Study on performance parameter correction formulaof GTCP131-9A APU

Performance parameter (exhaust temperature and fuel flow) correction formula of the GTCP131-9A auxiliary power unit(APU) was studied. A universal method of studying the gas turbine engines comparability was proposed at fist. By using this method, the necessary conditions to make this singlerotor and fixed shaft gas turbine engine similar were three equal, independent similarity criterion numbers, namely, flight Mach number, corrected speed and corrected power; other similarity criterion parameters were the functions of these three similarity criterion numbers. Later, according to the similarity of this engine, by using small deviation method, small deviation correction equations of the additional exhaust resistance, fuel heat value deviation and power deviation existing in the process of engine test were given. Result showed that under the condition that the ratio of the output power to atmosphere pressure was constant, GTCP1319A APUs performance parameter correction formula was the sum of the inlet total temperature polynomial, the correction term of additional exhaust resistance, the correction term of fuel heat variation and the correction term of power variation.