Transactions of Nanjing University of Aeronautics & Astronautics
微型叶轮机械联合试验台设计
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Abstract:
Microturbine engine has no enough space for measuring impeller chara cteristics, so the design and the construction of a new test facility of micro tu rbomachinery are presented for microcentrifugal compressors and radial turb ine s. The facility is used for the full speed compressor test and the long duration hot turbine test. To rapidly adjust the testing condition, all regulations of t he opera ting state are automatically completed by the control system. The facility is al so used for testing the impeller performance with a series of diameter from 55 m m t o 180 mm as a result of the modular design. A thermal protection system is desig ned to avoid the heat distortion caused by the high turbine inlet temperature ov er 1 100 K and provide a proper experimental environment for the electronic comp onents. A pho toelectric torque transducer with the accuracy of 1％ is designed to measure the torque of rigid shaft at a high speed of 125 000 r／min. The designing techniq ues for microturbomachineries are verified by the impeller testing of the f acility.
Keywords:
Project Supported:
Supported by the National Natural Science Foundation of China (50576034).
Clc Number:
CHINA AERO-SCIENCES
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