Patent ID: 6260349
Filing Date: 2001-07-17
Classification: F01D,F02C

Abstract:
A multistage gas turbo-machine comprising a first stage and a second stage of differing sizes, each stage having turbo-machine blades which are contacted by the gas, an inlet in each stage for introducing the gas to the turbo-machine blades in the stage, a discharge from each stage for discharging the gas from the turbo-machine blades in the stage, and the discharge from one said stage communicating with the inlet of the other said stage; andwherein said first and second stages are substantially identical to each other in design and geometric shape, but in which the linear dimensions of said second stage differ from those of said first stage substantially in accordance with the formulaL=Dwhere L is the ratio of the linear dimensions of the second stage to the first stage when said second stage is downstream of said first stage, and D is the gas density ratio of said first stage, and ##EQU39##where P.sub.I is the absolute pressure of the gas entering said first stage, P.sub.O is the absolute pressure of the gas as discharged from said first stage, T.sub.I is the absolute temperature of the gas entering said first stage, and T.sub.O is the absolute temperature of the gas as discharged from said first stage.