Experimental device for testing dynamic performance of simulated rotor of miniature gas turbine
A technology of micro gas turbine and simulating rotor, which is applied in the direction of measuring device, testing of mechanical parts, testing of machine/structural parts, etc., to achieve the effect of saving experimental cost, good sealing effect and reducing processing difficulty
Inactive Publication Date: 2011-12-07
XI AN JIAOTONG UNIV
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Problems solved by technology
[0004] At present, there is no special experimental device for dynamic performance testing of simulated rotors of micro gas turbines at home and abroad.
Method used
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[0026] The structural principle and working principle of the present invention will be described in detail below in conjunction with the accompanying drawings.
[0027] refer to figure 1 , an experimental device for testing the dynamic performance of a micro gas turbine simulating rotor, comprising a rotor part I, and the rotor part I is installed on a stator part II.
[0028] refer to figure 1 , figure 2 and image 3 , the rotor part I includes a tie rod 1 with threads at both ends, the middle part of the tie rod 1 is equipped with a rotor bushing 2, one end of the rotor bushing 2 close to the thrust disc is connected with a simulated compressor impeller 3, and the other end is connected with a simulated turbine impeller 4 , the other end of the simulated compressor impeller 3 is connected with a coupling connector 5, and the two ends of the tie rod 1 connect the simulated compressor impeller 3, the simulated turbine impeller 4, and the coupling through a lock nut 22 and ...
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The invention relates to an experimental device for testing the dynamic performance of a simulated rotor of a miniature gas turbine, comprising a rotor part and a stator part, wherein the rotor part comprises a simulated gas compressor impeller, a simulated turbine impeller, a shaft coupler connecting member and a rotor shaft sleeve, and a radial elastic foil gas bearing and a thrust elastic foilgas bearing are sleeved on the rotor shaft sleeve; the stator part comprises the radial elastic foil gas bearing, a bearing pedestal of the radial elastic foil gas bearing is arranged in a shell and forms a gas supply chamber with the shell, the gas supply chamber is connected with a gas supply system, a sensor for detecting the displacement signal of a rotor system is configured on the bearing pedestal and connected with a computer, a driving device drives the rotor system to rotate, when the rotation speed of the rotor system is lower, the rotor shaft sleeve comes into contact with the radial elastic foil gas bearing and the thrust elastic foil gas bearing, and the rotor system realizes the suspension in the radial direction and the axial direction along with the improvement of the rotation speed. The experimental device can test the dynamic performance of the simulated rotor to reflect the dynamic performance of a real rotor and has the advantage of simple structure.
Description
technical field [0001] The invention relates to the technical field of micro gas turbines, in particular to an experimental device for testing the dynamic performance of a simulated rotor of a micro gas turbine. Background technique [0002] Micro gas turbine is a newly developed small heat engine, which has the advantages of multiple integrated expansion, low fuel consumption rate, low noise, low emission and low vibration. Micro gas turbines have very broad application prospects in both military and civilian applications. At present, many companies in the United States, Russia and Japan are actively developing and manufacturing corresponding equipment, and many companies in the United States have produced commercial micro gas turbine power generation devices. my country's research and development of micro gas turbines is still in the stage of prototype design and manufacture, and testing the overall performance of the prototype through experiments is one of the most impor...
Claims
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IPC IPC(8): G01M13/00G01B7/02
Inventor 戚社苗谷苗雨王欢耿海鹏孙岩桦虞烈
Owner XI AN JIAOTONG UNIV