FR2910056A1 - Rotary wing-less vertical take-off and landing vehicle for transporting passengers by air, has rear wing whose variable incidence is set to generate lift force in take-off mode, and added to forces developed on front wings in cruise mode - Google Patents

Rotary wing-less vertical take-off and landing vehicle for transporting passengers by air, has rear wing whose variable incidence is set to generate lift force in take-off mode, and added to forces developed on front wings in cruise mode Download PDF

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Publication number
FR2910056A1
FR2910056A1 FR0611002A FR0611002A FR2910056A1 FR 2910056 A1 FR2910056 A1 FR 2910056A1 FR 0611002 A FR0611002 A FR 0611002A FR 0611002 A FR0611002 A FR 0611002A FR 2910056 A1 FR2910056 A1 FR 2910056A1
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France
Prior art keywords
air
mode
take
compressor
added
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.)
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Application number
FR0611002A
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French (fr)
Inventor
Michel Aguilar
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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 FR0611002A priority Critical patent/FR2910056A1/en
Priority to AT07823490T priority patent/ATE481318T1/en
Priority to PCT/FR2007/001452 priority patent/WO2008037865A1/en
Priority to DE602007009270T priority patent/DE602007009270D1/en
Priority to JP2009529729A priority patent/JP2010504249A/en
Priority to EP07823490A priority patent/EP2066564B1/en
Priority to CA002664424A priority patent/CA2664424A1/en
Priority to US12/442,778 priority patent/US20100006695A1/en
Publication of FR2910056A1 publication Critical patent/FR2910056A1/en
Withdrawn legal-status Critical Current

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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
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/055—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor being of the positive-displacement type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • 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
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/90—Application in vehicles adapted for vertical or short take off and landing (v/stol vehicles)

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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

The vehicle has a positive-displacement rotary compressor (5) supplying compressed air to a tank (6) that is connected to combustion chambers. Exhaust gases from one of the chambers actuate a compressor-driving turbine and are discharged onto an upper surface of a fixed rear wing. Exhaust gases from the other chamber are discharged directly onto an upper surface of a rear wing (8). A variable incidence of the wing (8) is set to generate a lift force in take-off mode, and is added to forces developed on front wings in cruise mode.

Description

1 La présente invention concerne une turbomachine à compresseur volumiqueThe present invention relates to a turbomachine with a supercharger

