WO2000039440A1 - Moteur a turbine rotative du type a reaction - Google Patents

Moteur a turbine rotative du type a reaction Download PDF

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Publication number
WO2000039440A1
WO2000039440A1 PCT/IT1999/000424 IT9900424W WO0039440A1 WO 2000039440 A1 WO2000039440 A1 WO 2000039440A1 IT 9900424 W IT9900424 W IT 9900424W WO 0039440 A1 WO0039440 A1 WO 0039440A1
Authority
WO
WIPO (PCT)
Prior art keywords
internal combustion
engine according
impeller
endothermic engine
combustion
Prior art date
Application number
PCT/IT1999/000424
Other languages
English (en)
Inventor
Giovanbattista Greco
Original Assignee
Giovanbattista Greco
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 Giovanbattista Greco filed Critical Giovanbattista Greco
Priority to AU20015/00A priority Critical patent/AU2001500A/en
Publication of WO2000039440A1 publication Critical patent/WO2000039440A1/fr

Links

Classifications

    • 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
    • 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
    • F02K7/005—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 the engine comprising a rotor rotating under the actions of jets issuing from this rotor
    • 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 present invention relates to an internal combustion endothermic engine with reactive propulsion and "circular motion”.
  • the invention relates to an engine of the above kind remarkably simplified.
  • turbo engines developed for terrestrial applications can be classified as high power “low” engines an little power “fast” engines.
  • the first one compete with diesel engines and steam turbines to be employed in fixed plants where, not being fundamental the weight and size reduction, it is possible to obtain a higher thermal efficiency of the cycle, also thanks to the adoption of numerous devices and solutions allowing to make different energy recovery.
  • turbo-propulsors for terrestrial applications is that of the power transmission mode: machines with a single axis or machines with two or more axis. Said solutions, that are well known and therefore will be not described further in the following, always provide a mechanical (shaft) and fluid mechanical (gas + turbine or gas + turbines) connection. Furthermore, turbo-propulsors can be constant pressure or constant volume propulsors.
  • the combustion chamber is provided with intake and discharge valves, or, in some cases, also with the intake valves.
  • Combustion in the first case occurs with a perfectly constant volume, and in the second case with an almost constant volume.
  • Intake valves can be automatic valves, so that they automatically close due to the effect of the fluid expansion, and open again due to the suction effect when gases outflow toward the turbine.
  • This kind of turbines has the feature that with the same temperature of compressed air, they reach maximum temperatures of the combustion cycle remarkably higher and thus with a higher ideal thermal efficiency.
  • a turbojet comprises a diffuser or dynamic drive, a compressor, and a series of combustion chambers, a turbine and an entrance cone, wherein the expansion is completed up to reaching the atmospheric pressure producing the increase of the gases kinetic energy.
  • thermal cycle of fluid is completely similar to the one of the gas turbine plants with adiabatic depression and expansion without recovery.
  • turbojet can be validly employed with good efficiencies with speed ranging between 800 - 1000 Km/h and more than 1500 - 2000 Km/h in the modern military supersonic aeroplanes.
  • an internal combustion endothermic engine comprising an impeller with shaped blades, an impeller rotation axis, an inlet of the fluid between the blades, combustion chambers between said blades, and a fluid shaped outlet.
  • said impeller is comprised of a centrifugal compressor or of an axial compressor.
  • an axial or centripetal turbine can be provided, within which the discharge of said impeller passes.
  • said impeller can be a one or more stage impeller, with the heaters support impeller, or it can be comprised of a centrifugal compressor for the part supporting the heaters, preceded by a one or more stage axial compressor.
  • said compressor can be provided of a speed limiting device to limit the "sonic" effect (particularly on the centrifugal compressor).
  • a one or more stage volumetric compressor before the heaters support impeller that can be a centrifugal or axial impeller.
  • said heaters support impeller can be provided of the possibility of singularly intercepting the same by servo controls.
  • Gas exhaust or air inlet within the impeller can be realised on the peripheral side or on the front and/or rear, inner face.
  • one or more heaters can be provided in said impeller.
  • Said heaters can be realised with an automatic air inlet valve, that is opened by the centrifugal force and is closed by the fluid expansion or inlet or outlet (discharge) closure valve with electromechanical or pneumatic control.
  • said heaters can be realised with air and/or fuel heating before the combustion, with heat exchanger or electric resistances fed by the current generator, or with precombustion chamber ignition with or without heating.
  • said heaters can be realised with direct injection within the flame tube.
  • said heaters can provide the insertion of a device to increase vortexes and thus the air - fuel combustion.
  • said heaters can be provided with air parzializzaée to guarantee the proper stoichiometric ratio, and thus diluting afterwards the mixture.
  • said heaters can be provided, according to the invention, electric or pneumatic operated injectors, with or without fuel pressurisation pump.
  • a glow plug with or without preheating an ignition by auxiliary injector with or without prechamber, an ignition with a downward injector to trigger a post- combustion (rapid instantaneous increase of power), an ignition with electricity feeding from an outer generator (by brush collector on a shaft or inside, by conductors integral with the rotation shaft and thus with the impeller), can be provided. Still according to the invention, it can be provided a by-pass of a part of the heated air, directly on the exhaust collector (ejector) or of a cold autonomous air flow rate fed from another dynamic feed opening.
