布莱顿循环
涡扇发动机
总压比
组分(热力学)
推进
推力
热效率
喷气发动机
涡轮机
联合循环
功率(物理)
质量流量
工程类
汽车工程
机械工程
气体压缩机
航空航天工程
燃烧
机械
热力学
物理
化学
有机化学
作者
Theodosios Korakianitis,David Gordon Wilson
摘要
Gas turbine performance is the result of choices of type of cycle, cycle temperature ratio, pressure ratio, cooling flows, and component losses. The output is usually given as efficiency (thermal, propulsive, specific thrust, overall efficiency) versus specific power. This paper presents a set of computer programs for the performance prediction of shaft-power and jet-propulsion cycles: simple, regenerative, intercooled-regenerative, turbojet, and turbofan. Each cycle is constructed using individual component modules. Realistic assumptions are specified for component efficiencies as functions of pressure ratio, cooling mass-flow rate as a function of cooling technology levels, and various other cycle losses. The programs can be used to predict design point and off-design point operation using appropriate component efficiencies. The effects of various cycle choices on overall performance are discussed.
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