WO2015069147A1 - Avion et installation de turbine à gaz avec moteur central distinct - Google Patents

Avion et installation de turbine à gaz avec moteur central distinct Download PDF

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Publication number
WO2015069147A1
WO2015069147A1 PCT/RU2014/000839 RU2014000839W WO2015069147A1 WO 2015069147 A1 WO2015069147 A1 WO 2015069147A1 RU 2014000839 W RU2014000839 W RU 2014000839W WO 2015069147 A1 WO2015069147 A1 WO 2015069147A1
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WO
WIPO (PCT)
Prior art keywords
compressor
gas turbine
engine
vortex
root
Prior art date
Application number
PCT/RU2014/000839
Other languages
English (en)
Russian (ru)
Inventor
Владимир Тарасович ШВЕДОВ
Original Assignee
Владимир Тарасович ШВЕДОВ
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Владимир Тарасович ШВЕДОВ filed Critical Владимир Тарасович ШВЕДОВ
Publication of WO2015069147A1 publication Critical patent/WO2015069147A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/16—Composite ram-jet/turbo-jet engines
    • 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 invention relates to mechanics, to engines, and more particularly, to jet engines without gas turbines, and can be used in the design of propulsors for vehicles moving in air, water and other fluids.
  • the invention may find application in aviation, water, and other modes of transport. .
  • Double-circuit jet engines are known in which the thrust is created in two circuits: a gas turbine and a fan (second) circuit. If there is no afterburner in the secondary circuit, the creation of draft in it includes: suction of air from the environment in the input device, its compression by a fan (or compressor), pumping of the second circuit through the air duct, and the implementation of the draft by expanding the flow in the output nozzle. (See A.L. Klyachkin. Theory of jet engines.
  • a fan circuit usually contains an input device (otherwise common with a gas turbine circuit), a compressor (fan), and an exhaust nozzle.
  • the fan circuit also contains one or more crowns of straightening vanes located behind the fan and designed to straighten the flow swirling on the fan.
  • the disadvantage of turbofan engines and, in particular, the fan circuit is the low efficiency (efficiency). So for the fan circuit there are losses of air flow created by the compressor on the turbine, mechanical transmission from the turbine to the fan (including the gearbox), the fan itself, the rectifying device, which leads to efficiency equal to 0.3-0.4. To create great traction, low efficiency is offset by high fuel consumption.
  • Known gas turbine installation with a dedicated root engine contains at least one root gas turbine engine and the movers located separately from it.
  • the root gas turbine engine comprises an external fairing, a compressor, a combustion chamber, and a turbine driving the compressor via a shaft.
  • such a dedicated root engine uses components and parts of known design to ensure its operation.
  • part of the air produced by the compressor is supplied to the combustion chamber and turbine and is used to drive the compressor.
  • Another part of the remaining high-pressure air enters the pipeline to power the propulsors.
  • the installation has at least one mover located separately from the specified root engine and provided with high pressure air from the specified root engine for its operation, and at least one controlled mover for controlling the aircraft, containing an air turbine located separately from the specified root engine and driven high-pressure air from said root engine; and a controlled fan driven by said air turbine.
  • the mover, located separately from the specified root engine has a fan driven by its turbine, operating directly from compressed air taken from the root engine, or may be equipped with an additional own combustion chamber to drive the turbine.
  • Such a gas turbine installation can be used on an aircraft with propulsion devices located on the fuselage, or on a wing, in particular a vertical take-off apparatus, for its vertical take-off or landing.
  • propulsion devices located on the fuselage, or on a wing, in particular a vertical take-off apparatus, for its vertical take-off or landing.
  • a vertical take-off apparatus for its vertical take-off or landing.
  • this embodiment of a turbofan engine with dedicated propulsion units can reduce the noise generated by the installation.
  • the convenience and simplicity of the layout of propulsion systems for aircraft for various purposes is provided.
  • the vortex mover is made in the form of a streamlined hollow nacelle, acting as a body, the inner surface of the nacelle is an air path, consisting of communicating in series located input device, made in the form of a confuser, a diffuser, a vortex chamber and an output device, in addition, the nacelle is equipped with a device for supplying compressed air inside the air path, made in the form of nozzles communicating with a source of compressed air located in front of the nacelle along the entire perimeter of the cross section and directed at an angle to the axis of the air path equal to 10-60 ° so that it swirls the air in it in one direction, creating a vortex.
  • the mover can be used to drive any vehicle unit, or as a pump for pumping fluids. To do this, it is necessary to equip it with a gas generator (for operation in the atmosphere).
  • the objective of the invention is to develop such a design of a gas turbine installation having an increased efficiency.
  • a gas turbine installation should have less weight and a simplified design, and an airplane using it should have a reduced fuel consumption.
