Gas-turbine plants and air intakes for jet-propulsion plants and controlling fuel supply in air-breathing jet-propulsion plants and (F02C)

F02C              Gas-turbine plants; air intakes for jet-propulsion plants; controlling fuel supply in air-breathing jet-propulsion plants (construction of turbines f01d; jet-propulsion plants f02k; construction of compressors or fans f04; combustion apparatus in which combustion takes place in a fluidised bed of fuel or other particles f23c0010000000; generating combustion products of high pressure or high velocity f23r; using gas turbines in compression refrigeration plants f25b0011000000; using gas-turbine plants in vehicles, see the relevant vehicle classes);(3070)

Blisk of cooled fuel feed pylons // 2642718
FIELD: engines and pumps.SUBSTANCE: each pylon has three channels plugged from side, open ends of two of these channels are closed by plugs, channels are connected by holes, and in central channel there is a damper with several holes.EFFECT: elimination of pylons burnout at high thermal loads, enhanced reliability of blisk of fuel supply, expanded performance range of fuel consumption at practically constant pressure drop on nozzles for improvement of combustion efficiency of fuel-air mixture.2 cl, 4 dwg

Gas turbine with bilateral drive // 2642714
FIELD: power industry.SUBSTANCE: gas turbine system comprising a gas turbine (23), a first load (71) and a second load (72) driven by a gas turbine. The gas turbine (23) comprises a gas generator (27), a low pressure turbine (50) and a drive shaft (65) driven by a low pressure turbine (50). The drive shaft has the first end (65H) connected with ability to transmit the driving force to the first load, and the second end (65C) connected with ability to transmit the driving force to the second load. The first load and the second load are located on opposite sides of the gas turbine, wherein the drive shaft (65) extends axially through the gas turbine from the first end to the second end. Wherein, the first load and the second load contain a compressor with a vertical housing connector. Method for operating gas turbine system is also provided.EFFECT: invention allows to increase the efficiency of system.14 cl, 5 dwg

Gas turbine engine control system // 2641786
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

Gear box for power take-off in gas turbine engine consisting of kinematic circuit with engagement lines arranged in non-parallel planes // 2641777
FIELD: engines and pumps.SUBSTANCE: gear box of the gas turbine engine for actuating its additional equipment comprises a housing, a kinematic circuit within the housing, a row of gears, and a power take-off mechanism for engagement with transmission shaft of the gas turbine engine. The housing comprises attachment points to the gas turbine engine and to the equipment, and the kinematic circuit comprises at least two end engagement lines arranged in non-parallel planes and joined to each other by adjacent engagement consisting of a pair of gears with non-parallel axes. At least one end engagement line at the end of the kinematic circuit is placed in the end branch of the housing which has the largest dimension in the axial direction of the gas turbine engine when the gearbox is attached to the gas turbine engine. Another engagement line is placed in the intermediate branch of the housing, in the circular section that partially surrounds a portion of gas turbine engine circumference when the box is attached to the gas turbine engine.EFFECT: invention makes it possible to reduce the overall dimensions of the gear box of the gas turbine engine.6 cl, 5 dwg

Controlling means for turbine with multiple combustion chamber // 2641776
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

Gas-liquid heat-exchange system with plurality of fluid flow modes // 2641772
FIELD: power industry.SUBSTANCE: pipe system for transferring heat from exhaust gas flow to feed water containing an economizer that includes four sections, as well as heat exchanger, and a plurality of valves. In this case, the economizer sections are within said gas flow, and the heat exchanger is outside this flow. In addition, the valves can be arranged in different configurations, which allows to provide a plurality of flow modes for controlling the temperature of feed water entering the gas box. A flow control method is also provided.EFFECT: invention enables to avoid damage of pipes of heat-recovery flow generator caused by strong corrosive action of sulfuric acid on material of pipes by raising the temperature of feed water in the heat exchanger which is external in relation to exhaust gas flow.24 cl, 6 dwg

Aircraft engine ignition device // 2641763
FIELD: engines and pumps.SUBSTANCE: engine ignition device comprises at least two spark plugs, a power supply source, a first channel for supply of a first spark plug and a second channel for supply of a second spark plug. Said channels are connected to the power supply source via power distribution means controlled by control system of FADEC type. Said distribution means comprise a first circuit for alternate feed of said first channel or said second channel and a second circuit for simultaneous feed of said first and second channels. The device is designed to use either the first circuit or the second circuit during the start-up.EFFECT: increased reliability of engine start-up.12 cl, 2 dwg

Oil-system of the gas turbine engine of the maneuvered aircraft // 2640900
FIELD: engines and pumps.SUBSTANCE: overflow valve is set behind the fuel-oil heat exchanger, and the overflow valve with internal piping products reported circulation compartment so that the outlet pipe is located at the top the recirculation cavity and down toward the septum, which separates the bays of each other.EFFECT: duration of the figured flights of the aircraft is prolonged, the reliability of the oil system is increased due to the bypass of the cooled oil in the tank, and the stable supply of oil to the entrance to the engine when the aircraft is flipped.1 dwg

Adjustable control of limit power in gas turbines // 2640874
FIELD: power industry.SUBSTANCE: method includes a step of determining at least one operational parameter of the gas turbine plant and a step of determining the power limit value depending on at least one determined operational parameter. While at least one operational parameter of the gas turbine plant includes ambient pressure of the medium and increase in the power limit value occurs when the ambient pressure increases.EFFECT: increasing the accuracy and flexibility of matching the power limit for the control of a gas turbine plant under varying environmental conditions.9 cl, 4 dwg

