Aeroengines and Rocket Science

Data:

Symbols and abbreviations have their usual meaning unless specified otherwise:

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1bar = 105 N/m2

Patm = 1.01325×105 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 tittle, 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 8, Turbine Entry Temperature (TET) 1568K, Combustor pressure loss (% of Compressor outlet pressure) = 5 %,

Air mass flow rate =110 kg/s, Include the fuel flow in your mass flow calculations.

Using the given data, please calculate and explain your results for the two-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. Calculate and comment on the change in thermal efficiency when Turbine Entry Temperature (TET) reduces by 100K. What changes you could do to increase the thermal efficiency in the jet engine, describe with suitable equations and references.
  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.

 

 

SN 2 2.5 3 4 4.5 5 8
T(K)              
P(kPa)              
𝑚(Kg/s)              
A(m^2)              
V(m/s)              
F(N)              
M              
Density              
SFC(hr-1)              

 

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