  • a gas turbine installation with a dedicated root engine comprising at least one root gas turbine engine, comprising an external fairing, a compressor, a combustion chamber and a turbine driving the compressor, and propulsion devices located separately from the root gas turbine engine, air produced the compressor, is fed into the combustion chamber and the turbine and used to drive the compressor, and the other part of the remaining high-pressure air enters the power supply pipeline of the propulsion devices, contains one or more vortex ejector propulsors made in the form of streamlined nacelles containing a flow path, consisting of an input confuser, a diffuser, a vortex chamber, and an output device, while the nacelle is equipped with an inlet pipe connected to the power supply pipe, and final year at the nozzles communicating with the inlet and disposed in the outlet portion of the diffuser along its circumference at an angle to the axis of the nacelle so that jets issuing from them would create a vortex in the flow path passing through the air stream.
  • a dedicated root engine comprising at least one root
  • each of the propulsors is made with a vortex chamber, the inner surface of which is made in the form of a truncated cone with a large base connected with the outlet cross section of the diffuser, and a smaller base constituting the exhaust hole.
  • the output devices of the propulsors are made in the form of an additional diffuser and are equipped with rectifying devices.
  • propulsion devices are made in the form of vortex ejector propulsors made in the form of streamlined nacelles containing a flow path consisting of an inlet confuser, a diffuser, a vortex chamber and an output device connected in series, while the nacelle is equipped with an inlet pipe connected to the power supply pipe, and exhaust nozzles communicating with the inlet pipe and located in the outlet part of the diffuser along its circumference at an angle to the axis of the nacelle such so that the jets emerging from them would create a vortex in the air flow passing through the propulsion duct;
  • the supply pipeline is made in the form of a common main pipeline connected with the inlet nozzles of the vortex ejector engines and with the annular samplers of each of the engines using nozzles equipped with check valves to prevent the supply of compressed air to the failed engine;
  • dedicated root engines are mounted on pylons under the wing, and eddy ejector propulsors are installed on the upper surface of the wing
  • FIG.1 - shows a diagram of a gas turbine installation, made in accordance with the invention and using two vortex propulsors, in longitudinal section along the axes of the engine and propulsors;
  • FIG. 2 - shows a vortex ejector propulsion in longitudinal section along the axis of symmetry
  • FIG. 3 - shows the general view of the aircraft (in plan) using gas turbine units with a dedicated root engine
  • FIG. 4 shows a section A-A of FIG. 3.
  • the invention is implemented as follows.
  • a gas turbine installation with a dedicated root engine contains at least one root gas turbine engine 1 and movers 9 and 10 located separately from it (see Figure 1).
  • the root gas turbine engine 1 contains an external cowling 3, a compressor 2, a combustion chamber 6 and a turbine 7 driving the compressor 2 by means of a shaft 4.
  • the root gas turbine engine is made according to the known construction of a gas turbine engine of the first circuit of a double-circuit gas turbine engine (DTRD), except that there is no second circuit in it (fan, casing, rectifier, gearbox, mechanical transmission that connects the turbine to the fan).
  • DTRD double-circuit gas turbine engine
  • the output of the compressor 2 is connected to the turbine 7 and is made with an annular sampler 5 for taking air for propulsors so that part of the air produced by the compressor is supplied to the combustion chamber, the turbine and used to drive the compressor, and the other part of the remaining high pressure air enters the power supply pipe 8 of the propulsion devices,
  • the root gas turbine engine is equipped with units and equipment of known designs necessary for its effective functioning.
  • a gas turbine installation contains one or more vortex ejector propulsors that play the role of a second DTRD circuit.
  • Vortex ejector propulsors are made (see Fig. 2) in the form of streamlined nacelles 1 1. containing a flow path 20, consisting of an inlet confuser 13 connected in series with each other, the diffuser 14, the vortex chamber 15 and the output device 16.
  • the nacelle is equipped with an inlet pipe 17 connected to the supply pipe 8, and exhaust nozzles 19.
  • the exhaust nozzles are made communicating with the inlet pipe 17 and located in the outlet of the diffuser around its circumference at an angle 22 to the axis of the nacelle so that the jets leaving them create a vortex 21 in the air flow passing through the flow path.
  • the connection of the nozzles 19 with the outlet pipe can be performed using the discharge chamber 18, made in the Hondola annular around the flow path.
  • each of the propulsors was made with a vortex chamber, the inner surface of which is conical, in the form of a truncated cone, with a large base associated with the outlet cross section of the diffuser and a smaller base constituting the exhaust opening.
  • the taper angle is 6-12 °.
  • each of the propulsors can be made with a vortex chamber, the inner surface of which is made in the form of a truncated cone with a large base connected with the outlet cross section of the diffuser, and a smaller base connected with the output device made in the form of an additional diffuser.
  • the output devices of the propulsors can be equipped with rectifying devices made of known designs, for example in the form of guide radial blades.
  • the design of the vortex ejector propulsion can be made of various known solutions.
  • the mover can be made comprising a housing, including a discharge chamber with insertion nozzles, a front part with an input device and a tail part with a vortex chamber and an output device mounted on shelves made in front and rear of the housing.
  • the body can be made of metal from aluminum or magnesium casting, and the front and rear parts can be made of composite materials.