rotatif avec au moins une chambre de combustion ouverte sur une turbine, et au moins une autre chambre de combustion directement ouverte sur une tuyère d'éjection des gaz brûlés. A ce jour les turbomachines qui créent une force propulsive se répartissent de la façon suivante : 1 û Le turboréacteurs prélèvent une masse d'air dans l'atmosphère, la comprime à l'aide d'un compresseur centrifuge ou axial, la mélange à un carburant (kérosène), la brûle dans une chambre dite de combustion, puis oriente ces gaz brûlés vers une turbine reliée au compresseur rendant ainsi autonome la turbomachine. Ces gaz brûlés sont ensuite éjectés à grande vitesse dans l'atmosphère au travers d'une tuyère, produisant ainsi une force propulsive. 2 û le statoréacteur autorise des très grandes vitesses mais nécessite au préalable d'être lancé à une vitesse importante afin que la compression de l'air puisse se faire par simple effet aérodynamique, s'affranchissant ainsi du compresseur mécanique et de sa turbine. 3 û le pulsoréacteur surtout utilisé pendant la dernière guerre par les allemands avec les fameux V1 fonctionnant sur un mode pulsé. La turbomachine selon l'invention cumule les avantages de ces trois modes de propulsion en ce sens qu'au travers d'un compresseur volumique rotatif à palettes (ou autres systèmes), une masse d'air prélevée dans l'atmosphère après avoir subi une compression modérée, remplira un réservoir dit de transit. De ce dernier partent différents conduits alimentant : - une (ou plusieurs) chambre de combustion ouverte sur une turbine dont la fonction est de convertir une partie de l'énergie thermodynamique due à la combustion du mélange air-carburant en énergie mécanique de rotation utilisée pour entraîner en retour le compresseur. La turbomachine est alors rendue autonome. L'énergie calorique restante servant à accélérer les gaz brûlés via une tuyère adaptée produisant ainsi une force propulsive. Le carburant pouvant être le kérosène ou tout autre produit qualifié de renouvelable (huile de tournesol, de colza...). 2910056 2 - une (ou plusieurs) autre chambre de combustion alimentée en air comprimé par le réservoir est directement ouverte sur une tuyère adaptée de 5 sorte à convertir totalement l'énergie calorique fournie par la combustion du mélange air-carburant en énergie cinétique. Les gaz brûlés ainsi éjectés à grande vitesse dans l'atmosphère produise une force propulsive conséquente. Par ailleurs, chaque conduit est équipé d'une valve dont la fonction est de commander et réguler les différents débits d'air de façon à optimiser le débit 10 carburant accordé aux différentes phases de fonctionnement de la turbomachine. Enfin, et pour une certaine application, un conduit relié au réservoir peut être ménagé sur la partie supérieure de l'entrée d'air au travers d'une valve commandée afin de produire selon le besoin un jet d'air à grande vitesse et 15 créer ainsi un mur aérodynamique L'entrée d'air, pourra présenter une géométrie variable adaptée aux différentes phases de fonctionnement.  rotary device with at least one combustion chamber open on a turbine, and at least one other combustion chamber directly open on a flue gas discharge nozzle. To date the turbomachines which create a propulsive force are distributed as follows: 1 - The turbojets take a mass of air into the atmosphere, compress it with the aid of a centrifugal or axial compressor, mix it with a fuel (kerosene), burns in a so-called combustion chamber, then directs these burnt gases to a turbine connected to the compressor thus making the turbomachine autonomous. These burned gases are then ejected at high speed into the atmosphere through a nozzle, thus producing a propulsive force. 2 - the ramjet allows very high speeds but requires prior to be launched at a high speed so that the compression of the air can be done by simple aerodynamic effect, thus avoiding the mechanical compressor and its turbine. 3 - the pulsoréacteur especially used during the last war by the Germans with the famous V1 operating in a pulsed mode. The turbomachine according to the invention combines the advantages of these three modes of propulsion in the sense that through a rotary vane volume compressor (or other systems), a mass of air taken from the atmosphere after having undergone a moderate compression, will fill a so-called transit tank. From the latter depart different ducts supplying: - one (or more) open combustion chamber on a turbine whose function is to convert a portion of the thermodynamic energy due to the combustion of the air-fuel mixture into mechanical energy of rotation used for drive the compressor back. The turbomachine is then made autonomous. The remaining caloric energy used to accelerate the burnt gases via a suitable nozzle thus producing a propulsive force. The fuel can be kerosene or any other renewable product (sunflower oil, rapeseed oil ...). 2 - one (or more) other combustion chamber supplied with compressed air by the tank is directly open on a nozzle adapted to convert completely the caloric energy provided by the combustion of the air-fuel mixture into kinetic energy. The flue gas thus ejected at high speed in the atmosphere produces a consequent propulsive force. Furthermore, each duct is equipped with a valve whose function is to control and regulate the different air flow rates so as to optimize the fuel flow rate given to the different operating phases of the turbomachine. Finally, and for some application, a conduit connected to the tank may be provided on the upper part of the air inlet through a controlled valve to produce a high velocity air jet as required. create an aerodynamic wall The air inlet, may have a variable geometry adapted to different phases of operation.

