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WO2012005619A1 - Moteur à turbine gaz active (variantes) - Google Patents

Moteur à turbine gaz active (variantes) Download PDF

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Publication number
WO2012005619A1
WO2012005619A1 PCT/RU2010/000383 RU2010000383W WO2012005619A1 WO 2012005619 A1 WO2012005619 A1 WO 2012005619A1 RU 2010000383 W RU2010000383 W RU 2010000383W WO 2012005619 A1 WO2012005619 A1 WO 2012005619A1
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WO
WIPO (PCT)
Prior art keywords
fuel
rotor
stator
channels
vanes
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/RU2010/000383
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English (en)
Inventor
Aleksandr Alekseevich Pavlov
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Individual
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Individual
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Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to PCT/RU2010/000383 priority Critical patent/WO2012005619A1/fr
Publication of WO2012005619A1 publication Critical patent/WO2012005619A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/34—Non-positive-displacement machines or engines, e.g. steam turbines characterised by non-bladed rotor, e.g. with drilled holes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F02C3/165—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant the combustion chamber contributes to the driving force by creating reactive thrust
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the claimed group of inventions relates to the field of of power-plant engineering in particular to gas turbine engines, and can be used at thermal power plants, also as primary engines in road and waterborne transport, aviation and other fields of national economy.
  • gas turbine engines c HenpeptiBHtiM cropaHHeM TonjiHBa npn nocToaHHOM flaBJieHHHare widely used including detachable housing with two cavities with interconnected nozzle assemblies; in one cavity, the compressor wheel is installed, and the other includes turbine wheel which are rigidly fixed on the common shaft installed in the housing, combustion chamber, heat exchanger, inlet and outlet nipples (See p.101 "Scientific and Technical Dictionary”, “Sovetskaya encyclopedia”, Moscow, 1977, and p.200 “Brief scientific and Technical Dictionary”, Gos. Izdatelstvo of technical and theoretical literature, Moscow, 1956 ).
  • thermodynamic process of the cycle is realized in the separate device; the devices are arranged along a common shaft in a certain sequence, that is, the working body compression is performed in the compressor, heat feed - in the combustion chamber, and the air expansion with performing useful work— in the gas turbine.
  • a gas turbine engine of internal combustion with the fuel mixture combustion in Otto cycle including a turbine installed on the shaft in the engine housing.; the turbine blades are situated in the combustion chamber; explosive mixture is supplied to the combustion chamber through the nozzles arranged around the blades and having continuous ignition, with synchronous cutoff; the obtained pressure is supplied to the turbine blades and reflectors (FR jNb 1538421).
  • a gas turbine engine including a housing wherein a compressor is situated including a rotor with a disk with working blades with are installed on its shaft kinematically connected with the turbine shaft, and an open diffuser, arranged concentratically relatively to the latter of the gas turbine; combustion chamber arranged uniformly along the internalsurface of the working wheel of the gas turbine at the same distance from the rotation axis and rigidly fixed on it; input is made as a diffuser , and the output is made as a nozzle, fuel burners, installed in the combustion chamber and connected with fuel tubes are characterised in that the compressor is provided with guiding device, input of each combustion chambers is located in the open diffuser over the blades of guiding device and is oriented towards its output, and output of each combustion chamber protrudes over the outer surface of the working wheel and is made as a Laval nozzle.
  • Each combustion chamber is provided with supersonic diffuser; the engine is provided with a generator with windings, a stator combined with the engine housing, and a rotor kinematically connected though transmission with the turbine shaft, and combustion chambers are provided with electrodes installed in the output portion of the diffuser and connected electrically with windings of the generator stator (RU jV° 2078968, prototype).
  • the disadvantages of this engine is high fuel consumption and hgih demands on its quality; high air consumption and lubricants; high volume of toxic releases of combustion products; instability of the moment created on the shaft and the number of revolutions of the latter; low specific power (on the unit mass); high prime cost; non- perfect stream formation; low efficiency (for devices of Segner wheel type cannot exceed 50%) due to energy loss with discharge of the hot compressed working body from the nozzles in the combustion chamber into the atmosphere; non-optimum structure of the working body stream and high losses with the output velocity; possibility of the structure destruction and the jet adhesion; thermal pollution of environment with discharged combustion products.
