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Conceptual Design of a Supersonic Jet Engine

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Conceptual Design of a Supersonic Jet Engine ( conceptual-design-supersonic-jet-engine )

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Pressure loss Figure 6: Typical burner [22] A pressure loss occurs in the combustion chamber due to skin friction and the rise in temperature. The skin friction loss is called the cold loss and accounts for approximately 90% of the total pressure loss. The loss due to rise in temperature is called the fundamental loss and accounts for the remaining 10% [23]. The pressure loss has been estimated using the method described in reference [22] and is dependent on the maximum area of the burner, the PLF and the inlet 𝑇0 and 𝑃0. The PLF is an assumed value and is typically in the range of 20 to 25 [23]. Efficiency The efficiency of the burner can be found from a chemical analysis of the combustion products. Knowing the fuel to air ratio and the proportion of incompletely burnt constituents, it is possible to calculate the ratio of the actual energy released to the theoretical quantity available. Due to a number of reasons this is a very complicated approach. In practice, the combustion is complete at high-power to mid-power conditions [19] and the burner efficiency has therefore been assumed to be 0,9999. 3.3.4 Internal ducts The ducts have been designed using cubic splines to allow for smooth surfaces between the components trying to minimize the pressure loss. However, no pressure loss calculations have been performed, the losses are assumptions based on the guidelines given in reference [11]. 3.3.5 Inlet Due to time limitations, only a basic 2D/axisymmetric inlet using oblique shocks to diffuse the incoming air has been designed. Tabulated values of normal shock properties found in reference [24] have been used to calculate the total pressure loss and new Mach numbers after the shocks. The inlet has been designed to create an oblique shock at the inlet start, reducing the Mach number to a value close to one, after which a normal shock at the venturi reduces the value to below one. After this, the velocity is diffused in the divergent part using the continuity equation to an acceptable value before entering the fan. These calculations assume an isentropic flow. To compensate for this the total pressure loss has been multiplied by a factor of 0,997 for the subsonic region to account for pressure losses due to skin friction. The necessary formulas and equations can be found in [24]. With 25

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