EP2946101A1 - Nacelle jet pipe with devices for regulating pressure - Google Patents

Nacelle jet pipe with devices for regulating pressure

Info

Publication number
EP2946101A1
EP2946101A1 EP14705821.8A EP14705821A EP2946101A1 EP 2946101 A1 EP2946101 A1 EP 2946101A1 EP 14705821 A EP14705821 A EP 14705821A EP 2946101 A1 EP2946101 A1 EP 2946101A1
Authority
EP
European Patent Office
Prior art keywords
nozzle
annular element
downstream end
outlet
air
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.)
Withdrawn
Application number
EP14705821.8A
Other languages
German (de)
French (fr)
Inventor
Xavier Bouteiller
Patrick Gonidec
Laurent Albert Blin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
Original Assignee
Aircelle SA
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 SA filed Critical Aircelle SA
Publication of EP2946101A1 publication Critical patent/EP2946101A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38—Introducing air inside the jet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • 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
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to the field of nozzle nacelles of turbojet engines and more precisely nozzles adapted to the operation of engines with a high dilution ratio.
  • An aircraft is propelled by one or more propulsion units each comprising a turbojet engine housed in a tubular nacelle.
  • Each propulsion unit is attached to the aircraft by a mast generally located under a wing or at the fuselage.
  • a nozzle generally has a structure comprising an upstream section of air inlet, upstream of the engine, a median section intended to surround a fan of the turbojet, and a downstream section intended to surround the combustion chamber of the turbojet engine and housing the most often means of thrust reversal.
  • upstream is what comes before the point or element considered, in the direction of the flow of air in a turbojet, and downstream which comes after the point or element considered, in the direction of flow air in a turbojet.
  • VAFN Variable-Area Fan Nozzle
  • the rate of compression is low, less than 1, 3 while the dilution ratio, that is to say the ratio between the air mass of the cold flow and that of the hot flow of a turbojet engine, is high.
  • the dilution ratio that is to say the ratio between the air mass of the cold flow and that of the hot flow of a turbojet engine
  • Document EP 0 578 951 A1 discloses a thrust nozzle for an engine block comprising a fixed nozzle and a divergent fixed nozzle extension that can be moved axially for an enlargement on the outlet side of the gas flow channel. which, in the extended position, is essentially connected to an identical shape at the diverging outlet end of the outer wall of the fixed nozzle.
  • the fixed nozzle extension, in the retracted position, and the fixed nozzle together form a controllable air outlet channel surrounding the wall end of the thrust nozzle in annular form.
  • the fixed nozzle extension is shaped so that, in the deployed position, its upstream end essentially connects to a shape identical to the downstream end of the fixed nozzle of the engine block. and in the retracted position it forms an air passage channel with the fixed nozzle.
  • the nozzle extension can take only two positions, the retracted position and the deployed position. Finally, in the retracted position, the fixed nozzle extension can not act on the air flow with the fixed nozzle.
  • a nozzle technology developed in vertical take-off aircraft with steerable nozzles has also been proposed with subsonic horns ejecting a flow through a fixed annular element (6).
  • This technology is essentially intended to help direct the thrust to the ground.
  • the invention aims to solve the aforementioned drawbacks and in particular the low efficiency of the devices of the prior art for a very high dilution rate and a low compression ratio of a turbojet of an aircraft flying at low speed thus causing risks of pumping the engine.
  • the present invention consists, to avoid pumping the engine, to adapt the static output pressure of a nozzle.
  • the invention proposes a nozzle comprising a device for regulating the output pressure of a remarkable air flow in that said device comprises an annular element surrounding the downstream end of the nozzle and at a distance of thereof, and means for adjusting the position of at least a portion of the annular element with respect to the downstream end of the nozzle, and in that the annular element forms with the downstream end of the nozzle.
  • nozzle a necking zone, the widest part of which is upstream of its narrowest part, and whose profile is variable depending on the position of the annular element.
  • the annular element and the nozzle together define an annular surrounding channel at the downstream end of the nozzle.
  • an air flow can take place between the annular element and the downstream end of the nozzle.
  • the annular element may be deformable so that only a part of the annular element can be adjusted in position.
  • adjusting the position of at least a portion of the annular element makes it possible to modulate the air flow between the annular element and the nozzle, that is to say, to modulate its speed and pressure. at the outlet of the annular element.
  • the air circulating between the annular element and the nozzle makes it possible to shrink the air flow at the outlet of the nozzle and thus to have an influence on the pressure of the flow of air leaving the nozzle. nozzle.
  • the zone of necking makes it possible to accelerate the flow of the air passing between the annular element and the nozzle, consequently the pressure at the end of the necking zone is smaller than the ambient pressure, this is called a necking effect (or trompe effect).
  • a necking effect or trompe effect.
  • the air flowing in the nozzle flows in a depression zone in the vicinity of the downstream end of the nozzle.
  • the outlet pressure of the nozzle and therefore the compression ratio are decreased.
  • the stronger the necking effect, the lower the pressure at the outlet of the necking zone, and therefore the lower the outlet pressure of the nozzle and the compression ratio are small.
  • the flow of air flowing between the annular element and the nozzle maximizes the structure of the current lines, in particular by keeping the current lines as close as possible to those present without the annular element.
  • the position of the annular element can be adjusted so that it forms with the nozzle a zone of necking substantially zero (or uniform). In this configuration, the air passing between the annular element and the nozzle is then not substantially accelerated and therefore has substantially no effect on the pressure of the air flow at the outlet of the nozzle.
  • the annular element is always inclined with respect to the downstream end of the nozzle in a necking configuration such that the necking zone generates a so-called shape thrust, it is that is, a thrust made possible only by the shape of a static part (in the same way that a ramjet uses a particular form of static input shaft to compress the air entering it), compensating for the drag friction added by the presence of the annular element.
  • the inner wall of the annular element forms with the nozzle a zone of convergence - divergence with respect to the direction of flow of the air.
  • the convergent zone situated upstream of the annular element serves to obtain the necking effect or trompe effect described above, and the dive region in which the annular element advantageously makes it possible to generate an increase the thrust force of the assembly formed by the nozzle and the turbojet engine.
  • the outer wall of the annular element is substantially flat and the upstream and downstream edges of the annular element are rounded.
  • the boundary line between the convergence and divergence zones of the annular element may be situated in the plane in which inscribes the downstream end of the nozzle in at least one of the positions of the annular element.
  • the annular element consists of a plurality of rigid flaps or sectors.
  • the rigid flaps are evenly distributed along the contour of the downstream end of the nozzle.
  • the rigid flaps thus distributed allow a flow of air between the annular element and the nozzle so that the air flow at the outlet of the nozzle is substantially sheathed by the flow of air at the outlet of the channel formed by the annular element and the downstream end of the nozzle, the control of the pressure of the air flow at the outlet of the nozzle is therefore easier.
  • the annular element consisting of a plurality of rigid flaps is rotatable along axes tangent to the nozzle and substantially orthogonal to the axis of the nozzle.
  • a slight increase in the inclination of the rigid flaps of the annular element relative to the nozzle of the order of a few degrees (for example 2 or 3 degrees) allows a displacement of the upstream end of the element.
  • the rigid flaps are rotatably mounted about an axis proper to each, each axis is carried by a support fixed on the downstream end of the nozzle.
  • the annular element is movable in translation, whether it is constituted by a plurality of rigid flaps or in any other manner.
  • the mobility in translation of the annular element constitutes a simple way of adjusting the necking effect.