  • the aim of the invention embodiments is development of an active gas turbine engine and expansion of the gas turbine engines inventory .
  • the technical result which provides the solution of the problem in both embodiments lies in multiple decrease in the fuel consumption with decrease in demanda to its quality and expansion of nomenclature including biologic fuel, paraffin oil, diesel fuel;
  • the bearing are located outside the high temperature zone
  • the rotor is installed relatively to the distributing stator and support stator with the gaps along circular and side surfaces connected with the channels of the cooling air;
  • the number of nozzles in two rows is equal to the number of blades in the support stator;
  • the rotor is made with with two rows of combustion chambers and nozzles shifted relatively to each other in angular direction; windows for exhaust gases removal in the stator are made radially and are directly connected to atmosphere;
  • the blades are made with the edges inclined towards the circle and are installed radially or at a slant position;
  • the nozzles are made with a critical cross-section at the cutoff in the plane inclined to the radial plane of the rotor on which recessions are made under each nozzle; direction of the nozzle symmetry axis is selected from the condition of the maximum approximation to the tangent surface of the rotor and perpendicular action of the jet on the support stator blades;
  • combustion chambers have
  • the gas turbine engine includes a shaft installed on bearings in the housing wherein a rotor of the gas turbine is mounted; on one side of the rotor of first and second centrifugal compressors between them an internal guiding device; the blades of the guiding device are made in the housing; an input guiding device is located on the suction side of first compressor; the rotor of the gas turbine is made with two rows of combustion chambers arranged in circumference and is installed so to provide rotation in the distributing stator made with fuel feed channels and mixing chambers to feed fuel mixture into inlet windows of each combustion chamber having inclined outlet nozzles faced with their cuts cpe3aMH the vanes of the support stator located in the circular gap; in the vanes, the channels for fuel overheat are made which are connected through fuel feed channels with the fuel burners of the combustion chambers made in the distributing stator around the blades of third compressor; the blades are made in the rotor
  • the bearing are located outside the high temperature zone
  • the rotor is installed relatively to the distributing stator and support stator with the gaps along circular and side surfaces connected with the channels of the cooling air;
  • the number of nozzles in two rows is equal to the number of blades in the support stator;
  • the rotor is made with with two rows of combustion chambers and nozzles shifted relatively to each other in angular direction; windows for exhaust gases removal in the stator are made radially and are directly connected to atmosphere;
  • the blades are made with the edges inclined towards the circle and are installed radially or at a slant posotion;
  • the nozzles are made with a critical cross-section at the cutoff in the plane inclined to the radial plane of the rotor on which recessions are made under each nozzle; direction of the nozzle symmetry axis is selected from the condition of the maximum approximation to the tangent surface of the rotor and perpendicular action of the jet on the support stator blades;
  • FIG.l a construction diagram of the engine with two-way air feed (longitudinal section) in the Fig.2 and Fig.3 - enlarged fragments of the Fig.1 , in the Fig.4 - cross-section according to the Fig.l, in the Fig.5 - enlarged fragment of the Fig.4, in the Fig.6— construction diagram of the engine rotora, in the Fig.7 - construction diagram of the distributing stator, in the Fig.8 - the end view of the engine according to the Fig.l, in the Fig.9 - construction diagram of the engine with one-way air feed (longitudinal section), in the Fig.10 - enlarged fragment of the Fig.9, in the Fig.l 1 - cross-section according to the Fig.9, in the Fig.12 - construction diagram of the engine rotor with third compressor, in the Fig.13 - construction diagram of the distributing stator, in the Fig.14 -
  • - rotor 8 of first centrifugal compressor - housing (made in the form of a flange) 9 of the internal guiding device with the vanes 4 of the internal guiding device;
  • the rotors 8,17 are installed of first H second centrifugal compressors with vanes 3,6, respectively; between the rotors an internal guiding device is placed; the vanes 4 thereof are made on two sides in the housing (flange) 9. From the suction side of first compressor in direction 16 from two sides (to the right and to the left according to the Figs.1-3) in the housing 14 an input guiding device is located the vanes 5 thereof are made on two sides in the housing 14, and bearings 7 for the shaft 1 installation in the housing 14.
