1612LTK13A: Exam Aircraft Gas Turbines - Engineering Assignment Help

Assignment Task:

TASK:

Exercise 1 – Engine performance calculation (70 points) An aircraft is equipped with an experimental turbofan engine shown in Figure 1. The engine is NOT ideal and there are losses within the different components of the machine. Use the data and assumptions provided in the Performance Data Table to answer the following questions. Use the numbering reported in Figure 1 in your solutions. There are 2 data tables provided. Choose the correct one according to the following criteria. (Choosing the wrong table results in incorrect answers) Student No. 67775X

Table1: The last digit of your student number is an even number (0,2,4,6,8)

Table2: The last digit of your student number is an odd number (1,3,5,7,9)

Exercise 2 – Engine performance calculation (30 points) The engine shown in Figure 1 will be conditioned for land usage in electricity production as a turbo-shaft configuration. For this purpose, the front Fan is removed and an electric generator will be attached to the LP shaft instead. The exhaust nozzle will be replaced by a duct directly to the atmosphere. The back-pressure at the LP Turbine will be P05 =1 bar. The engine will use natural gas as fuel LHV=40MJ/kg.

1. Calculate the fuel consumption in kg/s (Blackwell diagram cannot be used) (5 pts)

2. Calculate the exhaust gas temperature of the engine after the LP turbine (10pt.)

3. Calculate the power delivered to the electric generator (10pt.)

4. Is it possible to install a Recuperator to improve the efficiency of the engine? Explain your reasoning (3 lines max). (5pts) IMPORTANT: Since this is a stationary machine, perform your calculations at M=0 and standard atmosphere of 0ft. Use isentropic efficiencies, shaft efficiencies and combustion temperature from the same Data table you used in Problem 1. Consider the core mass flow to be the same as the one calculated in Exercise 1.

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