Seal assembly for gas turbine engine including grooves in inner band // 2640144
FIELD: engine devices and pumps.SUBSTANCE: seal assembly between a disc cavity and a hot gas channel passing through the turbine section of a gas turbine engine comprises a rotating blade assembly and a stationary assembly of guide blades. The rotating blade assembly includes a plurality of rotor blades which rotate together with the turbine rotor during operation of the engine. The fixed assembly of the guide blades includes a plurality of guide blades and an inner casing. The inner casing includes a radially outward facing first surface, a radially inward facing second surface, and a plurality of grooves extending from the second surface. The grooves are arranged so that a region having an extent in the circumferential direction is formed between adjacent grooves, at that during operation of the engine the grooves direct the purge air from the cavity of the disc towards the hot gas channel so that the purge air flows in the required direction with respect to the direction of the hot air flow through the hot gas channel. The grooves taper away from their inlets spaced from the axial end portion of the inner band to their outlets positioned near the axial end portion of the inner band so that the inputs have a width larger than the outputs.EFFECT: invention makes it possible to prevent the ingress of hot gas into the turbine disc cavity the turbine engine more effectively.9 cl, 4 dwg

ethod for washing and preserving gas-air path of aircraft engine and device for its implementation // 2639938
FIELD: engines and pumps.SUBSTANCE: method for washing and preserving the gas-air path of the engine is implemented during engine idling. At the first step, the formed fine-dispersed drops of the washing-preserving solution are supplied to gas-air path in a high-pressure air flow passing through the body of the spraying device (21). At the second stage, washing and preservation are carried out by flow of air when the supply of washing-preserving solution is switched off, after which air supply and the engine are switched off.EFFECT: invention improves the quality of washing and preservation of the engine.7 cl, 6 dwg

ethod to control boost pressure regulator of engine turbocharger and method to control engine turbocharger // 2639826
FIELD: engines and pumps.SUBSTANCE: various methods are provided to control the boost pressure regulator with a drive having a temperature-dependent magnetic field. In one example, the magnetic field is estimated based on the operating conditions and other parameters and used for applying magnetic correction to the voltage supplied to the drive. Methods can provide accurate control of the boost pressure regulator in the presence of alternating magnetic fields, ensuring proper supply of boost to the engine.EFFECT: improved accuracy.13 cl, 5 dwg

Reduction gear for high-speed and small-size fan drive turbine // 2639821
FIELD: engines and pumps.SUBSTANCE: gas turbine engine comprises a flexible support for a fan drive gear set. The first turbine section has a first output area and is capable to rotate at first speed. The second turbine section has a second output area and is capable to rotate at second speed which exceeds the first speed. The first characterizing parameter is the product of the square of the first speed and the first output area, the second characterizing parameter is the product of the square of the second speed and the second area of the output. The ratio of the first characterizing parameter to the second characterizing parameter ranges from 0.5 to 1.5. Frame has a lateral rigidity of the frame and a transverse rigidity of the frame, and flexible support has transverse rigidity of flexible support and lateral rigidity of flexible support. The lateral rigidity of the flexible support is less than said lateral rigidity of the frame, and said transverse rigidity of the flexible support is less than said transverse rigidity of the frame. The ratio of the thrust force provided by said engine to the volume of the turbine section including said high pressure turbine and said low-pressure turbine is greater than or equal to 1.5 and less than or equal to 5.5 lbs-force/inm3, at that said thrust is designed static thrust at take-off from sea level.EFFECT: reduction of turbine section concerning both diameter and axial length, increase of efficiency and extension of service life of gas turbine engine.18 cl, 11 dwg, 1 tbl

ethod and device to control oil cooling in impeller machine // 2639471
FIELD: machine engineering.SUBSTANCE: method for controlling oil cooling within a device and an oil cooling device of the impeller machine comprise a first heat exchanger mounted in series with a second heat exchanger. The first heat exchanger is an oil/air heat exchanger. The second heat exchanger is an oil/fuel heat exchanger. Each heat exchanger comprises an oil inlet and an oil outlet, a branch connecting directly the oil inlet of the first heat exchanger to the oil outlet of the first heat exchanger, and a flow controller for adjusting the rate of oil flow passing through the branch. The circulation of oil is provided through the branch by means of the flow controller. The flow controller comprises a the removable configured for opening, when the oil temperature is less than or equal to the predetermined temperature from 70 °C to 90 °C, preferably equal to about 80 °C.EFFECT: increase of adjustment accuracy.7 cl, 3 dwg

Box of actuators for power selection from the gas turbine engine containing the assembly casing // 2639460
FIELD: engines and pumps.SUBSTANCE: gear box of the gas turbine engine for actuating its additional equipment comprises a housing, a kinematic circuit within the housing, a row of gears, and a power takeoff mechanism for engagement with transmission shaft of the gas turbine engine. The body contains points of attachment to the gas turbine engine and to the auxiliary device. The kinematic chain consists of a set of successive lines of gears forming angles between themselves. The body includes two successive sections, united at the interface of the joint, forming an angle between them and each having one of the gear lines. The sections of the hull are made separately and combined with each other at the junction boundary.EFFECT: invention makes it possible to simplify the manufacture of the drive box of a gas turbine engine and reduce its dimensions.10 cl, 7 dwg
Control method of aircraft jet turbine engine // 2639409
FIELD: engines and pumps.SUBSTANCE: implementing the method preliminarily for this type of engine with a regular control program, it is tested at maximum and full forced mode with thrust measurement, then for each mode, the regulator is re-tuned to lower the rotor speeds and the gas temperature behind the turbine until a predetermined reduction in thrust is achieved and the regulator values are recorded. Then, based on the current values, they form an additional control program for rotation speeds of rotors and temperature of the gases behind the turbine and introduced it into the engine regulator or during the operation of the aircraft for training purposes, an additional control program for rotation speeds of the rotors and temperature of the gases behind the turbine is used, according to the signal from the aircraft and to the selected mode.EFFECT: preservation of engine lifetime during the operation of the aircraft for training purposes.1 tbl