  • the rigid flaps can be both movable in translation and in rotation so as to obtain a wider range of necking effect and a finer adjustment of the pressure of the flap. air flow at the outlet of the nozzle.
  • the annular element comprises inflatable boxes.
  • the inflatable chambers are deformable at least at their downstream end under the effect of pressure.
  • the flow of air passing through the channel formed by the annular element consisting of inflatable boxes and the nozzle can deform said boxes.
  • the inflatable chambers can be translatable and / or rotatably mounted around an axis specific to each, each axis being carried by a support fixed on the downstream end of the nozzle.
  • the internal pressure of the inflatable chambers is regulated by means of a device of the compressed air motor type.
  • the device of the compressed air motor type allows the regulation of the internal pressure of the air chambers as a function of the pressure of the air flow at the outlet of the desired nozzle.
  • the airbag technology can be combined with that of the rigid flaps such that the annular element consists of a plurality of flaps each having a rigid upstream zone and a deformable downstream zone under the pressure consisting of an inflatable box whose internal pressure can be regulated.
  • the inlet section in the necking zone has an area close to or greater than the exit section of the nozzle.
  • the necking effect is used to increase the thrust during take-off of the aircraft and improve the propulsive efficiency of the blower while maintaining a low dilution ratio suitable for cruising operation.
  • the annular element is displaced in such a manner that the necking effect is substantially zero.
  • the nozzle comprises a flexible pressurized air injection device located at the nozzle.
  • the modular pressurized air injection device performs an air injection in the upstream direction downstream of the nozzle and is oriented such that the resulting air flow enters the formed channel. by the annular element and the nozzle.
  • the device for injecting pressurized air is located upstream of the annular element in the immediate vicinity of the upstream end of the annular element or edge of attack of the annular element.
  • such a modular pressurized air injection device combined with the annular element eliminates the need to change the position of the annular element (fixed annular element relative to the nozzle) in order to control the pressure of the flow. air out of the nozzle.
  • FIG. 1a is a perspective view of a nacelle equipped with a nozzle according to a first embodiment of the present invention
  • FIG. 1b is a schematic view of a nozzle according to the first embodiment of the present invention.
  • FIG. 2a represents a perspective view of a nacelle equipped with a nozzle according to a second embodiment of the present invention
  • FIG. 2b is a schematic view of a nozzle according to the second embodiment of the present invention
  • FIG. 3 is a schematic view of a nozzle according to a third embodiment of the present invention.
  • FIG. 4 is a schematic view of a nozzle according to a fourth embodiment of the present invention.
  • FIGS. 1a and 1b are sectional views of a nozzle according to a fifth embodiment of the present invention.
  • a nacelle 1 is equipped with a nozzle 2 comprising a pressure regulating device 3 of the pressure of an air flow 4 at the outlet 5 of the nozzle 2.
  • ispositif 3 comprises an annular element 6 surrounding the downstream end 7 of the nozzle 2 and at a distance from the nozzle die 2, and means 8 for adjusting the position of the annular element 6 by translation of the annular element 6 along an axis substantially parallel to the axis ⁇ of the nozzle 2.
  • the annular element 6 is shaped in such a way that it forms with the downstream end 7 of the nozzle 2 a convergence zone 9a 9a - divergence 9b with regard to an air flow 10 between the annular element 6 and the nozzle 2.
  • the means 8 for adjusting the position of the annular element 6 by translation of the annular element 6 are shaped in such a way that the position of the annular element 6 is adjusted continuously ition in the unobtrusive way that is less flexible and does not allow such a fine tuning.
  • adjustment means 8 such that there would be a discretized adjustment of the position of the annular element 6.
  • the air flow 10 passing through the inlet section 11 in the convergence zone 9a-divergence 9b, undergoes a necking effect, that is to say that the air flow 10 is accelerated to the output section 12 of the convergence zone 9a 9a - divergence 9b.
  • the air flow 10 undergoes an increased expansion by the fact that the air flow 4 at the outlet 5 of the nozzle 2 "sucks" the air flow 10 to the adjacent to the outlet section 12, creating a negative pressure at the level of the diverging portion of the zone 9 so that the pressure in this diverging portion is lower than the atmospheric pressure.
  • the air flow 4 at the outlet 5 of the nozzle 2 is depressed by passing the outlet 5 of the nozzle 2 and penetrates more easily into the atmosphere.
  • the Part of the zone 9 makes it possible to obtain additional thrust force to that already provided by the air flow 4. This configuration makes it possible to reduce the energy consumption by the turbojet engine, and to limit the pumping risks of the turbojet.
  • a nacelle 1 is equipped with a nozzle 2 comprising and regulating the pressure of the air flow 4 at the outlet 5 of the nozzle 2.
  • Device 3 comprises a plurality of rigid flaps 6a, 6b, 6c forming an annular element 6 surrounding the downstream end 7 of the nozzle 2 in a uniformly distributed manner and at a distance from said nozzle 2, and means 8 for adjusting the position by rotating the rigid flaps each along an axis ⁇ 'tangential to the downstream end 7 of the nozzle 2 and orthogonal to the axis ⁇ of the nozzle 2.
  • the rigid flaps 6a, 6b, 6c are shaped so that each form with the downstream end 7 of the nozzle 2 a zone 9 of convergence 9a with respect to an air flow 1 0 between the rigid flap 6a, 6b, 6c and the nozzle 2.
  • the means 8 for adjusting the position of the rigid flaps 6a, 6b, 6c by rotation of the rigid flaps 6a, 6b, 6c are shaped in such a way re that the adjustment of the position of the rigid flaps 6a, 6b, 6c is continuous as opposed to the discrete manner which is less flexible and does not allow such a fine adjustment.
  • adjustment means 8 such that there would be a discretized adjustment of the position of the flaps 6a, 6b, 6c.
  • the air flow 10 through the inlet section 1 1 in the convergence zone 9a, undergoes a necking effect.
  • the air flow 10 undergoes an increased expansion by the fact that the air flow 4 at the outlet 5 of the nozzle 2 "sucks" the air flow 10 to the adjacent the outlet section 12, thereby creating a depression so that the downstream pressure in the vicinity of the outlet section 12 is lower than the atmospheric pressure.
  • the air flow 4 at the outlet 5 of the nozzle 2 undergoes a depression passing the outlet 5 of the nozzle 2 and penetrates more easily into the atmosphere.
  • a nozzle 2 comprises a device 3 for regulating the pressure of an air flow 4 at the outlet 5 of the nozzle 2.
  • the device 3 comprises a plurality of air chambers 6a, 6b, 6c forming annular element 6 surrounding the downstream end 7 of the nozzle 2 in a uniformly distributed manner and at a distance from said nozzle 2.
  • the inflatable caissons 6a, 6b, 6c are shaped in such a way that their upstream end is fixed without any degree of freedom on the nozzle by a fastening means 8a, that they are deformable under the action of the air flow 1 0, and that each forms with the downstream end 7 of the nozzle 2 a zone 9 of convergence 9a to the the air flow 1 0 between the inflatable chamber 6a, 6b, 6c and the nozzle 2.
  • the air flow 1 0 therefore acts as means 8 for adjusting the position of the air chambers.
  • the air flow 10 through the inlet section 1 1 in the convergence zone 9a, undergoes a necking effect.
  • the air flow 10 undergoes an increased expansion by the fact that the air flow 4 at the outlet 5 of the nozzle 2 "sucks" the air flow 10 to the adjacent the outlet section 12, thereby creating a depression so that the downstream pressure in the vicinity of the outlet section 12 is lower than the atmospheric pressure.
