Turbocompressor system and method for controlling the same

Claim 2

A turbocompressor system comprising: a load section requiring air for its operation and discharging exhaust gas; a compressor connected with said load section and delivering compressed air, which is at a pressure adjusted to a predetermined value, to said load section; a turbine having an inlet side connected with said load section and adapted to be driven by the exhaust gas discharged from said load section to said inlet side, said turbine being operably connected to drive said compressor; a flow control valve disposed at said turbine inlet side and cooperatively arranged with said turbine to directly control flow rate of all the exhaust gas supplied to said turbine inlet side; and a control means connected in a closed feedback loop with said compressor and said flow control valve for controlling degree of opening of said flow control valve in response singularly only to the air pressure of the compressed air delivered from said compressor whereby the pressure of the compressed air delivered from said compressor to said load section is adjusted to the predetermined value by control of exhaust gas flow rate to the inlet side of said turbine from the outlet side of said compressor through the closed feedback loop.

Claim 3

A turbocompressor system as set forth in claim 1 wherein said control means comprises: a pressure detector arranged in communication with said compressor in the closed feedback loop and detecting the air pressure of the compressed air delivered from said compressor; and a controller associated with said pressure detector and operably coupled to said flow control valve to control degree of opening of said flow control valve only in response to the singular air pressure detector.

Claim 4

A turbocompressor system as set forth in claim 1 wherein said flow control valve comprises a variable nozzle.

Claim 5

A turbocompressor system as set forth in claim 1 wherein said compressor and said turbine are mounted on a one and the same rotary shaft.

Claim 6

A turbocompressor system as set forth in claim 1 wherein said load section comprises a fuel cell power plant including a fuel cell body and a reformer and adapted to use the compressed air delivered from said compressor for producing a chemical reaction in said fuel cell body as well as for facilitating the combustion of fuel in said reformer.

Claim 7

A turbocompressor system comprising: a load section requiring air for its operation and discharging exhaust gas; a compressor connected with said load section and supplying compressed air to said load section; a turbine having an inlet side connected with said load section and adapted to be driven by the exhaust gas discharged from said load section to said inlet side, said turbine being operably connected with said compressor for driving thereof; a flow control valve disposed at said turbine inlet side and cooperatively arranged with said turbine to directly control flow rate of all exhaust gas supplied to said turbine inlet side; a first control means, operably connected with said compressor and said flow control valve, for controlling degree of opening of said flow control valve in response to pressure of the compressed air delivered from said compressor; an auxiliary burner communicating with said turbine inlet side through said flow control valve; and a second control means, operably connected with said flow control valve, for controlling combustion of fuel in said auxiliary burner in response to pressure of the exhaust gas discharge from said load section.

Claim 8

A turbocompressor system comprising: a load section requiring air for its operation and discharging exhaust gas; a compressor connected with said load section and supplying compressed air to said load section; a turbine having an inlet side connected with said load section and adapted to be driven by the exhaust gas discharged from said load section to said inlet side, said turbine being operably connected with said compressor for driving thereof; a flow control valve disposed at said turbine inlet side and cooperatively arranged with said turbine to directly control flow rate of all exhaust gas supplied to said turbine inlet side; a first control means, operably connected with said compressor and said flow control valve, for controlling degree of opening of said flow control valve in response to pressure of the compressed air delivered from said compressor; an auxiliary burner communicating with said turbine inlet side through said flow control valve; and a second control means, operably connected with said flow control valve, for controlling combustion of fuel in said auxiliary burner in response to pressure of the exhaust gas discharge from said load section.

Claim 9

A turbocompressor system as set forth in claim 6 wherein said second control means comprises: a conduit connecting said auxiliary burner to said turbine inlet side through said flow control valve; a pressure detector disposed in said conduit in communication with said flow control valve and responsive to the exhaust gas pressure at said turbine inlet side; and a controller associated with said pressure detector and operably coupled to said auxiliary burner to control amount of fuel to be fed to said auxiliary burner and amount of air to be fed to said auxiliary burner in response to operation of said control valve.

Claim 10

A turbocompressor system as set forth in claim 6 wherein said first control means comprises: a pressure detector arranged in communication with said compressor and detecting the air pressure of the compressed air delivered from said compressor; and a controller associated with said pressure detector and adapted to control degree of opening of said flow control valve in response singularly only to the air pressure detected by said pressure detector.

Claim 11

A turbocompressor system as set forth in claim 6 wherein said flow control valve comprises a variable nozzle.