ode of gas turbine plant operation on methane-contained steam-gas mixture and its actualization device // 2639397
FIELD: electricity-producing industry.SUBSTANCE: mode comprises the generated superheated high-pressure water steam injection into the combustion chamber, the steam most part injection into the combustion chamber, the superheated steam smaller part mixing with the natural gas, the injection and obtaining the methane-contained steam-gas mixture in the first adiabatic catalytic reactor, this mixture series heating-up by the gas turbine exhaust gas heat energy, and then by the heat energy of the combustion chamber cooling up to the 620-680°C temperature, the hydrogen density strengthening in the methane-contained steam-gas mixture above 20% in the second adiabatic catalytic reactor and this mixture injection in the function of the propellant into the gas turbine plant combustion chamber. The mode is implemented into the device, which comprises the compressor, the combustion chamber with the cooling jacket, the gas turbine, the conduit of the superheated steam injection into the combustion chamber, the driving assembly, the recovery boiler, which comprises the evaporator plant, the superheater, the convective heater of the methane-contained steam-gas mixture, the combustion products cooling and low-pressure steam condensation system, the natural gas pipeline, the steam conduit of the high-pressure steam, the mixer, two adiabatic catalytic reactors.EFFECT: thermodynamic and economical effectiveness upgrading of the plant, its design simplification and reliability growth.2 cl, 1 dwg

Device for lubricating bearing support of turbomachine rotor // 2639262
FIELD: engines and pumps.SUBSTANCE: oil supply branch pipe is made of two interconnected pipelines provided with intakes at the ends, one of the intakes is installed in the upper part of the oil cavity, and the other one is installed in its lower part, at that the intakes are equipped with autonomous loading ball valves.EFFECT: oil from the oil tank is prevented from getting into the oil cavity of the rotor main bearing in an inverted flight or in flight with negative overloads.1 dwg

ethod to control double-rotor gas-turbine engine // 2639260
FIELD: engines and pumps.SUBSTANCE: when stopping an engine, the electric power generated by the rotation of a low-pressure rotor shaft is transmitted to electric motor-generator of high-pressure rotor shaft to create additional acceleration which provides the ratio of the duration of the high-pressure rotor shaft running-out to the duration of the low-pressure rotor running-out equal to 1.5…6.0.EFFECT: excluding effect of dragging of high-pressure rotor shaft when shutdown.1 dwg

Gas turbine engine // 2638709
FIELD: engine devices and pumps.SUBSTANCE: gas turbine engine contains a fan, a compressor section, a combustion chamber in fluid communication with the compressor section, a fan drive turbine communicating with the combustion chamber, a geared system, a flexible support and a lubrication system. The geared system is designed to provide a speed reduction between the fan drive turbine and the fan and to transmit the input power from the fan drive turbine with an efficiency that exceeds 98% and less than 100% to the fan. The flexible support provides support for parts of the geared system. The support moves away from the fixed engine structure to compensate for at least radial movement between the geared system and the fixed structure. The lubrication system is designed to supply grease to the gear system and remove heat energy from the geared system. The fan drive turbine has the first outlet sectional area and is rotatable at the first speed and the engine further comprises of the second turbine having the second outlet sectional area and rotatable at a speed greater than the first speed of rotation. The first characterizing parameter is defined as the product of the square of the first speed and the first area, and the second characterizing parameter is defined as the product of the square of the second speed and the second area. The ratio of the first characterizing parameter to the second characterizing parameter is from 0.5 to 1.5.EFFECT: invention makes it possible to increase the efficiency of a gas turbine engine.11 cl, 1 tbl, 5 dwg

Engine dust-protecting device (versions) // 2638692
FIELD: engines and pumps.SUBSTANCE: engine dust-protecting device comprises cyclones that are fixed between the outer and inner cyclone panels forming a dust-removing path. In order to adapt the dust-protecting device for engines with frontal air intake and for convenience of the operation, the second version of the aircraft engine dust-protecting device contains cyclones fixed between the outer and inner cyclone panels which form an axially elongated body with a front cyclone panel displaced inwardly. A fairing is fixed at the outlet of the dust-protecting device inside the body. The mounting system is provided outside and configured for turning the body of the dust-protecting device. According the two versions, the arrangement of cyclones and the section of ducts for dust concentrate suction is determined by geometric relations protected by the invention.EFFECT: increased degree of cleaning, reduced hydraulic resistance along the dust suction path, provided convenience of the operation.2 cl, 8 dwg

ethod of gas-turbine engine control // 2638497
FIELD: engines and pumps.SUBSTANCE: invention can be used in electronic-hydro-mechanical systems of gas-turbine engine automatic control. The control signals of the electronic control, hydromechanical controller and selector signals are then converted into pneumatic signals, the control signals of the hydromechanical controller are cut off by the selector signal and the logic jet circuit cut off the control signal from the hydromechanical controller by the selector, and control signals of electronic control are send to executive mechanism, and the engine control is carried out, in case of electronic control failure the control signals of electronic control are cut off by the selector signal and logic jet circuit, and the control signals of the hydromechanical controller are supplied to the same executive mechanism, and the engine control is carried out.EFFECT: providing optimal control of the gas-turbine engine in all operation modes.4 dwg

