WO2008057002A1 - Procédé et dispositif de préservation et/ou de dépréservation interne de moteurs à turbine - Google Patents

Procédé et dispositif de préservation et/ou de dépréservation interne de moteurs à turbine Download PDF

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Publication number
WO2008057002A1
WO2008057002A1 PCT/RU2006/000581 RU2006000581W WO2008057002A1 WO 2008057002 A1 WO2008057002 A1 WO 2008057002A1 RU 2006000581 W RU2006000581 W RU 2006000581W WO 2008057002 A1 WO2008057002 A1 WO 2008057002A1
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WIPO (PCT)
Prior art keywords
engine
preservation
oil
gas
autonomous
Prior art date
Application number
PCT/RU2006/000581
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English (en)
Russian (ru)
Inventor
Viktor Ivanovich Gribakin
Viktor Nikolaevich Eliseev
Alexandr Alexandrovich Sarkisov
Original Assignee
Zakrytoe Aktsionernoe Obschestvo 'vao 'interprofavia'
Federalnoe Gosudarstvennoe Uchrezhdenie 'federalnoe Agentstvo Po Pravovoi Zaschite Rezultatov Intellekttualnoi Deyatelnosti Voennogo Spetsialnogo I Dvoinogo Naznachenia 'pri Ministerstve Yustitsii Ros
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Application filed by Zakrytoe Aktsionernoe Obschestvo 'vao 'interprofavia', Federalnoe Gosudarstvennoe Uchrezhdenie 'federalnoe Agentstvo Po Pravovoi Zaschite Rezultatov Intellekttualnoi Deyatelnosti Voennogo Spetsialnogo I Dvoinogo Naznachenia 'pri Ministerstve Yustitsii Ros filed Critical Zakrytoe Aktsionernoe Obschestvo 'vao 'interprofavia'
Priority to PCT/RU2006/000581 priority Critical patent/WO2008057002A1/fr
Publication of WO2008057002A1 publication Critical patent/WO2008057002A1/fr
Priority to IL198606A priority patent/IL198606A/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics

Definitions

  • the invention relates to the field of operation of gas turbine engines, in particular, to methods of internal conservation and de-preservation of engines carried out on idle engines installed both on an operating facility, for example, on an aircraft, and outside it, and devices for their implementation.
  • a known method of internal preservation of the fuel system of an aircraft gas turbine engine comprising pumping the oil heated in a preservation unit through the fuel system units on an idle engine mounted on an aircraft with open hydraulic and electrical distributors.
  • the method is carried out using a preservation unit connected to the fuel system of a gas turbine engine, and the oil of the fuel system of the engine is used.
  • the amount of oil drained into the process tank is controlled and after draining 25-30 l, the engine is considered mothballed.
  • De-preservation is carried out using working fuel instead of oil in the preservation unit.
  • a known method of preserving an aircraft gas turbine engine (SU, 1039129, A2), in which when scrolling the engine rotor from the starter and pumping the heated oil from the ground installation, part of the preserving oil is diverted from at least one of the engine pumps to the closed fuel cavities, opening the cavities they are produced both by oil pressure and by supplying command signals to electrically controlled switchgear, and at the same time opening the cavities of the units by means of electrically controlled switchgear
  • the equipment is produced alternately, and when the cavities of one unit are opened, the oil drain through all other units is stopped.
  • a known method of internal preservation of the fuel system of an aircraft gas turbine engine comprising pumping on an idle engine heated oil in a preservation unit through the cavities of open hydraulic and electrical distributors of the fuel system units and through the main cavities of its units, while the main cavities of the fuel system units are purged with neutral gas before pumping oil through them.
  • a device for cleaning and preserving a gas turbine engine (US, 4059123, B), having a starter for scrolling compressor stages, comprising a frame having support wheels for turning and mounted on this frame: a first water tank; additional tanks for cleaner, solvent and preservative solutions; internal combustion engine; management console an air rotary compressor and an alternator, and an internal combustion engine is started from both the air compressor and said generator; electric battery on the control console; electrical connectors between the generator and the battery for charging the battery, and electrical connectors include operator controls for controlling the transfer of energy from the generator to the battery; connecting means for communication between the air compressor and the first reservoir of compressed air; means for connecting the air volume with additional tanks for boosting these tanks and means for controlling each connection for controlling the boost of each of the tanks; an injection device mounted on a gas turbine for injecting fluid inside, a means for connecting each tank to the injection device, including fittings; a circuit device comprising a two-wire electric cable connecting the battery to the starter to start the specified compressor.