Claim 12

A turbocompressor system as set forth in claim 6 wherein said compressor and said turbine are mounted on one and the same rotary shaft.

Claim 13

A turbocompressor system as set forth in claim 6 wherein a part of the air delivered from said compressor is fed to said auxiliary burner.

Claim 14

A turbocompressor system comprising: a load section requiring air for its operation and discharging exhaust gas; a compressor connected with said load section and delivering compressed air to said load section; a turbine having an inlet side connected with said load section and adapted to be driven by the exhaust gas discharged from said load section to said inlet side, said turbine being operably connected with said compressor for driving thereof; means for maintaining constant the compressor delivery air pressure, said means comprising: a flow control valve disposed at said turbine inlet side and cooperatively arranged with said turbine to directly control flow rate of all the exhaust gas supplied to said turbine inlet side; and a control means connected in a closed feedback loop with said compressor and said flow control valve for controlling degree of opening of said flow control valve in response singularly to the compressor delivery air pressure whereby the compressor delivery air pressure is adjusted to a second predetermined value higher than the first predetermined value by control of exhaust gas flow rate to the inlet side of said turbine through the closed feedback loop.

Claim 15

A turbocompressor system comprising: a load section requiring air for its operation and discharging exhaust gas; a compressor connected with said load section and delivering compressed air to said load section; a turbine having an inlet side connected with said load section and adapted to be driven by the exhaust gas discharged from said load section to said inlet side, said turbine being operably connected with said compressor for driving thereof; means for maintaining constant the compressor delivery air pressure, said means comprising: a flow control valve disposed at said turbine inlet side and cooperatively arranged with said turbine to directly control flow rate of all the exhaust gas supplied to said turbine inlet side; and a control means connected in a closed feedback loop with said compressor and said flow control valve for controlling degree of opening of said flow control valve in response singularly to the compressor delivery air pressure whereby the compressor delivery air pressure is adjusted to a second predetermined value higher than the first predetermined value by control of exhaust gas flow rate to the inlet side of said turbine through the closed feedback loop.

Claim 16

A turbocompressor system as set forth in claim 12 wherein said control means comprises: a pressure detector arranged in communication with said compressor and detecting the singular air pressure of the air delivered from said compressor; and a first controller operably coupled to said pressure detector and said flow control valve and adapted to control the opening degree of said flow control valve only in response to the singular air pressure detected by said pressure detector.

Claim 17

A turbocompressor system as set forth in claim 12 wherein said flow control valve comprises a variable nozzle.

Claim 18

A turbocompressor system as set forth in claim 12 wherein said compressor and said turbine are mounted on one and the same rotary shaft.

Claim 19

A turbocompressor system as set forth in claim 12 further comprising a limiter means for defining a maximum limit and minimum limit of the opening degree of said flow control valve.

Claim 20

A turbocompressor system as set forth in claim 12 further comprising: an auxiliary burner between said load section and communicating with said turbine inlet side through said flow control valve; and a further control means, operably connected with said flow control valve, for controlling combustion of fuel in said auxiliary burner in response to operation of said flow control valve to adjust the pressure of the exhaust gas at said turbine inlet side to a predetermined level.

Claim 21

A turbocompressor system as set forth in claim 18 wherein said further control means comprises: a conduit connecting said auxiliary burner to said turbine inlet side through said flow control valve; a pressure detector disposed in said conduit in communication with said flow control valve and responsive to exhaust gas pressure of the exhaust gas at said turbine inlet side; and a controller associated with said pressure detector and operably coupled to said auxiliary burner to control amount of fuel fed to said auxiliary burner and amount of air fed to said auxiliary burner in response to operation of said control valve.

Claim 22

A turbocompressor system as set forth in claim 17 further comprising an exhaust-gas venting means, operably connected with said control valve, for venting exhaust gases discharged from said load section and said auxiliary burner to the ambient atmosphere in response to operation of said flow control valve.

Claim 23

A turbocompressor system as set forth in claim 19 wherein said exhaust-gas venting means comprises: a conduit connecting said auxiliary burner to said turbine inlet side through said flow control valve; a vent passage branched from said conduit and leading to the ambient atmosphere; a vent valve disposed in said vent passage for controlling the flow rate of the exhaust gas vented to the atmosphere; a pressure detector responsive to the exhaust gas pressure at said turbine inlet side; and a controller associate with said pressure detector and operably coupled to said vent valve to control degree of opening of said vent valve in response to operation of said flow control valve.

