Rotating-Plate Radial Turbine in Gas-Turbine-Cycle Configurations

Abstract

A novel power-producing concept is disclosed, employing a rotating-plate radial gas turbine in various gas-turbine cycle configurations. The “rotating-plate radial gas turbine” is a rotating barrel with robust rectangular plates fitted into the turbine rotor, performing the function and the role of turbine blades, contained within a motionless rigid horizontal cylinder (casing). Combustion can take place in the spaces confined between adjacent rotating plates and the static cylinder, thus enabling a practical achievement of the Atkinson cycle (constant-volume heat addition) with improved cycle thermal efficiency. Alternatively, two or more compressor stages can be combined to feed a single rotating-plate radial gas turbine in cascades, thus gradually increasing pressure of working gas within a volume bordered by adjacent un-cooled rotating plates of the radial gas turbine and the casing. Alternatively, a single compressor may be combined with one or more stages of an axial turbine for cascade feeding of a single rotating-plate radial gas turbine. This “isochoric stuffing” effect enables achievement of significantly and even drastically improved gas-turbine-cycle thermal efficiencies. Cycle heat addition may be either isobaric or isochoric in either an open-cycle or a closed-cycle configuration. Using a sufficiently efficient radial gas turbine, it is theoretically possible to obtain 100% cycle thermal efficiency in a simple radial-gas-turbine configuration with appropriately chosen compressor-stages compression pressure ratios.

1 . A simple open-cycle gas-turbine power-producing system comprising a conventional compressor ( 1 ) of any suitable type (axial, radial, reciprocating, etc.) compressing air (working gas), an isobaric (constant-pressure) combustion chamber ( 4 ) fuelled by a gaseous or a liquid fuel, and a load, typically an electric generator ( 8 ), connected to said compressor ( 1 ) via a common rotating shaft, wherein the improvement comprises use of a “rotating-plate radial gas turbine” ( 7 ), which is essentially a rotating barrel with robust rectangular plates fitted into the turbine rotor (turbine blades) contained within a motionless rigid horizontal cylinder (casing), connected to the said compressor ( 1 ) and the said electric generator ( 8 ) via the same said common rotating shaft, fed with air (working gas) by the said compressor ( 1 ) and also exhausting the expanded combustion gas from the radial direction thru corresponding side/top/bottom openings in the said cylinder/casing, with an optional isochoric (constant-volume) heat addition (instead of said isobaric combustion chamber ( 4 )) occurring in the spaces confined between adjacent un-cooled rotating plates and said static cylinder, where also a gaseous or a liquid fuel has to be injected and ignited by means of an electric spark, thus enabling a practical achievement of the Atkinson cycle (adiabatic compression and expansion, isochoric heat addition and isobaric heat rejection) with improved cycle thermal efficiency and greater cycle output. 
     
     
         2 . The gas-turbine power-producing system of the  claim 1 , wherein, in addition to the said compressor ( 1 ), the gas-turbine configuration comprises also a second stage of the compressor ( 2 ), accompanied by an intercooler ( 17 ) between the two said compressor stages, for achievement of a greater cycle output and a higher cycle thermal efficiency. 
     
     
         3 . The gas-turbine power-producing system of the  claim 1 , wherein the gas-turbine configuration additionally comprises an absorption refrigeration chiller ( 10 ), utilizing an appropriate refrigerant-carrier (ammonia-water or water-lithium bromide) mixture/solution, consisting of: a generator ( 11 ) heated by the exhaust gas from the said radial gas turbine ( 7 ) and evaporating the refrigerant from the solution, a condenser ( 12 ) for bringing the refrigerant into the liquid state, an absorber ( 16 ) for absorbing cold refrigerant vapor into the liquid solution, both said condenser ( 12 ) and said absorber ( 16 ) rejecting heat to cooling water or air from the environment, an expansion valve ( 13 ) for bringing the refrigerant to a lower temperature and an evaporator ( 14 ) for evaporating of the refrigerant by pre-cooling of air (working gas) at the inlet of the said compressor ( 1 ), thus enabling achievement of a greater cycle output and a higher cycle thermal efficiency. 
     