  • the air flow 4 at the outlet 5 of the nozzle 2 is depressed by passing the outlet 5 of the nozzle 2 and penetrates more easily into the atmosphere.
  • the ratio of the inlet section 1 1 to the outlet section 1 2 of each air box 6a, 6b, 6c, or necking ratio varies, so as to vary the necking effect provoked by the convergence zone 9a 9a of each inflatable box 6a, 6b, 6c.
  • each inflatable box 6a, 6b, 6c is substantially identical and adjustable under the action of a compressed air motor (not shown) included in the device 3 for regulating the pressure of an air flow 4 at the outlet 5 of the nozzle 2.
  • a compressed air motor included in the device 3 for regulating the pressure of an air flow 4 at the outlet 5 of the nozzle 2.
  • a nozzle 2 comprises a device 3 for regulating the pressure of an air flow 4 at the outlet 5 of the nozzle 2 as disclosed in FIGS. 2a and 2b and the description associated therewith, the device 3 comprising here in addition to this mode embodiment of FIGS. 2a and 2b an air injection means 13 making it possible to regulate the flow of air 1 0 entering the zone 9 of convergence 9a according to the embodiment of FIGS. 2a and 2b.
  • This air injection means 13 comprises a compressed air motor (not shown) and an outlet orifice for the compressed air in the zone 9 of convergence 9a. Once injected, said compressed air has a variable influence as a function of the pressure at which it is injected into the zone 9 of convergence 9a on the characteristics of the air flow 10.
  • a nozzle 2 comprises a device 3 for regulating the pressure of an air flow 4 at the outlet 5 of the nozzle 2 as disclosed in FIGS. 1a and 1b, the annular element 6 having dimensions such that the inlet section 1 1 of the convergent portion of the convergence zone 9a-divergence 9b has an area of a value in the vicinity of or greater than that of the outlet section 5 of the nozzle 2.
  • the horn effect is used to increase the thrust during take-off.
  • the annular element 6 can be moved by the means 8 to make this effect more modest and substantially find the operating line of the nacelle 1 without annular element 6.

Abstract

Jet pipe (2) comprising a device (3) for regulating the pressure of a flow (4) of air leaving (5) the jet pipe (2), characterized in that said device (3) comprises an annular element (6) surrounding the downstream end (7) of the jet pipe (2) and some distance therefrom, and means (8) for adjusting the position of at least part of the annular element (6) in relation to the downstream end (7) of the jet pipe (2), and in that the annular element (6) forms, with the downstream end (7) of the jet pipe (2), a constricted zone (9) the widest part (11) of which is situated upstream of the narrowest part (12) thereof and the profile of which can be varied according to the position of the annular element (6).

Description

Tuyère de nacelle à dispositifs de régulation de pression  Nacelle nozzle with pressure regulating devices
L'invention concerne le domaine des tuyères de nacelles de turboréacteurs et plus précisément des tuyères adaptées au fonctionnement des moteurs à taux de dilution élevé. The invention relates to the field of nozzle nacelles of turbojet engines and more precisely nozzles adapted to the operation of engines with a high dilution ratio.
Un aéronef est propulsé par un ou plusieurs ensembles propulsifs comprenant chacun un turboréacteur logé dans une nacelle tubulaire. Chaque ensemble propulsif est rattaché à l'aéronef par un mât situé généralement sous une aile ou au niveau du fuselage. An aircraft is propelled by one or more propulsion units each comprising a turbojet engine housed in a tubular nacelle. Each propulsion unit is attached to the aircraft by a mast generally located under a wing or at the fuselage.
Une tuyère présente généralement une structure comprenant une section amont d'entrée d'air, en amont du moteur, une section médiane destinée à entourer une soufflante du turboréacteur, et une section aval destinée à entourer la chambre de combustion du turboréacteur et abritant le plus souvent des moyens d'inversion de poussée. A nozzle generally has a structure comprising an upstream section of air inlet, upstream of the engine, a median section intended to surround a fan of the turbojet, and a downstream section intended to surround the combustion chamber of the turbojet engine and housing the most often means of thrust reversal.
On entend par amont ce qu i vient avant le point ou élément considéré, dans le sens de l'écoulement de l'air dans un turboréacteur, et par aval ce qui vient après le point ou élément considéré, dans l e sens de l'écoulement de l'air dans un turboréacteur. What is meant by upstream is what comes before the point or element considered, in the direction of the flow of air in a turbojet, and downstream which comes after the point or element considered, in the direction of flow air in a turbojet.
Actuellement l'adaptation du comportement des tuyères à des taux de dilution élevés pour éviter les risques de pompage, c'est-à-dire les risques d'oscillations de la vitesse et de la pression dans l'écoulement de l'air observée à certains régimes dans les turbomachines entraînant un nivellement des performances du compresseur et pouvant entraîner la rupture d'aubes du compresseur, est obtenue en augmentant la section de sortie dans les plages de fonctionnement de la soufflante où le débit est faible et le taux de compression élevé. Currently adapting the behavior of nozzles at high dilution rates to avoid the risks of pumping, that is to say the risks of oscillations of the speed and pressure in the flow of air observed at certain speeds in the turbomachines causing a leveling of the performance of the compressor and which can cause the rupture of compressor blades, is obtained by increasing the output section in the operating ranges of the fan where the flow is low and the high compression ratio .
L'inconvénient de cette technologie dite VAFN (pour Variable-Area Fan Nozzle, c'est-à-dire que l'on fait varier l'aire de la section de sortie d'une nacelle pour réguler l'écoulement d'air au niveau de la dite section) est la nécessité de m ise en œuvre de structu res lou rdes et com plexes . La technologie VAFN est également peu efficace dans le cas où le taux de compression est faible, inférieur à 1 ,3 tandis que le taux de dilution, c'est-à-dire le rapport entre la masse d'air du flux froid et celle du fl ux chaud d'un turboréacteur double flux, est élevé. Dans le cas particulier d'un turboréacteur double flux. The disadvantage of this technology called VAFN (for Variable-Area Fan Nozzle, that is to say that the area of the outlet section of a nacelle is varied to regulate the flow of air at the level of this section) is the need to implement leased and complex structures. The VAFN technology is also inefficient in the case where the rate of compression is low, less than 1, 3 while the dilution ratio, that is to say the ratio between the air mass of the cold flow and that of the hot flow of a turbojet engine, is high. In the particular case of a turbojet engine.
