the outer heat exchange shells can form a communicating S-shaped fluidchannel. As for every adjacent two rows, an outlet of the heat exchange module in the front row and an inlet of the heat exchange module in the rear row communicate. Therefore, safe recovery and high-pressure maintenance of supercritical heating kerosene after an engine open-loop active cooling test are ensured.

Jie Liu

Papers

A rocket-based combined-cycle engine prototype demonstrating comprehensive component compatibility and effective mode transition

Numerical analysis of flow features and operation characteristics of a rocket-based combined-cycle inlet in ejector mode

Double-channel variable geometry rocket base combined cycle engine

Efficient supercritical kerosene condenser for active cooling test