     
         4 . The gas-turbine power-producing system of the  claim 3 , wherein, in addition to said compressor ( 1 ) and the corresponding said evaporator ( 14 ), the gas-turbine configuration comprises also a second stage of the compressor ( 2 ), accompanied by an intercooler ( 17 ) and a corresponding second-stage evaporator ( 15 ) for pre-cooling of air (working gas) at the inlet of the said second-stage compressor ( 2 ), both said intercooler ( 17 ) and said second-stage evaporator ( 15 ) located between the two said compressor stages, for achievement of a greater cycle output and a higher cycle thermal efficiency. 
     
     
         5 . The gas-turbine power-producing system of the  claim 1 , wherein, in addition to said compressor ( 1 ), the gas-turbine configuration comprises also a second stage of the compressor ( 2 ), a third stage of the compressor ( 3 ) and, if need may be, a plurality of the compressor stages, combined in such a way as to feed said rotating-plate radial gas turbine ( 7 ) in cascades from the radial direction thru corresponding side/top/bottom openings in the said cylinder/casing, thus gradually increasing pressure of air (working gas) within a constant volume bordered by adjacent un-cooled rotating plates of the said radial gas turbine ( 7 ) and the said casing, thus enabling achievement of a greater cycle output and a higher cycle thermal efficiency, whereas said isobaric/isochoric combustion chamber ( 4 ) is located between the highest-pressure stage of the said compressor and the said radial gas turbine ( 7 ). 
     
     
         6 . A closed-cycle gas-turbine power-producing system similar to the open-cycle gas-turbine power-producing system of the  claim 5 , wherein a suitable working gas (helium, CO 2 , nitrogen, etc.) or a gas mixture is being circulated and wherein the gas-turbine configuration comprises a closed-type gas heater ( 4 ″) (heat input from: fossil fuels, nuclear fuels, renewable energy sources or waste heat) instead of said isobaric/isochoric combustion chamber ( 4 ), located between the outlet of the highest-pressure stage of said compressor and the inlet of said radial gas turbine ( 7 ), and also a closed-type heat rejection device ( 18 ), typically a heat exchanger cooled by the environmental water or air. 
     
     
         7 . The gas-turbine power-producing system of the  claim 5 , wherein the gas-turbine configuration does not comprise said isobaric/isochoric combustion chamber ( 4 ) or any other heat addition at all and wherein it employs solely the effect of a gradual increase of the air (working-gas) pressure within a constant volume bordered by adjacent rotating plates of said radial gas turbine ( 7 ) and the said static casing as a result of feeding the said rotating-plate radial gas turbine ( 7 ) in cascades from the radial direction by combining multiple stages of the said compressor, thus achieving a positive cycle output and the cycle thermal efficiency of 100%. 
     
     
         8 . A closed-cycle gas-turbine power-producing system similar to that of the  claim 6 , wherein the said closed-type gas heater ( 4 ″) is located: (a) either between the outlet of the highest-pressure stage of said compressor and the inlet of said radial gas turbine ( 7 ) (for higher-temperature heat addition), or (b) between the outlet of the said radial gas turbine ( 7 ) and the inlet of the lowest-pressure stage of the said compressor (for lower-temperature heat addition), whereas the said closed-cycle gas-turbine configuration does not comprise any heat rejection device, thus achieving a positive cycle output and the cycle thermal efficiency of 100%. 
     
     
         9 . The open-cycle gas-turbine power-producing system of the  claim 5 , or a similar closed-cycle gas-turbine power-producing system using a suitable working gas (helium, CO 2 , nitrogen, etc.) or a gas mixture and comprising said closed-type gas heater ( 4 ″) and also said closed-type heat rejection device ( 18 ) (typically a heat exchanger cooled by environmental water or air), wherein said open-cycle or said closed-cycle gas-turbine configuration additionally comprises an absorption refrigeration chiller ( 10 ), utilizing an appropriate refrigerant-carrier (ammonia-water or water-lithium bromide) mixture/solution, consisting of: a generator ( 11 ) heated by exhaust gas from the said radial gas turbine ( 7 ) and evaporating the refrigerant from the solution, a condenser ( 12 ) for bringing the refrigerant into the liquid state, an absorber ( 16 ) for absorbing cold refrigerant vapor into the liquid solution, both said condenser ( 12 ) and said absorber ( 16 ) rejecting heat to cooling water or air from the environment, an expansion valve ( 13 ) for bringing the refrigerant to a lower temperature and an evaporator ( 14 ) for evaporating of the refrigerant by pre-cooling of air (or any other working gas) at the inlet of the first stage ( 1 ) of the said multi-staged compressor, enabling achievement of a greater cycle output and a higher cycle thermal efficiency. 
     