On connaît le document EP 0 578 951 A1 , qui divulgue une tuyère de poussée pour bloc moteur comprenant une tuyère fixe et une rallonge de tuyère fixe divergente, pouvant être déplacée axialement pour un agrandissement du côté de la sortie du canal d'écoulement de gaz chauds qui, dans la position déployée, se raccorde pour l'essentiel à une forme identique, à l'extrémité de sortie divergente de la paroi extérieure de la tuyère fixe. La rallonge de tuyère fixe, en position escamotée, et la tuyère fixe, forment ensemble un canal de sortie d'air, commandable, entourant sous forme annulaire l'extrémité de paroi de la tuyère de poussée. Dans la plage inférieure des vitesses de vol où la rallonge de tuyère de poussée n'est pas nécessaire pour l'élargissement du contour extérieur du canal d'écoulement de gaz chauds, il se produit un écoulement d'air secondaire régulier sur la totalité de la périphérie extérieure de l'extrémité de tuyère fixe du bloc moteur. Dans ce document de l'art antérieur, la rallonge de tuyère fixe est conformée de manière à ce que, en position déployée son extrémité amont se raccorde pour l'essentiel à une forme identique à l'extrémité aval de la tuyère fixe du bloc moteur, et en position escamotée elle forme un canal de passage d'air avec la tuyère fixe. De plus, la rallonge de tuyère ne peut prendre que deux positions, la position escamotée et la position déployée. Enfin, en position escamotée, la rallonge de tuyère fixe ne peut agir sur le flux d'air avec la tuyère fixe. Document EP 0 578 951 A1 discloses a thrust nozzle for an engine block comprising a fixed nozzle and a divergent fixed nozzle extension that can be moved axially for an enlargement on the outlet side of the gas flow channel. which, in the extended position, is essentially connected to an identical shape at the diverging outlet end of the outer wall of the fixed nozzle. The fixed nozzle extension, in the retracted position, and the fixed nozzle together form a controllable air outlet channel surrounding the wall end of the thrust nozzle in annular form. In the lower range of flight speeds where the thrust nozzle extension is not required for enlarging the outer contour of the hot gas flow channel, there is a regular secondary air flow over the entire the outer periphery of the fixed nozzle end of the engine block. In this document of the prior art, the fixed nozzle extension is shaped so that, in the deployed position, its upstream end essentially connects to a shape identical to the downstream end of the fixed nozzle of the engine block. and in the retracted position it forms an air passage channel with the fixed nozzle. In addition, the nozzle extension can take only two positions, the retracted position and the deployed position. Finally, in the retracted position, the fixed nozzle extension can not act on the air flow with the fixed nozzle.
Une technologie de tuyère développée dans les avions à décollage vertical avec des tuyères orientables a également été proposée avec des trompes subsoniques éjectant un flux à travers un élément annulaire (6) fixe. Cette technologie est essentiellement destinée à permettre d'orienter la poussée vers le sol. L'invention vise à résoudre les inconvénients précités et notamment la faible efficacité des dispositifs de l'art antérieur pour un très grand taux de dilution et un taux de compression faible d'un turboréacteur d'un aéronef volant à faible vitesse entraînant ainsi des risques de pompage du moteur. La présente invention consiste, pour éviter les pompages du moteur, à adapter la pression statique de sortie d'une tuyère. A cet effet, l'invention propose une tuyère comprenant un dispositif de régulation de la pression de sortie d'un écoulement d'air remarquable en ce que le dit dispositif comprend un élément annulaire entourant l'extrémité aval de la tuyère et à distance de celle-ci, et des moyens de réglage de la position d'au moins une partie de l'élément annulaire par rapport à l'extrémité aval de la tuyère, et en ce que l'élément annulaire forme avec l'extrémité aval de la tuyère une zone de striction, dont la partie la plus évasée se situe en amont de sa partie la plus étrécie, et dont le profil est variable en fonction de la position de l'élément annulaire. A nozzle technology developed in vertical take-off aircraft with steerable nozzles has also been proposed with subsonic horns ejecting a flow through a fixed annular element (6). This technology is essentially intended to help direct the thrust to the ground. The invention aims to solve the aforementioned drawbacks and in particular the low efficiency of the devices of the prior art for a very high dilution rate and a low compression ratio of a turbojet of an aircraft flying at low speed thus causing risks of pumping the engine. The present invention consists, to avoid pumping the engine, to adapt the static output pressure of a nozzle. For this purpose, the invention proposes a nozzle comprising a device for regulating the output pressure of a remarkable air flow in that said device comprises an annular element surrounding the downstream end of the nozzle and at a distance of thereof, and means for adjusting the position of at least a portion of the annular element with respect to the downstream end of the nozzle, and in that the annular element forms with the downstream end of the nozzle. nozzle a necking zone, the widest part of which is upstream of its narrowest part, and whose profile is variable depending on the position of the annular element.
L'élément annulaire et la tuyère définissent ensemble un canal entourant sous forme annulaire l 'extrém ité aval de la tuyère. Ainsi, un écoulement d'air peut avoir lieu entre l'élément annulaire et l'extrémité aval de la tuyère. The annular element and the nozzle together define an annular surrounding channel at the downstream end of the nozzle. Thus, an air flow can take place between the annular element and the downstream end of the nozzle.
L'élément annulaire peut être déformable de manière à ce qu'une partie seulement de l'élément annulaire puisse être réglée en position. Avantageusement, le réglage de la position d'une partie au moins de l'élément annulaire permet de moduler l'écoulement d'air entre l'élément annulaire et la tuyère c'est-à-dire permet de moduler sa vitesse et sa pression en sortie de l'élément annulaire. Avantageusement, l'air circulant entre l'élément annulaire et la tuyère permet de gainer l'écoulement d'air en sortie de la tuyère et donc d'avoir une influence sur la pression de l'écoulement de l'air en sortie de la tuyère. The annular element may be deformable so that only a part of the annular element can be adjusted in position. Advantageously, adjusting the position of at least a portion of the annular element makes it possible to modulate the air flow between the annular element and the nozzle, that is to say, to modulate its speed and pressure. at the outlet of the annular element. Advantageously, the air circulating between the annular element and the nozzle makes it possible to shrink the air flow at the outlet of the nozzle and thus to have an influence on the pressure of the flow of air leaving the nozzle. nozzle.
Avantageusement, la zone de striction permet d'accélérer l'écoulement de l'air passant entre l'élément annulaire et la tuyère, par conséquent la pression en fin de zone de striction est plus faible que la pression ambiante, on appelle cela un effet de striction (ou effet de trompe). Ainsi, l'air circulant dans la tuyère s'écoule dans une zone de dépression au voisinage de l'extrémité aval de la tuyère. Ainsi, la pression de sortie de la tuyère et donc le taux de compression sont diminués. Advantageously, the zone of necking makes it possible to accelerate the flow of the air passing between the annular element and the nozzle, consequently the pressure at the end of the necking zone is smaller than the ambient pressure, this is called a necking effect (or trompe effect). Thus, the air flowing in the nozzle flows in a depression zone in the vicinity of the downstream end of the nozzle. Thus, the outlet pressure of the nozzle and therefore the compression ratio are decreased.
Avantageusement, plus l'effet de striction est fort, plus la pression en sortie de la zone de striction est faible, et donc plus la pression de sortie de la tuyère et le taux de compression sont faibles. Avantageusement, l'écoulement de l'air circulant entre l'élément annulaire et la tuyère préserve au maximum la structure des lignes de courant, en particulier en gardant les lignes de courant aussi proches que possible de celles présentes sans l'élément annulaire. Avantageusement, en fonctionnement de croisière du turboréacteur pendant lequel il n'est pas nécessaire de contrôler l'écoulement d'air en sortie de la tuyère, la position de l'élément annulaire peut être réglée de manière à ce qu'il forme avec la tuyère une zone de striction sensiblement nulle (ou uniforme). Dans cette configuration, l'air passant entre l'élément annulaire et la tuyère n'est alors pas sensiblement accéléré et n'a donc sensiblement pas d'effet sur la pression de l'écoulement d'air en sortie de la tuyère. Advantageously, the stronger the necking effect, the lower the pressure at the outlet of the necking zone, and therefore the lower the outlet pressure of the nozzle and the compression ratio are small. Advantageously, the flow of air flowing between the annular element and the nozzle maximizes the structure of the current lines, in particular by keeping the current lines as close as possible to those present without the annular element. Advantageously, in cruise operation of the turbojet during which it is not necessary to control the air flow at the outlet of the nozzle, the position of the annular element can be adjusted so that it forms with the nozzle a zone of necking substantially zero (or uniform). In this configuration, the air passing between the annular element and the nozzle is then not substantially accelerated and therefore has substantially no effect on the pressure of the air flow at the outlet of the nozzle.
