Patent ID: 6378287
Filing Date: 2002-04-30
Classification: F01D,F02C,Y10T

Abstract:
A multistage gas turbo-machine comprising a first stage and a subsequent 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 stage communicating with the inlet of the other stage; andwherein said first and subsequent stages are substantially identical to each other in design and geometric shape, but in which the linear dimensions of said subsequent stage differ from those of said first stage substantially in accordance with the formula LT=DT3where LT is the ratio of the linear dimensions of the subsequent stage to the first stage when said subsequent stage is downstream of said first stage, and DT is the gas density ratio of said subsequent stage, and DT=(MA+MB&it;totMA)&it;â€ƒ&it;(PI/POTI/TO)n-1where:MA=molar volume flow rate to intake of stage 1, moles/sec; MB tot=total tributary volume flow rate generated in or between all preceding stages, moles/sec; PI=absolute pressure of gas entering stage in question; PO=absolute pressure of gas leaving stage in question; TI=absolute temperature of gas entering stage in question; TO=absolute temperature of gas leaving stage in question; and n=number of the stage in question.