WO2010061071A2 - Nacelle integrated on a flying wing - Google Patents

Nacelle integrated on a flying wing Download PDF

Info

Publication number
WO2010061071A2
WO2010061071A2 PCT/FR2009/001305 FR2009001305W WO2010061071A2 WO 2010061071 A2 WO2010061071 A2 WO 2010061071A2 FR 2009001305 W FR2009001305 W FR 2009001305W WO 2010061071 A2 WO2010061071 A2 WO 2010061071A2
Authority
WO
WIPO (PCT)
Prior art keywords
wing
nacelle
flying wing
turbojet engine
flying
Prior art date
Application number
PCT/FR2009/001305
Other languages
French (fr)
Other versions
WO2010061071A3 (en
Inventor
Guy Bernard Vauchel
Original Assignee
Aircelle
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 Aircelle filed Critical Aircelle
Publication of WO2010061071A2 publication Critical patent/WO2010061071A2/en
Publication of WO2010061071A3 publication Critical patent/WO2010061071A3/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/10—All-wing aircraft
    • 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
    • B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/10—All-wing aircraft
    • B64C2039/105—All-wing aircraft of blended wing body type
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/022—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising bird or foreign object protections
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan 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
    • Y02T50/10—Drag reduction

Definitions

  • the invention relates to a nacelle for turbojet engine.
  • the invention also relates to a flying wing and an aircraft comprising such a nacelle.
  • An aircraft with a flying wing is distinguished from conventional aircraft in that it does not have a clear separation between the fuselage and the wing.
  • a flying wing has two wings and a central body mounted in continuity between them.
  • Conventional aircraft comprise, in turn, a substantially cylindrical fuselage on which a wing is reported.
  • Aircraft comprising a flying wing are propelled by one or more propulsion units comprising a turbojet engine housed in a substantially tubular nacelle.
  • a nacelle generally has a structure comprising an air intake structure upstream of the engine, a median structure intended to surround a fan of the turbojet engine, a downstream section intended to surround the combustion chamber of the turbojet engine.
  • downstream is understood here to mean the direction corresponding to the direction of the flow of air, in particular cold air, entering the turbojet engine.
  • upstream refers to the opposite direction.
  • Nacelles are known on the central body of the flying wing. However, such an arrangement of nacelles penalizes the aeronautical performance of the aircraft.
  • a flying wing in which the fan and the motor are arranged in two adjacent channels. The blower and the motor are connected by a transmission means passing through the two channels.
  • An object of the present invention is therefore to provide a nacelle for a flying wing that is simple to implement and does not adversely affect the performance of the aircraft.
  • the subject of the invention is a nacelle for a turbojet comprising an air intake structure capable of channeling an air flow towards a fan of a turbojet, a structure median intended to surround said fan and to which is attached the air inlet structure so as to provide aerodynamic continuity, and a downstream section to which is attached the central structure, characterized in that the input structure of air is able to come in continuity of the walls of a flying wing so that the air intake structure, the median structure and the downstream section are in aerodynamic continuity with the flying wing.
  • the nacelle of the invention is therefore configured to be integrated into the walls of the flying wing so that the latter and the nacelle of the invention have an aerodynamic profile promoting the aeronautical performance of the aircraft.
  • the nacelle of the invention is simple to implement because it is an integral part of the flying wing. It is therefore not necessary to provide structural elements to bring a nacelle to the flying wing.
  • the downstream section comprises thrust reverser means which improves the braking of the aircraft.
  • the nacelle is composed of at least two elements able to pass from an operating configuration in which the two elements are attached together so that the nacelle surrounds the turbojet engine, to a maintenance configuration in which the elements are more attached to each other which simplifies maintenance.
  • the invention relates to a flying wing, characterized in that it comprises at least one nacelle according to the invention each surrounding a turbojet engine.
  • the wing according to the invention comprises one or more of the following optional features considered alone or according to all the possible combinations:
  • At least one nacelle is disposed at the rear of the flying wing which ensures good propulsion of the flying wing;
  • Each turbojet engine is arranged in a channel whose front end opens on the extrados, the intrados or on the lateral sides of the flying wing which allows to capture the air for the operation of the turbojet engine;
  • a grid covers at least partially the front end of the channel opening at the level of the flying wing which makes it possible to protect the turbojet engine;
  • the grid has at least one blade which helps to capture the air;
  • the gate comprises a movable flap disposed rearwardly relative to the end of the channel, which makes it possible to improve the capture of the air; -
  • the nacelle is off-center relative to the median plane of the flying wing which improves the air intake in the channel while maintaining the aerodynamic continuity of the top or bottom of the flying wing.
  • the subject of the invention is an aircraft comprising a flying wing of the invention.
  • FIG. 1 is a view from above of the aircraft of the invention
  • FIG. 2 is a cross-section of the aircraft represented in FIG. 1,
  • FIGS. 3 and 4 are enlargements of the zone A of the nacelle of the invention of FIG.
  • FIGS. 5 and 6 are variants of the embodiment of the nacelle of the invention shown in FIGS. 3 and 4;
  • FIG. 7 is a rear perspective view of the aircraft of the invention;
  • FIG. 8 is a variant of the aircraft of the invention represented in FIG. 2,
  • FIG. 9 is a cross-section of a variant of FIG.
  • the aircraft 1 of the invention comprises a flying wing 3 forming continuously two lateral wings 5 and 7 and a central body 9.
  • the two wings 5 and 7 may comprise at their lateral ends a tail 11 and 13 substantially vertical relative to the plane of the flying wing 3.
  • the empennages 11 and 13 can reduce the drag induced by the lift without increasing the wingspan of the flying wing 3.
  • the flying wing 3 comprises at the front a leading edge 15 defining a volume in which a cockpit can be installed.
  • the "forward" and “rear” directions are defined relative to the direction of the aircraft in flight.
  • the height of the flying wing 3 is determined by the delimitation of a volume sufficient to receive goods and / or passengers. For this purpose, the height may be substantially constant.
  • the flying wing 3 of the invention comprises a lower surface, called "intrados”, and an upper surface 17, called “extrados", which meet in the front part of the flying wing 3 of the invention on the edge. of attack and in the rear part on a trailing edge 19.
  • the flying wing 3 comprises at least one turbojet engine 21 for propelling the aircraft 1 of the invention.
  • three turbojet engines 21 are arranged at the rear of the aircraft 1 of the invention at the level of the central body 9. Such a configuration makes it possible to improve the thrust of the flying wing 3.
  • the number of three turbojets is not limiting and is given here as an example.
  • the turbojet engines 21 may be substantially aligned, as shown in FIG. 1. According to another embodiment, the turbojet engine 21 disposed centrally at the rear of the central body 9 is substantially advanced with respect to the other turbojet engines 21. case of bursting turbine blades of a turbojet engine 21 which can damage at least one of the turbojet engines 21, the ejected portion of said turbojet engine 21 does not impact one of the turbojets 21 adjoining which thus avoids the mission of the aircraft 1 of the invention in danger.
  • the turbojet engine (s) 21 are attached laterally to the structure of the flying wing 3 by any means known to those skilled in the art in order to maintain them within said wing 3.
