| ZHAO Zinan,HUANG Enliang,ZHANG Kun,Guo Lei,LU Xingen,XU Gang.Overall Design of a Small，Low-Cost，Low-Fuel Consumption Twin-Shaft Turbofan Engine[J].航空发动机,2026,52(1):129-137 |
| Overall Design of a Small，Low-Cost，Low-Fuel Consumption Twin-Shaft Turbofan Engine |
| DOI：10.12482/ISSN.1672-3147.20240724002 |
| Key Words:low-cost low-fuel consumption twin-shaft turbofan engine booster stage overall performance cycle parameters unmanned aerial platforms |
| Author Name | Affiliation | | ZHAO Zinan | Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China；
National Key Laboratory of Light Turbine Power,Beijing 100190,China；
School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China | | HUANG Enliang | Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China；
National Key Laboratory of Light Turbine Power,Beijing 100190,China | | ZHANG Kun | Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China；
National Key Laboratory of Light Turbine Power,Beijing 100190,China | | Guo Lei | Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China；
National Key Laboratory of Light Turbine Power,Beijing 100190,China | | LU Xingen | Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China；
National Key Laboratory of Light Turbine Power,Beijing 100190,China | | XU Gang | Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China；
National Key Laboratory of Light Turbine Power,Beijing 100190,China |
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| Abstract:To address the high fuel consumption of short-life,low-cost single-shaft turbojet/turbofan engines and high cost of fuel-
efficient twin-shaft turbofan engines,an overall design of a low-cost,low-fuel-consumption twin-shaft turbofan engine was conducted.
Guided by a low-cost design philosophy,two engine configurations were developed under equivalent overall cycle parameters and within the
same envelope constraints.Using an overall performance simulation software,cycle parameter optimization and overall performance calcula?
tions were performed, and the mechanism for improved fuel efficiency was examined from a thermodynamic perspective. The results
demonstrate that,compared with scheme A(fan+mixed-flow/centrifugal compressor+reverse-flow annular combustor),scheme B(fan+booster
stage+centrifugal compressor+reverse-flow annular combustor)achieves thermal efficiency improvements of 2.56%,2.37% and 2.64% at the
design point, ground off-design point, and high-altitude off-design point, respectively. Correspondingly, the fuel consumption rates are
reduced by 0.66%,1.10%,and 1.18%.These advantages enable Scheme B to better meet the requirements of unmanned aerial platforms for
long endurance,low-cost,and expendability. |
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