Controlling means for turbine with multiple combustion chamber

FIELD: power industry.

SUBSTANCE: system for the progressive oxidation of fuel includes an oxidation reactor that has a reaction chamber with an inlet and an outlet. The reaction chamber is configured to receive a fluid containing the oxidizable fuel through the inlet. The oxidation reactor is designed to maintain the process of flameless oxidation. The system also includes the combustion chamber with an inlet and an outlet. The inlet of the combustion chamber is in fluid communication with the outlet of the reaction chamber. The combustion chamber is configured to receive fluid from the reaction chamber and selectively heat the fluid. A method for triggering a progressive oxidation in a gas turbine and a version of a system for progressive oxidation of fuel are also presented.

EFFECT: improved control of fuel oxidation process.

31 cl, 21 dwg

 



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: invention can be used in electronic hydro mechanical ACS of multimode gas turbine engines with afterburner combustion chamber in operation at training conditions to ensure reliable fuel firing at actuation of afterburning from lower modes of cold engine (below "Maximum" mode). By signal of afterburner chamber firing device an in-engine parameter magnitude is increased to adjust fuel feed to the main combustion chamber to preset level. After firing in afterburner chamber, fuel feed rate in is decreased by the same amount.

EFFECT: higher efficiency.

1 dwg

FIELD: power industry.

SUBSTANCE: invention relates to power industry. This is the method of gas-turbine plant operation in transient mode in which controller determines values of control command for mass-flow rate of incoming air, for fuel mass-flow rate, for mass-flow rate of water or steam, when water and steam are used; at least one command value is dynamically compensated in order to compensate various dynamics of supply systems for synchronisation of resulting changes in mass-flow rate of fuel, water, steam and combustion air delivered to combustion chamber, so that fuel-air mixture composition was within ignition zone. Also presented is a control system meant for implementation of proposed method, and gas-turbine plant including such control system.

EFFECT: providing fast operation in transient mode with consistent flame of premixed mixture.

13 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention may be used in electronic automatic control systems (ACS) of gas turbine engines (GTE) with a free turbine, applied within gas turbine plants (GTP) for driving of power generators (PG) of gas turbine power plants (GTPP). Additionally whenever speed of the free turbine reduces by a certain value, the value of the minimum permissible flow rate of fuel increases by the specified time above the actual flow rate of fuel by the specified value.

EFFECT: increased reliability of GTPP operation due to increased quality of GTE ACS operation.

1 dwg

FIELD: machine building.

SUBSTANCE: heat exchanger system through which the liquid flows comprises a heat exchanger with liquid inlet and outlet, a bypass valve with liquid inlet and outlet and a self-cleaning filter with a liquid inlet and two liquid outlets; one of the latter is meant for the filtered liquid and the other - for the unfiltered liquid. The filtered liquid outlet is connected to the heat exchanger inlet and the unfiltered liquid outlet - to the valve inlet, the heat exchanger outlet is connected downstream regarding the valve outlet.

EFFECT: heat exchanger clogging up is excluded.

9 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: control over high-pressure pump in gas turbine fuel feed circuit is executed by detection of feed and shutoff valve opening at fuel flow rate control valve, measurement of gas turbine rpm corresponding to opening of said valve and control over variations in said rpm to prompt high-pressure pump replacement when said rpm reaches preset threshold.

EFFECT: efficient control over high-pressure pump.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: at bench tests of two-spool gas turbine engine after renewal without disassembly of wheelspace units and parts rotor slip and takeoff thrust (power at maximum mode) are adjusted to magnitudes obtained in operation before renewal. In case said parameters fall beyond operating tolerances they are adjusted to magnitudes corresponding to closer top or bottom limits of operating tolerance..

EFFECT: stable operation of high-pressure compressor and angine thrust in operation after renewal.

FIELD: engines and pumps.

SUBSTANCE: proposed method consists in using engine inlet air temperature and compressor rotor rpm to generate control signal for actual reduced compressor rotor rpm. Magnitude of preset reduced compressor rotor rpm is set to compare it to generated actual reduced compressor rotor rpm. Note here that in case actual reduced compressor rotor rpm is smaller than preset one, compressor distributors are controlled by flow rate of air passing through compressor. Note here that in case actual reduced compressor rotor rpm exceeds preset one, compressor distributors are controlled by air compression ratio.

