CAJ | 학술논문

基于逐排模型,文章发展了一种预测涡轮小转速特性计算方法,并进一步基于涡扇发动机部件匹配技术,建立了某型涡扇发动机起动过程计算模型及相应算法,给出了不同供油规律对发动机起动过程、高压压气机动态工作线影响规律,结果表明增加最大涡轮前温度对涡扇发动机起动过程并无明显改善,但却对高压压气机稳定工作裕度造成不利影响.
기우축배모형,문장발전료일충예측와륜소전속특성계산방법,병진일보기우와선발동궤부건필배기술,건립료모형와선발동궤기동과정계산모형급상응산법,급출료불동공유규률대발동궤기동과정、고압압기궤동태공작선영향규률,결과표명증가최대와륜전온도대와선발동궤기동과정병무명현개선,단각대고압압기궤은정공작유도조성불리영향.
Subsection 1.1 of the full paper, with the help of Figs. 1 through 4, explains the principal results of our exploration; its core is that we develop an analytical method for simulating the low-speed low-flow characteristics of axial flow turbine based on row-by-row model; in our opinion, eqs. (8) and (9) are particularly worth noticing. On the basis of the results of exploration in subsection 1.1, subsection 1.2 presents a three-step procedure for predicting the start-up process of a mixed turbofan engine; this procedure solves the matching equations of the engine components. Section 2 presents the simulation results, which are given in Figs.5 through 9, and their analysis. Section 2 includes: (1) the general procedure for obtaining the starting dynamics of an augmented turbofan engine, (2) the analysis of the working process of an augmented turbofan engine in starting operation for different fuel schedulings, (3) the effects of fuel scheduling on the start-up process and on the dynamic working lines of the high-pressure compressor for the turbofan engine. It is particularly worth pointing out that the surge margin of the high-pressure compressor decreases with increasing inlet total temperature of the turbine.