In the turbojet lab, a model aircraft engine runs on a pure turbojet cycle, as shown in Fig. 1….

In the turbojet lab, a model aircraft engine runs on a pure turbojet cycle, as shown in Fig. 1. Using the conditions given in Table 1 and the data recorded in Table 2, answer the following questions. Note the turbojet is not equipped with a diffuser. The measured turbine outlet temperature (state 4) is a stagnation quantity. The compressor pressure ratio, P2/P1, is a function of the engine speed, ?, as expressed as

*Load cell voltage (V) is converted to thrust (N) at 1:1 ratio.

It asks for : T-s diagram of the cycle.

the turbine-inlet temperature, T3;

the exhaust velocity, v5;

the air flow rate (Note: the measured thrust is the output of an actual cycle and thus cannot be used for deriving the equations. )

Calculate the thrust produced by the ideal turbojet cycle; cycle thermal efficiency (ratio of the useful output and the required input) and plot it versus engine speed;

temperature and pressure at each state from 1 to 5.