  • said engine provides the flow of intake and exhaust air in the same direction, or according to a direction radially or axially different with respect to the rotation direction according to the constructive features chosen for convenience and/or in function of the engine application.
  • the engine according to the invention can be started by an auxiliary start engine, or by compressed air, e.g. by and electro blower. This would avoid some mechanical connections and the engine could switch off each time a transmission positive work on the shaft is not necessary, and rapidly switch on again following a control when necessary, thus contributing to the saving of consumption and to the pollution reduction.
  • the engine could continuously be alternated with an electric traction (when in low charge conditions), being it possible to better manage the switching on/ switching off with respect to an explosion engine.
  • a system to control the availability of accumulation of electric energy could limit this kind of alternation to allow the charge.
  • FIG. 1 is a schematic view of a first embodiment of the endothermic engine according to the invention
  • figure 2 is a schematic view of a second embodiment of the endothermic engine according to the invention
  • figure 3 is a schematic section view of the engine according to the invention
  • figure 4 is a second schematic section view of the endothermic engine according to the invention.
  • Impeller 1 has a rotation axis 3, with the inlet of air 4 parallel to the same axis 3 in the embodiment of figure 1, and tangential in the embodiment of figure 2, and a exhaust 5 of burned gases air.
  • a combustion chamber 6 is provided, possibly with an automatic valve 7, ignition sparkplug 8 and fuel injector 9.
  • ignition sparkplug 8 is provided in the peripheral end of the blades 2 .
  • fuel injector 9 By arrow A, the direction of impeller is indicated .
  • optimum operation conditions are created to be able to actuate a turbojet. If, for example, the impeller would be rotated with very high speed, obliging the same to rotate on itself and forcing the same to a rotary motion, and at the same time a continuously changed air flow would be fed (which is not realisable if a deviation of the dynamic fluid path is actuated, that would be naturally created), with the fuel and the electrical energy to ignite the combustion, the speed acquired directly using the propulsive thrust created by reaction can be exploited, to obtain a useful work on the rotation shaft coinciding with the axis 3 about which the same impeller rotates.
  • the two fluids air entering and exhaust gas
  • the two fluids are maintained separated to avoid an unavoidable by-pass of exhaust gases that would be sucked in the intake.
  • ignition can be obtained by surface discharge sparking plugs 8, self-fed by a generator, the rotor portion of which is integral with the impeller and the stator part of which is fixed to the fix structure, thus feeding could occur through the rotation shaft (inside or fixed outside), thus exploiting the same circular motion to produce electrical energy.
  • Start can be actuated by auxiliary starting engine, compressed air (e.g. by an electro blower, that would avoid a mechanical connection) conferring the first rotation to the machine, which is not subjected to particular friction. Inserting the automatic intake and/or exhaust valves in the combustion chamber, it is obtained even with the engine stopped the possibility of creating a propulsive thrust useful for the start or in any case for low rotation regimes (starting frequency variation).
  • compressed air e.g. by an electro blower, that would avoid a mechanical connection
  • combustion chamber provided in the same element where the first or in any case the last compression stage occurs, it is easy to be able to recover main part of the heat to heat both the air flow before combustion (by fins inside the channel before the combustion chamber or by a real heat exchanger), and the same fuel that eventually can pass through the cavities of the impeller always close to the combustion chamber and thus injecting at an already high temperature.
  • an inner electronic panel (always autofed) can be installed, which, dialoguing by a radio transmission system with another fixed outer panel, thus allowing to continuously measure the speed by a proximity sensor to be able to continuously calculate the stoichiometric flow rate of the fuel mixture; continuously measuring the temperature of the compressor stages and eventually automatically actuating a heat exchanger, for cooling between a stage and the other one; continuously measuring the temperature of the combustion chamber and eventual preheating; continuously measuring the exhaust gas temperature; continuously checking the ignition of the electroinjectors and of the sparking plugs in function of the load regime and/or of the desired speed, e.g.
  • blow-by of a part of exhaust gases contributes to the atmospheric pollution reduction, and particularly of the nitrogen oxide.
  • the present invention has been described for illustrative but not limitative purposes, according to its preferred embodiments, but it is to be understood that modifications and/or changes can be introduced by those skilled in the art without departing from the relevant scope as defined in the enclosed claims.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ignition Installations For Internal Combustion Engines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un moteur à turbine rotative du type à réaction, comprenant une roue à ailettes (1) présentant des ailettes profilées (2), un axe de rotation (3) de roue à ailettes, une admission de fluide située entre ces ailettes (4), des chambres de combustion (6) placées entre ces ailettes (4), et enfin une sortie de fluide profilée (5).
PCT/IT1999/000424 1998-12-28 1999-12-27 Moteur a turbine rotative du type a reaction WO2000039440A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU20015/00A AU2001500A (en) 1998-12-28 1999-12-27 Rotary turbine engine of the reaction type

