Gas turbine engine control system

FIELD: engines and pumps.

SUBSTANCE: method includes stages for controlling the supply of liquid fuel to a burner with high output power to provide high output power with extreme temperature at turbine inlet and control the supply of liquid fuel to the burner with low output power to provide low output power with limit pressure in the liquid fuel collector.

EFFECT: elimination of soot in the fuel combustion system, elimination of necessity in disassembling, cleaning and repair of burners after short operation period on liquid fuel under low loads, providing improved switching between the supply of gaseous and liquid fuel, reduction of emissions from the engine.

15 cl, 5 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: aircraft industry.

SUBSTANCE: invention relates to propeller speed control system making it possible for operator to control speed of engine for matching definite index of thrust with that required in flight. According to one of versions of implementation of invention, rotational speed analog signal is supplied to flight control device. Proposed system can be made to supply digital signal to power control device. Invention is aimed at correlation of deviation of thrust indicates measured at manufacture or major repair of engine.

EFFECT: prevention of operation of engines with excess thrust.

10 cl, 4 dwg

FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines.

SUBSTANCE: proposed system employs information received from aircraft engine parameter sensors and transmitted to multiplexing unit inputs and to on-board computer from output of this unit. Information received from sensors of very important parameters of engine is transmitted directly to command unit input. Present measured magnitudes are compared with specified limits in on-board computer and in command unit on basis of algorithms introduced in their storage. In case of deviation of these magnitudes from specified limits, limiting and dangerous commands are formed and are transmitted to on-board computer and to emergency information system for recording and warning the crew. Actual operating time and residual service life are determined in on-board computer with commands thus obtained taken into account and are transmitted to on-board information system for indication and recording.

EFFECT: possibility of monitoring the aircraft engine in standard, off-standard and augmented power rating conditions.

2 dwg

FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines.

SUBSTANCE: proposed system uses information transmitted from respective sensors to inputs of multiplexing unit and to on-board computer from output of this unit. Information from sensors of important parameters of aircraft engine is delivered directly to command unit input. Present magnitudes measured in on-board computer and in command unit on basis of algorithms introduced in their storage and information on dangerous parameters of engine: rotational speed of high-pressure compressor rotor, turbine outlet temperature, consumption and pressure of fuel, pressure of gas after fan doors are compared with limiting dangerous magnitudes and limiting commands are formed and transmitted to on-board computer and to emergency information system for warning the crew. Actual operating time and residual service life of aircraft engine are determined in on-board computer with commands thus obtained taken into account and are transmitted to on-board information system for indication and recording.

EFFECT: possibility of monitoring engine in standard, off-standard and augmented power rating conditions.

2 dwg

FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines.

SUBSTANCE: proposed system employs information received from aircraft parameter sensors and transmitted to multiplexing unit inputs and from output of this unit to on-board computer. Information received from sensors of very important parameters of engine is transmitted directly to command unit input. Measured present magnitudes are compared with specified limiting and dangerous magnitudes in on-board computer and in command unit on basis of algorithms introduced in their storage and information pertaining to dangerous parameters of aircraft engine: rotational speed of high-pressure compressor rotor, turbine outlet temperature, pressure of gas after fan doors and thrust. In case of deviation of these magnitudes from specified limits, limiting and dangerous commands are formed and are transmitted to on-board computer and to emergency information system for recording and warning the crew. Actual operating time and residual service life with commands thus obtained taken into account are determined in on-board computer and are transmitted to on-board information system for indication and recording.

EFFECT: possibility of monitoring the engine state in standard, off-standard and augmented power rating conditions.

2 dwg

FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines.

SUBSTANCE: proposed system employs information transmitted from sensors of aircraft engine parameters to inputs of multiplexing unit and from output of this unit to on-board computer. Information received from sensors of very important parameters of aircraft engine is transmitted directly to command unit input. Present measured magnitudes are compared with limiting and dangerous magnitudes in on-board computer and in command unit on basis of algorithms introduced in their storage and information received from sensors pertaining to dangerous magnitudes of aircraft parameters: rotational speed of high-pressure compressor, turbine outlet temperature, consumption and pressure of fuel and thrust. In case of deviation of these magnitudes from specified limits, limiting and dangerous commands are formed and are transmitted to on-board computer and to emergency information system for warning the crew. Actual operating time and residual service life of aircraft engine are determined in on-board computer with commands thus obtained taken into account and are transmitted to on-board information system for indication and recording.

EFFECT: possibility of monitoring the aircraft engine in standard, off-standard and augmented power rating conditions.

2 dwg

FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines.

