Computational and Experimental Testing of Aircraft Bell Nozzle: Technical Note

Ferdaus, F.; Ganapathi, None R.

doi:10.4273/ijvss.11.5.25

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“…Nozzle inlet temperature (T 04 ) is calculated from the mechanical efficiency formula by substituting the values of turbine inlet temperature (T 03 ), the mass flow rate of fuel (M f ) and air (Ma), mechanical efficiency (h m ), and compressor outlet temperature (T 02 ) [19,20].…”

Section: Amount Of Heat Added In Combustion Chambermentioning

confidence: 99%

Stage reduced counter-rotating axial compressor for jet engine

Ferdaus

Kumar²,

Sakthivel

et al. 2021

Int. J. Simul. Multidisci. Des. Optim.

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Variation in the states of system, mass flow and pressure are some of the disturbances which are experienced by the compressors in the jet engine under working condition. One of the main factors that influence the efficiency of a jet engine is the pressure ratio. In order to achieve the required pressure ratio, we should have relatively a greater number of stages in the compressor that leads to an increase in the weight of the engine. The stator and rotor are the essential parts of an aircraft's axial compressor. CFD is used in order to evaluate the pressure ratio. In this paper, we are going to analyze a three-stage compressor instead of an actual six-stage compressor. The mass flow rate inside the control system can be used to maintain the stability of the system. Compressor weight and pressure ratio at each stage can be reduced if we have a clockwise and anti-clockwise rotating rotor. With the use of a universal gear system, the two clockwise rotors and one anti-clockwise rotor were analyzed. The main outlook of this work is to show the maximum pressure ratio of the compressor at the outlet with our desired configurations. In conclusion, it was shown that the weight of the aircraft engine can be effectively reduced.

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Section: Amount Of Heat Added In Combustion Chambermentioning

confidence: 99%