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITRM98A000804 1998-12-28
IT1998RM000804A IT1302949B1 (it) 1998-12-28 1998-12-28 Motore endotermico a combustione interna con propulsione reattiva emoto "circolare".

Publications (1)

Publication Number Publication Date
WO2000039440A1 true WO2000039440A1 (fr) 2000-07-06

Family

ID=11406275

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IT1999/000424 WO2000039440A1 (fr) 1998-12-28 1999-12-27 Moteur a turbine rotative du type a reaction

Country Status (3)

Country Link
AU (1) AU2001500A (fr)
IT (1) IT1302949B1 (fr)
WO (1) WO2000039440A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10033653A1 (de) * 2000-06-16 2002-03-07 Sandor Nagy Kombinationsantrieb
DE10126632A1 (de) * 2000-08-08 2002-09-12 Sandor Nagy Kombinationsantrieb
WO2004076835A1 (fr) * 2003-02-28 2004-09-10 Micro Turbine Technology B.V. Microturbine a reaction a module integre constitue d'une chambre de combustion et d'un rotor
NL1030744C2 (nl) * 2005-12-22 2007-06-25 Micro Turbine Technology B V Reactieturbine.
WO2008140433A2 (fr) * 2007-05-15 2008-11-20 Ahmet Kaan Onay Turbomoteur cyclique à impulsion intégrale
GB2451704A (en) * 2007-08-10 2009-02-11 Keven Chappell Gas turbine engine with compressor formed from a plurality of stacked surfaces
US8333060B2 (en) 2003-02-28 2012-12-18 Micro Turbine Technology B.V. Micro reaction turbine with integrated combustion chamber and rotor