  • the above methods are mainly designed to preserve the engine installed on the object - the aircraft, and it is necessary to connect the aircraft to a power source or to scroll the engine from the starter and thus provide a “false” start. At the same time, for re-preservation of engines stored outside the aircraft, it is necessary to carry out their installation on the vessel, and then their dismantling;
  • the aim of the present invention is to develop a method of internal preservation and de-preservation of gas turbine engines, which allows for the least expenditure of time, energy, fuel and preservation media in any weather conditions to preserve and de-preserve engines, including engines installed in an operating facility, for example, an aircraft , and eliminating the need for a “false” start and scroll of the engine from the starter.
  • the aim of the invention is also the development of a method and device for the conservation of engines located outside the operating facility, while eliminating the need for placing engines on the facility to perform these operations, which also increase the reliability and quality of conservation of the engine and its components to increase the shelf life of the canned engine as a part object, and outside the object.
  • the task was to create a method of internal preservation or de-preservation of gas turbine engines, which allows due to automation of processes of pumping working fluids through engine aggregates and devices combined in a certain sequence, including when the gas-air path of the engine is destroyed, and due to the use of optimal compositions of working environments to ensure a low residual fuel content in the preservation medium after the preservation process, the absence of undesirable air inclusions, gaps and cavities, as well as additionally provide the technological possibility of preservation or de-preservation of the air starter during conservation or de-preservation of the engine.
  • the problem was solved by creating a method of internal preservation or de-preservation of gas turbine engines, in which the idle engine automatically supplies the working media used for preservation or de-preservation from autonomous sources of working media to the internal lines and cavities of the units and engine systems to be preserved or de-preservation, in a given sequence under pressure in a pulsed mode by feeding from an autonomous control device to power-assisted devices of these units and engine systems and actuators of autonomous sources of working media of control electric signals of a given duty cycle, coordinated among themselves in a given sequence, ensuring the operation of these actuators according to a given cycle in a number of cycles sufficient to achieve the required parameters of the pumped working medium, and when this, the power of the stand-alone control device is provided using a stand-alone power source .
  • neutral gas and a liquid preserving mixture in series as a working medium for the fuel and oil systems and main units, use neutral gas and aerosol of preservative mixture sequentially, use neutral gas and preservative mixture for air starter.
  • washing mixture aerosol and neutral gas it is advisable to re-consume the washing mixture or the washing mixture aerosol and neutral gas as working media for the fuel and oil systems and main units, to use the washing mixture aerosol and neutral gas for the gas-air path, and for air starter - sequentially aerosol flushing mixture and neutral gas.
  • a switchgear containing electrical actuators adapted in the “on” mode to ensure communication of the indicated outputs of the autonomous sources of the working medium with the corresponding inputs of the mains, systems and units of the engine subject to conservation or de-preservation;
  • an autonomous control device adapted for connection to an autonomous power source and providing:
  • the stand-alone sources of the working media additionally contain actuators providing heating of the working media.
  • the automated device can be adapted for the simultaneous preservation and / or de-preservation of several gas turbine engines and at the same time contain one autonomous control device with one power source and several autonomous sources of working media and several switchgears.
  • the automated device contains an autonomous device for scrolling the rotor of the engine with a low rotation speed.
  • the stand-alone control device was made with the possibility of current correction of the sequence and duty cycle of the control commands and the corresponding control electrical signals and parameters of the supply of working media.
  • FIG. l is a diagram of the implementation of the conservation or de-preservation of a gas turbine engine, according to the invention.
  • Figure 2 - schematic representation of a variant of the sequence diagram of the preservation of the fuel and oil systems and the gas-air path of the gas turbine engine of the helicopter, according to the invention
  • Fig. 3 is a schematic illustration of a variant of the conservation pattern of the fuel and oil systems, the gas-air path and the air starter of the aircraft gas turbine engine, according to the invention.
  • the examples of the implementation of the method of internal preservation and / or re-preservation and examples of the automated device for internal preservation or re-preservation of gas turbine engines according to the invention do not limit the options for the implementation and use of the inventions and do not go beyond patent claims. Best Mode for Carrying Out the Invention
  • the method of automated internal preservation and / or de-preservation of gas turbine engines according to the invention can be carried out using a device that allows for the operation of preservation or de-preservation in an automatic mode in a predetermined sequence with the supply of working media under a given pressure with on / off electrical actuators in a predetermined sequence ..
