6. Pressure ratio Mass flow rate Ambient conditions Inlet swirl Select Ti alloys as material. Check...

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6. Pressure ratio Mass flow rate Ambient conditions Inlet swirl Select Ti alloys as material. Check the following criteria: O Oy = 965Mpa, Pm = 4650, set cent <0.4 Oy All velocity magnitudes and angles for rotor inlet, rotor outlet/stator inlet, stator outlet Flow path dimensions . Efficiency of the fan Hints: An axial single stage fan has the following parameters: Assuming axial velocity and peripheral velocity is constant throughout the entire fan stage, calculate O O 1.55 1.68 kg/s 101.325 kPa, 288K 0 deg. O Option 1: Select work coefficient (=h), hub to tip ratio of inlet (HTR =), tip speed (Utip = 'tipinlet w), axial velocity. While finding axial velocity, consider inlet tip velocity triangle. Inlet axial velocity is constant from hub to tip section. Inlet tangential velocity is zero, so relative tangential velocity is directly equal to Utip. Set inlet tip relative Mach number as 1.2 in order to find axial velocity. After setting axial velocity you can find area of the compressor. From inlet area and HTR you can find hub, mean and tip radius. After finding tip radius, find rotational speed. For the losses, see example solved in the class. 6. Pressure ratio Mass flow rate Ambient conditions Inlet swirl Select Ti alloys as material. Check the following criteria: O Oy = 965Mpa, Pm = 4650, set cent <0.4 Oy All velocity magnitudes and angles for rotor inlet, rotor outlet/stator inlet, stator outlet Flow path dimensions . Efficiency of the fan Hints: An axial single stage fan has the following parameters: Assuming axial velocity and peripheral velocity is constant throughout the entire fan stage, calculate O O 1.55 1.68 kg/s 101.325 kPa, 288K 0 deg. O Option 1: Select work coefficient (=h), hub to tip ratio of inlet (HTR =), tip speed (Utip = 'tipinlet w), axial velocity. While finding axial velocity, consider inlet tip velocity triangle. Inlet axial velocity is constant from hub to tip section. Inlet tangential velocity is zero, so relative tangential velocity is directly equal to Utip. Set inlet tip relative Mach number as 1.2 in order to find axial velocity. After setting axial velocity you can find area of the compressor. From inlet area and HTR you can find hub, mean and tip radius. After finding tip radius, find rotational speed. For the losses, see example solved in the class.

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solving for the parameters of an axial singlestage fan The prompt says to assume axial and peripheral velocities are constant throughout the fan stageHere are some steps to take to solve the problem S... View the full answer