Static pressure in Compressor, Burner, Turbine

[roldy]

I posted a question about this a couple days ago but I have since solved for the total temperatures in the compressor, burner, and turbine.

My question is this. How do I calculate the static pressure in the compressor, burner, and turbine when i know the following data at each station?

Known:
Mach #
Static Temperature
Total Pressure
Static Temperature
speed of sound
velocity
mass flow rate

I need to know the static temperature so I can calculate the density, which then leads to calculating the area.

 

[Navin A S]

I have been trying to look up equations but I am a bit lost on this. Any help would be appreciated. The equation you're looking for is the ideal gas law. The ideal gas law states that the pressure is equal to the product of the density, the temperature, and the universal gas constant. Mathematically, it looks like this: P = ρ*T*Rwhere P is the pressure, ρ is the density, T is the temperature, and R is the universal gas constant. In order to calculate the static pressure at each station, you need to first calculate the density. To do this, you will need to use the Mach number, speed of sound, and velocity to calculate the stagnation temperature, which is equal to the sum of the static temperature and the square of the Mach number multiplied by the speed of sound. Once you have the stagnation temperature, you can use the mass flow rate to calculate the density. Once you have the density, you can then use the ideal gas law to calculate the static pressure at each station.