  • the method according to the invention is illustrated by the example of preservation of both the fuel and oil systems and the gas-air path of a small aircraft gas turbine engine, located on the aircraft inoperative or outside the aircraft, using an automated device for the conservation and / or de-preservation of small-sized gas turbine engines according to the invention as shown in the diagram of FIG.
  • the automated device 1 for preservation and / or de-preservation shown in Fig.l, contains:
  • - switchgear 5 for example, pneumohydraulic. communicated, for example, with the help of highways, with the inputs of the mains, systems and engine units to be preserved and / or re-preserved, and with the outputs of autonomous sources of working media;
  • stand-alone sources of 2 and 3 working media during preservation serve as sources of preservative mixtures and can be used during de-preservation as autonomous sources of washing mixtures.
  • An autonomous source of preservative mixture 2 may contain a tank 10 for placing the preservative mixture for preserving the fuel system and actuators: an electric pump 11 for its supply, a control valve 12 and a mixer 13 for the manufacture of aerosols of the preserving mixture.
  • An autonomous source 3 of preservative mixture may contain a tank 14 for placing a preservative mixture for preserving the oil system, an electric pump 15, a control valve 16 and a mixer 17 for the manufacture of aerosols of the preservative mixture,
  • tanks 10 and 14 of autonomous sources 2 and 3 of the working medium can be made with the possibility of heating the medium and controlling the temperature of the medium and contain actuators providing such heating, and must also be equipped with devices for indicating the quantity or level of the working medium in tanks 10 and 14 .
  • the electric pumps 11 and 15 can be made with the possibility of changing the pressure level of the working medium and equipped with automatic devices protection and unloading of the pump and a group of safety-overflow valves that are tunable to various pressure values of the working medium.
  • pumps 1 1 and 15 can be combined in one housing with separate suction and outlet pipes.
  • one pump can be used instead of two pumps 1 1 and 15, one pump can be used.
  • An autonomous source 4 of neutral gas used during preservation and during re-preservation for purging the fuel and oil systems and purging the gas-air duct, as well as for manufacturing aerosols of working media may contain a cylinder 18 for accommodating neutral gas, a pneumatic reducer 19, and a valve 20.
  • an oil or any other preservation liquid recommended by the engine manual is used as a preservative mixture, for example, liquid fuel used in an engine during its operation can be used as a flushing mixture, dried nitrogen can be used as a neutral gas .
  • the automated device 1 also includes a device 21 for supplying aerosols of the preserving mixture (or, when re-preserving, aerosols of the washing mixture) or neutral gas into the gas-air path of the engine.
  • the pneumohydraulic distribution device 5 may include an actuator 22 with valves 23 for supplying working media, for example, according to the invention, a preservative mixture or its aerosol (or, when re-preserving, a washing mixture or its aerosol), or dried nitrogen, in the main and to the actuators of the engine 24 in accordance with a given sequence and duration of the feed.
  • a preservative mixture or its aerosol or, when re-preserving, a washing mixture or its aerosol
  • dried nitrogen in the main and to the actuators of the engine 24 in accordance with a given sequence and duration of the feed.
  • valves 23-Mj for supplying oil lines and oil systems and engine assemblies 24
  • valves 23-Tj for supplying fuel lines and fuel systems and engine assemblies 24.
  • Autonomous control device 6 is electrically connected with all actuators of the automated device 1 and with actuators of systems and assemblies of the engine 24, subject to preservation (or de-preservation), for example with electric distributors of fuel and oil systems of the engine 24.
  • the autonomous control device 6 contains a software distribution device 25, including, for example, a two-level industrial processor containing in memory a database 26 of data of cyclograms of various operating modes of the automated device 1 during conservation or de-preservation for several types of engines.
  • a software distribution device 25 including, for example, a two-level industrial processor containing in memory a database 26 of data of cyclograms of various operating modes of the automated device 1 during conservation or de-preservation for several types of engines.
  • the software distribution device 25 at the control level generates control programs according to the data in the data base 26 of the operation sequence of the actuators of the automated device 1, and at the executive level using the electric device 27 generates control signals with a voltage level corresponding to the operating voltage of the electric power of the gas turbine engine 24 and electroautomatics device 1.