  • the flying wing 3 comprises at least one nacelle according to the invention to each surround a turbojet 21.
  • the nacelle 23 of the invention typically comprises an air inlet structure 25 capable of channeling an air flow towards a fan 27 of the turbojet engine 21, a median structure 29 intended to surround said fan 27 and to which is attached the air inlet structure 25 so as to provide aerodynamic continuity, and a downstream section 31 to which is attached the central structure 29.
  • the air inlet structure 25 is able to come into continuity with the walls 33 and 34 of the flying wing 3 of the invention so that the entry structure of the air 25, the middle structure 29 and the downstream section 31 are in aerodynamic continuity with the flying wing 3 of the invention.
  • the walls 34 and 33 interface with said middle structure 29 by any means known to those skilled in the art, including structural assembly such as bolting or mobile assembly like knife and groove for ease of maintenance of the motor.
  • the walls 33 and 34 extend behind the aircraft 3 of the invention so as to surround the turbojet engine 21.
  • the walls 33 and 34 incorporate at least one air intake structure 25. of the nacelle of the invention.
  • the air inlet structure 25 comprises an inner panel 26a and an outer panel 26b in continuity and / or integrated with the walls 33 and 34 of the flying wing of the invention.
  • the inner panel 26a is in contact with the air flow to the turbojet 21.
  • the outer panel 26b is in contact with the air flow bypassing the aircraft 1 of the invention.
  • the inner panel 26a makes it possible to properly channel the air towards the blades of the fan 27. To do this, the inner panel 26a is fixed at its downstream end to an upstream end of the fan casing, in particular by means of flanges. fixation. Thus, the inner panel 26a forms with the central structure 29 a fixed structure relative to the nacelle 23 of the invention.
  • the inner panel 26a is made of a carbon composite material, or even aluminum.
  • the inner panel 26a may be made of one piece or of several assembled parts.
  • the inner panel 26a may further comprise an acoustic shroud intended to reduce noise pollution due to the operation of the turbojet engine 21 and the vibrations of the nacelle 23 of the invention.
  • the acoustic ferrule is typically made of a honeycomb structure or any other structure known to those skilled in the art for absorbing acoustic vibrations.
  • the nacelle 23 of the invention may comprise an interface (not shown) for separating the flying wing 3 of the invention and the nacelle 23 of the invention.
  • the nacelle 23 of the invention can thus be attached to the flying wing 3 of the invention by any means known to those skilled in the art, in particular by direct bolting or reported fittings.
  • Such an interface may be made of aluminum, titanium, or even any composite material known to those skilled in the art.
  • the outer panel is attached by any means known to those skilled in the art to the median outer cover of the middle structure 29.
  • the outer panel and the median outer cover can form a single piece in extension of the wall 34 of the flying wing of the invention.
  • the middle structure 29 also includes a motor housing attached to one end of a blower housing for surrounding the fan blades 27, and at another end to the downstream section 31.
  • the motor housing is intended to surround a portion 21.
  • the attachment of said motor housing is carried out by any means known to those skilled in the art.
  • the middle structure 29 may also include a median outer cover for surrounding the blower housing and / or the motor housing.
  • the downstream section 31 comprises thrust reversing means which make it possible to improve the braking of the aircraft 1 of the invention.
  • the thrust means reverse the direction of the flow of air flowing in the nacelle 23 of the invention.
  • the thrust means may be of any type known to those skilled in the art, in particular pushing means with doors 41 or with grids 43 (see respectively FIGS. 3 and 4 as well as FIGS. 5 and 6). It should be noted that all nacelles installed on the wing may not all incorporate a means of inversion.
  • the nacelle 23 according to the invention may preferably be composed of at least two elements 51a and 51b able to pass from an operating configuration in which the two elements 51a and 51b are attached. between them so that the nacelle 23 of the invention surrounds the turbojet 21 to a maintenance configuration in which the elements 51a and 51b are no longer attached to each other.
  • the two elements 51a and 51b are in the maintenance position, they form a passage through which the turbojet 21 can be unhooked from the nacelle.
  • Such a configuration of the nacelle 23 of the invention simplifies maintenance. As shown in FIG.
  • the nacelle 23 of the invention can be composed of at least two elements 51a and 51b articulated on the side walls of said nacelle 23 of the invention and / or the flying wing. 3 of the invention.
  • the two elements 51a and 51b can have a shape half shell.
  • the two elements 51a and 51b are in particular configured to open on the upper surface 17 or on the underside of the flying wing 3 of the invention.
  • the two elements 51a and 51b may be symmetrical or not. It is also possible that only one of the elements is articulated on one side or the other of the structure of the flying wing 3.
  • the walls 33 and 34 define a channel 61 into which outside air enters to operate the fan 27 of the turbojet engine.
  • the air naturally enters the channel 61 through the scooping angle.
  • the angle of ecopage corresponds to the angle between the section of the channel comprising the turbojet engine 21 and the part that opens onto the intrados, the extrados 17 or on the lateral sides of the flying wing 3.
  • the channel 61 opens on the extrados 17 or on the lateral sides 62. More generally, when the turbojet 21 is positioned substantially centrally at the rear of the flying wing 3, the channel 61 opens typically substantially in the middle of the flying wing 3 on the lower surface or on the extrados 17. In the rear lateral position, the channel 61 can lead to the lateral edges of the flying wing 3.
  • a gate 71 may cover the front end 63 of the channel 61 at least partially, in particular the entirety, while opening on the extrados 17, the intrados or on the lateral sides of the channel. the flying wing 3 of the invention.
  • the gate 71 may optionally be placed inside the channel 61.
  • the gate 71 advantageously protects the turbojet 21 of any projectile that can enter the channel, such as a bird.
  • the gate 71 may be of any type known to those skilled in the art.
  • the grid 71 may comprise at least one blade to assist in capturing the air.
  • the flying wing 3 of the invention may comprise a movable flap 75 disposed at the rear of the end 63 of the channel to improve the capture of air.
  • the movable flap 75 can be controlled by an automated system, in particular by the pilot in the cockpit.
  • the automated system can be used at any time during flight or take-off when the incidence of the flying wing profile 3 may degrade the natural capture of the air according to the needs of the turbojet 21.
  • the nacelle 23 is off-center with respect to the median plane 81 of the flying wing, which makes it possible to improve the capture of the air in the channel 61 while preserving the aerodynamic continuity. from the top or bottom of the flying wing 3.
  • the median plane 81 corresponds to the plane passing through the leading edge 15 and the rear 19 of the flying wing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a nacelle (23) for a turbojet engine (21), comprising an air intake structure (25) capable of directing an air flow towards a fan (27) of a turbojet engine (21), a middle structure (29) for surrounding said fan (27) and to which the air intake structure (25) is secured so as to provide aerodynamic continuity, and a downstream section (31) to which the middle structure (29) is attached, characterised in that the air intake structure (25) is adapted so as to define a continuous extension of the walls (33; 34) of a flying wing (3) so that the air intake structure (25), the middle structure (29), and the downstream structure (31) are in aerodynamic continuity with the flying wing (3). The invention also relates to a flying wing (3) and to an aircraft (1) comprising such a nacelle.