ethod to control aircraft turbojet engine thrust disturbance // 2638417
FIELD: engines and pumps.SUBSTANCE: method is carried out by means of a computer placed on said apparatus, in case of change of target thrust value (N1CONS) of said turbojet engine, the actual thrust (N1EFF) of the turbojet engine changes during the transition phase to achieve the desired thrust (N1CONS), the method comprises the step of processing of given thrust value (N1CONS) by the filtering function and transition phase model in such a way as to obtain a simulated thrust (N1MOD), the step of measuring the actual phase (N1EFF), the step of comparing said modelled thrust (N1MOD) with said actual thrust (N1EFF) to determine the deflection of the thrust (Δ), a step of comparing of said deflection (Δ) of the thrust threshold (S) of the signalling and the step of transmitting an alarm signal if the threshold (S) of the signalling is exceeded, a method where in this iteration, the previously modelled thrust is known, the transient phase model provides a time constant based on the previously modelled thrust, the filtering function provides a simulated thrust (N1MOD) based on the obtained constant time modelled before the thrust and given thrust value (N1CONS).EFFECT: method improvement.8 cl, 8 dwg

Seal for gas turbine engine // 2638250
FIELD: engine devices and pumps.SUBSTANCE: seal for the gas turbine engine comprises a main portion located at the base of the turbine blade and a wing portion axially extending from said main body portion of the seal. The wing portion has a first portion substantially parallel to the central axis of the engine and an upwardly extending portion. The angle (A) between the central axis of the engine and said upwardly extending portion is approximately from 0° up to 90°.EFFECT: increase the efficiency of the seal.7 cl, 4 dwg

Gas-turbine engine combustion chamber operational control method // 2638245
FIELD: electricity-producing industry.SUBSTANCE: there is a gas-turbine engine combustion chamber operational control method, where the engine is composed of the compressor, two burners, the combustion chamber, which is located downstream of the noted burners, the turbine, two temperature probes downstream of the noted combustion chamber. Upon that, there is one vent for the part of the oxygen-containing gas withdrawal placed downstream of the noted compressor and upstream of the noted combustion chamber. Along with this, the noted vent is a part of the system of the oxygen-containing gas bypass in contravention of the combustion chamber and has a valve for the amount of the bypassing gas regulation. The method comprises stages, where one controls the combustion products temperature, compares the noted temperature probes value, opens the noted valve or increases the rate of its opening in case if in consequence of the noted comparison one find out that the difference between the noted temperature probes value goes beyond the fixed limit of the temperature differential.EFFECT: invention allows to reduce the probability of occurrence of high carbon monoxide emissions by virtue of the vent valve position automatic control.10 cl, 6 dwg

ethod and device for prevention of pass of interior objects into internal tract of ventilatory gas-turbine engine // 2638235
FIELD: engines and pumps.SUBSTANCE: method and device for preventing the passage of foreign objects into the inner path of ventilatory gas turbine engine to protect its parts from damage gas-and-air tract, based on inertial separation of heavy particles in rotary blade channels of ventilatory step and moving foreign objects away from the central sleeve zone of the ventilator in the peripheral zone in the outer engine. To implement a method and a device in the ventilator stages set barrier reflective racks to ensure effective separation of foreign objects in the radial direction in outer space within a tract of the axial ventilator stage, and prevent the passage of foreign objects into the inner path of ventilatory gas-turbine engine. The application of the method and the device does not cause a significant deterioration in the characteristics of the engine and can be used on different types of engines.EFFECT: internal protected engine of the aisle tract foreign bodies in a wide range of distribution of their size, and in addition, echelon location of barrier reflective rack doesn't cause high ascending hydraulic resistance in blade channel.5 cl, 9 dwg

Turbine assembly in turbine engine // 2638114
FIELD: engine devices and pumps.SUBSTANCE: turbine assembly in turbine engine having an outer housing, an inner housing, an annular exhaust gas path defined between outer and inner walls of the flow path, and a cavity of turbine exhaust casing. A plurality of structural braces supports the inner housing on the outer housing. Fairing surrounds each of the braces in a region extending between the outer and inner walls of the flow path. The first path of the purge air conducts cooling purge air radially inward towards the inner housing. The second purge air path conducts the cooling purge air radially outward to provide purge air flow to the position of the cavity of the exhaust casing radially outward from the outer wall of the flow path. The embodiment of the turbine assembly in the turbine engine is also presented.EFFECT: invention makes it possible to provide thermal protection of the turbine assembly exhaust casing.19 cl, 7 dwg

Helicopter engine air intake with increased bypass flow // 2638055
FIELD: aviation.SUBSTANCE: air intake of a helicopter gas turbine engine comprises a compressor and a duct for air supply to the compressor, edges (30, 32) and an anti-icing grid (36). The anti-icing grid is mounted on the outer ends (30a, 32a) of the edges (30, 32) of the air intake and is located in the path of the airflow entering the air intake (34). At least one edge (30, 32) of the air intake is made of a thin metal sheet.EFFECT: significant amount of bypass flow during icing.10 cl, 6 dwg