  • the operation of the device 27 is controlled from the remote control 7 and is controlled by a visual indication on the panel 8 the sequence of operations.
  • Visual indication can be made both on the basis of individual elements, such as pressure gauges, ammeters, voltmeters, light emitters (electric lamps, LEDs, etc.), and on the basis of the display of the necessary parameters of the preservation or de-preservation process by displaying, for example, liquid crystal, on which, in addition to indicating the actual parameters of the operations that can be performed, can also be displayed the sequence of technological operations that must be performed during the conservation or de-preservation of one igatelya or several motors.
  • control panel 7 with the display panel 8 is configured to enable the operator to manually control the change of the operating modes of the installation 1 and to monitor the progress of the preservation and de-preservation process, for example, as the commands are executed in accordance with the operation sequence diagram of the device 1, control the on and off sequence units of the device 1 and actuators of a gas turbine engine, in particular, hydraulic and electrical distributors of units fuel and oil systems, as well as the volume of working media in autonomous sources 2, 3 and 4 and the pressure of the working fluid.
  • the remote control 7 it is possible to transfer the automated device 1 to the manual control mode of the device 1, for example, for connecting to the previously selected sequence of individual necessary operating cycles of the actuators, for example, for cases where separate engine systems and engine units are used to ensure high quality preservation require significantly longer pumping of the working media, for example, with the adjustment of the parameters of the pulse pumping mode, for example, the duty cycle of the control elec ble signals.
  • Figure 1 also shows the device 28 discharge of spent preservative media from the fuel and oil system of the engine, the state of the samples which evaluate the quality of the conservation (or de-preservation), for example, by the presence of air impurities in the preservation mixture (or the presence of particles of oil in the washing mixture) .
  • Spent preservative mixtures can be cleaned and returned to stand-alone sources of working media. Cleaning can also be performed in an automated device 1.
  • the automated device 1 may include devices for collecting pumped preservative mixtures and washing mixtures and devices for cleaning them, which makes it possible to return the purified mixtures to their respective tanks 10 and 14 for reuse or the need for repeatedly pumping media.
  • Autonomous power supply 9 includes, for example, a battery with an output voltage of 27V.
  • the method of internal conservation or de-preservation according to the invention is as follows.
  • control panel 7 select the type of engine and the preservation mode, that is, select a certain sequence of operation of actuators of the automated device 1 and engine 24.
  • the preservative mixture passes through pipelines and through all engine units that operate in a certain sequence, as well as through engine mounts. They are being mothballed.
  • a preservative mixture for example, an aerosol of oil, called oil mist
  • the rotor of the turbocompressor is smoothly scrolled using a standard key or an autonomous electrical device.
  • Preservation is carried out, for example, by 2-3 repetitions of the selected sequence diagram 7 on the remote control from the number of cyclograms available in the database, or if necessary, correct the cyclogram by introducing additional cycles from the number of cycles available in the database.
  • the sequence of operations and the number of cycles can be different and depends on the type of engine, its exhausted resource, design features of the engine.
  • Figure 2 shows a schematic representation of a variant of the sequence diagram of the internal preservation of the fuel and oil systems and the gas-air path of the gas turbine engine of the helicopter according to the invention using only oil supply as a preservation medium for the fuel and oil systems, and only oil aerosols for the gas-air path .
  • the cyclogram (Fig. 2), including two conservation cycles, shows the signals of one preservation cycle and at the same time “i” is the number of the electric actuator or unit:
  • B is the on-switch-off signal of the electric oil pump 15 for preservation of the oil system, while the valve 16, which provides oil supply to the distribution pneumohydraulic device 5, is open and then closed in accordance with the specified duty cycle of the signal;
  • C is the signal for supplying oil to the oil system, while the valves 23-Mj are open and then closed in accordance with a given duty cycle of the signal;
  • D is the signal for supplying oil to the fuel system, while the valves 23-Tj are open and then closed in accordance with a given duty cycle of the signal;
  • E and g are the opening and closing signals of the 24-Ti, 24-T 2 , ... 24-Tj, 24-Mi, ... 24-Mj actuators, respectively, of the fuel and oil systems;
  • F is the valve opening-closing signal (not shown in the drawing) of oil supply to the engine nozzles
  • H is the gas supply signal to the gas-air path of the engine, while the valves 20 and 13 are open;
  • the total duration of preservation in this sequence is a total of not more than 68 seconds (two cycles of 34 seconds).