     
         10 . The open-cycle gas-turbine power-producing system of the  claim 5 , or a similar closed-cycle gas-turbine power-producing system using a suitable working gas (helium, CO 2 , nitrogen, etc.) or a gas mixture and comprising said closed-type gas heater ( 4 ″) and also said closed-type heat rejection device ( 18 ) (typically a heat exchanger cooled by the environmental water or air), wherein said open-cycle or said closed-cycle gas-turbine configuration additionally comprises a recuperator ( 9 ), which is typically a counter-current heat exchanger for preheating of air (or any other working gas) exiting each of the said compressor stages by exhaust gas from the said radial gas turbine ( 7 ), thus enabling achievement of a greater cycle output and a higher cycle thermal efficiency, whereas heat is being added to each of the compressed working-gas streams coming from each of the said compressor stages after said working-gas preheating in the said recuperator ( 9 ), using corresponding number of said combustion chambers ( 4   a ,  4   b ,  4   c , . . . ) or said closed-type gas heaters ( 4   a ″,  4   b ″,  4   c ″, . . . ). 
     
     
         11 . The open-cycle or the closed-cycle gas-turbine power-producing system of the  claim 10 , wherein said recuperator ( 9 ) is located between the lowest-pressure compressor stage ( 1 ) and the second compressor stage ( 2 ), preheating air (or any other working gas) at the outlet of the said lowest-pressure compressor stage ( 1 ) (prior to the inlet of the said second compressor stage ( 2 )) by exhaust gas from the said radial gas turbine ( 7 ), thus enabling achievement of a lower cycle output and a similar cycle thermal efficiency. 
     
     
         12 . The open-cycle or the closed-cycle gas-turbine power-producing system of the  claim 10 , wherein said open-cycle or said closed-cycle gas-turbine configuration with said recuperator ( 9 ) additionally comprises an absorption refrigeration chiller ( 10 ), utilizing an appropriate refrigerant-carrier (ammonia-water or water-lithium bromide) mixture/solution, consisting of: a generator ( 11 ) heated by exhaust gas from the said radial gas turbine ( 7 ) and evaporating the refrigerant from the solution, a condenser ( 12 ) for bringing the refrigerant into the liquid state, an absorber ( 16 ) for absorbing cold refrigerant vapor into the liquid solution, both said condenser ( 12 ) and said absorber ( 16 ) rejecting heat to cooling water or air from the environment, an expansion valve ( 13 ) for bringing the refrigerant to a lower temperature and an evaporator ( 14 ) for evaporating of the refrigerant by pre-cooling of air (or any other working gas) at the inlet of the first stage ( 1 ) of the said multi-staged compressor, thus enabling achievement of a greater cycle output and a higher cycle thermal efficiency. 
     
     
         13 . The open-cycle or the closed-cycle gas-turbine power-producing system of the  claim 12 , wherein said recuperator ( 9 ) is located between the lowest-pressure compressor stage ( 1 ) and the second compressor stage ( 2 ), preheating air (or any other working gas) at the outlet of the said lowest-pressure compressor stage ( 1 ) (prior to the inlet of the said second compressor stage ( 2 )) by exhaust gas from the said radial gas turbine ( 7 ), thus enabling achievement of a lower cycle output and a similar cycle thermal efficiency. 
     
     
         14 . An open-cycle gas-turbine power-producing system similar to the gas-turbine power-producing system of the  claim 5 , wherein, instead of the said multi-staged compressor, said single-stage compressor ( 1 ) is being used coupled with an axial turbine ( 5 ), or with an additionally provided second stage of the axial turbine ( 6 ), or, if need may be, with additionally provided multiple axial turbine stages, combined with the said compressor ( 1 ) in such a way as to feed said rotating-plate radial gas turbine ( 7 ) in cascades from the radial direction thru corresponding side/top/bottom openings in the said cylinder/casing, thus gradually increasing pressure of air (working gas) within a constant volume bordered by adjacent un-cooled rotating plates of the said radial gas turbine ( 7 ) and the said casing, thus enabling achievement of a greater cycle output and a higher cycle thermal efficiency, whereas said isobaric/isochoric combustion chamber ( 4 ) is located between the said compressor ( 1 ) and the first stage of the said axial gas turbine ( 5 ), adding heat to the total air (working gas) flow rate. 
     