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR934755A (fr) * 1946-10-14 1948-06-01 Moteur thermique à tuyères tournantes
FR999958A (fr) * 1946-02-07 1952-02-06 Perfectionnements aux turbines à réaction
US2670597A (en) * 1946-10-14 1954-03-02 Villemejane Jacques Rotating jet motor with regulation of power output
US3727401A (en) * 1971-03-19 1973-04-17 J Fincher Rotary turbine engine
US4177637A (en) * 1976-12-23 1979-12-11 Rolls-Royce Limited Inlet for annular gas turbine combustor
GB2064666A (en) * 1979-05-29 1981-06-17 Weir Group Ltd Rotary Fluid-flow Machines
US4706452A (en) * 1981-10-22 1987-11-17 Gaston Lavoie Engine
US5185541A (en) * 1991-12-02 1993-02-09 21St Century Power & Light Corporation Gas turbine for converting fuel to electrical and mechanical energy
EP0565373A2 (fr) * 1992-04-10 1993-10-13 Ingersoll-Rand Company Méthode et appareil pour détecter et prévenir le pompage dans un compresseur centrifugal
US5282356A (en) * 1993-01-07 1994-02-01 Abell Irwin R Flywheel engine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR999958A (fr) * 1946-02-07 1952-02-06 Perfectionnements aux turbines à réaction
FR934755A (fr) * 1946-10-14 1948-06-01 Moteur thermique à tuyères tournantes
US2670597A (en) * 1946-10-14 1954-03-02 Villemejane Jacques Rotating jet motor with regulation of power output
US3727401A (en) * 1971-03-19 1973-04-17 J Fincher Rotary turbine engine
US4177637A (en) * 1976-12-23 1979-12-11 Rolls-Royce Limited Inlet for annular gas turbine combustor
GB2064666A (en) * 1979-05-29 1981-06-17 Weir Group Ltd Rotary Fluid-flow Machines
US4706452A (en) * 1981-10-22 1987-11-17 Gaston Lavoie Engine
US5185541A (en) * 1991-12-02 1993-02-09 21St Century Power & Light Corporation Gas turbine for converting fuel to electrical and mechanical energy
EP0565373A2 (fr) * 1992-04-10 1993-10-13 Ingersoll-Rand Company Méthode et appareil pour détecter et prévenir le pompage dans un compresseur centrifugal
US5282356A (en) * 1993-01-07 1994-02-01 Abell Irwin R Flywheel engine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10033653A1 (de) * 2000-06-16 2002-03-07 Sandor Nagy Kombinationsantrieb
DE10126632A1 (de) * 2000-08-08 2002-09-12 Sandor Nagy Kombinationsantrieb
WO2004076835A1 (fr) * 2003-02-28 2004-09-10 Micro Turbine Technology B.V. Microturbine a reaction a module integre constitue d'une chambre de combustion et d'un rotor
EA008268B1 (ru) * 2003-02-28 2007-04-27 Майкро Тербин Текнолоджи Б.В. Микрореактивная турбина с объединёнными камерой сгорания и ротором
US8333060B2 (en) 2003-02-28 2012-12-18 Micro Turbine Technology B.V. Micro reaction turbine with integrated combustion chamber and rotor
NL1030744C2 (nl) * 2005-12-22 2007-06-25 Micro Turbine Technology B V Reactieturbine.
WO2007073185A1 (fr) * 2005-12-22 2007-06-28 Micro Turbine Technology B.V. Dispositif de combustion rotatif
WO2008140433A2 (fr) * 2007-05-15 2008-11-20 Ahmet Kaan Onay Turbomoteur cyclique à impulsion intégrale
WO2008140433A3 (fr) * 2007-05-15 2008-12-31 Ahmet Kaan Onay Turbomoteur cyclique à impulsion intégrale
GB2451704A (en) * 2007-08-10 2009-02-11 Keven Chappell Gas turbine engine with compressor formed from a plurality of stacked surfaces

Also Published As

Publication number Publication date
IT1302949B1 (it) 2000-10-10
ITRM980804A1 (it) 2000-06-28
ITRM980804A0 (it) 1998-12-28
AU2001500A (en) 2000-07-31

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