the engine is having high pressure inside the combustion chamber.the flow has to move trough nozzle.incase the pressure is very high at nozzle compared to the intake pressure the flow moves forward.then the compressors shape changed it is not enough to compress the intake air.it is compressor stall
Inefficiencies in the compressor of a gas turbine cycle increase the back-work ratio and decrease the thermal efficiency of the gas turbine cycle, since they increase the compressor work.
Compressor Inlet Temperature sensorfor a Gas turbine engine.
Some varieties of gas turbine engines (e.g. RR Trent and RB211) have 3 concentric rotating shafts. Each shaft connects a compressor with a turbine. The low pressure compressor, or fan, is driven by the low pressure turbine. The high pressure compressor is driven by the high pressure turbine. Between the low and high pressure compressors there is an intermediate pressure compressor and, guess what... it's driven by the intermediate pressure turbine.
The compressor on a gas turbine and other jet engine types takes the air around us at normal pressures, and compresses it to much higher pressures and temperatures. Like the compression stroke on a internal combustion engine, the incoming air needs to be at extreeme pressures for the engine to be efficient.
In a turbine engine, the High-Pressure Compressor (HPC) compresses incoming air, increasing its pressure and temperature before it enters the combustion chamber. Here, fuel is injected and ignited, producing high-temperature, high-pressure gas. This gas expands rapidly and is directed through the turbine, causing it to spin and drive the compressor. The remaining energy in the exhaust gas is used to produce thrust, propelling the aircraft forward.
Inefficiencies in the compressor of a gas turbine cycle increase the back-work ratio and decrease the thermal efficiency of the gas turbine cycle, since they increase the compressor work.
GT compressor pulsation ?
Rotating axial compressor.
GT compressor pulsation ?
Air compressor alone consumes about 50 to 60 % of energy generated by a gas turbine..
This relationship is the reason advances in turbines and axial compressors often find their way cutaway showing an axi-centrifugal compressor gas turbine.
self sustaining speed is output of a turbine= input into compressor
Compressor Inlet Temperature sensorfor a Gas turbine engine.
because anyone can cause you a prodigal son
the types of statore are compressor, gas turbine, turboprop, and jet engine
Damage of the blades of the compressor ,cauesd due high angles of pressure ,caused by air flow is called stalling of a compressor
Some varieties of gas turbine engines (e.g. RR Trent and RB211) have 3 concentric rotating shafts. Each shaft connects a compressor with a turbine. The low pressure compressor, or fan, is driven by the low pressure turbine. The high pressure compressor is driven by the high pressure turbine. Between the low and high pressure compressors there is an intermediate pressure compressor and, guess what... it's driven by the intermediate pressure turbine.