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WO/2002/033226A1 |
A system is described for allowing short term power augmentation of a gas turbine (12) or a gas turbine combined cycle power plant. A reservoir of pressurized and/or liquefied gas (100) is installed to store a temporary supply of gas tur...
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WO/2002/031332A1 |
A rotor overspeed protection system (40) for a gas turbine engine (10) controls engine fuel flow to prevent an engine rotor from over-speeding. The engine fuel metering system (42) includes a fuel metering valve (46) in flow communicatio...
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WO/2002/029318A1 |
The invention relates to a method and device for supplying fuel to a premix burner, which has at least one burner shell (1, 2) that at least partially delimits an axially extending premix combustion chamber, in order to operate a gas tur...
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WO/2002/027242A1 |
A control and method for arresting flashback in a gas turbine engine combustion system having a venturi for delivering a mixture of air and fuel to a combustion chamber and a valve for controlling the amount of air flowing to the venturi...
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WO/2002/020950A1 |
This disclosure describes a system and method for providing efficiency and cost analysis for a power generation unit (7). The system of this disclosure includes a current condition data acquisition logic (83) that acquires a plurality of...
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WO/2002/012692A1 |
A large compressor (18) is powered by a single-shaft gas turbine (12) via shaft (14), gearbox (16) and a hydraulic torque converter (10), which is undersized relative to the maximum shaft power requirement of compressor (18). The hydraul...
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WO/2002/012691A1 |
A gas turbine engine and a method of operating the same at idle speed are presented. The engine has a drive motor for causing the compressor to rotate and a motor control system having a motor power-up module with an input connected to t...
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WO/2002/012795A2 |
A control system (110) and method for controlling the split between premix fuel flow and pilot fuel flow to a combustor (10) in a gas turbine engine (1) are presented, so that acceptable emission levels are maintained. Engine speed and e...
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WO/2002/010569A1 |
An unbalance compensated bypass valve (14, 21, 23) for a gas turbine engine fuel supply system is responsive to the fuel pressure differential across a fuel metering valve (15) to open and close a bypass orifice (37, 39, 41; 89, 91, 93; ...
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WO/2002/004797A1 |
Control logic and a method for controlling turbine speed. The control logic (300, 400) controls turbine speed by triggering a bypass valve. Turbine generator (10) is operating in a stand-alone mode and/or a grid mode.
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WO/2002/005046A2 |
A method for operating a proportional flow valve with a pilot valve member (74) over an extended range and at a low flow rate. The pilot valve member may be operated, by varying the frequency or duty cycle or both of the pulse width modu...
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WO/2002/002920A1 |
A system and method for closed loop control of a gaseous fuel supply system for a turbogenerator/motor include a variable speed compressor with compressor speed controlled to reduce the error between a desired and actual compressor outle...
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WO/2002/002919A1 |
A method of transition control for a pulse width modulated valve operating at a variable frequency (such as those employed with turbine generators) comprising determining that a transition is to be made between valve frequencies and smoo...
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WO/2002/001055A1 |
Methods and apparatus are disclosed for providing shutoff, overspeed protection, and directional control of a bypass flow in a fuel delivery system (10) for a combustion engine, such as a gas turbine engine. A valve pack (72) is integrat...
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WO/2001/096785A1 |
The invention relates to a method for operating a burner comprising at least one first fuel supply (5) with a first group of fuel outlets (6) for a first amount of premix fuel, said first group of fuel outlets being essentially arranged ...
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WO/2001/092701A1 |
A closed cycle gas turbine system (40) comprising system comprising a compressor (52) for producing compressed gas, a gas turbine (42) for receiving the compressed gas, a heat storage means (44) having a first heat transfer means and ada...
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WO/2001/092702A1 |
A gas turbine unit has a fuel gas compressor system (5) for increasing the pressure of a fuel gas before entering a fuel system of the gas turbine unit, the fuel gas compressor system comprising at least one compressor (10, 12), gas inle...
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WO/2001/088355A1 |
The invention is characterized in that a remote monitoring center monitors the combustion vibratory state of the combustor in a turbine installed in a plant, e.g. a power plant. In order to monitor the combustion vibratory state, combust...
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WO/2001/084053A1 |
A controller for controlling self excited oscillations in a combustion system. The controller comprises a phase lead compensator, and a Smith controller. The controller has the form: (I) V is the output voltage from the controller which ...
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WO/2001/083965A1 |
A gas turbine has a fuel injection system for supplying pressurized fuel gas to a combustion chamber (2) of a gas turbine, the fuel injection system having at least one electrically controllable magnetic valve (3, 4, 5) working with puls...
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WO/2001/071172A2 |
The invention concerns a method for generating energy, which consists in conveying to an air separation apparatus (5) air from a compressor (1) coupled to an expansion machine (3). A nitrogen-enriched gaseous flow (11) containing between...
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WO/2001/057380A1 |
A variable cycle gas turbine engine (10) includes first and second compressors (18, 16), combustion apparatus (20) and first and second turbines (22, 24) operable to drive the first and second compressors (18, 16) respectively via interc...
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WO/2001/048574A2 |
The invention concerns a device for adjusting the power of a power pack driving a helicopter rotor, comprising means for dosing the fuel feed rate. The invention is characterised in that it further comprises: an electronic control device...
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WO2000020738A9 |
A gas turbine engine has a turbine (12) mounted downstream of a compressor (16) and a compressor turbine (18) mounted downstream of the turbine (12) for driving the compressor (16). The compressor turbine (18) has a rotor disk that is me...
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WO/2001/046567A1 |
A gas turbine controller of a single-shaft combined cycle power generating plant, for accurately calculating a gas turbine output at a back wash/ forward wash operation switching. A valve opening correction coefficient calculated from a ...