Avantageusement, et même en fonctionnement de croisière du turboréacteur, l'élément annulaire est toujours incliné par rapport à l'extrémité aval de la tuyère en configuration de striction de telle manière que la zone de striction engendre une poussée dite de forme, c'est-à-dire une poussée rendue possible uniquement par la forme d'une pièce statique (de la même manière qu'un statoréacteur utilise forme particulière de manche statique d'entrée pour réaliser la compression de l'air y pénétrant), compensant la traînée de friction ajoutée par la présence de l'élément annulaire. Advantageously, and even in cruise operation of the turbojet engine, the annular element is always inclined with respect to the downstream end of the nozzle in a necking configuration such that the necking zone generates a so-called shape thrust, it is that is, a thrust made possible only by the shape of a static part (in the same way that a ramjet uses a particular form of static input shaft to compress the air entering it), compensating for the drag friction added by the presence of the annular element.
Selon une caractéristique optionnelle de l'invention, la paroi intérieure de l 'élément annulaire forme avec la tuyère une zone de convergence - divergence au regard du sens d'écoulement de l'air. Ainsi, la zone convergente située en amont de l'élément annulaire sert à obtenir l'effet de striction ou effet de trompe décrit plus haut, et la zone d i ve rg e n te e n a va l d e l 'élément annulaire permet avantageusement d'engendrer un accroissement de la force de poussée de l'ensemble formé par la tuyère et le turboréacteur. According to an optional feature of the invention, the inner wall of the annular element forms with the nozzle a zone of convergence - divergence with respect to the direction of flow of the air. Thus, the convergent zone situated upstream of the annular element serves to obtain the necking effect or trompe effect described above, and the dive region in which the annular element advantageously makes it possible to generate an increase the thrust force of the assembly formed by the nozzle and the turbojet engine.
Préférentiellement, la paroi externe de l'élément annulaire est sensiblement plane et les bords amont et aval de l'élément annulaire sont arrondis. Preferably, the outer wall of the annular element is substantially flat and the upstream and downstream edges of the annular element are rounded.
Selon une caractéristique optionnelle de l'invention, et dans le cas où l'élément annulaire présente cette forme convergente - divergente, la ligne de frontière entre les zones de convergence et de divergence de l'élément annulaire peut être située dans le plan dans lequel s'inscrit l'extrémité aval de la tuyère dans au moins l'une des positions de l'élément annulaire. According to an optional feature of the invention, and in the case where the annular element has this convergent-divergent form, the boundary line between the convergence and divergence zones of the annular element may be situated in the plane in which inscribes the downstream end of the nozzle in at least one of the positions of the annular element.
L'écoulement de l'air circulant entre l'élément annulaire et l'extrémité aval de la tuyère est ainsi accéléré jusqu'au plan dans lequel s'inscrit l'extrémité aval de la tuyère. A partir du plan dans lequel s'inscrit l'extrémité aval de la tuyère, l'écoulement de l'air en sortie de l'élément annulaire entre en contact avec l'écoulement de l'air en sortie de la tuyère avec une pression plus faible que la pression ambiante diminuant ainsi la pression de l'écoulement de l'air en sortie de la tuyère. Selon une caractéristique optionnelle de l'invention, l'élément annulaire est constitué d'une pluralité de volets rigides ou secteurs. The flow of the air flowing between the annular element and the downstream end of the nozzle is thus accelerated to the plane in which the downstream end of the nozzle is inscribed. From the plane in which the downstream end of the nozzle is inscribed, the flow of air at the outlet of the annular element comes into contact with the flow of air leaving the nozzle with a pressure lower than the ambient pressure thus decreasing the pressure of the flow of air at the outlet of the nozzle. According to an optional feature of the invention, the annular element consists of a plurality of rigid flaps or sectors.
On entend pa r vol ets rig id es d es vol ets q u i n e sont pas sensiblement déformables sous l'action de l'écoulement de l'air circulant entre l'élément annulaire et la tuyère et sous l'action de l'écoulement de l'air en sortie de tuyère. It is meant by theft and rigidity of flight and are not substantially deformable under the action of the flow of air flowing between the annular element and the nozzle and under the action of the flow of the air at the outlet of the nozzle.
Préférentiellement, les volets rigides sont répartis uniformément le long du contour de l'extrémité aval de la tuyère. Les volets rigides ainsi répartis permettent un écoulement de l'air entre l'élément annulaire et la tuyère de sorte que l'écoulement d'air en sortie de tuyère est sensiblement gainé par l'écoulement d'air en sortie du canal formé par l'élément annulaire et l'extrémité aval de la tuyère, le contrôle de la pression de l'écoulement de l'air en sortie de la tuyère est donc plus aisé. Selon une caractéristique optionnelle de l ' invention , l 'élément annulaire constitué d'une pluralité de volets rigides est mobile en rotation selon des axes tangents à la tuyère et sensiblement orthogonaux à l'axe de la tuyère. Preferably, the rigid flaps are evenly distributed along the contour of the downstream end of the nozzle. The rigid flaps thus distributed allow a flow of air between the annular element and the nozzle so that the air flow at the outlet of the nozzle is substantially sheathed by the flow of air at the outlet of the channel formed by the annular element and the downstream end of the nozzle, the control of the pressure of the air flow at the outlet of the nozzle is therefore easier. According to an optional feature of the invention, the annular element consisting of a plurality of rigid flaps is rotatable along axes tangent to the nozzle and substantially orthogonal to the axis of the nozzle.
Avantageusement, une légère augmentation de l'inclinaison des volets rigides de l'élément annulaire par rapport à l a tuyère de l'ordre de quelques degrés (par exemple 2 ou 3 degrés) permet un déplacement de l'extrém ité amont de l'élément annulaire de l'ordre du centimètre en même temps qu'un déplacement de l'extrémité aval de l'élément annulaire de telle manière q u e l 'on obtien n e u n effet d e striction , variant en fonction de l'inclinaison des volets rigides de l'élément annulaire. Advantageously, a slight increase in the inclination of the rigid flaps of the annular element relative to the nozzle of the order of a few degrees (for example 2 or 3 degrees) allows a displacement of the upstream end of the element. annular centimeter at the same time as a displacement of the downstream end of the annular element in such a way that one obtains a necking effect, varying according to the inclination of the rigid flaps of the element annular.
Les volets rigides sont montés mobiles en rotation autour d'un axe propre à chacun, chaque axe est porté par un support fixé sur l'extrémité aval de la tuyère. The rigid flaps are rotatably mounted about an axis proper to each, each axis is carried by a support fixed on the downstream end of the nozzle.
Selon une caractéristique optionnelle de l ' invention , l 'élément annulaire est mobile en translation, qu'il soit constitué par une pluralité de volets rigides ou de toute autre manière. Avantageusement, la mobilité en translation de l'élément annulaire constitue une manière simple de régler l'effet de striction According to an optional feature of the invention, the annular element is movable in translation, whether it is constituted by a plurality of rigid flaps or in any other manner. Advantageously, the mobility in translation of the annular element constitutes a simple way of adjusting the necking effect.
Avantageusement, quand l'élément annulaire est constitué de volets, les volets rigides peuvent être à la fois mobiles en translation et en rotation de manière à obtenir une plage d'effet de striction plus large et un réglage plus fin de la pression de l'écoulement d'air en sortie de la tuyère. Advantageously, when the annular element consists of flaps, the rigid flaps can be both movable in translation and in rotation so as to obtain a wider range of necking effect and a finer adjustment of the pressure of the flap. air flow at the outlet of the nozzle.