  • first and second right and left compressors with the rotors 8,17 and vanes 3,6 are located symmetrically according to drawing in the Figs.1-3, the right and left guiding devices with the vanes 4,5, and also a TaK3 ⁇ 4ce right and left bearings 7.
  • the rotor 2 of the gas turbine is symmetrical with two rows of combustion chambers 11 arranged in circumference so to provide their capability of rotation in the distributing stator 22 made with fuel feed channels 23 and mixing chambers 21 for feeding the fuel mixture into inlet windows 26 of each combustion chamber 11 with inclined outlet nozzles 24 uniformly distributed over the circumference faced in pairs with their cutoffs the blades 18 of the support stator 19 located in the circular gap where channels 25 for fuel overheat are made connected through fuel feed channels 23 with fuel burners 20 of the mixing chambers 21 made in the distributing stator 22 around the vanes 6 of the second compressor.
  • the bearings 7 are located on both sides of on the suction side of first compressor, that is, outside the high temperature zone.
  • the rotor 2 is installed relatively the distributing stator 22 and support stator 19 with the gaps over circular and side surfaces connected with cooling air circulation channels (not shown).
  • the number of nozzles in two rows is equal to 24 the number of blades 18 of the support stator 19.
  • the rotor 2 of the gas turbine is made with two rows of combustion chambers 11 and nozzles 24 relatively to each other in angular direction.
  • the windows 30 for removal exhaust gases are made in the support stator 19 radially and directly connected with atmosphere.
  • the blades 18 in the support stator 19 are made with the edges inclined to circumference and are installed radially or at a slant position.
  • the nozzles 24 are made with the critical section on the cutoff in the plane inclined to the radial plane of the rotor 2 where pits are made beneath under each nozzle 24.
  • Direction of the axis of symmetry of the nozzle 24 is selected from the condition the maximum approach to the tangent surface of the rotor 2, and perpendicular action of the jet on the blades 18 of the support stator 19.
  • the combustion chambers 11 are made of trapezoidal shape diverging to periphery at an inclined against direction of rotation.
  • each of them is connected with fuel overheat channels 25 of each other vane 18 alternately with fuel overheat channels of other blades 18.
  • the inlet windows 26 of the combustion chambers 11 are made of rectangular cross-section in the internal surface of the active rotor 2 and represent an aerodynamic stage of flash expansion in the internal volume of the combustion chamber 11 against the direction of the active rotor 2 rotation.
  • the combustion chambers 11 are also inclined against the rotor 2 rotation.
  • Internal distributing stator 22 gas has converging mixing chambers 21 of rectangular cross-section faced with the narrow critical portion rectangular inlet windows 26 of combustion chambers 11 .
  • the mixing chambers 21 of the distributing stator 22 in the median cross-section have diverging nozzles (fuel burners) 20 for injecting evaporated fuel directly in to the air stream.
  • the nozzles 24 are made with their configuration convex in direction of the rotor 2 rotation.
  • Direction of the axis of the nozzles 24 symmetry is located at a small angle to the rotor 2 radius in the rotational plane; direction 27,28 of the combustion products exhaust from the nozzles 24 in two rows of the combustion chambers 11 are defined with the fact that direction of the nozzle 24 axis of symmetry is selected from the condition of the maximum approach to the tangent surface of the rotor 2 and perpendicular action of the jet on the blades 18 of the support stator 19.
  • the channels 23 for fuel feed provided with fuel burners 20 are made in the distributing stator 22 on both sides of the rotor 2.
  • a bevel locking device 33 is installed in front of the first compressor.