EFFECT: maximum efficiency and gas-dynamic stability.

1 dwg

FIELD: machine building.

SUBSTANCE: proposed method consists in abrupt closure of fuel valve. Simultaneously, axial compressor discharge air valves are opened.

EFFECT: reduced overspeed.

3 cl, 2 dwg

FIELD: aircraft engineering.

SUBSTANCE: proposed method comprises accelerating engine rotor to rotor rpm required for igniting combustion chamber, combustion chamber ignition, and reaching idling conditions maintaining preselected engine limiting parameter. Note here that T4 max is selected to make maintained parameter of engine operation. Note also that in adjustment of T4 max temperature is increased to maximum tolerable value by increasing fuel feed into combustion chamber while temperature is decreased to minimum tolerable vale by increasing air feed into combustion chamber where T4 max is maximum tolerable temperature of gas downstream of turbine.

EFFECT: faster starting and acceptable high-pressure compressor stability.

FIELD: engines and pumps.

SUBSTANCE: control of gas-turbine engine (GTE) with afterburner is performed as per one of three control loops; individual control programme is specified on each loop and corrected as per certain group of sensors the readings of which are the most essential for operation exactly in that mode.

EFFECT: invention allows improving operating reliability and safety of GTE with afterburner of airborne vehicle due to reducing the time of augmented and full acceleration of GTE and expansion of safe startup area of afterburner, and providing GTE operation in wide range in optimum modes.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed plant comprises gas turbine engine with compressor, gas turbine air preparation device, fuel system with combustion chamber, fuel feed and adjustment device, engine and actuator oil lubing system with oil cooling heat exchanger, pressure pump, fuel heating heat exchanger, all being arranged in separate adjustable circulation circuit. Additionally, said plant incorporated a heat pump. The latter comprises at least one heat exchanger, one pressure booster, one condenser heat exchanger and one pressure reducer. Evaporator heat exchanger inlet is connected to gas turbine air preparation device outlet. Evaporator heat exchanger outlet is connected to compressor inlet. Condenser heat exchange inlet is connected with fuel feed device while its outlet is connected with fuel heating heat exchanger.

EFFECT: higher efficiency, reduced influence of atmospheric air parameters, higher safety.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: power plant (112) includes gas turbine engine (116) fed with fuel through fuel feed circuit (122) passing from tank (124) located on the level of frame (110), and engine cooling circuit (118, 130) containing the first and heat exchanger (120, 132) of the engine to remove calories. Frame (110) includes source (134) of heat emissions. The fuel used to feed gas turbine engine (116) is used as heat carrier fluid medium to dissipate thermal emissions generated on the level of frame (110) on the level of power plant (112). Some amount of the heat transferred with fuel is extracted with heat carrier fluid medium of the engine cooling circuit (118, 130) and is dissipated with the first heat exchanger (120, 132) of the engine so that the temperature of the fuel fed to gas turbine engine (116) can be maintained below a certain threshold value.

EFFECT: improvement of the method.

6 cl, 6 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to fuel compression system. Gas conditioning system comprises compressor for gas compression and heating, air feed device, heat exchanger transfer of heat from hot gas to airflow, moisture separator and heater with one channel receiving the flow of saturated gas from moisture separator and another channel receiving hot airflow from heat exchanger for transfer of heat from hot air to saturated gas to produce overheated gas with temperature exceeding saturation temperature. Micro turbine engine comprises air compressor, gas conditioning system, combustion chamber for combustion of compressed air with overheated gas, power turbine, generator to produce electric power in rotation of the turbine, and recuperator heating compressed air by combustion products prior to feed into combustion chamber.

EFFECT: ruled out moisture residues in fuel consuming hardware.