  • Fig. 3 shows a schematic illustration of a variant of the sequence diagram for preserving the fuel and oil systems, the gas-air path and, accordingly, the air starter of a gas turbine engine of an airplane according to the invention.
  • Fig. 3 the sequence diagram shows the sequence and duty cycle of the control electric signals supplied, according to the invention, from an autonomous control device 6 to the actuators of the automated device 1 and the gas turbine engine 24 when it is preserved, with sequential automatic processing according to the invention:
  • Cycle A - supply of dried nitrogen (from 1 to 19 seconds):
  • E is the opening-closing signal of the executive mechanisms of the 24-Ti engine fuel system, providing the supply of dried nitrogen to the engine fuel system, creating the pressure necessary to open them in the hydraulic distributors, maintaining this mode for a specified time, and then, by stopping nitrogen supply, - pressure relief to close them;
  • F is the opening-closing signal of the 23-Ti valves, which supply dried nitrogen to the 24-TF input to the collector of the nozzles of the combustion chamber;
  • G is the opening-closing signal of the 23-Mi valves, which supply dried nitrogen to the inputs of the mains and actuators of the 24-Mi units of the engine oil system;
  • H is a signal for switching on / off the pneumatic reducer 19, which ensures the intake of dried nitrogen from the cylinder 18 and its supply to the valve 20;
  • Q is the signal for opening and closing the valve 20, which provides the supply of dried nitrogen to the actuator 22;
  • J is the on / off signal of the mixer 17, providing the supply of aerosol preserving mixture in the actuator 22;
  • K is the on-off signal of the mixer 13, which provides the supply of the aerosol preserving mixture to the device 21 for supplying preserving media to the gas-air duct of the engine;
  • G is the open-close signal of the valves 23-Ti of the actuator 22, providing the supply of dried nitrogen to the actuators 24-Ti of the fuel system of the engine;
  • M is the open-close signal of the valves 23-Mi of the actuator 22, which supply dried nitrogen to the inputs of the mains and actuators 24-Mj of the units of the engine oil system;
  • N is the on-off signal of the device 21 for supplying dried nitrogen to the gas-air path and the air starter of the engine;
  • P is the on-off signal of the mixer 13, which provides the supply of the aerosol preserving mixture to the actuator 22.
  • Cycle B - oil supply (from 20 to 46 seconds):
  • A is the on-switch-off signal of the electric pump 11 ( Figure 1), which provides for the intake of oil from the tank 10 and the creation of the desired pressure level in the oil supply line;
  • B is the on-switch-off signal of the electric pump 15 of the oil system, which provides for the intake of oil from the tank 14 and the creation of the desired pressure level in the oil supply line;
  • C is the on / off signal of the control valve 16 (Fig-1), which supplies oil from the pump 15 to the actuator 22 of the distributing pneumohydraulic device 5;
  • “D” is the on / off signal of the control valve 12 (Fig. 1), which supplies oil from the pump 11 to the actuator 22 of the distributing pneumohydraulic device 5;
  • E is the on-off signal of the actuators 24-Tj of the engine fuel system, providing oil supply to the engine fuel system, creating the pressure in hydraulic distributors (not shown in the drawings) necessary to open them, maintaining this mode for a specified time, and then, by shutting off the oil supply, - depressurizing and closing them;
  • F is the signal of the opening-closing of the valve 23-Tj, which supplies oil to the manifold of the nozzles of the combustion chamber;
  • H is the on-off signal of the pneumatic reducer 19, which provides the intake of dried nitrogen from the cylinder 18 and its supply to the valve 20 is absent;
  • J is the on-off signal of the mixer 17, providing the supply of aerosol preserving mixture in the actuator 22 - is absent;
  • R is the open-close signal of the valves 23-Tj, providing oil supply to the actuators 24-Tj of the fuel system of the engine;
  • M is the open-close signal of the valves 23-Mj, providing oil supply to actuators 24-Mj of the engine oil system,
  • N the on-off signal of the device 21 for supplying dried nitrogen to the gas-air path and the air starter of the engine is absent;
  • A is the on-switch-off signal of the electric pump 11 ( Figure 1), which provides for the intake of oil from the tank 10 and the creation of the desired pressure level in the oil supply line;