Wireless electronic system of control and diagnostics of aircraft gas turbine engine // 2637801
FIELD: engines and pumps.SUBSTANCE: system is equipped with an energy radiator, a set of energy receivers, an input device, an interference analyzer, a band-elimination filter, a subtracter, a storage, where the digital control unit is connected to the storage, the data receiving and scheduling radio module is connected to the subtractor, the outputs of a set of wireless smart sensors of the aircraft engine performance are connected via radio channels to the input of the input device, which is connected to the inputs of the interference analyzer and the band-elimination filter, the output of the interference analyzer is connected to the second input of the band-elimination filter, the output of which is connected to the input of the substracter, the output of which is connected to the input of the data receiving and scheduling radio module, and the second input of the subtracter is connected to the storage output, the input of which is connected to one of the outputs of the digital control unit, the other output of which is connected to the energy radiator which is through a radio channel is associated with a set of energy receivers, the outputs of which are connected to the inputs of a set of wireless smart sensors of aircraft engine performance.EFFECT: increase of reliability and noise immunity of the electronic monitoring and diagnostic system, increase in the overhaul life of the system components.2 dwg

System and method for turbine combustion chamber // 2637609
FIELD: machine engineering.SUBSTANCE: fuel combustion system is proposed, comprising a turbine combustion chamber that includes a head part with a head chamber. The head part contains the exhaust gas channel, the fuel channel and the oxidant channel. The turbine combustion chamber also comprises a combustion chamber portion located downstream of the head chamber. The turbine combustion chamber includes a partition located between the head chamber and the combustion chamber so that the fuel from the fuel channel and the oxidant from the oxidant channel are intended for combustion inside the combustion chamber located downstream of the partition. The turbine combustion chamber comprises an end plate having at least one port connected to the exhaust gas channel or oxidant channel, the head chamber being coaxial between the partition and the end plate. Variants of a system for fuel combustion and a method for fuel combustion are also presented.EFFECT: increased service life of the components, allows to control the temperature, pressure, flow rate, moisture content, particle content and the composition of the exhaust gas.50 cl, 20 dwg, 2 tbl

Feeding and discharging device for injector // 2637344
FIELD: machine engineering.SUBSTANCE: feeding and purge device (1) for a nozzle of a turbomachine chamber, which comprises: a tube (2) with a first opening (3) and a second opening (4), a blocking system (5) to block the tube, allows to control the passage of fluids into the tube (2). At that, the blocking system (5) is arranged with the possibility to provide the flow of fuel from the first opening (3) to the second opening (4) only from the first pressure of said fuel, for passage of fuel feed. At that, the blocking system (5) is also configured to provide the air flow from the second opening (4) to the first opening (3) only from the second pressure of said air, for the passage of the purge air with the second pressure being greater than the first pressure. Also, an assembly of a turbomachine, a nozzle for a combustion chamber of the turbomachine, and the turbomachine comprising a combustion chamber nozzle, are provided.EFFECT: invention makes it possible to develop simple and compact device, which is made with possibility of adjustment of both fuel and purge air supply, which allows to provide complete blowing.6 cl, 7 dwg

Aircraft turbomachine calculator // 2637286
FIELD: aviation.SUBSTANCE: calculator is described containing a metal body in the form of a parallelepiped with an electronic circuit placed therein, in which a regulation channel and a control channel are built. The body according to the invention comprises the first cavity with the first electronic board installed therein for controlling the regulation channel and the second cavity independent of the first cavity with the second electronic board installed therein for controlling the regulation channel, wherein these electronic boards are made in two planes oriented at an angle of 90° to each other.EFFECT: eliminating the causes of all general type failures, providing high flexibility.9 cl, 4 dwg

Structure based on superplastic forming/diffusion binding for reducing noise from air flow // 2637276
FIELD: aviation.SUBSTANCE: inner wall of nacelle includes a monolithic layered structure based on superplastic forming and diffusion binding, monolithic layered structure comprises a core disposed between the first and second facing sheets with formation of a layered structure. Moreover, the core includes a plurality of cells, and the first facing sheet has a plurality of wholes to ensure the arrival of noise and air into the cells.EFFECT: higher structural strength and high resistance to damage, heat resistance, noise reduction without increasing the weight of the structure are achieved.15 cl, 14 dwg

Gas-driven turbine under fractional loads control mode // 2637152
FIELD: electricity-producing industry.SUBSTANCE: there is a known gas-driven turbine under fractional loads control mode, which includes the obtaining of the assignment of the gas-driven turbine capacity value, the gas-driven turbine shaft velocity measurement in real-time mode. In this mode for the predetermined capacity value according to the rotation velocity-gas-driven turbine capacity dependence diagram with respect to the minimum fuel one determines the commanded speed level of the gas-driven turbine shaft rotation, compares it with the current rotation velocity value and forms the instruction for the change in fuel and air supply into the gas-driven turbine combustor for the commanded speed level value achievement.EFFECT: decrease in fuel consumption.1 dwg

