Fans, Compressors & Turbines for Jet Engines

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Presentation transcript:

Fans, Compressors & Turbines for Jet Engines P M V Subbarao Professor Mechanical Engineering Department Life Management Systems for A Flying Machine.

Fans & Compressors

Euler Turbo-machine Equation Vwhirl, out Vwhirl, in Applying conservation of angular momentum, the torque, T, must be equal to the time rate of change of angular momentum in a stream tube that flows through the device

Axial Flow Turbo-machines Fan or compressor Rotor Blades The power, P of a fluid Machine

Action & Reaction If the tangential velocity increases across a moving blade then work is added to the flow ( a fan or a compressor). If the tangential velocity decreases across a moving blade then work is removed from the flow (a turbine).

Classification of Fans & Compressors Roto-dynamic Compressors Positive Displacement of Compressors Reciprocating Compressors Rotory Centrifugal Compressors Hybrid Compressors Axial Compressors

Multistage Axial flow fans & Compressors

Schematic representation of a multi stage axial flow compressor

Need for a Stator in multi-stage fan or compressor In general, a rotor also adds kinetic energy along with enthalpy to the fluid. A diffuser known as stator succeed the rotor to convert the excess kinetic energy into enthalpy.

Thermodynamics of An Ideal Axial flow fan/Compressor Stage p02 = p03 T02 = T03 V32/cp p3 V22/cp p2 T p01 T01 V12/cp p1 T1 s

Euler’s Action behind the increase in Enthalpy of Air

Mean Stream line Kinematics of An Ideal Axial Flow fan/ Compressor Stage Inlet Velocity Triangle Outlet Velocity Triangle

Kinetics of An Axial Flow Fan/Compressor Stage Rate of Change of Momentum: Power Consumed by an Ideal Moving Blade Inlet Velocity Triangle Current Design Practice: Outlet Velocity Triangle

Energy Analysis of An Axial Flow Fan /Compressor Stage Change in Enthalpy of fluid in moving blades: Inlet Velocity Triangle Outlet Velocity Triangle

Level of Compression in A Rotor Power consumed by an ideal rotor : Power absorbed by fluid in a rotor : First law for relative flow through moving blades: Isentropic compression in A Rotor Blade Degree of Reaction of A Stage

Total Effect by an isentropic Stage of a Fan /compressor:

Irreversible Adiabatic Stage of an Axial Flow Fan/Compressor p03s=p02s p02 p03 T03=T02 Rotor Losses Total Losses T02s T03s T p01 T01 s