  • B is the on-switch-off signal of the electric pump 15 of the oil system, which provides for the intake of oil from the tank 14 and the creation of the desired pressure level in the oil supply line;
  • C is the on / off signal of the control valve 16 (Fig-1), which supplies oil from the pump 15 to the actuator 22 of the distributing pneumohydraulic device 5;
  • “D” is the on / off signal of the control valve 12 (Fig.l), which supplies oil from the pump 1 1 to the actuator 22 of the distributing pneumohydraulic device 5;
  • E is the on-off signal of the actuators 24-Tj of the engine fuel system, which provide the supply of oil aerosol to the engine fuel system, the creation of the hydraulic pressure distributors (not shown in the drawings) necessary to open them, maintaining this mode for a specified time and then, by stopping the supply of oil aerosols, to relieve pressure and close them;
  • F is the signal of the opening-closing of the valve 23-T f , which supplies the aerosol oil to the manifold of the nozzles of the combustion chamber;
  • H is the on-off signal of the pneumatic reducer 19, which ensures the intake of dried nitrogen from the cylinder 18 and its supply to the valve 20;
  • Q is the signal of the opening-closing of the valve 20, which provides the supply of dried nitrogen to the actuator 22 of the distributor pneumohydraulic device 5;
  • R is the open-close signal of the valves 23-Tj, providing oil supply to the actuators 24-Tj of the fuel system of the engine
  • M is the open-close signal of the valves 23-Mj, providing oil supply to the actuators 24-Mj of the engine oil system
  • N "N" - on-off signal of the device 21 for supplying dried nitrogen to the gas-air path and the air starter of the engine is absent;
  • P is the on-off signal of the mixer 13, providing the supply of aerosol preserving mixture in the actuator 22. Cycle /? 2 - oil pumping (from 75 to 100 sec.):
  • A is the on-switch-off signal of the electric pump 1 1 (Fig. 1), which ensures the intake of oil from the tank 10 and the creation of the desired pressure level in the oil supply line;
  • B is the on-switch-off signal of the electric pump 15 of the oil system, which provides for the intake of oil from the tank 14 and the creation of the desired pressure level in the oil supply line;
  • C is the on / off signal of the control valve 16 (Fig-1), which supplies oil from the pump 15 to the actuator 22 of the distributing pneumohydraulic device 5;
  • “D” is the on / off signal of the control valve 12 (Fig.l), which supplies oil from the pump 1 1 to the actuator 22 of the distributing pneumohydraulic device 5;
  • E is the on-off signal of the actuators 24-Tj of the engine fuel system, providing oil supply to the engine fuel system, creating the pressure in hydraulic distributors (not shown in the drawings) necessary to open them, maintaining this mode for a specified time, and then, by shutting off the oil supply, - depressurizing and closing them;
  • F is the signal of the opening-closing of the valve 23-Tj, which supplies oil to the manifold of the nozzles of the combustion chamber;
  • “G” - on-off signal of actuators 24-Mj of the oil system providing oil supply to the engine oil system, creating the pressure necessary for their opening in hydraulic distributors, maintaining this mode for a specified time, and then, by cutting off the oil supply , - pressure relief and their closure;
  • “H” is the on-off signal of the pneumatic reducer 19, which provides the intake of dried nitrogen from the cylinder 18 and its supply to the valve 20 is absent;
  • R is the signal of the opening-closing of the valves 23-T 1 , providing oil supply to the actuators 24-Tj of the fuel system of the engine;
  • M is the open-close signal of the valves 23-M, providing oil supply to the actuators 24-Mj of the engine oil system,
  • N "N" - on-off signal of the device 21 for supplying dried nitrogen to the gas-air path and the air starter of the engine is absent;
  • Cycle C preservation of the gas-air tract (from 101 to 114 sec.):
  • A is the on-switch-off signal of the electric pump 11 (Fig.l), which provides for the intake of oil from the tank 10 and the creation of the desired pressure level in the oil supply line;
  • H is the on-off signal of the pneumatic reducer 19, providing for the intake of dried nitrogen from the cylinder 18 and its supply to the valve of the device 21,
  • K is the on-off signal of the mixer 13, which supplies the aerosol oil to the device 21 for supplying working media to the gas-air duct of the engine;
  • N is the on-off signal of the device 21, which provides the spray of the aerosol mixture in the gas-air duct of the engine.
