초록 ▼

A compact, highly efficient single spool gas turbine gas generator uses a double-entry centrifugal first stage compressor, a single-entry centrifugal second stage compressor, and a radial inflow turbine to achieve an overall pressure ratio of greater than 15:1. The first stage pressure ratio is more

A compact, highly efficient single spool gas turbine gas generator uses a double-entry centrifugal first stage compressor, a single-entry centrifugal second stage compressor, and a radial inflow turbine to achieve an overall pressure ratio of greater than 15:1. The first stage pressure ratio is more than twice the second stage pressure ratio, and the first stage entrance Mach numbers are greater than about 1.4. The specific speed of each the compressors ranges from 0.65 to 0.85, and of the turbine from 0.50 to 0.75.

대표청구항 ▼

A high efficiency, single spool gas turbine gas generator comprising: (a) compressor means for providing an overall pressure ratio of greater than about 15:1, said compressor means including: (i) a first stage, double-entry centrifugal air compressor having a pair of entrances and a common exit, (ii

A high efficiency, single spool gas turbine gas generator comprising: (a) compressor means for providing an overall pressure ratio of greater than about 15:1, said compressor means including: (i) a first stage, double-entry centrifugal air compressor having a pair of entrances and a common exit, (ii) a second stage, centrifugal air compressor positioned adjacent to said first stage compressor, said second compressor stage having an entrance that is flow-connected to said first stage common exit and also having a second stage exit, and (iii) a shaft assembly for mechanically interconnecting said first and said second stage for rotation at the same angular speed; (b) combustor means operatively connected to the second stage exit for receiving the compressed air and combusting fuel using the compressed air to generate combustion gases; (c) a single stage radial inflow turbine having an inlet and an outlet, said turbine being operatively connected directly to said shaft assembly drive and also being flow connected to said combustor means for receiving at said turbine inlet, and partially expanding, the combustion gases; and (d) exhaust means flow connected to said turbine outlet flro channeling the partially expanded combustion gases for further external work-producing expansion, and wherein (i) said first and said second compressor stages each having a configuration selected to provide a pressure ratio of said first compressor stage greater than about twice the pressure ratio of said second compressor stage, and (ii) said first and second compressor stages each having a configuration selected to exhibit a respective specific speed each greater than about 0.60 at about optimum efficiency.