gsphelp  Turbine Stage

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gsphelp  Turbine Stage

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SGP_TurbineStage

 

Inheriting basic functionality from the turbine details are added to model a single turbine stage.

 

The gas conditions of the NGV exit will be calculated accordingly to the specified input. The basic functionality is similar to the turbine. Calculations are based on a chocked nozzle guide vane. Pressure losses due to friction (non-isentropic expansion) are taken into account. To calculate the pressure losses, the isentropic (ideal) expansion pressure is compared to the non-isentropic expansion pressure corrected for ηis,turbine. This pressure loss can be distributed over the nozzle and rotor using the Stator loss fraction numeric input field. Default the pressure loss is distributed equally (0.5) over the nozzle and rotor blade rows. In case the nozzle is responsible for the entire pressure loss, the Stator loss fraction needs to be set to 0, if the rotor is responsible for the entire pressure loss, the fraction needs to be 1.