Mathematical model of double-channel shunting characteristic of combined air inlet channel
A technology of mathematical models and shunt characteristics, which is used in complex mathematical operations, electrical digital data processing, instruments, etc.
Active Publication Date: 2022-04-08
AECC SICHUAN GAS TURBINE RES INST
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[0004] The purpose of the present invention is to provide a mathematical model of the dual-channel shunt characteristics of the combined intake port to solve the technical problem of how to calculate the total pressure recovery coefficient and flow coefficient of the intake system under the condition of the parallel TBCC engines working together
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[0018] Embodiments of the present invention are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. Apparently, the described embodiments are only some of the embodiments of the present invention, but not all of them. The present invention can also be implemented or applied through other different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scop...
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The invention relates to a mathematical model of a dual-channel shunting characteristic of a combined air inlet channel, belongs to the technical field of a dual-channel flow calculation method in a TBCC engine, and solves the technical problem of how to calculate a total pressure recovery coefficient and a flow coefficient of an air inlet system of an internal parallel TBCC engine. The method comprises the steps that S101, an overall flow distribution model is determined according to airflow static pressure of outlets of an air inlet system turbine engine channel and an air inlet system ramjet engine channel in combination with a flow conservation equation; s102, according to the design parameters of the air inlet system and the respective static pressure or Mach number of the outlets of the two channels of the air inlet system, the initial preset position of the ending shock wave at the expansion section is determined; s103, presetting a plurality of given models; and S104, according to the multiple given models and the initial preset position of the ending shock wave in the expansion section, the total pressure recovery coefficient and the flow coefficient of an air inlet system of the turbine engine and the ramjet engine are determined, and flow distribution of the flow channels of the turbine engine and the ramjet engine is calculated.
Description
technical field [0001] The invention belongs to the technical field of dual-channel flow calculation methods in TBCC engines, and in particular relates to a mathematical model of dual-channel flow splitting characteristics of combined intake ports. Background technique [0002] The conventional air intake system and the engine generally perform flow matching through the position change of the ending shock wave. For the combined engine, that is, the parallel TBCC engine (combined use of the ramjet engine and the turbine engine), due to the internal parallel connection in the air intake system With the introduction of the structure, the flow matching law of the two channels will be affected by the coupling of the end shock wave positions of the respective channels under the condition that the capture flow rate in the supersonic state is constant, which is relatively complicated. At present, the distribution rules are mostly based on experimental data, and there is little resea...
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IPC IPC(8): G06F30/20G06F17/18G06F17/11G06F113/08
CPCY02T90/00
Inventor 张宇超桂丰李丹李中龙袁永青钟世林侯玉柱于广元杨磊李梦娜杨昊何琛
Owner AECC SICHUAN GAS TURBINE RES INST