  • P - no signal.
  • a pause “D” can be provided in the cyclogram, during which, for example, stabilization of an air-drop mixture of oil aerosol with air inclusions in the internal cavities of the units and engine systems can be achieved, which, when pumping the preservative medium further, will more effectively eliminate air gaps. Or in a pause, necessary tests of pumped mixtures can be carried out.
  • the shown cycles can be repeated as many times as necessary until the required quality of preservation or de-preservation is achieved. For example, when the engine is mothballed - with the supply of the washing mixture until there are no particles of fuel or oil in the pumped washing mixture. Or during conservation - until there are no air inclusions in the preservative mixture pumped through the units and lines of the fuel and oil systems of the engine.
  • the operation of the automated device 1 is controlled by the indication on the panel 8. If desired, periodically during the cycle or after completing the entire set of cycles of the given sequence, the quality of the pumped preserving mixture, for example, oil, is monitored at the drain outlet pipes 28-Mj and 28-Ti of engine 24, and by the presence of air inclusions in the oil make a conclusion about the sufficiency or insufficiency of the number of completed conservation cycles.
  • the quality of the pumped preserving mixture for example, oil
  • the cyclogram is started again and the entire set of cycles of the given cyclogram is repeated, or other cyclograms, for example, a shortened type, are used, containing some of the cycles shown in Fig. 3, with the repetition of only individual cycles.
  • the developed technology for the execution of work also provides for the possibility of performing a semi-automated conservation of an air starter after performing internal engine conservation in an automatic mode.
  • the method of internal preservation and / or de-preservation of gas turbine engines allows simultaneous conservation and / or de-preservation of several engines, simultaneously combining internal preservation for some engines and internal re-preservation for others, using one automated device, equipped with several autonomous sources of preserving media, several autonomous sources of flushing media, at least one dispensing device, one autonomous control device, one autonomous power source.
  • significant invariance and mobility of preservation or de-preservation of various engines outside the aircraft is achieved, for example, in a warehouse.
  • the method of internal conservation and / or de-preservation of gas turbine engines according to the invention can be carried out using devices containing known components, or using an automated device for internal conservation and / or re-conservation according to the invention.
  • the method allows both simultaneous or sequential preservation or de-preservation of systems and units of one idle engine, and simultaneous or sequential preservation and de-preservation of systems and units of several idle engines. This eliminates the need for dismantling the engines from the aircraft and connecting the aircraft to power sources.
  • the method according to the invention does not require a significant investment of time for preservation, additional technological capacities of a significant volume, powerful energy sources, additional fuel consumption for the operation of the auxiliary power plant. Spent working fluids do not pollute the environment and can be used repeatedly after cleaning.
  • the automated device according to the invention is maintainable, easy to operate and can be easily modified in accordance with the tasks of internal conservation or de-preservation of systems and units of gas turbine engines. Professionals in the field of aircraft engineering should be clear that the method and device for internal conservation according to the invention can be made improvements and improvements that do not go beyond patent claims.
  • a quality control system for a pumped mixture can be automated, actuators of a distributing device can be unified, an aerosol preparation system for working mixtures of various concentrations can be automated, the possibilities of invariance in compiling cyclograms for preservation of engines of various types are expanded.
  • actuators of a distributing device can be unified
  • aerosol preparation system for working mixtures of various concentrations can be automated, the possibilities of invariance in compiling cyclograms for preservation of engines of various types are expanded.
  • the method of internal conservation and / or de-preservation of gas turbine engines according to the invention can be carried out using known devices, simple to operate, and known technologies for creating automated control programs.