Selon une caractéristique optionnelle de l ' invention , l 'élément annulaire comprend des caissons gonflables. Avantageusement, les caissons gonflables sont déformables au moins au niveau de leur extrémité aval sous l'effet de la pression. According to an optional feature of the invention, the annular element comprises inflatable boxes. Advantageously, the inflatable chambers are deformable at least at their downstream end under the effect of pressure.
Ainsi, l'écoulement d'air passant dans le canal formé par l'élément annulaire constitué des caissons gonflables et la tuyère peut déformer les dits caissons. Thus, the flow of air passing through the channel formed by the annular element consisting of inflatable boxes and the nozzle can deform said boxes.
Les caissons gonflables peuvent être translatables et / ou montés mobiles en rotation autour d'un axe propre à chacun, chaque axe étant porté par un support fixé sur l'extrémité aval de la tuyère. The inflatable chambers can be translatable and / or rotatably mounted around an axis specific to each, each axis being carried by a support fixed on the downstream end of the nozzle.
Selon une caractéristique optionnelle de l'invention, la pression interne des caissons gonflables est régulée à l'aide d'un dispositif de type moteur à air comprimé. According to an optional feature of the invention, the internal pressure of the inflatable chambers is regulated by means of a device of the compressed air motor type.
Avantageusement, le dispositif de type moteur à air comprimé permet la régulation de la pression interne des caissons gonflables en fonction de la pression de l'écoulement de l'air en sortie de tuyère désirée. Avantageusement, on peut combiner la technologie des caissons gonflables avec celle des volets rig ides de tel le man ière que l'élément annulaire soit constitué d'une pluralité de volets chacun présentant une zone amont rigide et une zone aval déformable sous la pression constituée d'un caisson gonflable dont la pression interne peut être régulée. Advantageously, the device of the compressed air motor type allows the regulation of the internal pressure of the air chambers as a function of the pressure of the air flow at the outlet of the desired nozzle. Advantageously, the airbag technology can be combined with that of the rigid flaps such that the annular element consists of a plurality of flaps each having a rigid upstream zone and a deformable downstream zone under the pressure consisting of an inflatable box whose internal pressure can be regulated.
Selon une caractéristique optionnelle de l'invention, la section d'entrée dans la zone de striction présente une aire voisine ou supérieure à la section de sortie de la tuyère. Avantageusement, dans cette configuration l'effet de striction est utilisé pour accroître la poussée lors du décollage de l'aéronef et améliorer le rendement propulsif de la soufflante tout en maintenant un taux de dilution faible adapté au fonctionnement en croisière. En fonctionnement de croisière d u tu rboréacteu r, l 'élément annulaire est déplacé de telle manière que l'effet de striction soit sensiblement nul. Selon une caractéristique optionnelle de l'invention, la tuyère comprend un dispositif d'injection d'air sous pression modulable située au niveau de la tuyère. According to an optional feature of the invention, the inlet section in the necking zone has an area close to or greater than the exit section of the nozzle. Advantageously, in this configuration the necking effect is used to increase the thrust during take-off of the aircraft and improve the propulsive efficiency of the blower while maintaining a low dilution ratio suitable for cruising operation. In cruise operation of the rboreactant, the annular element is displaced in such a manner that the necking effect is substantially zero. According to an optional feature of the invention, the nozzle comprises a flexible pressurized air injection device located at the nozzle.
Le dispositif d'injection d'air sous pression modulable réalise une injection d'air dans le sens de l'amont vers l'aval de la tuyère et orienté de telle manière que l'écoulement d'air en résultant pénètre dans le canal formé par l'élément annulaire et la tuyère. The modular pressurized air injection device performs an air injection in the upstream direction downstream of the nozzle and is oriented such that the resulting air flow enters the formed channel. by the annular element and the nozzle.
Préférentiellement, le dispositif d'injection d'air sous pression modulable est situé en amont de l'élément annulaire à proximité immédiate de l'extrémité amont de l'élément annulaire ou bord d 'attaq ue de l 'élément annulaire. Preferably, the device for injecting pressurized air is located upstream of the annular element in the immediate vicinity of the upstream end of the annular element or edge of attack of the annular element.
Avantageusement, un tel dispositif d'injection d'air sous pression modulable combiné avec l'élément annulaire dispense de changer la position de l'élément annulaire (élément annulaire fixe par rapport à la tuyère) pour contrôler la pression de l'écoulement d'air en sortie de la tuyère. Advantageously, such a modular pressurized air injection device combined with the annular element eliminates the need to change the position of the annular element (fixed annular element relative to the nozzle) in order to control the pressure of the flow. air out of the nozzle.
On décrit à présent, à titre d'exemples non limitatifs, plusieurs modes de réalisation possibles de l'invention, en référence aux figures annexées ; sur l'ensemble des figures, des références identiques ou analogues désignent des organes ou ensembles d'organes identiques ou analogues : Several possible embodiments of the invention will now be described by way of nonlimiting examples, with reference to the appended figures; in the set of figures, identical or similar references denote identical or similar organs or sets of members:
- la figure 1 a est une vue en perspective d'une nacelle équipée d'une tuyère selon un premier mode de réalisation de la présente invention,FIG. 1a is a perspective view of a nacelle equipped with a nozzle according to a first embodiment of the present invention,
- la figure 1 b est une vue schématique d'une tuyère selon le premier mode de réalisation de la présente invention, FIG. 1b is a schematic view of a nozzle according to the first embodiment of the present invention,
- la figure 2a représente une vue en perspective d'une nacelle équipée d'une tuyère selon un second mode de réalisation de la présente invention, - la figure 2b est une vue schématique d'une tuyère selon le second mode de réalisation de la présente invention, FIG. 2a represents a perspective view of a nacelle equipped with a nozzle according to a second embodiment of the present invention, FIG. 2b is a schematic view of a nozzle according to the second embodiment of the present invention,
- la figure 3 est une vue schématique d'une tuyère selon un troisième mode de réalisation de la présente invention,  FIG. 3 is a schematic view of a nozzle according to a third embodiment of the present invention,
- la figure 4 est une vue schématique d'une tuyère selon un quatrième mode de réalisation de la présente invention,  FIG. 4 is a schematic view of a nozzle according to a fourth embodiment of the present invention,
- la figure 5 est une vue en coupe d'une tuyère selon un cinquième mode de réalisation de la présente invention. En référence aux figures 1 a et 1 b, une nacelle 1 est équipée d'une tuyère 2 com prenant u n d ispos itif 3 de rég u lation d e l a pression d'un écoulement d'air 4 en sortie 5 de la tuyère 2. Le d ispositif 3 comprend un élément annulaire 6 entourant l'extrémité aval 7 de la tuyère 2 et à distance de la d ite tuyère 2 , et des moyens 8 de réglage de la position de l 'élément annulaire 6 par translation de l'élément annulaire 6 selon un axe sensiblement parallèle à l'axe Δ de la tuyère 2. L'élément annulaire 6 est conformé de telle man ière qu'il forme avec l'extrém ité aval 7 de la tuyère 2 u ne zone 9 de convergence 9a - divergence 9b au regard d'un écoulement d'air 10 entre l'élément annulaire 6 et la tuyère 2. Les moyens 8 de réglage de la position de l'élément annulaire 6 par translation de l'élément annulaire 6 sont conformés de telle manière que le réglage de la position de l'élément annulaire 6 se fait de manière continue par opposition à la manière discrète qui est moins flexible et ne permet pas un réglage aussi fin . Toutefois, on pourrait envisager d'utiliser des moyens 8 de réglage tels que l'on aurait un réglage discrétisé de la position de l'élément annulaire 6.  - Figure 5 is a sectional view of a nozzle according to a fifth embodiment of the present invention. With reference to FIGS. 1a and 1b, a nacelle 1 is equipped with a nozzle 2 comprising a pressure regulating device 3 of the pressure of an air flow 4 at the outlet 5 of the nozzle 2. ispositif 3 comprises an annular element 6 surrounding the downstream end 7 of the nozzle 2 and at a distance from the nozzle die 2, and means 8 for adjusting the position of the annular element 6 by translation of the annular element 6 along an axis substantially parallel to the axis Δ of the nozzle 2. The annular element 6 is shaped in such a way that it forms with the downstream end 7 of the nozzle 2 a convergence zone 9a 9a - divergence 9b with regard to an air flow 10 between the annular element 6 and the nozzle 2. The means 8 for adjusting the position of the annular element 6 by translation of the annular element 6 are shaped in such a way that the position of the annular element 6 is adjusted continuously ition in the unobtrusive way that is less flexible and does not allow such a fine tuning. However, it could be envisaged to use adjustment means 8 such that there would be a discretized adjustment of the position of the annular element 6.