Filtration system and cleaning method for inlet gas of gas turbine // 2636705
FIELD: machine engineering.SUBSTANCE: filtration system contains a flow channel (110), surrounded with walls (142), having an inlet opening (146) and outlet opening (148), a partition wall (108), which is located between the inlet opening (146) and the outlet opening (148) and limited by the walls (142) of the flow channel (110), with at least two openings (116) and at least two filters (100) for cleaning the fluid flowing down the flow channel (110). At least one first filter (100) is mounted in the first opening (116) on the dirty side of the partition wall (108), and at least one second filter (100) is mounted in the second opening (116) on the clean side of the partition wall (108). The filters (100) are located in at least one row in the partition wall (108). The filters (100) of the same row are alternatively fixed to the dirty side and clean side of the partition wall. The cleaning method for the inlet gas of a gas turbine is implemented in this system.EFFECT: increased system reliability.9 cl, 39 dwg
Disposal turbine plant // 2636643
FIELD: machine engineering.SUBSTANCE: disposal turbine plant contains a turbine generator, a power gas turbine, a gas cooler, a pressurizing compressor. The power gas turbine is cinematically connected to the turbine generator and is connected at the gas inlet to the outlet of the hot gas source through gas. The gas cooler is connected at the gas inlet to the outlet of the power gas turbine through gas. The pressurizing compressor is connected at the gas inlet to the gas-cooler outlet through gas, at the gas outlet - to the atmosphere and installed on the same shaft as the power gas turbine. The disposal turbine plant also comprises a bypass flue connected at the gas inlet with a hot gas source through gas, an additional gas cooler installed at the bypass gas flue outlet and a smoke exhauster communicating at the gas inlet via the gas cooler path through gas with the bypass flue, at the gas outlet - with the atmosphere. The smoke exhauster is equipped with a drive motor with AC frequency converter, electrically connected to the turbine generator, or the smoke exhauster rotor is cinematically connected to the power gas turbine shaft. The turbine generator is equipped with an alternating current frequency conversion device configured to supply voltage with varying frequency and amplitude of the alternating current consumers with a voltage of constant frequency and amplitude.EFFECT: decreased metal consumption of turbine equipment and increased efficiency.2 dwg

Torque transmitting mechanism of turbojet engine units, central bevel gear of turbojet engine, main conical gear pair of turbojet engine central bevel gear, body of turbojet engine central bevel gear, drive gear of central bevel gear, driven gear of central bevel gear, turbojet engine central bevel gear // 2636626
FIELD: engine devices and pumps.SUBSTANCE: single torque transmission mechanism to a two-shaft, double-flow aircraft turbojet engine having coaxial shafts of high-pressure rotor and low-pressure rotor dynamically interconnected and includes connected to high-pressure rotor to transfer torque to units from high-pressure turbine of the central bevel gear and reduction drives of propulsion motor gearbox and a gearbox of aircraft units. The reduction drives of the gearbox of aircraft units are connected by torque to the central bevel gear via a multi-stage reduction gear and via a flexible shaft with end hinges and bellows. The central bevel gear comprises a main gear pair of conical driving and driven gears which have gear rims. The main gear pair of the gear wheels of the central bevel gear is made with gear ratio i1,rn=(1.12÷1.43) [b/p]. The drive wheel of the main gear pair is mounted on the shaft installed in ball and roller bearings. The driven wheel is provided with a shaft mounted in a roller bearing and in a ball bearing which is mounted in the cover of the central bevel gear casing. Teeth of conical rims of driving and driven wheels have variable height decreasing towards axial apex of conventional cone of teeth apexes. Angle αr.c.g. of slope of conventional reference cone generator of gear rim to the axis of wheel shaft is determined in the range αr.c.g.1=(0.7÷1.1) [rad] for the driving wheel and αr.c.g.2=(0.55÷0.83) [rad] for the driven wheel. Angle of spiral βW, expressed in the same projection as the angle between the tangent to the tooth line to the midpoint of the latter and the radius of the same point drawn from the axis of the wheel shaft is variably determined in the range of values βW=(0.21÷0.32) [rad].EFFECT: increased efficiency and operation life of the engine.23 cl, 6 dwg

ethod for monitoring engine start cycle of gas-turbine plant // 2636602
FIELD: engines and pumps.SUBSTANCE: invention relates to a method for monitoring a starting cycle of an engine, in particular a gas-turbine plant, and comprising the following steps: (i) duration of ignition in the engine is determined at a certain start parameter, (ii) the ignition duration in the engine determined thuswise is compared to the control ignition duration for the control engine and at this start parameter, (iii) the engine start index is determined, (iv) the steps (i) - (iii) are repeated for this start parameter at each start of the engine during the cycle, and (v) depending on the indicator change, an alarm signal on engine start cycle degradation is generated.EFFECT: improved reliability of failure detection of the entire engine system or its part engaged in gas-turbine plant start.16 cl, 4 dwg

Hybrid power plant // 2636599
FIELD: power industry.SUBSTANCE: plant contains a reactor associated with a suspension producing unit, a shaft, installed in the gasostatic bearings, at one end of which a Segner wheel is set, which has the ability to connect with the consumer or energy converter, and the other end is associated with an air compressor, a separation unit of steam mixture, hydrogen and aluminium oxides and hydrogen into hydrogen, aluminium oxides and water, the inlet of which is associated with the Segner wheel, combustion chamber, the inlets of which are associated with the separation unit for feeding hydrogen and water to the combustion chamber, as well as associated with the air compressor for air feed, and the outlet of the combustion chamber is associated with the steam gas turbine. The plant is equipped with an additional turbine that runs on a mixture of steam, hydrogen and aluminium oxides, and an air compressor, the rotors of which are interconnected by the shaft, installed in gasostatic bearings. The inlet of said additional turbine is connected to the outlet of the reactor, and the outlet of the additional air compressor is connected to the gasostatic bearings of the shafts. The claimed plant provides for highly efficient power generation, as well as recycling of aluminium powder in different ratios followed by hydrogen generation and power usage when burning it. Due to the use of two circuits, the output power smooth adjustment of the plant is provided, maintaining the maximum performance efficiency.EFFECT: at the same time, the tasks of reducing the shaft rotation speed are solved due to the reduction of peak loads and the optimal operating conditions of the gasostatic bearings, which increases the operational life of the plant.1 dwg

