Symbols and abbreviations have their usual meaning unless specified otherwise: 1bar = 105 N/m2

Patm = 1.01325x105 Pa

Air density = 1.2252 kg/m3

For air:

γ = 1.4, R= 287 J/kg.K, CP= 1004 J/kg K

For the combustion products:

γ = 1.3, CP= 1140 J/Kg K, R=283 J/kg.K

The Lower Calorific Value of hydrocarbon aviation fuel: hPR= 45,000KJ/kg Unless specified otherwise, turbomachinery efficiencies are isentropic.

A report of approximately 1200 words (+/-10% words) in length is required with comments and all the assumptions /calculation down for the analysis. The report should follow the technical structure with clear title, table of contents, figures, nomenclature, abstract, introduction, literature review, methodology, results and discussion and conclusion. The report is to be correctly formatted and referenced in accordance with the Harvard referencing system. Each student is to submit their own individual report via Turnitin which should be their work except were stated otherwise. If academic misconduct of any nature is suspected (e.g. plagiarism or collusion), it will be considered using the appropriate procedures as per the University regulation.

The following are the design parameters of a two-spool jet engine with a convergent nozzle at ISA Sea Level Static test rig:

Low Pressure Compressor (LPC) and High Pressure Compressor (HPC) pressure ratio: 5 and 10, Turbine Entry Temperature (TET) =1411, Combustor pressure loss (% of Compressor outlet pressure) = 5 %,

Air mass flow rate =150 kg/s to the jet engine core, Include the fuel flow in your mass flow calculations.

Using the given data, please calculate and explain your results for a twin-spool jet engine.

1. Calculate the mass flow rates, pressures, temperatures through the jet engine inlet to exhaust.

2. Calculate the thrust, Specific Fuel Consumption (SFC), velocity, speed of sound and Mach number at the exit of the jet engine nozzle. Discuss whether the exit nozzle is choked or not?

3. What if the core jet engine is changed with a by-pass turbofan with by-pass ratio of 6 and fan pressure ratio of 1.5 is added to jet engine? What impact it will have on the thrust? Calculate the thrust with this design change and explain whether the turbofan will be fuel efficient compared to pure turbo jet engine.

4. Please populate the blank parameters in the below mentioned excel sheet (not the blocked red colour part) and include it at the start of the results section of your report.