Multi-stage turbomachine and design method
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United States of America Patent
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Apr 30, 2002
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app pub date -
Jun 18, 2001
filing date -
Mar 17, 2000
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Abstract
A gas turbo-machine and method of designing and constructing such machine includes preselecting specific operating conditions for the gas turbo-machine, and constructing a master stage as a model to have a given design and geometric shape which results in substantially the optimum efficiency during operation of the master stage at the preselected operating conditions. At least one additional stage is then added to the master stage which is substantially identical to the master stage in geometric shape and design, but in which the linear dimensions of the additional stage differ from those of the master stage in accordance with the formula L.sub.T =D.sub.T +L where L is the ratio of the linear dimensions of the additional stage to the master stage and D is the gas density ratio of the master stage. The turbo-machines of the present invention may be either axial or radial flow, compressors or gas turbines, and isothermal, adiabatic or combinations thereof in operation, there may or may not be tributary flow to or from one or more of the stages and the turbo-machines may be utilized in the generation of electrical power.
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