System of fuel feed to combustion chamber of aircraft gas turbine engine // 2636360
FIELD: engines and pumps.SUBSTANCE: system is equipped with a shut-off valve, a fuel metering unit including a metering element and an actuator for controlling the position of the metering element, and with a control unit to the input of which an engine rotor speed sensor can be connected. The shut-off valve is connected to the control unit and mounted in a fuel channel connecting the output of the plunger pump and metering unit inlet, the outlet of the metering unit is connected to the main fuel channel through a backup fuel channel. The actuator for controlling the position of the metering element is connected with the control unit, wherein the system is further equipped with a position sensor of the dosing metering element associated with the control unit.EFFECT: increase of the reliability of the system and simplified design.5 cl, 1 dwg

Heat insulating casing of ship gas turbine engine // 2636229
FIELD: engine devices and pumps.SUBSTANCE: heat insulating casing of the ship gas turbine engine comprises a ship gas turbine engine with exhaust confuser branch pipe turned relative to the engine axis with exhaust cut at level of exhaust pipe base, an inlet ventilation branch pipe, an outlet branch pipe of the casing connected thereto. An annular perforated partition is arranged in the outlet branch pipe of the casing at a distance from a flange connector and the exhaust pipe, in which holes are made with the possibility of providing required consumption of ventilation air for engine cooling. The partition is secured over outer diameter the on casing outlet branch pipe, and along inner diameter is made in form of elastic blades bent towards exhaust side or secured over inner diameter on the exhaust confuser branch pipe, and outer diameter is made in form of elastic blades bent in opposite direction from the exhaust and resting with possibility of motion on inner surface of the casing outlet branch pipe.EFFECT: improving the reliability of operation of marine gas turbine engines.4 dwg

On-board device for protection of engine from ingestion // 2636201
FIELD: engine devices and pumps.SUBSTANCE: on-board protection device comprises a movable bottom panel (1) which is pivotally connected to the actuator rod rigidly fixed to the air intake housing (7). The lower panel (1) has in its rear part two rows of slits (12) with relative width , located at the relative length . The relative distance of the location of the second row of slits , where l is the bottom panel length, m; C is the length from the trailing edge of the lower panel to the axis of the first row of slits, m; D is the width of slits, m; K is the distance between rows of slits, m.EFFECT: invention increases the efficiency of engine protection device.3 dwg

Discharge method and bleed manifold of helicopter fuel pipeline // 2636188
FIELD: aviation.SUBSTANCE: helicopter engine manifold (4) comprises an outer longitudinal wall (41) and two closed end walls (42, 43), a longitudinal symmetry axis (X'X) inclined upwardly, a branch pipe (51-53) for connecting to bleed drains, and a connection (54) connected to the gas ejection nozzle (5) and connected to the bottom end wall (43). The manifold (4) also contains a housing (6) with a symmetry axis E'E substantially parallel to the axis of the manifold (X'X) in its inner volume (V). The housing (6) has a longitudinal wall (61) and two transverse end walls (62, 63). The housing (6) is connected to the drain pipe (53) of the injection wheel through a radial coupling (64) opening onto its longitudinal wall (61), the symmetry axis (E'E) is inclined with respect to the bearing horizontal ground surface (S0) when the helicopter is in position (H0) on the ground. The reference angle (A0), as well as this axis (E'E), is parallel to the bearing ground surface (S0) when the helicopter is in the acceleration phase.EFFECT: prevention of smoke formation when restarting engines.10 cl, 3 dwg

ethod and device to adjust fuel consumption threshold // 2635861
FIELD: engine devices and pumps.SUBSTANCE: method for adjusting fuel consumption threshold for use in open circuit for adjusting a turbojet engine driving an aircraft includes the stage for recieving a first estimation of fuel consumption injected into the combustion chamber of the turbine engine; the stage for recieving a second estimation of fuel consumption, wherein the second estimation is more accurate than the first estimation for at least one range of fuel consumption values, and the stage for adjusting fuel consumption threshold using the difference calculated between the first estimation and the second estimation. In this case, the threshold is intended for use in the open circuit for adjusting the turbine engine. The application of the open circuit fuel consumption threshold for adusting the turbine engine is also provided comprising a control unit comprising a computer program including instructions to perform the adjustment procedure, a device for adjusting the fuel consumption threshold and a turbine engine.EFFECT: invention allows to increase effectiveness of the turbine engine.12 cl, 7 dwg

Combustion chamber sealing segments, equipped with damping devices // 2635858
FIELD: electricity-producing industry.SUBSTANCE: band sealing construction for the burner assembly first front plate sealing with the second front plate of the adjoining burner assembly of the gas turbine comprises the sealing plate with channels and also containers that are attached to the sealing plate back side. The sealing plate front side faces the combustion chamber, and its back side faces away from the combustion chamber. The containers have the predefined volume and are attached to the sealing plate back side. Every container is in fluid communication with the channel for the acoustic damper creation. The other invention of the group refers to the gas turbine combustion chamber that is composed of the above-mentioned band sealing construction. When the above-mentioned band sealing construction fabrication one joins the containers, that have the predefined volume, to the sealing plate back side in such a way that these containers were in fluid communication with the channels that are implemented in the sealing plate for the acoustic damper creation.EFFECT: simplification of the fabrication and installation of the band sealing construction, which has the possibility of damping the required acoustic frequencies of the gas turbine combustion chamber.13 cl, 7 dwg