  • Two rows of the combustion chambers 11 and the nozzles 24 are shifted relatively to each other in angular direction by a half of the central angle between the nozzles in the same row.
  • the support blades 18 of the stator 19 and the windows 30 are common for two rows of the combustion chambers 11 and nozzles 24 of the rotor 2. Curvature of the nozzles 24 are selected from the conditions of uniform wearing of their internal surface.
  • the combustion chambers 11 are formed of two neighboring detachable elements (not designated) of 1-shaped cross-section.
  • the zone 29 for removal the exhaust gases is common for all the exhaust gases incoming from chambers 11.
  • the gas turbine engine with one-way air feed (intake) includes a shaft installed on bearings 7 in the housing 9,14 where the rotor 2 of the gas turbine is mounted, one one side thereof the rotors 8,17 of first H second centrifugal compressors with the vanes 3,6 are installed, respectively; between them , the internal guiding device is located, the vanes 4 thereof are made kin the housing (flange) 9. From the suction side of first compressor an input guiding device is located, the vanes 5 thereof are made in the housing 14.
  • first and second compressors with rotors 8,17 and the blades nonacTaMH 3,6, guiding devices with the vanes 4,5 are installed on one side of the rotor 2 right and left according to drawings Figs.9,10.
  • the rotor 2 of the gas turbine is symmetrical with two rows of combustion chambers 11 arranged on the circumference and is installed so to provide a capability of rotation in the distributing stator 22 made with the fuel feed channels 23 and mixing chambers 21 for feeding the fuel mixture into inlet windows 26 of each combustion chamber 11 having inclined outlet nozzles 24 uniformly distributed over the circumference and faced in pairs with their cutoffs the blades 18 of the support stator 19; the vanes where fuel overheat channels 25 are made are located in the circular gap; the channels are connected through fuel feed channels 23 with fuel burners 20 of the mixing chambers 21 made in the distributing stator 22 around the vanes 31 of third compressor.
  • the roller bearing 7 are located on both sides from the suction side of first compressor, that is, outside the high temperature zone.
  • the rotor 2 is installed relatively the distributing stator 22 and support stator 19 with the gaps on circumferential and side surfaces connected with the cooling air circulation channels (not shown) .
  • the number of the nozzles 24 in two rows is equal to the number of the blades
  • the rotor 2 of the gas turbine is made with two rows of the combustion chambers 11 and nozzles 24 shifted relatively to each other in angular direction.
  • the windows 30 for removal the exhaust gases are made in the support stator 19 radially and are direct connected with atmosphere.
  • the blades 18 of the support stator 19 are made with the edge inclined to circumference and installed radially or at a slant position.
  • the nozzles are made with the critical cross-section on the cutoff in the plane inclined to the radial plane of the rotor where pits (not designated) are made beneath each nozzle 24.
  • Direction of the axis of symmetry of the nozzle 24 is selected from the condition of the maximum approximation to the tangent surface of the rotor 2 and perpendicular action of the jet on the support stator blades 18 of the support stator 19.
  • the combustion chambers 11 are made of trapezoidal shape diverging to periphery at an angle to direction of rotation.
  • the inlet windows 26 of the combustion chambers 11 are made of rectangular cross-section in the internal surface of the active rotor 2 and represent an aerodynamic stage of flash expansion in the internal volume of the combustion chamber 11 against the direction of the active rotor 2 rotation.
  • the combustion chambers 11 are also inclined against the rotor 2 rotation.
  • Internal distributing stator 22 gas has converging mixing chambers 21 of rectangular cross-section faced with the narrow critical portion rectangular inlet windows 26 of combustion chambers 11 .
  • the mixing chambers 21 of the distributing stator 22 in the median cross-section have diverging nozzles (fuel burners) 20 for injecting evaporated fuel directly in to the air stream.
  • the nozzles 24 are made with their configuration convex in direction of the rotor 2 rotation.