SUBSTANCE: proposed system employs information transmitted from aircraft engine parameter sensors to multiplexing unit input and to on-board computer from output of this unit. Information transmitted from sensors of important parameters of engine is transmitted directly to command unit input. Present measured magnitudes are compared with limiting and dangerous magnitudes in on-board computer and in command unit on basis of algorithms introduced in their storage and information received from sensors: rotational speed of high-pressure compressor, consumption and pressure of fuel, pressure of gas after fan doors and thrust. In case of deviation of these magnitudes from specified limits, limiting and dangerous commands are formed and are transmitted to on-board computer and to emergency information system for recording and warning the crew. Actual operating time and residual service life of aircraft engine are determined in on-board computer with commands thus obtained taken into account and are transmitted to on-board information system for indication and recording.

EFFECT: possibility of monitoring the aircraft engine in standard, off-standard and augmented power rating conditions.

2 dwg

FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines.

SUBSTANCE: proposed system employs information transmitted from aircraft parameter sensors to inputs of multiplexing unit and to on-board computer from output of this unit. Information received from sensors of very important parameters of engine is transmitted directly to command unit input. Present measured magnitudes are compared with limiting and dangerous magnitudes in on-board computer and in command unit on basis of algorithms introduced in their storage and received from sensors of very important parameters: turbine outlet temperature, consumption and pressure of fuel, pressure of gas after fan door and thrust. In case of deviation of these magnitudes from specified limits, limiting and dangerous commands are formed and are transmitted to on-board computer and to emergency information system for recording and warning the crew. Actual operating time and residual service life of aircraft engine with commands thus obtained taken into account are determined in on-board computer and are transmitted to on-board information system for indication and recording.

EFFECT: possibility of monitoring the aircraft engine in standard, off-standard and augmented power rating conditions.

2 dwg

FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines.

SUBSTANCE: proposed system employs information transmitted from aircraft engine parameter sensors to multiplexing unit inputs and to on-board computer from output of this unit. Information received from sensors of very important parameters of engine is transmitted directly to command unit input. Present limiting and dangerous magnitudes are compared with preset magnitudes in on-board computer and in command unit on bases of algorithms and information of sensors introduced in their storage. In case of deviation of these magnitudes from specified limits, limiting and dangerous commands are formed and are transmitted to on-board computer and to emergency information system for recording and warning the crew. Actual operating hours and residual service life of aircraft engine are determined in on-board computer with commands thus obtained taken into account and are transmitted to on-board information system for indication and recording.

EFFECT: possibility of monitoring the aircraft engine in standard, off-standard and augmented power rating conditions.

2 dwg

FIELD: aircraft industry.

SUBSTANCE: invention relates to aircraft instruments and it can be used for in-flight monitoring of aircraft engine, mainly, gas-turbine engine, using on-board computer and command unit. According method, limit and critical parameters are revealed from controllable parameters of aircraft engine and limit and critical values of said parameters are found, parameter settings are introduced into memory of on-board computer through command unit for calculating limit and critical values and also time of tolerable operation of aircraft engine at afterburning and algorithms of calculations of current values of limit and critical values as function of current values of parameters of aircraft engine and algorithms of calculation of effective, forced and actual running times and residual service life of aircraft engine, and current values of limit and critical values are calculated in on-board computer and results are delivered into command unit, current values of controllable parameters are supplied to input of on-board computer, and current values of limit and critical parameters of aircraft engine are supplied to input of command unit, and current values of said parameters are compared in command unit with current values of limit and critical values, and if parameter values comes out of limits of limit or critical values, corresponding commands are formed and transmitted into aircraft emergency system and into on-board computer, and said computer calculates actual values of running time and residual service life of aircraft engine using said commands and measured time of operation of engine at afterburning and transmits them into interacting on -board information systems, measured time of operation of aircraft engine at afterburning is compared with tolerable time and if tolerable time value is exceeded, corresponding command is formed which is transmitted through command unit into aircraft emergency system.

EFFECT: possibility of checking condition of aircraft engine at standard, emergency and afterburning operation.

2 dwg

FIELD: aircraft instrumentation engineering; monitoring of gas-turbine engines.

SUBSTANCE: proposed onboard monitoring system ensures check of engine in standard, off-standard and augmented power rating modes. Monitoring is based on use of information received from aircraft engine sensors and transmitted to inputs of multiplexing unit and from outputs of this unit to onboard computer. Information received from sensors of very important parameters of aircraft engine is fed directly to input of command unit. Computational algorithms and information received from sensors pertaining to dangerous parameters of aircraft engine, viz.: rotational speed of high-pressure compressor rotor, consumption and pressure of fuel and thrust are compared with limiting and dangerous magnitudes; in case signals are beyond these magnitudes, limiting and dangerous commands are formed and are transmitted to onboard computer and to emergency information system of aircraft for recording and for warning the crew. Actual operating hours and remaining service life of aircraft engine are determined in onboard computer with the commands taken into account and are transmitted to onboard information recording and indication system.

EFFECT: enhanced efficiency of monitoring the engine working at increased thrust.

2 dwg

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