17 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: air is compressed in compressor to be fed into combustion chamber for fuel combustion. Resulted hot gas is fed for expansion to active gas power turbine to drive compressor. Converted fuel with increased absolute calorific power is afterburnt in endothermic reaction of initial fuel in steam reforming reactor. Parallel thermal cycle is conducted wherein heated mix of water with hydrocarbon fuel is fed via turbine hollow shaft into reaction chamber. Reaction chamber comprises porous carbon metal container arranged inside pressure gas turbine that stays in contact with power turbine or makes an integral part thereof. Reactor is rotated to compress said mix partially during endothermic reaction. Mix is partially heated by turbine cooling and by waste gas heat and, then, is discharged via jet nozzles to generate extra torque.

EFFECT: higher efficiency and safety.

FIELD: engines and pumps.

SUBSTANCE: proposed method consists in feeding carbon fuel to compressor inlet. Said feed is accompanied with fuel feed into main combustion chamber reduced by amount of fuel fed to compressor inlet. Fuel consumption at compressor inlet does not exceed three percent of air consumption. Fuel nozzles mounted at compressor inlet can be directed towards airflow.

EFFECT: improved thrust, reduced fuel consumption of high-rpm gas turbine engines.

2 cl, 3 dwg

FIELD: power industry.

SUBSTANCE: combustion chamber assembly includes the main housing formed with a supply header with a fuel feed system and fuel atomisers continued from the supply header and provided with fuel by means of the fuel feed system of the supply header. The supply header has a sandwich structure and is made of separate elements. The number of separate elements of the header exceeds the number of fuel types in the fuel feed system. The fuel feed system includes at least one gas line channel and at least one liquid fuel channel. The supply header is made of at least three separate elements.

EFFECT: invention allows designing an effective combustion chamber assembly at considerable reduction of costs for manufacture of the main housing.

12 cl, 6 dwg

FIELD: aircraft engineering.

SUBSTANCE: proposed fuel system comprises fuel tank (1) with booster pump (2), fuel line (3) arranged partly inside rotor shaft and blades. Fuel line of every blade is provided with rotor rpm controller. Electrically driven starting and low-rpm pump (5) is arranged at fuel line section downstream of booster pump with outlets in number corresponding to that of engines (8) and engine working condition control pump (7) driven by rotor shaft (11) via gearing (12) of gearbox (10). Fuel manifold (15) is arranged at inlet of blade (14) fuel lines (9) to transfer fuel from fixed fuel line sections to their moving sections (9′) in every blade (14). Fuel manifold (15) consists of two compartments (16, 17). Fixed compartment (16) is secured at fixed pipe (13) inside rotor shaft (11). Moving compartment (17) is fitted on rotor shaft (11) and has circular chambers (18, 19) for fuel transfer.

EFFECT: possibility to rule out inertia of fuel feed and to effect the fuel pressure control.

3 cl, 2 dwg

FIELD: power industry.

SUBSTANCE: invention relates to power industry. This is the method of gas-turbine plant operation in transient mode in which controller determines values of control command for mass-flow rate of incoming air, for fuel mass-flow rate, for mass-flow rate of water or steam, when water and steam are used; at least one command value is dynamically compensated in order to compensate various dynamics of supply systems for synchronisation of resulting changes in mass-flow rate of fuel, water, steam and combustion air delivered to combustion chamber, so that fuel-air mixture composition was within ignition zone. Also presented is a control system meant for implementation of proposed method, and gas-turbine plant including such control system.

EFFECT: providing fast operation in transient mode with consistent flame of premixed mixture.

13 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention can be used in het engine fuel feed systems. Proposed is the heat engine fuel feed system. Note here that the latter consists of at least one fuel line (1) extending to combustion process (3) along which at least one vale unit is arranged. At first step 1 when exhaust valve (7) is closed shutoff valve (4) and control valve (5) are closed. At step 2 exhaust valve (7) opens to make fuel (V1) evacuate from fuel line section (1') and drain line (6'). At step 3 exhaust valve (7) closes. At step 4 control valve (5) opens. At step 5, fuel chamber (V1) is filled with fuel forced from fuel line extending to combustion process (3). Then, at step 6 control valve (5) is closed and exhaust valve (7) is opened to drain said fuel (V1) fed after step (5).

EFFECT: controlled pumping of fuel residues from line extending to combustion process.

7 cl, 1 dwg

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