  • Direction of the axis of the nozzles 24 symmetry is located at a small angle to the rotor 2 radius in the rotational plane; direction 27,28 of the combustion products exhaust from the nozzles 24 in two rows of the combustion chambers 11 are defined with the fact that direction of the nozzle 24 axis of symmetry is selected from the condition of the maximum approach to the tangent surface of the rotor 2 and perpendicular action of the jet on the blades 18 of the support stator 19.
  • the channels 23 for fuel feed provided with fuel burners 20 are made in the distributing stator 22 on both sides of the rotor 2.
  • Two rows of the combustion chambers 11 and the nozzles 24 are shifted relatively to each other in angular direction by a half of the central angle between the nozzles in the same row.
  • the support blades 18 of the stator 19 and the windows 30 are common for two rows of the combustion chambers 1 1 and nozzles 24 of the rotor 2.
  • Curvature of the nozzles 24 are selected from the conditions of uniform wearing of their internal surface.
  • the combustion chambers 11 are formed of two neighboring detachable elements (not designated) of 1-shaped cross-section.
  • the zone 29 for removal the exhaust gases is common for all the exhaust gases incoming from chambers 11.
  • the gas turbine engine with two-way air feed (intake) according to the
  • Figs.1-8 operates as follows.
  • the shaft 1 of the engine with c rotor 2, rotors of 8,17 first and second centrifugal compressors is brought to rotation from any start-up source.
  • the first centrifugal compressor 8 with 3 intakes the atmospheric air 16 and in the guiding device 4 increases pressure and velocity on other side at the output from the blades c .zrpyrofi CTopoHw Ha Bbrxo ⁇ e c jionacTefi 3 yeejiHOiBaeT .zxaBJiemie H cKopocTB B HanpaBJifliomeM annapare 4. Further the compressed air through the radial converging channel enters second centrifugal compressor (rotor 17) with vanes 6. At the output of the vanes 6 the air pressure increases under action of the vanes 31.
  • the vanes 4,5 of the guiding device provide optimization of compressors operation and increasing their efficiency.
  • the compressed air enters converging rectangular mixing chambers 21 of the internal distributing stator 22 and increases pressure, density and velocity in their converging critical part.
  • the system of air feed support system (not shown) operates independently with the maximum dosing accuracy and pressure and velocity rise in in converging mixing chambers 21 of the distributing stator 22.
  • fuel burners 20 for fuel injection are located in the critical part of the converging chambers 21 of the distributing stator 22. With the fuel injection directly in the air stream compressed with compressors, the completed fuel mixture enters the combustion chamber 11 through the injection windows 26. As the fuel mixture is formed directly at the input of the combustion chamber 11, and the fuel and the air are in the same aggragative state, efficiently blended fuel enters the combustion chamber 11.
  • Directions 27,28 of combustion products exhaust from the nozzles 24 in two rows of combustion chambers 11 is determined by the fact that the direction of axis of symmetry of the nozzle 24 is selected from the condition the maximum approach to the tangent surface of the rotor 2 and perpendicular action of the jet on the blades 18 of the support stator 19. With that, the working body (combustion products) does not transfer mechanical energy to any intermediate element (piston or turbine blades). Energy of the combustion product jet exhausting from the nozzles 24 acts on support planes of the blades 18 inducing rotation of the rotor 2.
  • the blades 18 of the stator 19 have through fuel overheat channels 25 and provide fuel feed to all the mixing chambers 21 of the distributing stator 22 (the number of the nozzles 24 is equal to the number of the vanes 18 of the support stator 18). Rather small amount of the exhaust gases is removed in direction 10 into the windows 30 radially creating no pressure in the secondary zone 29.
  • the active rotor 2 of the gas turbine is cooled efficiently (no shown) of the central part and side surfaces of the chambers 11 , temperature of the chamber 11 outer walls of the active rotor 2 is considerably lower that the temperature of fuel combustion.
  • the bearings 7 do not contact with the high temperature zone and operates under the ideal conditions.
  • the gas turbine engine with one-way air feed (intake) operates as follows.
  • the shaft 1 of the engine with rotor 2, rotors 8,17 of first and second centrifugal compressors and the vanes 31 of third compressor is brought to rotation from any start-up source.
