高温升燃烧室与双燃烧室发动机性能对比分析

采用一维定常计算方法,考虑各种部件效率的影响,在双燃烧室发动机总增压比为32,涡轮前总温为1900K时,与高温升燃烧室涡轮前总温为2400K时进行了总体性能对比,并指出了双燃烧室结构发动机2个燃烧室的热量分配方法.结果表明:温升同为1463K时,高温升燃烧室发动机比双燃烧室发动机单位推力高2.7%,耗油率低3.8%.双燃烧室结构发动机更有利克服超声速下的冲压损失, Ma大于1.5之后,增力比大于高温升燃烧室发动机. 

Performance comparison and analysis of high temperature rise combustor engine and two-combustor engine

One-dimensional steady method was used to calculate the high temperature rise combustor engine and two-combustor engine's overall performance in consideration of the component efficiency. The overall performance was compared at total pressure ratio 32 and turbine inlet temperature 1900K for two-combustor engine and turbine inlet temperature 2400K for high temperature rise combustor engine. The way of temperature rise distribution between combustors of two-combustor engine was also analyzed. Results show that the specific thrust of high temperature rise combustor engine is 2.7 percent higher than that of two-combustor engine, while the specific thrust fuel consumption is 3.8 percent lower. The two-combustor engine is helpful to decrease the total pressure loss under supersonic condition, and its specific thrust increase ratio is higher than high temperature rise combustor engine when Mach number is more than 1.5.