Claim 24

A turbocompressor system as set forth in claim 12 further comprising: an auxiliary burner communicating with said turbine inlet side through said flow control valve; and an exhaust-gas venting means, operably connected with said flow control valve, for venting exhaust gas discharged from said load section and said auxiliary burner to the ambient atmosphere in response to operation of said control valve.

Claim 25

A turbocompressor system as set forth in claim 21 wherein said exhaust-gas venting means comprises: a conduit connecting said auxiliary burner to said turbine inlet side through said flow control valve; a vent passage branched from said conduit and leading to the ambient atmosphere; a vent valve disposed in said vent passage for controlling the flow rate of the exhaust gas vented to the atmosphere; a pressure detector responsive to pressure of exhaust gas discharged from said load section at said turbine inlet side; and a controller associated with said pressure detector and operably coupled to said vent valve to control degree of opening of said vent valve in response to operation of said flow control valve.

Claim 26

A turbocompressor system as set forth in claim 12 wherein said load section comprises a fuel cell power plant including a fuel cell body and a reformer and adapted to use the compressed air delivered from said compressor for producing a chemical reaction in said fuel cell body as well as for facilitating combustion in said reformer.

Claim 27

A turbocompressor system comprising: a load section requiring air for its operation and discharged exhaust gas; a compressor connected with said load section for supplying compressed air to said load section; a turbine having an inlet side connected with said load section and adapted to be driven by the exhaust gas discharged from said load section to said inlet side, said turbine being operably connected with said compressor for driving thereof; a flow control valve disposed at said turbine inlet side and cooperatively arranged with said turbine to directly control the flow rate of all exhaust gas supplied to said turbine inlet side; a conduit connected to said turbine inlet side; an auxiliary burner connected by said conduit to said turbine inlet side through said flow control valve; a second control means, operably connected with said flow control valve, for controlling the combustion of fuel in said auxiliary burner in response to the direct control by said flow control valve of all exhaust gas at said turbine inlet side to adjust the pressure of the exhaust gas at said turbine inlet side to a first predetermined level; a bypass passage branched from said conduit and leading toward the ambient atmosphere; a bypass valve operably arranged in said bypass passage to control the flow rate of the exhaust gas vented to the atmosphere and bypassing said turbine; and a third control means connected in a closed feedback loop with said bypass valve and said flow control valve for controlling degree of opening of said bypass valve in response to the direct control of all exhaust gas at said turbine inlet side to adjust the exhaust gas pressure at said turbine inlet side to a second predetermined level higher than said first predetermined level.

Claim 28

A turbocompressor system comprising: a load section requiring air for its operation and discharged exhaust gas; a compressor connected with said load section for supplying compressed air to said load section; a turbine having an inlet side connected with said load section and adapted to be driven by the exhaust gas discharged from said load section to said inlet side, said turbine being operably connected with said compressor for driving thereof; a flow control valve disposed at said turbine inlet side and cooperatively arranged with said turbine to directly control the flow rate of all exhaust gas supplied to said turbine inlet side; a conduit connected to said turbine inlet side; an auxiliary burner connected by said conduit to said turbine inlet side through said flow control valve; a second control means, operably connected with said flow control valve, for controlling the combustion of fuel in said auxiliary burner in response to the direct control by said flow control valve of all exhaust gas at said turbine inlet side to adjust the pressure of the exhaust gas at said turbine inlet side to a first predetermined level; a bypass passage branched from said conduit and leading toward the ambient atmosphere; a bypass valve operably arranged in said bypass passage to control the flow rate of the exhaust gas vented to the atmosphere and bypassing said turbine; and a third control means connected in a closed feedback loop with said bypass valve and said flow control valve for controlling degree of opening of said bypass valve in response to the direct control of all exhaust gas at said turbine inlet side to adjust the exhaust gas pressure at said turbine inlet side to a second predetermined level higher than said first predetermined level.

Claim 29

A turbocompressor system as set forth in claim 24 wherein said second control means comprises: a pressure detector disposed in said conduit in communication with said control valve and responsive to the exhaust gas pressure at said turbine inlet side; and a controller associated with said pressure detector and operably coupled to said auxiliary burner to control the amount of fuel fed to said auxiliary burner and the amount of air fed to said auxiliary burner in response to the pressure of the exhaust gas detected by said pressure detector.

