Performance Analysis of Multi Stage Axial Flow Compressors

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Presentation transcript:

Performance Analysis of Multi Stage Axial Flow Compressors P M V Subbarao Professor Mechanical Engineering Department Design of Performance….

Irreversible Stage of an Axial Flow Compressor T03=T02 T02s Rotor Losses Total Losses T03s T p01 T01 s

Thermodynamics of Irreversible Compressor

Stage Efficiency The stage efficiency of an adiabatic compressor stage is: For calorically perfect gas

Power input to the compressor : Inlet Velocity Triangle Outlet Velocity Triangle Current Practice: Theoretical Power input to the compressor:

For an isentropic compressor:

Polytropic Stage Efficiency The ratio of the ideal specific work input to actual specific input for a differential pressure change

For a differential isentropic compression Integrating for the complete stage

Loss Factors in an Irreversible Compressor stage Cascade testing gives the values of these loss factors. General value of Loss factors:

Conservation of Rothalpy Define the rothalpy which is constant throughout the rotor. The rothalpy is useful for calculating the outlet conditions of the rotor. For an isentropic rotor

Relative total pressures & Total Temperatures

Current Design Practice Fan or low pressure Compressor Parameter Range Pressure ratio for single stage 1.5 – 2.0 Pressure ratio for two stages 2.0 – 3.5 Pressure ratio for three stages 3.5 – 4.5 Inlet mass flow rates 195 – 205 kg/m2.s Tip speed 427 – 457 m/s Diffusion factor 0.5 – 0.55

Current Design Practice High pressure Compressor Parameter Range Stage loading coefficient 0.3 – 0.35 Flow coefficient 0.45 – 0.55 Hub/tip ratio 0.6 – 0.75 Inlet mass flow rates 175 – 185 kg/m2.s Tip speed 386 – 457 m/s Diffusion factor 0.5 – 0.55

Compressor Maps

Reciprocating Engine Vs Jet Engine

Fire is An Accident… How to make it More reliable Resource….

Laws of Combustion A Special Device is required to hold the flame, called Burner. The maximum quantity of fuel that can be handled by a single burner is limited. The maximum allowable air to establish efficient combustion of a given amount of fuel is limited. The maximum temperature due to efficient combustion is always higher than the maximum safe temperature: limited by turbine blades. Infra structure should be provided to facilitate these conditions.

Requirements of A Reliable Combustion MATtr Theory Mixing: Fuel preparation systems. Air: Draught systems. T : Preheating of fuel. t : Dimensions of combustion chamber. r: Turbulence generation systems.