Series-parallel hybrid three-power combined engine design method

Abstract

A series-parallel hybrid three-power combined engine design method comprises the steps that (1) the maximum windward flow channel sectional area of combined power is determined according to the size index of an aircraft for the combined power; an engine air inlet channel is of an axial symmetry structure with an air inlet blocking cone capable of moving front and back, and the capturing area of the air inlet channel is selected as the maximum windward flow channel sectional area. (2) according to the minimum Mach number of independent ramjet work, the flow coefficient and the Mach number of the maximum section of the turbine engine and the inlet sectional area of a ramjet subsonic combustion chamber are calculated; 3) the throat area of the adjustable nozzle is calculated according to the outlet flow, the total pressure and the total temperature of the ramjet subsonic combustion chamber under different flight conditions; the method further includes: 4) calculating to obtain the thrust and the oil consumption rate of the engine according to the outlet flow, the total pressure, the total temperature and the like of the spray pipe under different flight conditions; 5) completing the design of the length along the flow direction; and 6) combining the maximum thrust demand of the rocket engine in the whole flight profile to complete the size and quantity design of the rocket engine.

Description

technical field [0001] The invention relates to the field of combined engines, in particular to a design method for a series-parallel hybrid three-power combined engine. Background technique [0002] Hypersonic flight is considered to be the third revolution after propeller and jet propulsion. The most important technology for developing hypersonic aircraft is hypersonic propulsion technology, because the performance of the propulsion system directly affects the design of the entire aircraft. success. However, in different flight Mach number ranges, various air-breathing propellers have different economics. Therefore, to meet the power requirements of the air-breathing aircraft in the full working range, the combined power system is an ideal and very effective Prospects for engineering applications. At present, there are two common forms of combined power systems that can be used for the selection of hypersonic vehicles: turbine-based combined cycle power unit (TBCC) and r...

AI Technical Summary

Problems solved by technology

Secondly, as the air-breathing power of the turbine and the ramjet, the combination of the two powers will inevitably increase the size and weight. During high-speed flight, due to the increase in size, the frontal area will increase, and the unit head-on thrust will decrease. The combined power that inevitably leads to an increase in aircraft drag will exacerbate the thrust-drag imbalance of the aircraft / combined power

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