Description

Nacelle intégrée sur aile volante Integrated nacelle on flying wing
L'invention concerne une nacelle pour turboréacteur. L'invention concerne également une aile volante et un aéronef comportant une telle nacelle.The invention relates to a nacelle for turbojet engine. The invention also relates to a flying wing and an aircraft comprising such a nacelle.
Un aéronef comportant une aile volante se distingue des aéronefs conventionnels en ce qu'il ne présente pas de séparation nette entre le fuselage et l'aile. Ainsi, une aile volante comporte deux ailes et un corps central monté en continuité entre ces dernières. Les aéronefs conventionnels comportent, quant à eux, un fuselage sensiblement cylindrique sur lequel une aile est rapportée.An aircraft with a flying wing is distinguished from conventional aircraft in that it does not have a clear separation between the fuselage and the wing. Thus, a flying wing has two wings and a central body mounted in continuity between them. Conventional aircraft comprise, in turn, a substantially cylindrical fuselage on which a wing is reported.
Les aéronefs comportant une aile volante sont propulsés par un ou plusieurs ensembles propulsifs comprenant un turboréacteur logeant dans une nacelle de forme sensiblement tubulaire. Une nacelle présente généralement une structure comprenant une structure d'entrée d'air en amont du moteur, une structure médiane destinée à entourer une soufflante du turboréacteur, une section aval destinée à entourer la chambre de combustion du turboréacteur.Aircraft comprising a flying wing are propelled by one or more propulsion units comprising a turbojet engine housed in a substantially tubular nacelle. A nacelle generally has a structure comprising an air intake structure upstream of the engine, a median structure intended to surround a fan of the turbojet engine, a downstream section intended to surround the combustion chamber of the turbojet engine.
On entend ici par le terme « aval » la direction correspondant au sens du flux d'air, notamment d'air froid, pénétrant dans le turboréacteur. Le terme « amont » désigne la direction opposée.The term "downstream" is understood here to mean the direction corresponding to the direction of the flow of air, in particular cold air, entering the turbojet engine. The term "upstream" refers to the opposite direction.
Il est connu des nacelles disposées sur le corps central de l'aile volante. Cependant, une telle disposition de nacelles pénalise la performance aéronautique de l'aéronef. Dans la demande US2008/0121756, on propose une aile volante dans laquelle la soufflante et le moteur sont disposés dans deux canaux adjacents. La soufflante et le moteur sont reliés par un moyen de transmission traversant les deux canaux.Nacelles are known on the central body of the flying wing. However, such an arrangement of nacelles penalizes the aeronautical performance of the aircraft. In the application US2008 / 0121756, there is provided a flying wing in which the fan and the motor are arranged in two adjacent channels. The blower and the motor are connected by a transmission means passing through the two channels.
Cependant, une telle disposition est complexe à réaliser et pénalise la performance aéronautique de l'aéronef.However, such an arrangement is complex to achieve and penalizes the aeronautical performance of the aircraft.
Un but de la présente invention est donc de fournir une nacelle pour une aile volante simple à mettre en œuvre et ne pénalisant pas les performances de l'aéronef.An object of the present invention is therefore to provide a nacelle for a flying wing that is simple to implement and does not adversely affect the performance of the aircraft.
A cet effet, selon un premier aspect, l'invention a pour objet une nacelle pour turboréacteur comportant une structure d'entrée d'air apte à canaliser un flux d'air vers une soufflante d'un turboréacteur, une structure médiane destinée à entourer ladite soufflante et à laquelle est rattachée la structure d'entrée d'air de manière à assurer une continuité aérodynamique, et une section aval à laquelle est rattachée la structure médiane, caractérisé en ce que la structure d'entrée d'air est apte à venir en continuité des parois d'une aile volante de telle sorte que la structure d'entrée d'air, la structure médiane et la section aval sont en continuité aérodynamique avec l'aile volante.For this purpose, according to a first aspect, the subject of the invention is a nacelle for a turbojet comprising an air intake structure capable of channeling an air flow towards a fan of a turbojet, a structure median intended to surround said fan and to which is attached the air inlet structure so as to provide aerodynamic continuity, and a downstream section to which is attached the central structure, characterized in that the input structure of air is able to come in continuity of the walls of a flying wing so that the air intake structure, the median structure and the downstream section are in aerodynamic continuity with the flying wing.
La nacelle de l'invention est donc configurée pour être intégrée dans les parois de l'aile volante pour que cette dernière et la nacelle de l'invention présentent un profil aérodynamique favorisant les performances aéronautiques de l'aéronef.The nacelle of the invention is therefore configured to be integrated into the walls of the flying wing so that the latter and the nacelle of the invention have an aerodynamic profile promoting the aeronautical performance of the aircraft.
En outre, la nacelle de l'invention est simple à mettre en œuvre car celle-ci fait partie intégrante de l'aile volante. Il n'est donc pas nécessaire de prévoir des éléments structuraux permettant de rapporter une nacelle à l'aile volante. De préférence, la section aval comporte des moyens d'inversion de poussée ce qui permet d'améliorer le freinage de l'aéronef.In addition, the nacelle of the invention is simple to implement because it is an integral part of the flying wing. It is therefore not necessary to provide structural elements to bring a nacelle to the flying wing. Preferably, the downstream section comprises thrust reverser means which improves the braking of the aircraft.
De préférence, la nacelle est composée d'au moins deux éléments aptes à passer d'une configuration de fonctionnement dans laquelle les deux éléments sont attachés entre eux de sorte que la nacelle entoure le turboréacteur, à une configuration de maintenance dans laquelle les éléments ne sont plus attachés entre eux ce qui permet de simplifier la maintenance.Preferably, the nacelle is composed of at least two elements able to pass from an operating configuration in which the two elements are attached together so that the nacelle surrounds the turbojet engine, to a maintenance configuration in which the elements are more attached to each other which simplifies maintenance.
Selon un deuxième aspect, l'invention a pour objet une aile volante, caractérisée en ce qu'elle comporte au moins une nacelle selon l'invention entourant chacune un turboréacteur. Selon d'autres caractéristiques de l'invention, l'aile selon l'invention comporte l'une ou plusieurs des caractéristiques optionnelles suivantes considérées seules ou selon toutes les combinaisons possibles:According to a second aspect, the invention relates to a flying wing, characterized in that it comprises at least one nacelle according to the invention each surrounding a turbojet engine. According to other features of the invention, the wing according to the invention comprises one or more of the following optional features considered alone or according to all the possible combinations:
- Au moins une nacelle est disposée à l'arrière de l'aile volante ce qui assure une bonne propulsion de l'aile volante ; - chaque turboréacteur est disposé dans un canal dont l'extrémité avant débouche sur l'extrados, l'intrados ou sur les côtés latéraux de l'aile volante ce qui permet de capter l'air pour le fonctionnement du turboréacteur ;- At least one nacelle is disposed at the rear of the flying wing which ensures good propulsion of the flying wing; - Each turbojet engine is arranged in a channel whose front end opens on the extrados, the intrados or on the lateral sides of the flying wing which allows to capture the air for the operation of the turbojet engine;
