Compressor for aerodynamic performance comprehensive test platform of no-tail rotor anti-torque system
A technology for aerodynamic performance and comprehensive testing, applied in the field of aviation, can solve problems such as accurate computer simulation of working conditions, and achieve the effects of simple structure, simple test preparation, and improved test efficiency.
Inactive Publication Date: 2014-09-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
The tailless anti-torque system is located in the downwash flow field of the rotor. At present, it is difficult to accurately simulate its working state by computer, and relevant data can only be obtained through experiments.
Method used
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[0019] The accompanying drawings disclose, without limitation, the structural schematic diagrams of the preferred embodiments involved in the present invention; the technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings.
[0020] Such as figure 1 and figure 2 As shown, the compressor for the aerodynamic performance comprehensive test platform of the non-tail rotor anti-torque system of the present invention includes an air inlet, an air intake casing, a diffuser casing and a compressor disk assembly; the air inlet, the air inlet The casing and the diffuser casing are connected in series according to the air flow direction, and the air inlet, the air inlet casing, and the diffuser casing are all partition wall structures, and the partition walls of the air inlet, air intake casing, and diffuser casing Connected to form an air flow channel; the compressor disk assembly includes a compressor shaft and a compre...
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The invention discloses a compressor for an aerodynamic performance comprehensive test platform of a no-tail rotor anti-torque system. The compressor comprises an air inlet, an air inlet casing, a diffusing casing and a compressor disk assembly, wherein the air inlet, the air inlet casing and the diffusing casing are sequentially connected in series in accordance with an air flow direction, the air inlet, the air inlet casing and the diffusing casing are in a dividing wall type structure, dividing walls of the air flow direction, the air inlet, the air inlet casing and the diffusing casing are in communication to form an air flow channel, the compressor disk assembly comprises a compressor shaft and a compressor disk which is fixed to the compressor shaft, the compressor shaft is supported in the inner cavity of the air inlet casing through a bearing, blades of the compressor disk are located in the air flow channel, the axis of an air inlet port of the air inlet is vertical to the axis of an air outlet port of the air inlet, and the inner layer wall of the diffusing casing is in a shrinking rotary body with the axis serving as a center along the flow direction. Therefore, the compressor is suitable to the aerodynamic performance comprehensive test platform of the no-tail rotor anti-torque system. The compressor is simple in structure, convenient to maintain and reliable.
Description
technical field [0001] The invention relates to an air compressor, which is used for a comprehensive test platform of aerodynamic performance of a tailless anti-torque system and provides an air source for the research test of the aerodynamic characteristics of a tail beam with circulation control, belonging to the field of aviation. Background technique [0002] The tailless rotor anti-torque system is a new type of anti-torque system applied to single main rotor helicopters, which is used to balance the anti-torque generated by the main rotor and perform heading control. Compared with the conventional tail rotor of the traditional anti-torque system, the structure of the non-tail rotor anti-torque system is simpler, so it has higher reliability and maintainability. The tailless anti-torque system has no high-speed rotating parts exposed to the air, so the ground personnel are safer when the helicopter takes off and lands, and the helicopter itself is safer when flying at l...
Claims
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IPC IPC(8): F04D29/00F04D29/40B64F5/00B64F5/60
Inventor 李家春杨卫东武珅
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS