The design,manufacture and experiment of a shaft power unit for converting a microturbojet engine to a micro-turboprop in the class of less than 20 kW with the aim of obtaining maximum shaft power were described in th...The design,manufacture and experiment of a shaft power unit for converting a microturbojet engine to a micro-turboprop in the class of less than 20 kW with the aim of obtaining maximum shaft power were described in this study.For this purpose,a Wren 100 micro-turbojet engine was used as the gas generator,and the specifications of its outflow were measured.The optimal configuration of the inter-stage diffuser,which was an annular S-type diffuser,was selected based on its small total pressure drop and outlet flow uniformity.The power turbine was a single stage axial turbine that was designed based on the fixed nozzle angle assumption without any taper or twist in its stator.The turbine rotor was a bladed disk(Blisk)in which its unique blade profiles were designed based on the Wilson method.Subsequently,the shaft power unit was completed by designing and manufacturing an exhaust complex and gearbox.Finally,the micro-turboprop engine was tested with an overloading propeller.The results show a significant increase in the extracted power,an acceptable efficiency of the power turbine,and a significant reduction in the Specific Fuel Consumption(SFC)compared to other engines that use similar gas generators.展开更多
文摘The design,manufacture and experiment of a shaft power unit for converting a microturbojet engine to a micro-turboprop in the class of less than 20 kW with the aim of obtaining maximum shaft power were described in this study.For this purpose,a Wren 100 micro-turbojet engine was used as the gas generator,and the specifications of its outflow were measured.The optimal configuration of the inter-stage diffuser,which was an annular S-type diffuser,was selected based on its small total pressure drop and outlet flow uniformity.The power turbine was a single stage axial turbine that was designed based on the fixed nozzle angle assumption without any taper or twist in its stator.The turbine rotor was a bladed disk(Blisk)in which its unique blade profiles were designed based on the Wilson method.Subsequently,the shaft power unit was completed by designing and manufacturing an exhaust complex and gearbox.Finally,the micro-turboprop engine was tested with an overloading propeller.The results show a significant increase in the extracted power,an acceptable efficiency of the power turbine,and a significant reduction in the Specific Fuel Consumption(SFC)compared to other engines that use similar gas generators.