- une grille couvre au moins partiellement l'extrémité avant du canal débouchant au niveau de l'aile volante ce qui permet de protéger le turboréacteur ; - la grille comporte au moins une aube ce qui permet d'aider à la captation de l'air ;a grid covers at least partially the front end of the channel opening at the level of the flying wing which makes it possible to protect the turbojet engine; - The grid has at least one blade which helps to capture the air;
- la grille comporte un volet mobile disposé à l'arrière relativement à l'extrémité du canal ce qui permet d'améliorer la captation de l'air ; - la nacelle est décentrée par rapport au plan médian de l'aile volante ce qui permet d'améliorer la captation de l'air dans le canal tout en préservant la continuité aérodynamique du dessus ou du dessous de l'aile volante.the gate comprises a movable flap disposed rearwardly relative to the end of the channel, which makes it possible to improve the capture of the air; - The nacelle is off-center relative to the median plane of the flying wing which improves the air intake in the channel while maintaining the aerodynamic continuity of the top or bottom of the flying wing.
Selon un troisième aspect, l'invention a pour objet un aéronef comportant une aile volante de l'invention.According to a third aspect, the subject of the invention is an aircraft comprising a flying wing of the invention.
L'invention sera davantage comprise à la lecture de la description non limitative qui va suivre, faite en référence aux figures ci-annexées.The invention will be better understood on reading the nonlimiting description which follows, with reference to the appended figures.
- La figure 1 est une vue du dessus de l'aéronef de l'invention,FIG. 1 is a view from above of the aircraft of the invention,
- La figure 2 est une coupe transversale de l'aéronef représenté à la figure 1 ,FIG. 2 is a cross-section of the aircraft represented in FIG. 1,
- Les figures 3 et 4 sont des agrandissements de la zone A de la nacelle de l'invention de la figure 2,FIGS. 3 and 4 are enlargements of the zone A of the nacelle of the invention of FIG.
- Les figures 5 et 6 sont des variantes du mode de réalisation de la nacelle de l'invention représentée aux figures 3 et 4, - La figure 7 est une vue en perspective arrière de l'aéronef de l'invention,FIGS. 5 and 6 are variants of the embodiment of the nacelle of the invention shown in FIGS. 3 and 4; FIG. 7 is a rear perspective view of the aircraft of the invention;
- La figure 8 est une variante de l'aéronef de l'invention représenté à la figure 2,FIG. 8 is a variant of the aircraft of the invention represented in FIG. 2,
- La figure 9 est une coupe transversale d'une variante de la figure 2.FIG. 9 is a cross-section of a variant of FIG.
Comme représenté sur la figure 1, l'aéronef 1 de l'invention comporte une aile volante 3 formant de manière continue deux ailes latérales 5 et 7 et un corps central 9. Les deux ailes 5 et 7 peuvent comprendre à leurs extrémités latérales un empennage 11 et 13 sensiblement vertical par rapport au plan de l'aile volante 3. Lesdits empennages 11 et 13 permettent de réduire la traînée induite par la portance sans augmenter l'envergure de l'aile volante 3.As represented in FIG. 1, the aircraft 1 of the invention comprises a flying wing 3 forming continuously two lateral wings 5 and 7 and a central body 9. The two wings 5 and 7 may comprise at their lateral ends a tail 11 and 13 substantially vertical relative to the plane of the flying wing 3. The empennages 11 and 13 can reduce the drag induced by the lift without increasing the wingspan of the flying wing 3.
L'aile volante 3 comporte à l'avant un bord d'attaque 15 définissant un volume dans lequel une cabine de pilotage peut être installée. Les directions « avant » et « arrière » sont définies relativement au sens de l'aéronef en plein vol. De manière générale, la hauteur de l'aile volante 3 est déterminée par la délimitation d'un volume suffisant pour recevoir des marchandises et/ou des passagers. A cet effet, la hauteur peut être sensiblement constante.The flying wing 3 comprises at the front a leading edge 15 defining a volume in which a cockpit can be installed. The "forward" and "rear" directions are defined relative to the direction of the aircraft in flight. In general, the height of the flying wing 3 is determined by the delimitation of a volume sufficient to receive goods and / or passengers. For this purpose, the height may be substantially constant.
L'aile volante 3 de l'invention comporte une surface inférieure, dite « intrados », et une surface supérieure 17, dite « extrados », qui se rejoignent dans la partie avant de l'aile volante 3 de l'invention sur le bord d'attaque et dans la partie arrière sur un bord de fuite 19.The flying wing 3 of the invention comprises a lower surface, called "intrados", and an upper surface 17, called "extrados", which meet in the front part of the flying wing 3 of the invention on the edge. of attack and in the rear part on a trailing edge 19.
L'aile volante 3 comprend au moins un turboréacteur 21 servant à la propulsion de l'aéronef 1 de l'invention. Selon le mode de réalisation représenté à la figure 1 , trois turboréacteurs 21 sont disposés à l'arrière de l'aéronef 1 de l'invention au niveau du corps central 9. Une telle configuration permet d'améliorer la poussée de l'aile volante 3. Bien évidemment, le nombre de trois turboréacteurs n'est pas limitatif et est donné ici à titre d'exemple.The flying wing 3 comprises at least one turbojet engine 21 for propelling the aircraft 1 of the invention. According to the embodiment shown in FIG. 1, three turbojet engines 21 are arranged at the rear of the aircraft 1 of the invention at the level of the central body 9. Such a configuration makes it possible to improve the thrust of the flying wing 3. Of course, the number of three turbojets is not limiting and is given here as an example.
Les turboréacteurs 21 peuvent être sensiblement alignés, comme représenté à la figure 1. Selon un autre mode de réalisation, le turboréacteur 21 disposé de manière centrale à l'arrière du corps central 9 est sensiblement avancé par rapport aux autres turboréacteurs 21. Ainsi, en cas d'éclatement d'aubes de turbine d'un turboréacteur 21 pouvant endommager au moins un des turboréacteurs 21 mitoyens, la partie éjectée dudit turboréacteur 21 ne vient pas impacter un des turboréacteurs 21 mitoyens ce qui évite, ainsi, de mettre la mission de l'aéronef 1 de l'invention en péril.The turbojet engines 21 may be substantially aligned, as shown in FIG. 1. According to another embodiment, the turbojet engine 21 disposed centrally at the rear of the central body 9 is substantially advanced with respect to the other turbojet engines 21. case of bursting turbine blades of a turbojet engine 21 which can damage at least one of the turbojet engines 21, the ejected portion of said turbojet engine 21 does not impact one of the turbojets 21 adjoining which thus avoids the mission of the aircraft 1 of the invention in danger.
Le ou les turboréacteurs 21 sont attachés latéralement à la structure de l'aile volante 3 par tout moyen connu de l'homme du métier afin de les maintenir au sein de ladite aile 3. Afin de protéger et de couvrir les éléments participant au fonctionnement des turboréacteurs 21 , l'aile volante 3 comporte au moins une nacelle conforme à l'invention pour entourer chacune un turboréacteur 21.The turbojet engine (s) 21 are attached laterally to the structure of the flying wing 3 by any means known to those skilled in the art in order to maintain them within said wing 3. In order to protect and cover the elements involved in the operation of the airfoils 21, the flying wing 3 comprises at least one nacelle according to the invention to each surround a turbojet 21.