Claim 30

A turbocompressor system as set forth in claim 24 wherein said first control means comprises: a pressure detector operably connected to said compressor to detect the pressure of the air delivered from said compressor; and a controller associated with said pressure detector and operably coupled to said flow control valve to control degree of opening of said flow control valve in response singularly only to the air pressure detected by said pressure detector.

Claim 31

A turbocompressor system as set forth in claim 24 further comprising a limited means for defining a minimum level of the combustion of fuel in said auxiliary burner.

Claim 32

A turbocompressor system as set forth in claim 24 wherein said flow control valve comprises a variable nozzle.

Claim 33

A turbocompressor system as set forth in claim 24 wherein said compressor and said turbine are mounted on one and the same rotary shaft.

Claim 34

A turbocompressor system as set forth in claim 24 wherein a part of the air delivered form said compressor is fed to said auxiliary burner.

Claim 35

A turbocompressor system as set forth in claim 24 wherein said load section comprises a fuel cell power plant including a fuel cell body and a reformer and adapted to use the compressed air delivered from said compressor for producing a chemical reaction in said fuel cell body as well as for facilitating combustion in said reformer.

Claim 38

A method for controlling a turbocompressor system as set forth in claim 32 wherein said load section comprises a fuel cell power plant including a fuel cell body and a reformer and wherein said method further comprises delivering the compressed air from said compressor in said load section for producing a chemical reaction in said fuel cell as well as for facilitating combustion in said reformer.

Claim 41

A method for controlling a turbocompressor system as set forth in claim 34 further comprising: detecting pressure of the exhaust gas from said load section and said auxiliary burner at said inlet side of said turbine; maintaining constant compressor delivery air pressure by directly controlling, through regulation of a flow control valve disposed at an inlet side of aid turbine, pressure of all exhaust gas fed to said to said turbine; and controlling the amount of fuel to be fed to said auxiliary burner and the amount of air to be fed to said auxiliary burner in response to the detected pressure of the exhaust gas.

Claim 42

A method for controlling a turbocompressor system as set forth in claim 34 further comprising: detecting the pressure of the air delivered from said compressor; and controlling the opening degree of said flow control valve in response to the detected air pressure.

Claim 45

A method for controlling a turbocompressor system as set forth in claim 37 further comprising defining a maximum limit and a minimum limit of the opening degree of said flow control valve.

Claim 46

A method for controlling a turbocompressor as set forth in claim 37 further comprising: combusting fuel in an auxiliary burner disposed in a conduit connected said load section and said turbine to increase the output power of said turbine; and controlling the amount of fuel in said auxiliary burner in response to said pressure control, through said flow control valve, of all exhaust gas fed to said turbine to adjust the pressure of the exhaust gas at an inlet side of said turbine to a predetermined level.

Claim 47

A method for controlling a turbocompressor system as set forth in claim 37 further comprising bypassing a part of the exhaust gas discharged from said load section to the ambient atmosphere in response to said control pressure, through said flow control valve, of all exhaust gas fed to said turbine.

Claim 48

A method for controlling a turbocompressor system as set forth in claim 39 further comprising bypassing a part of the exhaust gas discharged from said load section and said auxiliary burner to the ambient atmosphere in response to said control pressure, through said flow control valve, of all exhaust gas fed to said turbine.

Claim 49

A method for controlling a turbocompressor system as set forth in claim 37 wherein said load section comprises a fuel cell power plant including a fuel cell body and a reformer and wherein said method further comprises using the compressed air delivered from said compressor for producing a chemical reaction in said fuel cell body as well as for facilitating combustion in said reformer.

Claim 52

A method for controlling a turbocompressor system as set forth in claim 43, further comprising; detecting the pressure of the exhaust gases from said load section and said auxiliary burner at said inlet side of said turbine; and controlling the amount of fuel to be fed to said auxiliary burner and the amount of air to be fed to said auxiliary burner in response to the detected pressure of the exhaust gases.

Claim 53

A method for controlling a turbocompressor system as set forth in claim 43 further comprising defining a minimum level of the combustion of fuel in said auxiliary burner.

Claim 54

A method for controlling a turbocompressor system as set forth in claim 43 further comprising feeding a part of the air delivered from said compressor to said auxiliary burner.

Claim 55

A method for controlling a turbocompressor as set forth in claim 43 wherein said load section comprises a fuel cell power plant including a fuel cell body and a reformer and wherein said method further comprises using the compressed air delivered from said compressor for producing a chemical reaction in said fuel cell body as well as for facilitating combustion in said reformer.