it is used balance axial thrust on turbine rotor due to admitting of high pressure steam in to turbine. it basic purpose is to save thrust bearing.
A gas turbine engine will usually yield more power by weight than a piston engine. Main downside is that it can't be throttled very well. Energy efficiency isn't all that good to start with, and will drop right down if it has to be operated outside its optimum range.
Turbine maintain very good thrust force balance in IP rolling and high pressure and temp is not required in this.
for thrust balancing.
a compressor does work on the gas , raising its pressure and temperaturea turbine does the reverse , it expands the gas as it passes through the turbine, extracting energy from the gas to do mechanical work.For a typical jet engine , the flow track on a compressor is of a converging cross section while is it diverging for the turbine, which is as per gas dynamic laws.The Turbine does two things here in the jet engine, one ,it runs the compressor and two, expands the gas to the propelling nozzle which produces thrust by accelerating the gas upto its exit.
HP Turbine is High Performance Turbine LP Turbine is Low Performance Turbine
Main difference is that in a gas turbine, combustion is continuous. In a piston engine, combustion is pulsed.
It is used as a compressor. It has the same advantages over a piston compressor as a gas turbine engine has over a piston engine. i.e. no valves, much lower part count and much greater efficiency.
because they have a light weight frame they are able to get away with a piston engine witch make is that much cheaper
One believes you are talking about piston engines- such as a V-l2 or Flat-6 as opposed to Jet or turbine engines. almost all automobiles with the exception of the Rotary-engined Mazda, use piston internal-combustion engines. With aircraft there are piston engined, Turbo-Prop, and straight turbine or turbo-jets. Rockets are a bit out of the pale for common use.
I think your question is self explanatory. A piston engine develops thrust by using pistons. The turbojet engine develops thrust by rotating a turbine. Here both piston and turbine are means of converting thermal energy to mechanical energy. For the piston engine the thermal energy resulted from combustion at constant volume is used to push down the pistons which in turn rotate a shaft. For the turbojet engine(more precisely gas-turbine engine) the thermal energy resulted from the combustion at constant pressure is used to rotate a turbine which is connected to a shaft.
They are either powered by a turbine engine like a jet engine or a piston engine.
Due to the pressure rise developed through the impeller, a pressure difference exists across the hubs and covers such that the impellers have a net thrust in the direction of the compressor inlet. The balance piston counteracts that by being located behind the last impeller. This is accomplished by subjecting the outboard side of the balance piston to a low pressure from the inlet side of the compressor thereby creating a pressure differential opposite to the direction of the impellers. This pressure is acheived by connecting the area behind the piston to the inlet using a line. The impeller thrust not balanced by the balace piston is absorbed by the thrust bearings. I hope this helps
Dummy piston is provided to oppose the axial thrust generated (in the direction of steam) due to incoming steam.
the best of piston's the point of graph
A variation of Aviation Turbine Fuel has always been used in turbine engines. Variations of gasoline have always been used in aircraft with piston engines.
There's an engine-driven compressor. On a turbine engine they pull bleed air off one of the turbine sections; on a piston engine plane it's an accessory to the engine. (Having said that, very few piston planes have pressurized cabins--they don't go high enough to need them.)
Several. Oil less , Turbine, Oiled Piston , single stage, two stage,etc,