Comme représenté à la figure 2, la nacelle 23 de l'invention comporte typiquement une structure d'entrée d'air 25 apte à canaliser un flux d'air vers une soufflante 27 du turboréacteur 21 , une structure médiane 29 destinée à entourer ladite soufflante 27 et à laquelle est rattachée la structure d'entrée d'air 25 de manière à assurer une continuité aérodynamique, et une section aval 31 à laquelle est rattachée la structure médiane 29.As represented in FIG. 2, the nacelle 23 of the invention typically comprises an air inlet structure 25 capable of channeling an air flow towards a fan 27 of the turbojet engine 21, a median structure 29 intended to surround said fan 27 and to which is attached the air inlet structure 25 so as to provide aerodynamic continuity, and a downstream section 31 to which is attached the central structure 29.
Dans la nacelle 23 de l'invention, la structure d'entrée d'air 25 est apte à venir en continuité des parois 33 et 34 de l'aile volante 3 de l'invention de telle sorte que la structure d'entrée d'air 25, la structure médiane 29 et la section aval 31 sont en continuité aérodynamique avec l'aile volante 3 de l'invention.In the nacelle 23 of the invention, the air inlet structure 25 is able to come into continuity with the walls 33 and 34 of the flying wing 3 of the invention so that the entry structure of the air 25, the middle structure 29 and the downstream section 31 are in aerodynamic continuity with the flying wing 3 of the invention.
Pour ce faire, les parois 34 et 33 viennent en interface avec ladite structure médiane 29 par tout moyen connu de l'homme du métier, notamment par assemblage structural comme du boulonnage ou de l'assemblage mobile genre couteau et rainure afin de facilité la maintenance du moteur.To do this, the walls 34 and 33 interface with said middle structure 29 by any means known to those skilled in the art, including structural assembly such as bolting or mobile assembly like knife and groove for ease of maintenance of the motor.
Dans une variante, les parois 33 et 34 se prolongent en arrière de l'aéronef 3 de l'invention de sorte à entourer le turboréacteur 21. Autrement dit, les parois 33 et 34 intègrent au moins une structure d'entrée d'air 25 de la nacelle de l'invention.In a variant, the walls 33 and 34 extend behind the aircraft 3 of the invention so as to surround the turbojet engine 21. In other words, the walls 33 and 34 incorporate at least one air intake structure 25. of the nacelle of the invention.
Dans la nacelle 23 de l'invention, la structure d'entrée d'air 25 comporte un panneau interne 26a et un panneau externe 26b en continuité et/ou intégrés aux parois 33 et 34 de l'aile volante de l'invention. Le panneau interne 26a est en contact avec le flux d'air arrivant au turboréacteur 21. Le panneau externe 26b est en contact ave le flux d'air contournant l'aéronef 1 de l'invention.In the nacelle 23 of the invention, the air inlet structure 25 comprises an inner panel 26a and an outer panel 26b in continuity and / or integrated with the walls 33 and 34 of the flying wing of the invention. The inner panel 26a is in contact with the air flow to the turbojet 21. The outer panel 26b is in contact with the air flow bypassing the aircraft 1 of the invention.
Le panneau interne 26a permet de canaliser convenablement l'air vers les aubes de la soufflante 27. Pour ce faire, le panneau interne 26a est fixé à son extrémité aval à une extrémité amont du carter de soufflante, notamment par l'intermédiaire de brides de fixation. Ainsi, le panneau interne 26a forme avec la structure médiane 29 une structure fixe par rapport à la nacelle 23 de l'invention. Typiquement, le panneau interne 26a est réalisé dans un matériau composite en carbone, voire en aluminium. Le panneau interne 26a peut être constitué d'une seule pièce ou de plusieurs pièces assemblées. Le panneau interne 26a peut en outre comprendre une virole acoustique destinée à atténuer les nuisances sonores dues au fonctionnement du turboréacteur 21 et aux vibrations de la nacelle 23 de l'invention. La virole acoustique est typiquement constituée d'une structure en nid d'abeille ou de toute autre structure connue de l'homme du métier permettant d'absorber les vibrations acoustiques.The inner panel 26a makes it possible to properly channel the air towards the blades of the fan 27. To do this, the inner panel 26a is fixed at its downstream end to an upstream end of the fan casing, in particular by means of flanges. fixation. Thus, the inner panel 26a forms with the central structure 29 a fixed structure relative to the nacelle 23 of the invention. Typically, the inner panel 26a is made of a carbon composite material, or even aluminum. The inner panel 26a may be made of one piece or of several assembled parts. The inner panel 26a may further comprise an acoustic shroud intended to reduce noise pollution due to the operation of the turbojet engine 21 and the vibrations of the nacelle 23 of the invention. The acoustic ferrule is typically made of a honeycomb structure or any other structure known to those skilled in the art for absorbing acoustic vibrations.
La nacelle de 23 de l'invention peut comprendre une interface (non représentée) permettant de séparer l'aile volante 3 de l'invention et la nacelle 23 de l'invention. La nacelle 23 de l'invention peut ainsi être rattachée à l'aile volante 3 de l'invention par tout moyen connu de l'homme du métier, notamment par boulonnage direct ou ferrures rapportées. Une telle interface peut être réalisée en aluminium, en titane, voire en tout matériau composite connu de l'homme du métier.The nacelle 23 of the invention may comprise an interface (not shown) for separating the flying wing 3 of the invention and the nacelle 23 of the invention. The nacelle 23 of the invention can thus be attached to the flying wing 3 of the invention by any means known to those skilled in the art, in particular by direct bolting or reported fittings. Such an interface may be made of aluminum, titanium, or even any composite material known to those skilled in the art.
Le panneau externe est rattaché par tout moyen connu de l'homme du métier au capot externe médian de la structure médiane 29. Selon une variante, le panneau externe et le capot externe médian peuvent former une seule pièce en prolongement de la paroi 34 de l'aile volante de l'invention.The outer panel is attached by any means known to those skilled in the art to the median outer cover of the middle structure 29. According to a variant, the outer panel and the median outer cover can form a single piece in extension of the wall 34 of the flying wing of the invention.
La structure médiane 29 comporte également un carter de moteur rattaché à une extrémité d'un carter de souflante destiné à entourer les pâles de soufflante 27, et à une autre extrémité à la section aval 31. Le carter de moteur est destiné à entourer une partie du turboréacteur 21. Le rattachement dudit carter de moteur est effectué par tout moyen connu de l'homme du métier. La structure médiane 29 peut comporter également un capot externe médian destiné à entourer le carter de souflante et/ou le carter de moteur. De manière avantageuse, la section aval 31 comporte des moyens d'inversion de poussée qui permettent d'améliorer le freinage de l'aéronef 1 de l'invention. Pour ce faire, les moyens de poussée inversent le sens du flux d'air circulant dans la nacelle 23 de l'invention. Les moyens de poussée peuvent être de tout type connu par l'homme du métier, notamment des moyens de poussée à portes 41 ou à grilles 43 (voir respectivement les figures 3 et 4 ainsi que les figures 5 et 6). Il est à préciser que toutes les nacelles installées sur l'aile peuvent ne pas toutes intégrer un moyen d'inversion.The middle structure 29 also includes a motor housing attached to one end of a blower housing for surrounding the fan blades 27, and at another end to the downstream section 31. The motor housing is intended to surround a portion 21. The attachment of said motor housing is carried out by any means known to those skilled in the art. The middle structure 29 may also include a median outer cover for surrounding the blower housing and / or the motor housing. Advantageously, the downstream section 31 comprises thrust reversing means which make it possible to improve the braking of the aircraft 1 of the invention. To do this, the thrust means reverse the direction of the flow of air flowing in the nacelle 23 of the invention. The thrust means may be of any type known to those skilled in the art, in particular pushing means with doors 41 or with grids 43 (see respectively FIGS. 3 and 4 as well as FIGS. 5 and 6). It should be noted that all nacelles installed on the wing may not all incorporate a means of inversion.