Transportable gas turbine module, ground gas turbine installation with transportable gas turbine module and method for assembly of such gas turbine installation // 2635756
FIELD: machine engineering.SUBSTANCE: module contains a base on which a power gas turbine and load are supported, as well as a structure that surrounds the turbine and the load and is connected to the base. The base comprises longitudinal beams extending parallel to the direction of the axis of gas turbine rotation, and transverse beams extending transversely to the axis of rotation. Longitudinal and transverse beams form a primary lattice structure on which the power gas turbine and load are located, and the power gas turbine and load are located on a pair of longitudinal beams. The power gas turbine is attached to the turbine frame connected to the module base by means of legs attached to a pair of longitudinal beams. Another invention of the group relates to a ground gas turbine plant comprising the above gas turbine module and a foundation. The foundation has a flat support surface for the gas turbine module, while the flat support surface has ruptures, and the foundation has passages parallel to the longitudinal beams and designed to accommodate lifting and moving platforms therein. During ground gas-turbine plant assembly, first, a foundation is created on the installation and test sites. A base is manufactured and attached to the first foundation forming a base support surface having fastening zones arranged according to the first configuration and intended to secure the said base on the said foundation. The gas turbine, the load, the auxiliary equipment and the structure surrounding the gas turbine, the load and the auxiliary equipment forming a module are assembled on the base. The gas turbine and the load are tested, then the module is removed from the first foundation. The module is transported to the destination and fixed to the second foundation forming a base support surface having the second fastening zones arranged according to the second configuration and intended to attach the said base to the said foundation. The first configuration corresponds to the second configuration. In the first and second foundations, empty spaces are formed, into which lifting and moving platforms are introduced.EFFECT: time required for installation and start-up of a gas turbine plant is shortened by ensuring that all commissioning work is carried out on the test site.25 cl, 17 dwg

ethod of dismounting turbojet engine, device for heating // 2635741
FIELD: engine devices and pumps.SUBSTANCE: two-shaft turbojet engine comprises a front fan, a high-pressure module with a high-pressure rotor, a low-pressure turbine module, an intermediate housing containing a thrust bearing of the high-pressure rotor. The high-pressure rotor is held in bearing by means of a connecting nut. When dismantling of said engine after removal of the low-pressure turbine module with corresponding shaft without removal of the fan, a heating device is introduced along the axis of the engine at the rear side into a central space freed by the module of low-pressure turbine, and heated from the inside by the connecting nut. After heating the connecting nut, the rear unscrewing tool is inserted and the unscrewing torque is applied thereto. At that the value of the torque is less than the value of forces that can destruct the teeth. In case of unsuccessful attempts to dismantle at the rear, removal of the fan is carried out, to release said connecting nut from the front the connecting nut is heated and the front unscrewing tool is arranged to apply the unscrewing torque to the connecting nut. Another invention of the group relates to a heating device for implementing said method and comprising a carriage with a tubular element mounted thereon. The tubular element is arranged with the possibility of introduction into said central space and equipped at one side with a facility for production of hot gas in the tubular element and a side hole at distance from said side.EFFECT: group of inventions makes it possible to simplify the method for dismantling the two-shaft turbojet engine.10 cl, 12 dwg

Steam-gas generator // 2635723
FIELD: power industry.SUBSTANCE: steam-gas generator comprises a fuel-cooled chamber, a mixing head which includes a housing, at the ends of which an upper and a lower bottoms are mounted, an intermediate bottom located between the housing and the head, an oxidizer manifold mounted on the housing, a fuel swirler located on the axis of the mixing head, spray swirlers located evenly around the circumference and including a hollow tip with screw channels and a sleeve covering the tip with an annular clearance and connecting the oxidizer cavity with the chamber cavity, wherein the axial channel of the tip connects the cavity of the ballasting component with the chamber cavity, and the fuel cavity is connected to the chamber cavity via tangential holes performed on the cylindrical surface of the fuel swirler, wherein the cavity of the chamber cooling path is connected with the fuel cavity of the mixing head.EFFECT: invention allows to increase the uniformity of the temperature field of the vapour-gas mixture at the outlet in a wide range of temperatures and pressures due to the intensification of the evaporation process of the ballasting component.4 dwg

Gas pumping unit with heat recovery system // 2635423
FIELD: machine engineering.SUBSTANCE: assembly containing a gas turbine engine, a centrifugal compressor, an air purifying device with an anti-icing system, a gas-exhaust path, an exhaust gas heat recovery system, is described. The heat recovery system of exhaust gases is represented by a plate heat exchanger installed outside the exhaust path. The input of the heating cavities of the heat exchanger is gas-bound to the exhaust path, and the outlet - to the atmosphere; the input of the heated cavities of the heat exchanger is gas-bound to the atmosphere, and the output of the heated cavities of the heat exchanger is connected to the heat consumer. In addition, an exhaust fan is connected to the outlet of the heating cavities of the heat exchanger, and a pressure fan is connected to the inlet of the heated cavities.EFFECT: aerodynamic characteristics of the exhaust system are improved.2 cl, 1 dwg

ethod of operation of gas turbine in mode with partial load and gas turbine // 2635422
FIELD: machine engineering.SUBSTANCE: gas turbine has a compressor for air preparation, a combustion chamber with a burner and a turbine for pressure relief. A bypass flow channel is provided and designed to direct compressor air during operation of the gas turbine to the burner and to the hot gas flow generated in the combustion chamber. In this case, the cross-section of the opening of the bypass flow channel can be adjusted by means of a controlling element, the gap section change rate being selected such that the relative pressure loss in the combustion chamber or the temperature of the combustion chamber material are constant.EFFECT: invention allows the partial load range to be lowered to create lower power levels without exceeding the carbon monoxide emission limit values.9 cl, 6 dwg
 
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