L'écoulement d'air 10, en passant par la section d'entrée 1 1 dans la zone 9 de convergence 9a - divergence 9b, subit un effet de striction, c'est-à- dire que l'écoulement d'air 10 est accéléré jusqu'à la section de sortie 12 de la zone 9 d e convergence 9a - divergence 9b. A la section de sortie 12, l'écoulement d'air 10 subit une dilatation accentuée par le fait que l'écoulement d'air 4 au niveau de la sortie 5 de la tuyère 2 « aspire » l'écoulement d'air 10 au voisinage de la section de sortie 1 2, créant a insi au n iveau de la partie divergente de la zone 9 une dépression de telle sorte que la pression dans cette partie d ivergente est inférieure à la pression atmosphérique . Ainsi, l'écoulement d'air 4 en sortie 5 de la tuyère 2 subit une dépression en passant la sortie 5 de la tuyère 2 et pénètre plus facilement dans l'atmosphère. La pa rtie d iverg ente de la zone 9 permet d 'obten i r u ne force de poussée supplémentaire à celle déjà fournie par l'écoulement d'air 4. Cette configuration permet de réduire la consommation d'énergie par le turboréacteur, et de limiter les risques de pompages du turboréacteur. The air flow 10, passing through the inlet section 11 in the convergence zone 9a-divergence 9b, undergoes a necking effect, that is to say that the air flow 10 is accelerated to the output section 12 of the convergence zone 9a 9a - divergence 9b. At the outlet section 12, the air flow 10 undergoes an increased expansion by the fact that the air flow 4 at the outlet 5 of the nozzle 2 "sucks" the air flow 10 to the adjacent to the outlet section 12, creating a negative pressure at the level of the diverging portion of the zone 9 so that the pressure in this diverging portion is lower than the atmospheric pressure. Thus, the air flow 4 at the outlet 5 of the nozzle 2 is depressed by passing the outlet 5 of the nozzle 2 and penetrates more easily into the atmosphere. The Part of the zone 9 makes it possible to obtain additional thrust force to that already provided by the air flow 4. This configuration makes it possible to reduce the energy consumption by the turbojet engine, and to limit the pumping risks of the turbojet.
Lorsque l'élément annulaire 6 est translaté selon l'axe Δ vers l'aval de la tuyère 2, la section d'entrée 1 1 et la section de sortie 12 s'agrandissent, diminuant ainsi l'effet de striction provoqué par la partie convergente de la zone 9 de convergence 9a - divergence 9b. Lorsque l'élément annulaire 6 est translaté selon l'axe Δ vers l'amont de la tuyère 2, la section d'entrée 1 1 et la section de sortie 12 se réduisent, augmentant ainsi l'effet de striction provoqué par la partie convergente de la zone 9 de convergence 9a - divergence 9b.  When the annular element 6 is translated along the axis Δ downstream of the nozzle 2, the inlet section 11 and the outlet section 12 expand, thereby reducing the necking effect caused by the part convergent of the convergence zone 9a 9a - divergence 9b. When the annular element 6 is translated along the axis Δ upstream of the nozzle 2, the inlet section 11 and the outlet section 12 are reduced, thereby increasing the necking effect caused by the converging portion of the convergence zone 9a 9a - divergence 9b.
En référence aux figures 2a et 2b, une nacelle 1 est équipée d'une tuyère 2 com pren a nt u n d ispos itif 3 d e rég u l ation d e l a press ion de l'écoulement d'air 4 en sortie 5 de la tuyère 2. Le dispositif 3 comprend une plural ité de volets rigides 6a, 6b, 6c formant élément annulaire 6 entourant l'extrémité aval 7 de la tuyère 2 de manière uniformément répartis et à distance de la dite tuyère 2, et des moyens 8 de réglage de la position par rotation des volets rigides chacun selon un axe Δ' tangent à l'extrémité aval 7 de la tuyère 2 et orthogonal à l'axe Δ de la tuyère 2. Les volets rig ides 6a, 6b, 6c sont conformés de telle manière que chacun forme avec l'extrém ité aval 7 de la tuyère 2 une zone 9 de convergence 9a au regard d'un écoulement d'air 1 0 entre le volet rigide 6a, 6b, 6c et la tuyère 2. Les moyens 8 de réglage de la position des volets rigides 6a, 6b, 6c par rotation des volets rigides 6a, 6b, 6c sont conformés de telle manière que le réglage de la position des volets rigides 6a, 6b, 6c se fait de manière continue par opposition à la manière discrète qui est moins flexible et ne permet pas un réglage aussi fin. Toutefois, on pourrait envisager d'util iser des moyens 8 de réglage tels que l'on aurait un réglage discrétisé de la position des volets 6a, 6b, 6c. With reference to FIGS. 2a and 2b, a nacelle 1 is equipped with a nozzle 2 comprising and regulating the pressure of the air flow 4 at the outlet 5 of the nozzle 2. Device 3 comprises a plurality of rigid flaps 6a, 6b, 6c forming an annular element 6 surrounding the downstream end 7 of the nozzle 2 in a uniformly distributed manner and at a distance from said nozzle 2, and means 8 for adjusting the position by rotating the rigid flaps each along an axis Δ 'tangential to the downstream end 7 of the nozzle 2 and orthogonal to the axis Δ of the nozzle 2. The rigid flaps 6a, 6b, 6c are shaped so that each form with the downstream end 7 of the nozzle 2 a zone 9 of convergence 9a with respect to an air flow 1 0 between the rigid flap 6a, 6b, 6c and the nozzle 2. The means 8 for adjusting the position of the rigid flaps 6a, 6b, 6c by rotation of the rigid flaps 6a, 6b, 6c are shaped in such a way re that the adjustment of the position of the rigid flaps 6a, 6b, 6c is continuous as opposed to the discrete manner which is less flexible and does not allow such a fine adjustment. However, it would be possible to use adjustment means 8 such that there would be a discretized adjustment of the position of the flaps 6a, 6b, 6c.