     
         15 . A closed-cycle gas-turbine power-producing system similar to the open-cycle gas-turbine power-producing system of the  claim 14 , wherein a suitable working gas (helium, CO 2 , nitrogen, etc.) or a gas mixture is being circulated and wherein the gas-turbine configuration comprises a closed-type gas heater ( 4 ″) (heat input from: fossil fuels, nuclear fuels, renewable energy sources or waste heat) instead of said isobaric/isochoric combustion chamber ( 4 ), located between the outlet of the said compressor ( 1 ) and the inlet of the first stage of the said axial gas turbine ( 5 ), and also a closed-type heat rejection device ( 18 ), typically a heat exchanger cooled by the environmental water or air. 
     
     
         16 . The open-cycle gas-turbine power-producing system of the  claim 14 , or a similar closed-cycle gas-turbine power-producing system using a suitable working gas (helium, CO 2 , nitrogen, etc.) or a gas mixture and comprising said closed-type gas heater ( 4 ″) and also said closed-type heat rejection device ( 18 ), wherein said open-cycle or said closed-cycle gas-turbine configuration additionally comprises a recuperator ( 9 ), which is typically a counter-current heat exchanger for preheating of air (or any other working gas) exiting the said compressor ( 1 ) by exhaust gas from the said radial gas turbine ( 7 ), thus enabling achievement of a greater cycle output and a higher cycle thermal efficiency. 
     
     
         17 . The open-cycle or the closed-cycle gas-turbine power-producing system of the  claim 16 , wherein said recuperator ( 9 ) is located between the said compressor ( 1 ), being the lowest-pressure compressor stage, and additionally included second compressor stage ( 2 ), preheating air (or any other working gas) at the outlet of the said lowest-pressure compressor stage ( 1 ) (prior to the inlet of the said second compressor stage ( 2 )) by exhaust gas from the said radial gas turbine ( 7 ), thus enabling achievement of a similar or greater cycle output and a higher cycle thermal efficiency. 
     
     
         18 . The open-cycle gas-turbine power-producing system of the  claim 14 , or a similar closed-cycle gas-turbine power-producing system using a suitable working gas (helium, CO 2 , nitrogen, etc.) or a gas mixture and comprising said closed-type gas heater ( 4 ″) and also said closed-type heat rejection device ( 18 ), wherein said open-cycle or said closed-cycle gas-turbine configuration additionally comprises an absorption refrigeration chiller ( 10 ), utilizing an appropriate refrigerant-carrier (ammonia-water or water-lithium bromide) mixture/solution, consisting of: a generator ( 11 ) heated by exhaust gas from the said radial gas turbine ( 7 ) and evaporating the refrigerant from the solution, a condenser ( 12 ) for bringing the refrigerant into the liquid state, an absorber ( 16 ) for absorbing cold refrigerant vapor into the liquid solution, both said condenser ( 12 ) and said absorber ( 16 ) rejecting heat to cooling water or air from the environment, an expansion valve ( 13 ) for bringing the refrigerant to a lower temperature and an evaporator ( 14 ) for evaporating of the refrigerant by pre-cooling of air (or any other working gas) at the inlet of the said compressor ( 1 ), thus enabling achievement of a greater cycle output and a higher cycle thermal efficiency. 
     
     
         19 . The open-cycle or the closed-cycle gas-turbine power-producing system of the  claim 18 , wherein said open-cycle or said closed-cycle gas-turbine configuration with said absorption refrigeration chiller ( 10 ) additionally comprises a recuperator ( 9 ), typically a counter-current heat exchanger for preheating of air (or any other working gas) exiting the said compressor ( 1 ) by exhaust gas from the said radial gas turbine ( 7 ), thus enabling achievement of a greater cycle output and a higher cycle thermal efficiency. 
     
     
         20 . The open-cycle or the closed-cycle gas-turbine power-producing system of the  claim 19 , wherein said recuperator ( 9 ) is located between the said compressor ( 1 ), being the lowest-pressure compressor stage, and additionally included second compressor stage ( 2 ), preheating air (or any other working gas) at the outlet of the said lowest-pressure compressor stage ( 1 ) (prior to the inlet of the said second compressor stage ( 2 )) by exhaust gas from the said radial gas turbine ( 7 ), thus enabling achievement of a similar or greater cycle output and a higher cycle thermal efficiency.