  • the engine with one-way air intake differs from the previous one in the presence of two serial centrifugal compressors one one side and the presence of flow third compressor. As a whole, the operation algorithm almost completely corresponds to that of the engine with two-way air intake.
  • the first centrifugal compressor 8 with vanes 3 intakes the atmospheric air 16, and on the opposite side at the vanes 3 output increases the pressure and velocity in the guiding device 4. Then the compressed air through the radial converging channel it is sucked with second centrifugal compressor (rotor 17) with the vanes 6. At the output of the vanes 6 the air pressure increases under action of the vanes 3, further the pressure rises under action of the vanes 31.
  • the vanes 4,5 of the guiding device provide optimization of the compressor functioning and efficiency improvement.
  • the compressed air enters in converging rectangular mixing chambers 21 of the internal distributing 22 and increases pressure, density and velocity in their converging critical part.
  • the system for the air (not shown) operates independently with the maximum dosing accuracy and pressure and velocity rise in in converging mixing chambers 21 of the distributing stator 22.
  • fuel burners 20 for fuel injection are located in the critical part of the converging chambers 21 of the distributing stator 22. As the fuel mixture is formed directly at the input of the combustion chamber 11, and the fuel and the air are in the same aggregative state, efficiently blended fuel enters the combustion chamber 11. With the fuel injection directly in the air stream 383
  • the completed fuel mixture enters the combustion chamber 11 through the injection windows 26.
  • pressure in the combustion chambers 11 increases, constantly obtainable gas volume (of gaseous combustion products) under the pressure existing in the combustion chambers 11 is directed into the intake intake part of converging nozzles 24.
  • rectangular (flattened) gas jet with high energy density (elevated velocity and pressure) acts on the vane Ha JionaTKy 18 of the stator 19 and loses its energy completely as the jet velocity drops to zero.
  • the number of the support vanes 18 of the stator 19 is equal to the number of rotating combustion chambers 11 and the number of active nozzles 24 in left and right rows (stages) of the active rotor 2.
  • the combustion chambers 11 with the nozzles 24 in each stage (row) are shifted relatively another by a half of the central angle between the nozzles 24 in them same stage the gas jets in directions 27,28 with the active rotor 2 rotation alternately acts on their respective support vane 18 of the stator 19 without deformation and power pulse repetition per revolution doubles.
  • a smoothed shifted characteristic is obtained (the total number of phase of interaction between the jet with blades 18 per one complete revolution of the active rotora 2 rises).
  • the interval between the power contact peaks is reduced with peaks of power contacts.
  • Directions 27,28 of combustion products exhaust from the nozzles 24 in two rows of combustion chambers 11 is determined by the fact that the direction of axis of symmetry of the nozzle 24 is selected from the condition the maximum approach to the tangent surface of the rotor 2 and perpendicular action of the jet on the blades 18 of the support stator 19.
  • combustion products does not transfer mechanical energy to any intermediate element (piston or turbine blades).
  • Energy of the combustion product jet exhausting from the nozzles 24 acts on support planes of the blades 18 inducing rotation of the rotor 2.
  • the blades 18 of the stator 19 have through fuel overheat channels 25 and provide fuel feed to all the mixing chambers 21 of the distributing stator 22 (the number of the nozzles 24 is equal to the number of the vanes 18 of the support stator 18). Rather small amount of the exhaust gases is removed in direction 10 into the windows 30 radially creating no pressure in the secondary zone 29.
  • the active rotor 2 of the gas turbine is cooled efficiently (not shown) of the central part and side surfaces of the chambers 11 , temperature of the chamber 11 outer walls of the active rotor 2 is considerably lower that the temperature of fuel combustion.
  • the bearings 7 do not contact with the high temperature zone and operates under the ideal conditions.
  • the pressure in the zone 29 is equal to atmospheric pressure
  • the pressure in the combustion chamber 11 is that serial air pressiruzation a can provide (many times higher than atmospheric pressure) providing large pressure difference at inlet and outlet with account of the minimum air consumption and expenditure and, as a consequence, corresponding lower minimum fuel consumption.