  • An automated device for the internal preservation and / or de-preservation of gas turbine engines according to the invention allows the operation of the method of internal preservation and / or de-preservation according to the invention in optimal conditions with low energy and working media without starting the engine and without using fuel and oil resources of the engine installed on operated facility, for example, on an aircraft.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)

Abstract

La présente invention relève du domaine du fonctionnement de moteurs à turbine. Le procédé et le dispositif de préservation et/ou de dépréservation interne de moteurs à turbine de cette invention permettent de mettre en oeuvre, sur un moteur à l'arrêt, une succession d'opérations comprenant l'introduction automatique, dans un ordre prédéfini, à une pression donnée et en mode impulsionnel, de milieux de travail utilisés pour la préservation ou la dépréservation à partir de sources autonomes (2, 3, 4) de milieux de travail dans les conduits et cavités internes d'ensembles et de systèmes du moteur (24) sujets à la préservation ou à la dépréservation au moyen de la transmission de signaux électriques de commande présentant un rapport période-durée défini et coordonnés les uns par rapport aux autres dans un ordre prédéfini, à partir d'un dispositif de commande autonome (6), à destination de dispositifs d'actionnement (24-Mi, 24-Ti) des ensembles et systèmes susmentionnés du moteur (24), de dispositifs d'actionnement (23-Mi, 23-Ti) du dispositif de distribution (5) et de dispositifs d'actionnement (11, 12, 13, 15, 16, 17, 19, 20) des sources autonomes (2, 3, 4) de milieux de travail, les signaux électriques servant à fournir les conditions requises pour l'introduction de milieux de travail et à faire fonctionner les mécanismes d'actionnement susmentionnés en mode automatique conformément à un cycle donné et en un nombre de cycles suffisant pour l'obtention de paramètres requis du milieu de travail pompé, l'alimentation électrique assurée par une source autonome (9) d'alimentation électrique.
PCT/RU2006/000581 2006-11-07 2006-11-07 Procédé et dispositif de préservation et/ou de dépréservation interne de moteurs à turbine WO2008057002A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/RU2006/000581 WO2008057002A1 (fr) 2006-11-07 2006-11-07 Procédé et dispositif de préservation et/ou de dépréservation interne de moteurs à turbine
IL198606A IL198606A (en) 2006-11-07 2009-05-06 Method and device for internal preservation and/or depreservation of gas-turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2006/000581 WO2008057002A1 (fr) 2006-11-07 2006-11-07 Procédé et dispositif de préservation et/ou de dépréservation interne de moteurs à turbine

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WO2008057002A1 true WO2008057002A1 (fr) 2008-05-15

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2558699A1 (fr) * 2010-04-12 2013-02-20 MTU Aero Engines GmbH Dispositif et procédé de protection de systèmes à fluide et d'un moteur
CN106814642A (zh) * 2015-11-27 2017-06-09 上海船厂船舶有限公司 用于船舶管路清洗泵站的电控系统
US10287909B2 (en) 2015-05-29 2019-05-14 Pratt & Whitney Canada Corp. Method and kit for preserving a fuel system of an aircraft engine
US11885287B2 (en) 2021-07-09 2024-01-30 Rtx Corporation De-preserving a fuel system of a turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11053863B2 (en) * 2017-09-01 2021-07-06 Raytheon Technologies Corporation Integrated fuel pump and control preservation system

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4059123A (en) * 1976-10-18 1977-11-22 Avco Corporation Cleaning and preservation unit for turbine engine
RU2067680C1 (ru) * 1981-12-18 1996-10-10 Моторостроительное конструкторское бюро Способ консервации топливорегулирующей системы
JP2000035379A (ja) * 1998-07-16 2000-02-02 Tokyo Meeta Kk 内燃機関試験装置

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4059123A (en) * 1976-10-18 1977-11-22 Avco Corporation Cleaning and preservation unit for turbine engine
RU2067680C1 (ru) * 1981-12-18 1996-10-10 Моторостроительное конструкторское бюро Способ консервации топливорегулирующей системы
JP2000035379A (ja) * 1998-07-16 2000-02-02 Tokyo Meeta Kk 内燃機関試験装置

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2558699A1 (fr) * 2010-04-12 2013-02-20 MTU Aero Engines GmbH Dispositif et procédé de protection de systèmes à fluide et d'un moteur
US10287909B2 (en) 2015-05-29 2019-05-14 Pratt & Whitney Canada Corp. Method and kit for preserving a fuel system of an aircraft engine
CN106814642A (zh) * 2015-11-27 2017-06-09 上海船厂船舶有限公司 用于船舶管路清洗泵站的电控系统
CN106814642B (zh) * 2015-11-27 2024-04-26 上海外高桥造船海洋工程项目管理有限公司 用于船舶管路清洗泵站的电控系统
US11885287B2 (en) 2021-07-09 2024-01-30 Rtx Corporation De-preserving a fuel system of a turbine engine

Also Published As

Publication number Publication date
IL198606A (en) 2012-04-30
IL198606A0 (en) 2010-02-17

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