2910056 3 Les dessins annexés illustrent l'invention : La figure 1 représente en perspective l'agencement de l'entrée d'air (2') 5 du compresseur à palettes (2). Un conduit (9) via une valve de commande (10) du débit d'air relie le réservoir (3) à la chambre de combustion (4) elle-même ouverte sur une turbine (6) dont la fonction est d'entraîner le compresseur (2). Un autre conduit (9) alimente en air la chambre de combustion (5) ouverte quant à elle directement sur une tuyère (8) dont la fonction est d'accélérer les 10 gaz brûlés et produire ainsi une force propulsive conséquente. La figure 2) représente le mécanisme (12) reliant la turbine (6) au compresseur (2) La figure 3 représente le compresseur (2) et son entrée d'air (2') sur la partie supérieur de laquelle est aménagé un conduit (11) relié d'une part au 15 réservoir (3) via une valve de commande (10), et d'autre part directement ouvert sur l'extérieur afin de produire un écoulement d'air (12) agissant comme un mur aérodynamiqueThe accompanying drawings illustrate the invention: Figure 1 shows in perspective the arrangement of the air inlet (2 ') 5 of the vane compressor (2). A duct (9) via a control valve (10) of the air flow connects the reservoir (3) to the combustion chamber (4) itself open on a turbine (6) whose function is to drive the compressor (2). Another duct (9) supplies air to the combustion chamber (5) which in turn is directly open to a nozzle (8) whose function is to accelerate the flue gases and thus produce a substantial propulsive force. FIG. 2) shows the mechanism (12) connecting the turbine (6) to the compressor (2). FIG. 3 shows the compressor (2) and its air intake (2 ') on the upper part of which a duct is arranged. (11) connected on the one hand to the reservoir (3) via a control valve (10), and on the other hand directly open to the outside to produce an air flow (12) acting as an aerodynamic wall

Claims (1)

REVENDICATIONS 5 1) Turbomachine caractérisée en ce qu'une masse d'air prélevée dans l'atmosphère est comprimée par son compresseur volumique rotatif (2) à palettes (ou autres), transite dans un réservoir (3) avant d'alimenter des chambres de combustion (4) et (5) dans lesquelles cette masse d'air est 10 mélangée à un carburant inflammable. L'entrée d'air (2') du compresseur (2) pouvant être à géométrie variable.  1) Turbomachine characterized in that a mass of air taken from the atmosphere is compressed by its rotary vane (2) rotary volume compressor (or other), transits into a tank (3) before feeding chambers of combustion (4) and (5) in which this air mass is mixed with a flammable fuel. The air inlet (2 ') of the compressor (2) can be of variable geometry. 2) Turbomachine selon la revendication 1, caractérisée en ce qu'une de ses chambres de combustion (4) oriente les gaz brûlés vers une turbine (6) dimensionnée pour entraîner le compresseur (2) à l'aide d'un mécanisme (12) 15 approprié de façon à rendre autonome la turbomachine. Cette chambre de combustion (4) produisant par ailleurs une force propulsive.  2) turbomachine according to claim 1, characterized in that one of its combustion chambers (4) directs the burnt gases to a turbine (6) sized to drive the compressor (2) using a mechanism (12). ) Suitable to make the turbomachine autonomous. This combustion chamber (4) also producing a propulsive force. 3) Turbomachine selon l'une des revendications précédentes, caractérisée en ce que une ou plusieurs de ses chambres de combustion (5) oriente les gaz brûlés directement dans une tuyère (8) afin de les éjecter à grande vitesse dans 20 l'atmosphère, produisant alors une force propulsive conséquente.  3) turbomachine according to one of the preceding claims, characterized in that one or more of its combustion chambers (5) directs the burnt gases directly into a nozzle (8) in order to eject them at high speed into the atmosphere, producing then a consequent propulsive force. 4) Turbomachine selon l'une des revendications précédentes, caractérisée en ce que le débit d'air circulant dans les différents conduits (9) reliant le réservoir (3) à l'une quelconque des chambres de combustion (4) ou (5) et suivantes, est régulé par une valve (10). 25  4) turbomachine according to one of the preceding claims, characterized in that the flow of air flowing in the various ducts (9) connecting the reservoir (3) to any of the combustion chambers (4) or (5) and following, is regulated by a valve (10). 25 5) Turbomachine selon l'une des revendications précédentes, caractérisée en ce que l'entrée d'air (2') du compresseur (2) est reliée au réservoir (3) par un conduit (11) produisant un jet d'air (12) régulé par une valve (10), et produisant ainsi un mur aérodynamique  5) A turbomachine according to one of the preceding claims, characterized in that the air inlet (2 ') of the compressor (2) is connected to the reservoir (3) by a duct (11) producing an air jet ( 12) regulated by a valve (10), thereby producing an aerodynamic wall
FR0611002A 2006-09-25 2006-12-18 Rotary wing-less vertical take-off and landing vehicle for transporting passengers by air, has rear wing whose variable incidence is set to generate lift force in take-off mode, and added to forces developed on front wings in cruise mode Withdrawn FR2910056A1 (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
FR0611002A FR2910056A1 (en) 2006-12-18 2006-12-18 Rotary wing-less vertical take-off and landing vehicle for transporting passengers by air, has rear wing whose variable incidence is set to generate lift force in take-off mode, and added to forces developed on front wings in cruise mode
AT07823490T ATE481318T1 (en) 2006-09-25 2007-09-10 VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITHOUT ROTARY WINGS
PCT/FR2007/001452 WO2008037865A1 (en) 2006-09-25 2007-09-10 Vertical take-off and landing vehicle which does not have a rotary wing
DE602007009270T DE602007009270D1 (en) 2006-09-25 2007-09-10 SENKRECHT STARTING AND LANDING AIRPLANE WITHOUT ROTATING WINGS
JP2009529729A JP2010504249A (en) 2006-09-25 2007-09-10 Vertical take-off and landing aircraft without rotor blades
EP07823490A EP2066564B1 (en) 2006-09-25 2007-09-10 Vertical take-off and landing vehicle which does not have a rotary wing
CA002664424A CA2664424A1 (en) 2006-09-25 2007-09-10 Vertical take-off and landing vehicle which does not have a rotary wing
US12/442,778 US20100006695A1 (en) 2006-09-25 2007-09-10 Vertical take-off and landing vehicle which does not have a rotary wing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0611002A FR2910056A1 (en) 2006-12-18 2006-12-18 Rotary wing-less vertical take-off and landing vehicle for transporting passengers by air, has rear wing whose variable incidence is set to generate lift force in take-off mode, and added to forces developed on front wings in cruise mode