Selon le mode de réalisation représenté à la figure 7, la nacelle 23 selon l'invention peut être préférentiellement composée d'au moins deux éléments 51a et 51b aptes à passer d'une configuration de fonctionnement dans laquelle les deux éléments 51a et 51b sont attachés entre eux de telle sorte que la nacelle 23 de l'invention entoure le turboréacteur 21 à une configuration de maintenance dans laquelle les éléments 51a et 51b ne sont plus attachés entre eux. Ainsi lorsque les deux éléments 51a et 51 b sont en position de maintenance, ces derniers forment un passage par lequel le turboréacteur 21 peut être décroché de la nacelle. Une telle configuration de la nacelle 23 de l'invention permet de simplifier la maintenance. Comme représenté sur la figure 7, il est possible que la nacelle 23 de l'invention soit composée d'au moins deux éléments 51a et 51b articulés sur les parois latérales de ladite nacelle 23 de l'invention et/ou de l'aile volante 3 de l'invention. Dans ce cas, les deux éléments 51a et 51b peuvent avoir une forme de demi coquille. Les deux éléments 51a et 51 b sont notamment configurés pour s'ouvrir sur l'extrados 17 ou sur l'intrados de l'aile volante 3 de l'invention. Les deux éléments 51a et 51b peuvent être symétriques ou non. Il est également possible que seul un des éléments soit articulé d'un côté ou de l'autre de la structure de l'aile volante 3.According to the embodiment shown in FIG. 7, the nacelle 23 according to the invention may preferably be composed of at least two elements 51a and 51b able to pass from an operating configuration in which the two elements 51a and 51b are attached. between them so that the nacelle 23 of the invention surrounds the turbojet 21 to a maintenance configuration in which the elements 51a and 51b are no longer attached to each other. Thus when the two elements 51a and 51b are in the maintenance position, they form a passage through which the turbojet 21 can be unhooked from the nacelle. Such a configuration of the nacelle 23 of the invention simplifies maintenance. As shown in FIG. 7, it is possible for the nacelle 23 of the invention to be composed of at least two elements 51a and 51b articulated on the side walls of said nacelle 23 of the invention and / or the flying wing. 3 of the invention. In this case, the two elements 51a and 51b can have a shape half shell. The two elements 51a and 51b are in particular configured to open on the upper surface 17 or on the underside of the flying wing 3 of the invention. The two elements 51a and 51b may be symmetrical or not. It is also possible that only one of the elements is articulated on one side or the other of the structure of the flying wing 3.
Les parois 33 et 34 délimitent un canal 61 dans lequel pénètre de l'air extérieur pour faire fonctionner la soufflante 27 du turboréacteur. L'air pénètre naturellement dans le canal 61 grâce à l'angle d'écopage. L'angle d'écopage correspond à l'angle entre la section du canal comportant le turboréacteur 21 et la partie qui débouche sur l'intrados, l'extrados 17 ou sur les côtés latéraux de l'aile volante 3. Selon le mode de réalisation représenté à la figure 1, le canal 61 débouche sur l'extrados 17 ou sur les côtés latéraux 62. De manière plus générale, lorsque le turboréacteur 21 est positionné sensiblement de manière centrale à l'arrière de l'aile volante 3, le canal 61 débouche typiquement sensiblement au milieu de l'aile volante 3 sur l'intrados ou sur l'extrados 17. En position latérale arrière, le canal 61 peut déboucher sur les bords latéraux de l'aile volante 3.The walls 33 and 34 define a channel 61 into which outside air enters to operate the fan 27 of the turbojet engine. The air naturally enters the channel 61 through the scooping angle. The angle of ecopage corresponds to the angle between the section of the channel comprising the turbojet engine 21 and the part that opens onto the intrados, the extrados 17 or on the lateral sides of the flying wing 3. According to the method of embodiment shown in Figure 1, the channel 61 opens on the extrados 17 or on the lateral sides 62. More generally, when the turbojet 21 is positioned substantially centrally at the rear of the flying wing 3, the channel 61 opens typically substantially in the middle of the flying wing 3 on the lower surface or on the extrados 17. In the rear lateral position, the channel 61 can lead to the lateral edges of the flying wing 3.
Selon le mode de réalisation représenté à la figure 8, une grille 71 peut couvrir l'extrémité avant 63 du canal 61 au moins partiellement, notamment l'intégralité, en débouchant sur l'extrados 17, l'intrados ou sur les côtés latéraux de l'aile volante 3 de l'invention. La grille 71 peut éventuellement être placée à l'intérieur du canal 61. La grille 71 permet avantageusement de protéger le turboréacteur 21 de tout projectile susceptible de pénétrer dans le canal, tel qu'un oiseau. La grille 71 peut être de tout type connu de l'homme du métier.According to the embodiment shown in FIG. 8, a gate 71 may cover the front end 63 of the channel 61 at least partially, in particular the entirety, while opening on the extrados 17, the intrados or on the lateral sides of the channel. the flying wing 3 of the invention. The gate 71 may optionally be placed inside the channel 61. The gate 71 advantageously protects the turbojet 21 of any projectile that can enter the channel, such as a bird. The gate 71 may be of any type known to those skilled in the art.
En particulier, la grille 71 peut comporter au moins une aube pour aider à la captation de l'air.In particular, the grid 71 may comprise at least one blade to assist in capturing the air.
Selon le mode de réalisation représenté à la figure 8, l'aile volante 3 de l'invention peut comporter un volet mobile 75 disposé à l'arrière de l'extrémité 63 du canal pour améliorer la captation de l'air. De manière avantageuse, le volet mobile 75 peut être commandé par un système automatisé, notamment par le pilote dans la cabine de pilotage. Le système automatisé peut être employé à tout moment du vol ou au décollage lorsque l'incidence du profil de l'aile volante 3 risque de dégrader la captation naturelle de l'air en fonction des besoins du turboréacteur 21. Selon un autre mode de réalisation représenté à la figure 9, la nacelle 23 est décentrée par rapport au plan médian 81 de l'aile volante ce qui permet d'améliorer la captation de l'air dans le canal 61 tout en préservant la continuité aérodynamique du dessus ou du dessous de l'aile volante 3. Le plan médian 81 correspond au plan passant par le bord d'attaque 15 et l'arrière 19 de l'aile volante. According to the embodiment shown in Figure 8, the flying wing 3 of the invention may comprise a movable flap 75 disposed at the rear of the end 63 of the channel to improve the capture of air. Advantageously, the movable flap 75 can be controlled by an automated system, in particular by the pilot in the cockpit. The automated system can be used at any time during flight or take-off when the incidence of the flying wing profile 3 may degrade the natural capture of the air according to the needs of the turbojet 21. According to another embodiment shown in FIG. 9, the nacelle 23 is off-center with respect to the median plane 81 of the flying wing, which makes it possible to improve the capture of the air in the channel 61 while preserving the aerodynamic continuity. from the top or bottom of the flying wing 3. The median plane 81 corresponds to the plane passing through the leading edge 15 and the rear 19 of the flying wing.

