Single rotor minitype turbofan engine adopting axial flow oblique flow serial composite compressing system

Abstract

The invention provides a single rotor minitype turbofan engine adopting an axial flow oblique flow serial composite compressing system. The structure of the single rotor minitype turbofan engine adopting the axial flow oblique flow serial composite compressing system is that airflow of an outer duct of a turbofan engine and the airflow which enters into a combustor of an inner duct are both supplied by the axial flow oblique flow serial composite compressing system, the axial flow oblique flow serial composite compressing system adopts a combination of both an axial flow fan rotor and an oblique flow compressor rotor, and provides pressure boosting airflow for both the inner duct and the outer duct. The serial axial flow fan rotor is relative to the portion of the inner duct, and directly forms an oblique flow compressor impeller to a serial blade lattice form; a row of stator impellers is arranged on the axial flow fan rotor corresponding to the portion of the outer duct, the air flow is adjusted to the rear direction of the meridian plane through rectification deceleration, and flows into a turbofan engine outer duct bypass along the outer surface of an intermediary cartridge receiver. The single rotor minitype turbofan engine adopting the axial flow oblique flow serial composite compressing system has the advantages of being capable of realizing to provide the pressure boosting airflow for the inner duct and the outer duct by the needs of the turbofan engine, lowering an oil consumption rate of the engine, improving windward side thrust of each unit of the engine, and effectively improving voyage and enhancing load when the single rotor minitype turbofan engine adopting the axial flow oblique flow serial composite compressing system is applied in carriers of unmanned planes, loitering munitions, and the like.

Description

technical field [0001] The invention relates to a single-rotor miniature turbofan engine adopting an axial-flow oblique-flow tandem compound compression system, having a novel structure and a corresponding design method. It can be used for tiny turbofan engines with a thrust of hundreds of DaN or less. It specifically relates to the design of the compression system of the turbofan engine, which adopts the axial flow fan rotor impeller and the oblique flow compressor rotor impeller arranged in series as a composite compression system rotor, and there is no stator impeller between them. The composite compression system rotor can effectively increase the pressure ratio of the inner duct and provide pressurized air flow for the outer duct. Compared with the micro turbojet engine, the thrust of the micro turbofan engine is significantly increased and the fuel consumption rate is significantly reduced under the condition of only a small modification of the structure; thus, it can m...

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Problems solved by technology

[0003] These structural forms provide possible development directions for micro turbofan engines, but they all have their own shortcomings: 1) The front fan dual-rotor concentric shafting scheme is the form adopted by existing large engines, and its miniaturization design is in structural design, There are many technical difficulties in installation and commissioning, bearings, lubrication, and engine starting; 2) In the rear fan scheme, the integral structural design of the low-pressure turbine and fan and the sealing problems of the cold and hot air flow are quite large in the size range of micro-miniature engines. Difficult, in addition, the fan can not play the role of increasing the boost ratio of the compression system; 3) The common single-rotor turbofan engine scheme can avoid the concentric shafting problem and complicated flow channel structure of the dual-rotor turbofan engine, but in practical applications , the single-rotor solution also has problems such as the mismatch between the fan and the core machine, the Mach number of the fan blade tip is too high, and the single-stage turbine is overloaded.

However, its inner channel is essentially a single-stage centrifugal compressor, and the supercharging ratio of the inner channel is limited to the range that can be achieved by a single-stage centrifugal compressor; A large total pressure loss is generated; in addition, the axial flow compression section extended forward needs to lengthen the axial length of the wheel, resulting in a large increase in the weight of the wheel

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