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FR2910056A1 true FR2910056A1 (en) 2008-06-20

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FR0611002A Withdrawn FR2910056A1 (en) 2006-09-25 2006-12-18 Rotary wing-less vertical take-off and landing vehicle for transporting passengers by air, has rear wing whose variable incidence is set to generate lift force in take-off mode, and added to forces developed on front wings in cruise mode

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FR (1) FR2910056A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2960259A1 (en) * 2010-05-19 2011-11-25 Eads Europ Aeronautic Defence Turbocharger for use in e.g. turbojet engine of aircraft, has combustion chamber supplied with compressed air by opening that allows introduction of air in chamber, and compressor whose air outlets are opened in inner volume of reservoir
EP2604822A1 (en) 2011-12-16 2013-06-19 José Ramón Martinez Casañ Jet engine with sliding vane compressor

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2696078A (en) * 1952-08-30 1954-12-07 Waitzman Simon Jet propulsion apparatus having a combination ram-jet and turbojet engine
DE1131467B (en) * 1959-04-30 1962-06-14 Daimler Benz Ag Compound engine for propulsion of aircraft
GB1008322A (en) * 1964-08-04 1965-10-27 Rolls Royce Gas turbine engine
US5568724A (en) * 1991-10-15 1996-10-29 Mtu Motoren-Und Turbinen Union Munchen Gmbh Turbofan engine with means to smooth intake air

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2696078A (en) * 1952-08-30 1954-12-07 Waitzman Simon Jet propulsion apparatus having a combination ram-jet and turbojet engine
DE1131467B (en) * 1959-04-30 1962-06-14 Daimler Benz Ag Compound engine for propulsion of aircraft
GB1008322A (en) * 1964-08-04 1965-10-27 Rolls Royce Gas turbine engine
US5568724A (en) * 1991-10-15 1996-10-29 Mtu Motoren-Und Turbinen Union Munchen Gmbh Turbofan engine with means to smooth intake air

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2960259A1 (en) * 2010-05-19 2011-11-25 Eads Europ Aeronautic Defence Turbocharger for use in e.g. turbojet engine of aircraft, has combustion chamber supplied with compressed air by opening that allows introduction of air in chamber, and compressor whose air outlets are opened in inner volume of reservoir
EP2604822A1 (en) 2011-12-16 2013-06-19 José Ramón Martinez Casañ Jet engine with sliding vane compressor

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