Claims

REVENDICATIONS
1. Aile volante (3) comportant au moins une nacelle (23) pour turboréacteur (21 ) comportant une structure d'entrée d'air (25) apte à canaliser un flux d'air vers une soufflante (27) d'un turboréacteur (21), une structure médiane (29) destinée à entourer ladite soufflante (27) et à laquelle est rattachée la structure d'entrée d'air (25) de manière à assurer une continuité aérodynamique, et une section aval (31) à laquelle est rattachée la structure médiane (29), caractérisée en ce que la structure d'entrée d'air (25) est apte à venir en continuité des parois (33 ; 34) de l'aile volante (3) de telle sorte que la structure d'entrée d'air (25), la structure médiane (29) et la section aval (31) sont en continuité aérodynamique avec l'aile volante (3).Flying wing (3) comprising at least one nacelle (23) for a turbojet engine (21) comprising an air inlet structure (25) capable of channeling a flow of air towards a fan (27) of a turbojet engine (21), a medial structure (29) for surrounding said blower (27) and to which the air inlet structure (25) is attached to provide aerodynamic continuity, and a downstream section (31) to which is attached the middle structure (29), characterized in that the air inlet structure (25) is adapted to come in continuity with the walls (33; 34) of the flying wing (3) so that the air intake structure (25), the middle structure (29) and the downstream section (31) are aerodynamically continuous with the flying wing (3).
2. Aile (3) selon la revendication 1 , caractérisée en ce que la section aval (31 ) comporte des moyens d'inversion de poussée (41 ; 43).2. Wing (3) according to claim 1, characterized in that the downstream section (31) comprises thrust reversing means (41; 43).
3. Aile (3) selon l'une quelconque des revendications 1 ou 2, caractérisée en ce que la nacelle (23) est composée d'au moins deux éléments (51a ; 51 b) aptes à passer d'une configuration de fonctionnement dans laquelle les deux éléments (51a ; 51b) sont attachés entre eux de sorte que la nacelle (23) entoure le turboréacteur (21 ), à une configuration de maintenance dans laquelle les éléments (51a ; 51 b) ne sont plus attachés entre eux.3. Wing (3) according to any one of claims 1 or 2, characterized in that the nacelle (23) is composed of at least two elements (51a, 51b) able to pass from an operating configuration in wherein the two members (51a; 51b) are attached together so that the nacelle (23) surrounds the turbojet engine (21) to a maintenance configuration in which the elements (51a; 51b) are no longer attached to each other.
4. Aile (3) selon l'une quelconque des revendications 1 à 3, caractérisée en ce qu'au moins une nacelle (23) est disposée à l'arrière de l'aile volante (3).4. Wing (3) according to any one of claims 1 to 3, characterized in that at least one nacelle (23) is disposed at the rear of the flying wing (3).
5. Aile (3) selon l'une quelconque des revendications 1 à 4, caractérisée en ce que chaque turboréacteur (21) est disposé dans un canal (61) dont l'extrémité (63) avant débouche sur l'extrados (17), l'intrados ou sur les côtés latéraux (62) de l'aile volante (3). 5. Wing (3) according to any one of claims 1 to 4, characterized in that each turbojet engine (21) is disposed in a channel (61) whose end (63) before opens on the upper surface (17) , the intrados or on the lateral sides (62) of the flying wing (3).
6. Aile (3) selon la revendication précédente, caractérisée en ce qu'une grille (71 ) couvre au moins partiellement l'extrémité (63) avant du canal (61 ) débouchant au niveau de l'aile volante (3).6. Wing (3) according to the preceding claim, characterized in that a grid (71) at least partially covers the end (63) of the front channel (61) opening at the wing (3).
7. Aile (3) selon la revendication précédente, caractérisée en ce que la grille (71 ) comporte au moins une aube. 7. Wing (3) according to the preceding claim, characterized in that the gate (71) comprises at least one blade.
8. Aile (3) selon la revendication précédente, caractérisée en ce qu'elle comporte un volet mobile (75) disposé à l'arrière relativement à l'extrémité (63) du canal (61 ).8. Wing (3) according to the preceding claim, characterized in that it comprises a movable flap (75) disposed at the rear relative to the end (63) of the channel (61).
9. Aile(3) selon l'une quelconque des revendications 1 à 8, caractérisée en ce que la nacelle (23) est décentrée par rapport au plan médian (81) de l'aile volante (3).9. Wing (3) according to any one of claims 1 to 8, characterized in that the nacelle (23) is off-center with respect to the median plane (81) of the flying wing (3).
10. Aéronef (1 ) comportant une aile volante (3) selon l'une quelconque des revendications 1 à 9. 10. Aircraft (1) comprising a flying wing (3) according to any one of claims 1 to 9.
PCT/FR2009/001305 2008-11-26 2009-11-13 Nacelle integrated on a flying wing WO2010061071A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0806636A FR2938824A1 (en) 2008-11-26 2008-11-26 NACELLE INTEGRATED ON FLYING WING
FR08/06636 2008-11-26

Publications (2)