  • serial air pressiruzation a can provide (many times higher than atmospheric pressure) providing large pressure difference at inlet and outlet with account of the minimum air consumption and expenditure and, as a consequence, corresponding lower minimum fuel consumption.
  • the number of the support vanes 18 of the support stator 19 is 32.
  • the total number of interaction per one revolution is 1024; with the length of involute of the outer diameter of the rotora of 942 mm, pulse density and repetition rate can be easily calculated.
  • Operating temperature in the combustion chamber 11 does not exceed 450 degrees at the temperature of the fuel mixture combustion from 735C 0 . 13.
  • the bearing 7 work under ideal conditions and do not contact with the high temperature zone.
  • Angle of the focusing part of the nozzle 24 - from 3°30'.
  • the claimed gas turbine engines of the new design surpass all the available modern gas turbine engines in all parameters.
  • the gas turbine engine can be used in aviation as the engine has the relation power/weight many times better; higher power with the minimum fuel consumption per the unit power; lower power consumption and lower release of exhaust gases. With considerably better cooling of strength elements, the engine reliability is many times higher; operational lifetime also increases.
  • the engine can be used in road transport (under conditions of high dust concentration), and on the thermal power plants, waterborne transport and other fields of national economy.
  • the present invention is implemented using the universal modern equipment available in the industry. All parts forming the structure of turbine are bodies of revolution; all the components of required length and diameter are made of the relevant modern steels can be manufactured on modern equipment.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention porte sur un moteur à turbine à gaz ayant une alimentation en air à deux voies, laquelle turbine comprend un arbre 1, un rotor actif 2 de la turbine à gaz sur les deux côtés duquel sont montés des rotors 8, 17 de premier et second compresseurs centrifuges possédant des aubes 3, 6 ; entre ces rotors, un dispositif de guidage intérieur ; des aubes 4 de ce dispositif étant formées dans le carter. Dans le carter 14, sont disposé des paliers et un dispositif de guidage d'entrée, des aubes étant formées dans le carter 14. Le rotor 2 est composé de deux rangées de chambres de combustion 11 ; il est monté sur le stator de distribution 32 comportant des canaux 23 pour l'alimentation en carburant et des chambres de mélange 21 pour l'amenée du mélange de carburant dans des fenêtres d'entrée 26 de chaque chambre 11 qui ont des buses de sortie 24 disposées par paires qui font face aux aubes 18 du stator porteur 19 ; à l'intérieur, des canaux 25 pour la surchauffe du carburant reliés par des canaux 23 servant pour l'amenée du carburant à des brûleurs de carburant 20 contenus dans les chambres de mélange 21 qui sont formées dans le stator de distribution 22 autour des aubes 6. Le moteur à turbine à gaz à air sur une voie comprend un arbre monté sur les paliers 7 dans le carter 9, 14, un rotor 2 de la turbine à gaz ; d'un côté de l'arbre, sont montés des rotors 8, 17 des premier et second compresseurs centrifuges équipés d'aubes 3, 6, un dispositif de guidage intérieur étant interposé entre eux ; des aubes 4 de ce dispositif étant formées dans le carter 9. En partant de l'entrée d'aspiration du premier compresseur, est placé un dispositif de guidage d'entrée, dont les aubes 5 sont formées dans le carter 14. Le rotor 2 est équipé de deux rangées de chambres à combustion 11 et il est monté dans le stator de distribution 22 muni de canaux 23 pour l'amenée du mélange de carburant, et des chambres de mélange 21 pour l'amenée du mélange de carburant dans des fenêtres d'entrée 26 de chaque chambre de mélange 11 qui possède des buses de sorties inclinées 24 qui font face par leur coupure aux aubes 18 du stator porteur 19 dans lequel sont formés des canaux pour la surchauffe du carburant 25, qui sont reliés par des canaux d'amenée du carburant 2 aux brûleurs de carburant 20 dans les chambres de mélange 21 servant pour l'amenée du mélange de carburant dans les fenêtres d'entrée 26 formées dans chaque chambre 11 qui ont des buses de sortie inclinées 24 qui font face par leur coupure aux aubes 18 du stator porteur 19, des canaux 25 pour le réchauffage du carburant étant formés dans le stator de distribution 22 autour des aubes 31 du troisième compresseur. Dans les deux modes de réalisation, on obtient une diminution de la consommation de carburant et une diminution de ses exigences de qualité ; une diminution de la consommation d'air et de lubrifiant ; une diminution des rejets de produits de combustion ; un rendement et une durabilité améliorés ; une grande puissance spécifique et une diminution du coût initial.
