Transcritical based co 2 Multi-modal combined power cycle system and method

Abstract

A transcritical CO2 multi-mode combined power cycle system and method, belonging to the field of aerodynamic propulsion. The invention couples the turbine engine, the ramjet engine and the supercritical CO2 Brayton cycle, so that the hypersonic aircraft can be switched in multiple modes, so as to achieve the purpose of working in a wider area. The system includes intake duct (1), inner duct (2), outer duct (3), precooler (4), compressor (5), main combustion chamber (6), air turbine (7), afterburner Combustor (8), nozzle (9), CO2 turbine (12), condenser (13), pump (14), liquid CO2 tank (10), liquid oxygen tank (15), first switch (11) and Second switch (16). The combined power cycle proposed by the present invention adopts a transcritical CO2 closed-type thermal energy cascade recovery Brayton cycle in the super-precooling flight mode, and uses liquid oxygen to condense, so that the energy utilization of the system is maximized. In addition, the present invention uses supercritical CO2 as the pre-cooling working fluid to replace traditional helium, the system structure is more compact, the thrust is greater, and it can quickly realize the working requirements in a wider area.

Description

technical field [0001] The invention relates to a transcritical CO2 multi-mode combined power cycle system and method, and belongs to the field of improvement of aero-engine combined power cycle systems. Background technique [0002] For hypersonic long-range cruising flight, the power system needs to meet the optimum performance within the flight envelope of Ma0~5, and it is difficult for the traditional single-form engine to achieve stable operation in the full speed range. The combined power cycle developed in recent years, such as the turbo ramjet combined cycle engine, can meet the requirements of wide speed range work, but when the flight speed increases, it will cause the total temperature of the inlet airflow to increase, and at the same time, it is limited by the material. There is an upper limit to the total inlet temperature of the air turbine, so the increase in the total temperature of the incoming air will gradually reduce the heating capacity of the air, and t...

AI Technical Summary

Problems solved by technology

The "Scimitar" engine combines the characteristics of the turbine engine and the ramjet engine, making it work in a wider speed range and a wider working airspace, while avoiding the problem of "thrust gap" at the mode transition point of the TBCC engine and avoiding the low-speed section of the RBCC engine Insufficient thrust gain in the ejection mode, all parts of the engine in the entire working area can achieve high-efficiency work, but the "scimitar" engine chooses helium as the cooling medium, due to its low density and effective use of sensible heat transfer capacity The characteristics will inevitably lead to insufficient pre-cooling capacity and the large and complex structure of the pre-cooling system, which puts forward high requirements on the thermal management technology of the aircraft. One of the key factors, so designing an aircraft with strong pre-cooling capacity and simple structure of the pre-cooling system has become an important direction for the next development of turbo-ramjet combined engines

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