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WO/2001/044047A1 |
A two spool environmental control system includes a low pressure spool subsystem (38) comprising a low pressure turbine (28) and a condenser (19) downstream of the low pressure turbine. A high pressure spool subsystem (39) is in air flow...
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WO/2001/040644A1 |
A system and method for modular control of a multi-fuel turbogenerator include separate controllers (24, 28, 34) for controlling fuel supplied to the combustor and power output from the generator (30). The power controller (24) generates...
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WO/2001/038699A1 |
This invention relates to a combustion turbine power plant (10) having a gas turbine. The plant includes a compressor (30) for generating a compressed gas stream (20), a fuel delivery system (30) for supplying a combustible fuel to the g...
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WO/2001/027452A1 |
A gas turbine engine comprising a turbine mounted downstream of a compressor and a heat exchanger interconnected between the turbine and compressor and to a heated fluid source, which is connected to a fuel source, has a compressor flow ...
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WO/2001/025738A1 |
In a reciprocating engine, power strokes of pistons (32) apply torque to a crankshaft (30) causing it to twist proportionally. Datum time moments are established by triggers (52) rotating with, at one end of, the crank shaft and a sensor...
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WO/2001/023725A1 |
A service life management system comprising one server system and a plurality of client systems hooked up together over an intranet, wherein the server system manages a remaining life evaluation and a service life of a high-temperature p...
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WO/2001/020148A2 |
A liquid fuel system (40) is provided for controlling gas turbines. The fuel system (40) preferably includes a variable speed, coupled-element fuel pumping CEFP assembly (52) positioned in fluid communication with a fuel supply and one t...
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WO/2001/018372A1 |
A generating plant with improved capacity at high ambient temperatures comprises a gas turbine (32) matched to a generator (26) for summer peaking conditions. The plant includes a system for limiting turbine output at lower ambient tempe...
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WO/2001/012968A1 |
A low hysterisis fuel control valve for proportioning fuel being supplied to the combustor of the turbine engine into a first portion for delivery to primary fuel nozzles and a second portion for delivery to secondary fuel nozzles is pro...
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WO/2001/013184A1 |
A fuzzy logic based fuel flow selection (control) system is presented. Control loops are used to provide desired engine fuel flow control. These loops receive engine operating parameters and provide fuel flow command values in accordance...
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WO/2001/009694A1 |
The invention relates to a method for diagnosing and detecting the cause of a defect in a technical installation (1). A reliable, flexible and simple option for diagnosing said installation is provided by an array of state variables (M) ...
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WO/2001/000975A1 |
A supercharging system for gas turbine power plants (11). The system includes a supercharging fan (30, 32) and a controller (50) for limiting turbine power output to prevent overload of the generator (28) at lower ambient temperatures. T...
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WO/2000/071876A1 |
The present invention provides a fan speed indication system enabling the operator to control engine rotational speed to match specific thrust performance to flight requirements. The invention accommodates variations in engine thrust per...
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WO/2000/060225A1 |
A biomass fuel combustor for use in the pressurized combustion comprising of biomass fule particles to produce a pressurized exhaust gas, the combustor comprising: a cyclonic combustion chamber having a combustion region and first and se...
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WO/2000/060227A1 |
The invention relates to a method for regulating a steam turbine (1). Steam tapping (21, 23) is carried out according to different operating tasks (BA, BB, BC) which are characterised by the type of regulating variables (R1, R2) respecti...
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WO/2000/053907A1 |
A gas turbine engine that has a turbine (1) mounted downstream of a combustor (5), a compressor turbine (2) mounted downstream of turbine (1) for producing power for driving a compressor (3), a heat exchanger (6) having a first circuit (...
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WO/2000/052315A2 |
A control and method is provided that continuously adjusts fuel sensitive schedules in an electric control unit (ECU) for changes in the heating value of the fuel being combusted by the engine. The control and method includes calculating...
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WO2000008326A9 |
Methods and apparatus for injecting water into a turbine engine are described. In one embodiment, water injection apparatus is provided for injecting water into the gas flow through the engine, e.g., at a high pressure and/or low pressur...
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WO/2000/044665A2 |
According to the present invention, a fuel control has an electronic primary control for scheduling a flow of fuel to an engine in a primary mode and hydromechanical secondary control for scheduling the flow of fuel to the engine in a ba...
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WO2000009875A9 |
Precompressor and pre-booster water spray injection apparatus and methods are described. In an exemplary embodiment, a plurality of long and short nozzles are configured so that water injected into the gas flow to the high pressure compr...
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WO/2000/039442A2 |
A turbine engine (49) fuel delivery system of the type including a pneumatic governor has an electronic governor and an engine excess stress avoidance feature which disable the pneumatic governor (70) so long as the engine speed exceeds ...
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WO/2000/034639A1 |
A fuel flow control system for turbine engine compries a hot-start overtemperature avoidance system. The fuel line to the engine nozzle includes a pump (15) having a pressure regulation bypass and additionally, a trim line (33) connectin...
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WO/2000/031449A1 |
The invention concerns a fuel valve comprising a first opening (1) for fuel input, a distributing assembly comprising a rotary slide valve (3) in a sleeve (2). The slide valve and the bushing comprise each an opening slot (19, 23), an op...
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WO/2000/023700A1 |
The invention relates to a fuel dosing system for a turbojet engine, comprising a supply line (4) fed by a pump, a feed line connected to the engine (5), a recirculation line (6), a main dosing valve (7), a pressure regulating device for...
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WO/2000/022287A2 |
A gas turbine engine includes a compressor (12), a combustor (16) receiving with a part (A) of the compressed air, and a turbine rotor disk (14). A part (B) of the compressed air is bled from the compressor (12) and directly bypassed thr...
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