  • part of the air produced by the compressor 2 is supplied to the combustion chamber 6, where it is mixed with the combustion products and enters the turbine 7, bringing it into action.
  • the turbine is used to drive a compressor that produces the required amount of compressed air.
  • High-pressure air entering the discharge chamber 18 is discharged in the form of high-energy jets through the nozzles 19 into the flow path 20 at an angle of 22 to the axis nacelles so that the jets leaving them create a vortex 21 in the passing air stream 23.
  • the vortex 21 created in the air stream 23 acts on it, turning the stream into a vortex, which in turn creates a rarefaction at the entrance to the mover, contributing to an increase in air flow through the mover.
  • the accelerated air flow together with the ejection air from the nozzles creates increased draft and power due to environmental energy. Aircraft using gas turbine units with a dedicated root engine.
  • Aircraft 30 (see Fig. 3) includes a fuselage 33, half wings 31 and 32, tail unit 35 with vertical and horizontal surfaces.
  • the aircraft also contains a marching power plant consisting of left 37 and right 38 dedicated root engines mounted on pylons under the wing.
  • each root gas turbine engine is made according to the known design of the gas turbine engine of the first circuit of a double-circuit gas turbine engine (DTRD), except that there is no second circuit in it (fan, casing, rectifier, gearbox, mechanical transmission that connects the turbine to the fan).
  • DTRD double-circuit gas turbine engine
  • the root gas turbine engine is equipped with units and equipment of known designs necessary for its effective functioning.
  • each engine is made with an annular sampler 49 ( Figure 4) for air extraction for propulsors so that part of the air produced by the compressor is supplied to the combustion chamber, turbine and used to drive the compressor, and the other part of the remaining air is high pressure enters the pipeline 43 installed in the front compartment of the wing floor and center section for. power propulsion devices.
  • the annular sampler of each engine is connected to a pipe 45 (46 for the right engine) installed in the pylon, the other end connected to the pipe 43.
  • a pipe 45 46 for the right engine installed in the pylon, the other end connected to the pipe 43.
  • Each of the pipes 45, 46 is equipped with a check valve (not shown in the diagram) to prevent compressed air from flowing into the failed engine. From the pipeline 43 compressed air enters the discharge chamber 51 of each propulsion device connected by its inlet pipe to the pipeline using an adapter.
  • This embodiment of power plants allows you to increase the flight safety of the aircraft in connection with less damage to the engines, reduce the height of the landing gear.
  • Root isolated gas turbine engines are installed in a known manner inside the fuselage (in particular in its rear part), providing air flow to them using air intakes, and vortex ejector engines are located on its surface, or on pylons or special surfaces, plumage. At the same time, all structural units, communications remain the same. Otherwise, the aircraft is equipped with well-known systems and equipment that ensure its functioning.
  • the accelerated air flow from the propulsors creates increased circulation on the wing, which leads to an increase in the load-bearing properties of the wing.
  • the air flow from the propulsors is a vortex, this contributes to an increase in this effect.
  • the direction of rotation of the air stream (jets) from two movers located on the same wing is multidirectional (which is determined by the design of the mover, namely, the direction of deviation of the axes of the nozzles, creating a clockwise or counterclockwise rotation) ..
  • the direction of rotation creating a direction of influence of the vortices (jets) on top of each other, sticking of the jets to the wing surface and increase in traction will be prevented.
  • the jets will contribute to adhesion to the wing surface and create an increased lifting force of the wing.
  • a gas turbine plant with a dedicated root engine and an airplane using such a plant as vortex ejector engines do not require new unknown technologies for their production and can be produced using existing ones.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une installation de turbine à gaz avec moteur central distinct comprenant une carène externe, un compresseur, une chambre de combustion et une turbine, ainsi que des dispositifs de propulsion distincts du moteur de type turbine à gaz central. Une partie de l'air généré par le compresseur est envoyée vers la chambre de combustion et la turbine et est utilisée pour actionner le compresseur, tandis que l'autre partie de l'air restant à haute pression est envoyée dans un conduit d'alimentation des dispositifs de propulsion. L'invention se caractérise en ce qu'elle comprend des dispositifs de propulsion à éjecteurs à tourbillon qui se présentent sous forme de nacelles carénées comportant un trajet d'écoulement comprenant un concentrateur d'entrée, un diffuseur, une chambre à tourbillon et un dispositif de sortie connectés entre eux séquentiellement. La nacelle comprend un conduit d'entrée connecté à un conduit d'alimentation, et des buses de sortie communiquant avec le conduit d'entrée et disposées dans la partie de sortie du diffuseur sur sa périphérie à un certain angle par rapport à l'axe de la nacelle de sorte que les flux qui en sortent créent un tourbillon dans le flux d'air passant dans le trajet d'écoulement du propulseur. On parvient à obtenir un rendement plus élevé, une masse inférieure et une structure plus simple de l'installation, et l'avion consomme moins de carburant.
PCT/RU2014/000839 2013-11-07 2014-11-06 Avion et installation de turbine à gaz avec moteur central distinct WO2015069147A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2013149503/06A RU2567914C2 (ru) 2013-11-07 2013-11-07 Самолёт с газотурбинной силовой установкой, содержащей вихревые эжекторные движители
RU2013149503 2013-11-07

