Optimization of gas turbines for sustainable turbojet propulsion  

作　　者：Yousef S.H.Najjar Ibrahim A.I.Balawneh 

机构地区：[1]Mechanical Engineering Department,Jordan University of Science and Technology,Irbid,Jordan

出　　处：《Propulsion and Power Research》2015年第2期114-121,共8页推进与动力（英文）

摘　　要：Gas-turbines are widely used to power aero planes because they are light,compact with a high power-to-weight ratio.In the turbo jet engine,the main operating variables are:compressor pressure ratio rp and turbine inlet temperature(TIT).These variables affect the specific thrust and specific fuel consumption(SFC),which represent the main performance parameters.In addition to the analytical work,a computer program of the General Algebraic Modeling System(GAMS)was used for analysis and optimization.The analysis shows that the specific thrust strongly depends on turbine inlet temperature(TIT),where a 10%decrease in TIT results in 6.7%decrease in specific thrust and 6.8%decrease in SFC.Furthermore,the value of optimum pressure ratio rf for maximum specific thrust increases with TIT.A 10%decrease from design TIT results in 11.43%decrease in rf.The value of optimum pressure ratio for the turbojet engine operating at Ma=0.8 and altitude Alt=13000 m,and TIT=1700 K was found to be 14.&2015 National Laboratory for Aeronautics and Astronautics.Production and hosting by Elsevier B.V.

关 键 词：OPTIMIZATION Green technology Sustainable turbojet engines Performance carpets 

分 类 号：Z89[文化科学]