A24-043 CHALLENGES TO DEVELOP MINIATURE GAS TURBINE ENGINE WITH CERAMIC UNITARY COMPRESSOR/TURBINE ROTOR

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Turbomachinery components of a miniature-size gas turbine engine were prototyped and tested as a joint effort of Stanford University and Honda R&D. Compared with a turbo machinery engine with conventional size, there lie many technical challenges to scale down the engine into miniature size. One of the biggest challenges is aerodynamic components with small features. Three dimensional compressor and turbine with 12mm diameter and 250 μm blade thickness were designed for aerodynamic performance and fabricated as a unitary rotor with shaft out of silicone nitride by Mold SDM process. Another challenge is a high-speed bearing supporting a unitary rotor, which is designed to spin at up to 800k rpm. For bearing performance testing, the specially designed bearing was successfully able to run at the speed of 456k rpm in a stable manner. Current target of our testing is to implement the aerodynamically designed impeller out of silicon nitride and clarify if the compressor of our miniature gas turbine engine can perform as designed. A unitary rotor was installed in a cold spin test rig and compressor performance testing was conducted at room temperature. Temperature, pressure and mass flow rate were measured at 420k rpm to determine the performance and the results were compared with CFD analysis data at this speed. A good agreement of experimental and CFD data suggests that our preliminary impeller design method combined with CFD can be used for further development. It appears that a combination of Mold SDM process and further research of high-speed bearing would enable us to realize a miniature gas turbine engine.
社団法人日本機械学会の論文
2003-11-30

A24-043 CHALLENGES TO DEVELOP MINIATURE GAS TURBINE ENGINE WITH CERAMIC UNITARY COMPRESSOR/TURBINE ROTOR

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