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WO2015069147A1 true WO2015069147A1 (fr) 2015-05-14

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3041992A1 (fr) * 2015-10-05 2017-04-07 Snecma Aeronef avec un moyen de propulsion a soufflante deportee

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4732324A (en) * 1984-12-19 1988-03-22 Rolls-Royce Inc. Variable flow area nozzle
EP1331378A2 (fr) * 2002-01-16 2003-07-30 National Aerospace Laboratory of Japan Moteur à réaction avec soufflante séparée
RU2413859C2 (ru) * 2006-12-18 2011-03-10 Аэроджет-Дженерал Корпорейшн Объединенная система камеры сгорания и сопла с комбинированным циклом
RU2465481C2 (ru) * 2010-12-06 2012-10-27 Владимир Тарасович Шведов Вихревой движитель

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4732324A (en) * 1984-12-19 1988-03-22 Rolls-Royce Inc. Variable flow area nozzle
EP1331378A2 (fr) * 2002-01-16 2003-07-30 National Aerospace Laboratory of Japan Moteur à réaction avec soufflante séparée
RU2413859C2 (ru) * 2006-12-18 2011-03-10 Аэроджет-Дженерал Корпорейшн Объединенная система камеры сгорания и сопла с комбинированным циклом
RU2465481C2 (ru) * 2010-12-06 2012-10-27 Владимир Тарасович Шведов Вихревой движитель

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3041992A1 (fr) * 2015-10-05 2017-04-07 Snecma Aeronef avec un moyen de propulsion a soufflante deportee
FR3041991A1 (fr) * 2015-10-05 2017-04-07 Snecma Aeronef avec un moyen de propulsion a soufflante deportee
US10850859B2 (en) 2015-10-05 2020-12-01 Safran Aircraft Engines Aircraft with a propulsion unit with offset fan

Also Published As

Publication number Publication date
RU2567914C2 (ru) 2015-11-10
RU2013149503A (ru) 2015-05-20

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