Publication Number Publication Date
WO2010061071A2 true WO2010061071A2 (en) 2010-06-03
WO2010061071A3 WO2010061071A3 (en) 2010-10-07

Family

ID=40791665

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2009/001305 WO2010061071A2 (en) 2008-11-26 2009-11-13 Nacelle integrated on a flying wing

Country Status (2)

Country Link
FR (1) FR2938824A1 (en)
WO (1) WO2010061071A2 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2578490A2 (en) 2011-10-05 2013-04-10 Rolls-Royce plc A propulsion unit for an aircraft
US9493244B2 (en) 2011-05-24 2016-11-15 Bae Systems Plc Structural element of an air vehicle air intake composed of an array of passages with a hexagonal cross section
RU209424U1 (en) * 2021-08-18 2022-03-16 Публичное акционерное общество (ПАО) "Туполев" AIRCRAFT ENGINE INTAKE
DE102022113595A1 (en) 2022-05-30 2023-11-30 Reiner Brach Aircraft for flying in ambient air using dynamic buoyancy

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11247776B2 (en) * 2019-04-01 2022-02-15 The Boeing Company Aircraft having embedded engines

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2553512A (en) * 1949-08-22 1951-05-15 Jr Thomas J Cotton Gas turbine apparatus
FR1168084A (en) * 1956-12-10 1958-12-04 Carrier-fuselage aircraft with integrated propulsion
US3202383A (en) * 1961-10-25 1965-08-24 Bel John P Le Aircraft
US4506850A (en) * 1983-01-04 1985-03-26 The Boeing Company Engine installation for aircraft
WO2000020272A1 (en) * 1998-10-06 2000-04-13 Northrop Grumman Corporation Aircraft engine air intake system
EP1243782A2 (en) * 2001-03-23 2002-09-25 The Boeing Company Double jet engine inlet
EP1344915A2 (en) * 2002-03-15 2003-09-17 ROLLS-ROYCE plc A variable position intake for an aircraft mounted gas turbine engine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2553512A (en) * 1949-08-22 1951-05-15 Jr Thomas J Cotton Gas turbine apparatus
FR1168084A (en) * 1956-12-10 1958-12-04 Carrier-fuselage aircraft with integrated propulsion
US3202383A (en) * 1961-10-25 1965-08-24 Bel John P Le Aircraft
US4506850A (en) * 1983-01-04 1985-03-26 The Boeing Company Engine installation for aircraft
WO2000020272A1 (en) * 1998-10-06 2000-04-13 Northrop Grumman Corporation Aircraft engine air intake system
EP1243782A2 (en) * 2001-03-23 2002-09-25 The Boeing Company Double jet engine inlet
EP1344915A2 (en) * 2002-03-15 2003-09-17 ROLLS-ROYCE plc A variable position intake for an aircraft mounted gas turbine engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
LIEBECK R H: "DESIGN OF THE BLENDED WING BODY SUBSONIC TRANSPORT" JOURNAL OF AIRCRAFT, AIAA, RESTON, VA, US, vol. 41, no. 1, 1 janvier 2004 (2004-01-01), pages 10-25, XP001047563 ISSN: 0021-8669 *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9493244B2 (en) 2011-05-24 2016-11-15 Bae Systems Plc Structural element of an air vehicle air intake composed of an array of passages with a hexagonal cross section
EP2578490A2 (en) 2011-10-05 2013-04-10 Rolls-Royce plc A propulsion unit for an aircraft
US8857760B2 (en) 2011-10-05 2014-10-14 Rolls-Royce Plc Propulsive unit for an aircraft
RU209424U1 (en) * 2021-08-18 2022-03-16 Публичное акционерное общество (ПАО) "Туполев" AIRCRAFT ENGINE INTAKE
DE102022113595A1 (en) 2022-05-30 2023-11-30 Reiner Brach Aircraft for flying in ambient air using dynamic buoyancy

Also Published As

Publication number Publication date
FR2938824A1 (en) 2010-05-28
WO2010061071A3 (en) 2010-10-07

Similar Documents

Publication Publication Date Title
EP2406133B1 (en) Airplane with a tailcoat tail assembly and rear engine
EP0822327B1 (en) Thrust reverser for a turbofan engine with thrust reverser doors which form scoops
EP0806563B1 (en) Doors with deflector vanes for a thrust reverser of a turbofan engine
EP2543864B1 (en) Aircraft propulsion assembly with a heat shield for thermal protection of a rear aerodynamic fairing of a pylon and a cooling method for the heat shield
EP2665909B1 (en) Engine nacelle for turbofan engine
FR2958624A1 (en) AIRCRAFT TURBOHOMOTING MACHINE, COMPRISING AN INCOMING MOBILE REAR FLAP
EP2179163B1 (en) Chevron for a nozzle, corresponding nozzle and turboreactor
FR2919267A1 (en) Aircraft e.g. silence aircraft, has high-bypass-ratio fan engines placed side-by-side in propulsion system such that outlets of nozzles are located between vertical fins of vertical tail, above fuselage in front of rear end of fuselage
EP0601910B1 (en) Thrust reverser door with deflector vanes to guide the jet
CA2796017A1 (en) Reverser having doors
FR2958688A1 (en) PROPULSIVE ASSEMBLY FOR AIRCRAFT PROVIDED WITH THRUST INVERSION MEANS
EP0947688A1 (en) Thrust reverser for a jet engine whose doors form scoops having a linked external cowling
EP0534815A1 (en) Thrust-reverser with improved guidance of the reversed jets
EP3495651B1 (en) Screen for forming a reversal flow of a jet engine of an aircraft
EP0754849B1 (en) Double flux turbine thrust reverser with asymmetric doors
WO2010061071A2 (en) Nacelle integrated on a flying wing
EP0882882A1 (en) Doors with deployable front spoilers for a jet engine thrust reverser
FR2947868A1 (en) Nacelle for airplane, has thrust reverser device including flaps adapted to occupy folded and deployed states, and ring arranged remotely from inner wall of nacelle and outer surface supporting flaps
EP3891374B1 (en) Thrust reverser provided with a lightweight thrust reverser flap
FR2955154A1 (en) THRUST INVERTER FOR TURBO AIRCRAFT WITH DOUBLE FLOW SEMI-BURIAL
EP3999422B1 (en) Propulsion unit with improved boundary layer ingestion
WO2010061070A1 (en) Flying wing for an aircraft
EP3959134B1 (en) Nacelle air intake with acoustic panel
WO2018002560A1 (en) Arrangement for the attachment of a connecting rod of a thrust reversal flap to a fixed internal structure of a jet engine nacelle and associated method for assembly/disassembly
FR2964704A1 (en) Device for orienting air flow deviated by thrust reverser of e.g. double flow propeller of commercial aircraft, has ailerons placed within air flow deviated by reverser, where ailerons has geometry to modify orientation of local air flow

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 09760934

Country of ref document: EP

Kind code of ref document: A2

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 09760934

Country of ref document: EP

Kind code of ref document: A2