The intake and exhaust are linked by the mass conservation equation, so the mass flow at the exhaust will be the same as at the intake plus any added fuel. Fuel mass is generally negligible as turbines tend to run very lean, but if you have it then you can use it.
If you have the mass flow at the exhaust and want the volumetric flow all you need is to link the mass and the volume, i.e. you need the density.
If this turbine is dealing with a fluid that behaves according to the ideal gas law, you could simply obtain the density from the temperature, which you also have. However this disregards any compressibility effects of the fluid, effectively assuming the Mach number at the exhaust is close to zero: $M_8 = 0$. This can also be solved, but requires more data than you seem to have; see equations 10.16 and 10.21 of the linked document, I'll type them in and elaborate once I have a minute.
Alternatively, since you know the thrust and the mass flow, you could use Tsiolkovsky's equation, or more specifically the fact that: $$F_{thrust} = v_e \cdot \dot{m}$$
where $v_e$ is the effective exhaust velocity. Note that this is not the actual, measurable, exhaust velocity except for the case where the engine exhausts into a vacuum.
