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Cfd Analysis of Convergent- Divergent Supersonic Nozzle
Continuity -0.001, X Velocity-0.001, Y Velocity-0.001, Energy -0.001. The iteration continues till the
convergence is reached and convergence history has been shown in Figs. 3.2, 3.3 and 3.4 respectively for
3mm,4mm & 5mm axial gaps of nozzle and turbine rotor blades as a case of partial admission.
Fig 3.2 Convergence history as a Partial admission case of nozzle and rotor blades with 3mm axial gap.
Fig. 3.3: Convergence history as a Partial admission case of Nozzle and rotor blades with 4mm axial gap.
Fig. 3.4: Convergence history as a Partial admission case of Nozzle and rotor blades with 5mm axial gap.
IV. RESULTS AND DISCUSSION
Nozzle profile which is examined in 2D is as shown in Fig. 1.1. Results shown in normal direction is
nothing but 3D flow through the nozzle for given input condition with velocity as 183 m/s and maximum output
was observed as a 1436 m/s, such that Mach Number is increased from 0.2 to 1.54 in which nozzle is acting as
supersonic nozzle and contours of mach number as shown in Fig. 4.1. The velocity contours of nozzle are
plotted in Fig. 4.2, the pressure contours of nozzle is plotted in Fig.4.3, and temperature contours of nozzle are
plotted in figure4.4. The velocity, temperature, Mach number, pressure variation along the nozzle is compared
with theoretical calculation and with experimental results obtained from the literature.
Fig. 4.1: Mach number contours of nozzle.
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