发明名称 VARIOUS ENERGY CONSERVATION CYCLE COMBINED ENGINE
摘要 PROBLEM TO BE SOLVED: To make CO2-emission-free space flight florescent by minimizing CO2 emissions for going around the earth sixteen times a day, considering that existing airplanes have an enormous amount of CO2 emission because of very great air resistance during flight in the atmosphere. SOLUTION: A liquid metal gravity type cold-driven turbine as a core and various heat-driven turbines are driven in combination to develop mercury power having the same speed and the same capacity as the atmospheric pressure, about 10,000-23,000 times that of an existing steam turbine. A number of heat pumps are used for compressing solar-heated air to produce heat which is recovered with the solar-heated air heated and compressed. Hot superheated steam and cold compressed air are produced and dividedly conserved to serve the rotation outputs of the plurality of turbines. Thus, a solar heat gravity helicopter 39C having a combined engine jet part 78W for jet propulsion utilizing the power about 23,000 times that of the existing steam turbine is driven to reduce theoretically best cost using a jet-powered rocket for reaching space from near the maximum flight altitude of existing airplanes, down to 1/100 or smaller, thus actualizing fully popular space flight with zero air resistance and fully enjoyable one-day trip and space trip anywhere on the earth. COPYRIGHT: (C)2011,JPO&INPIT
申请公布号 JP2011185051(A) 申请公布日期 2011.09.22
申请号 JP20090290373 申请日期 2009.12.22
申请人 TANIGAWA HIROYASU;TANIGAWA KAZUNAGA 发明人 TANIGAWA HIROYASU;TANIGAWA KAZUNAGA
分类号 F03G3/00 主分类号 F03G3/00
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