PCT/RU2010/000383 2010-07-09 2010-07-09 Moteur à turbine gaz active (variantes) Ceased WO2012005619A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/RU2010/000383 WO2012005619A1 (fr) 2010-07-09 2010-07-09 Moteur à turbine gaz active (variantes)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2010/000383 WO2012005619A1 (fr) 2010-07-09 2010-07-09 Moteur à turbine gaz active (variantes)

Publications (1)

Publication Number Publication Date
WO2012005619A1 true WO2012005619A1 (fr) 2012-01-12

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PCT/RU2010/000383 Ceased WO2012005619A1 (fr) 2010-07-09 2010-07-09 Moteur à turbine gaz active (variantes)

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WO (1) WO2012005619A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012116285A3 (fr) * 2011-02-25 2013-01-31 Board Of Trustees Of Michigan State University Appareil de moteur à disque à ondes
USRE45396E1 (en) 2004-11-12 2015-03-03 Board Of Trustees Of Michigan State University Wave rotor apparatus
GB2526581A (en) * 2014-05-28 2015-12-02 Gabrielle Engine Ltd Combustion engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3811877A1 (de) * 1988-04-09 1989-10-19 Jochen Dipl Ing Wittenbrock Waermekraftmaschine fuer fluessige oder gasfoermige brennstoffe oder daempfe
RU2009350C1 (ru) * 1991-06-14 1994-03-15 Анатолий Гаврилович Серков Способ организации рабочего процесса в газотурбинном двигателе и газотурбинный двигатель
RU2078968C1 (ru) * 1993-06-08 1997-05-10 Юрий Семенович Глуздаков Газотурбинный двигатель глуздакова ю.с.
RU2084666C1 (ru) * 1994-12-30 1997-07-20 Юрий Васильевич Дробышевский Газотурбинный двигатель

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3811877A1 (de) * 1988-04-09 1989-10-19 Jochen Dipl Ing Wittenbrock Waermekraftmaschine fuer fluessige oder gasfoermige brennstoffe oder daempfe
RU2009350C1 (ru) * 1991-06-14 1994-03-15 Анатолий Гаврилович Серков Способ организации рабочего процесса в газотурбинном двигателе и газотурбинный двигатель
RU2078968C1 (ru) * 1993-06-08 1997-05-10 Юрий Семенович Глуздаков Газотурбинный двигатель глуздакова ю.с.
RU2084666C1 (ru) * 1994-12-30 1997-07-20 Юрий Васильевич Дробышевский Газотурбинный двигатель

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE45396E1 (en) 2004-11-12 2015-03-03 Board Of Trustees Of Michigan State University Wave rotor apparatus
WO2012116285A3 (fr) * 2011-02-25 2013-01-31 Board Of Trustees Of Michigan State University Appareil de moteur à disque à ondes
US9856791B2 (en) 2011-02-25 2018-01-02 Board Of Trustees Of Michigan State University Wave disc engine apparatus
GB2526581A (en) * 2014-05-28 2015-12-02 Gabrielle Engine Ltd Combustion engine
WO2015181519A1 (fr) * 2014-05-28 2015-12-03 Gabrielle Engine Limited Moteur à combustion interne
US10385775B2 (en) 2014-05-28 2019-08-20 Gabrielle Engine Limited Combustion engine

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