L'écoulement d'air 10, en passant par la section d'entrée 1 1 dans la zone 9 de convergence 9a, subit un effet de striction. A la section de sortie 12, l'écoulement d'air 10 subit une dilatation accentuée par le fait que l'écoulement d'air 4 au niveau de la sortie 5 de la tuyère 2 « aspire » l'écoulement d'air 10 au voisinage de la section de sortie 12, créant ainsi une dépression de telle sorte que la pression en aval au voisinage de la section de sortie 1 2 est inférieure à la pression atmosphérique. Ainsi, l'écoulement d'air 4 en sortie 5 de la tuyère 2 subit une dépression en passant la sortie 5 de la tuyère 2 et pénètre plus facilement dans l'atmosphère. Cette configuration permet de réduire la consommation d'énerg ie par le turboréacteur, et de l im iter les risques de pompages du turboréacteur. The air flow 10, through the inlet section 1 1 in the convergence zone 9a, undergoes a necking effect. At the outlet section 12, the air flow 10 undergoes an increased expansion by the fact that the air flow 4 at the outlet 5 of the nozzle 2 "sucks" the air flow 10 to the adjacent the outlet section 12, thereby creating a depression so that the downstream pressure in the vicinity of the outlet section 12 is lower than the atmospheric pressure. Thus, the air flow 4 at the outlet 5 of the nozzle 2 undergoes a depression passing the outlet 5 of the nozzle 2 and penetrates more easily into the atmosphere. This configuration makes it possible to reduce the energy consumption by the turbojet engine and to reduce the risks of pumping the turbojet engine.
Lorsque les volets rigides 6a, 6b, 6c pivotent chacun selon son axe de rotation tangent à l 'extrém ité aval 7 de la tuyère 2, le rapport section d'entrée 1 1 sur section de sortie 1 2 de chaque volet ou rapport de striction varie, faisant ainsi varier l'effet de striction provoqué par l a zon e 9 d e convergence 9a de chaque volet. Plus le rapport de striction est grand, plus l'effet de striction est fort dans la zone 9 de convergence 9a.  When the rigid flaps 6a, 6b, 6c each pivot along its axis of rotation tangential to the downstream end 7 of the nozzle 2, the input section ratio 1 1 output section 1 2 of each flap or necking report varies, thereby varying the necking effect caused by convergence zone 9a 9a of each component. The greater the necking ratio, the stronger the necking effect is in the convergence zone 9a.
Préférentiellement, les vo l ets rig id es 6a, 6b, 6c pivotent simultanément, et de telle manière que l'inclinaison des volets rigides 6a, 6b, 6c est la même pour tous les volets rigides 6a, 6b, 6c par rapport à la tuyère. En référence à la figure 3, une tuyère 2 comprend un dispositif 3 de régulation de la pression d'un écoulement d'air 4 en sortie 5 de la tuyère 2. Le dispositif 3 comprend une pluralité de caissons gonflables 6a, 6b, 6c formant élément annulaire 6 entourant l'extrémité aval 7 de la tuyère 2 de manière uniformément répartis et à distance de la dite tuyère 2. Les caissons gonflables 6a, 6b, 6c sont conformés de telle manière que leur extrémité amont soit fixée sans degré de liberté sur la tuyère par un moyen de fixation 8a, qu'ils soient déformables sous l'action de l'écoulement d'air 1 0, et que chacun forme avec l'extrémité aval 7 de la tuyère 2 une zone 9 de convergence 9a au regard de l'écoulement d'air 1 0 entre le caisson gonflable 6a , 6b, 6c et la tuyère 2. L'écoulement d'air 1 0 joue donc le rôle de moyen 8 de réglage de la position des caissons gonflables.  Preferably, the rigid beams 6a, 6b, 6c pivot simultaneously, and in such a way that the inclination of the rigid flaps 6a, 6b, 6c is the same for all the rigid flaps 6a, 6b, 6c with respect to the nozzle. Referring to Figure 3, a nozzle 2 comprises a device 3 for regulating the pressure of an air flow 4 at the outlet 5 of the nozzle 2. The device 3 comprises a plurality of air chambers 6a, 6b, 6c forming annular element 6 surrounding the downstream end 7 of the nozzle 2 in a uniformly distributed manner and at a distance from said nozzle 2. The inflatable caissons 6a, 6b, 6c are shaped in such a way that their upstream end is fixed without any degree of freedom on the nozzle by a fastening means 8a, that they are deformable under the action of the air flow 1 0, and that each forms with the downstream end 7 of the nozzle 2 a zone 9 of convergence 9a to the the air flow 1 0 between the inflatable chamber 6a, 6b, 6c and the nozzle 2. The air flow 1 0 therefore acts as means 8 for adjusting the position of the air chambers.
L'écoulement d'air 10, en passant par la section d'entrée 1 1 dans la zone 9 de convergence 9a, subit un effet de striction. A la section de sortie 12, l'écoulement d'air 10 subit une dilatation accentuée par le fait que l'écoulement d'air 4 au niveau de la sortie 5 de la tuyère 2 « aspire » l'écoulement d'air 10 au voisinage de la section de sortie 12, créant ainsi une dépression de telle sorte que la pression en aval au voisinage de la section de sortie 1 2 est inférieure à la pression atmosphérique. Ainsi, l'écoulement d'air 4 en sortie 5 de la tuyère 2 subit une dépression en passant la sortie 5 de la tuyère 2 et pénètre plus facilement dans l'atmosphère. Cette config u ration permet de réd u ire l a consommation d'énergie par le turboréacteur, et de limiter les risques de pompages du turboréacteur. The air flow 10, through the inlet section 1 1 in the convergence zone 9a, undergoes a necking effect. At the outlet section 12, the air flow 10 undergoes an increased expansion by the fact that the air flow 4 at the outlet 5 of the nozzle 2 "sucks" the air flow 10 to the adjacent the outlet section 12, thereby creating a depression so that the downstream pressure in the vicinity of the outlet section 12 is lower than the atmospheric pressure. Thus, the air flow 4 at the outlet 5 of the nozzle 2 is depressed by passing the outlet 5 of the nozzle 2 and penetrates more easily into the atmosphere. This configuration makes it possible to reduce the energy consumption by the turbojet engine, and to limit the risks of pumping the turbojet engine.
Lorsque les caissons gonflables 6a, 6b, 6c se déforment chacun sous l'action de l'écoulement d'air 10, le rapport section d'entrée 1 1 sur section de sortie 1 2 de chaque caisson gonflable 6a, 6b, 6c, ou rapport de striction, varie, fa isant a insi varier l 'effet de striction provoq ué par la zone 9 de convergence 9a de chaque caisson gonflable 6a, 6b, 6c.  When the air chambers 6a, 6b, 6c are each deformed under the action of the air flow 10, the ratio of the inlet section 1 1 to the outlet section 1 2 of each air box 6a, 6b, 6c, or necking ratio, varies, so as to vary the necking effect provoked by the convergence zone 9a 9a of each inflatable box 6a, 6b, 6c.
La pression interne de chaque caisson gonflable 6a , 6b, 6c est sensiblement identique et réglable sous l'action d'un moteur à air comprimé (non représenté) compris dans le dispositif 3 de régulation de la pression d'un écoulement d'air 4 en sortie 5 de la tuyère 2. Ainsi la déformation subie par les caissons gonflables 6a, 6b, 6c est réglable puisque les caissons gonflables 6a, The internal pressure of each inflatable box 6a, 6b, 6c is substantially identical and adjustable under the action of a compressed air motor (not shown) included in the device 3 for regulating the pressure of an air flow 4 at the outlet 5 of the nozzle 2. Thus the deformation undergone by the inflatable caissons 6a, 6b, 6c is adjustable since the inflatable chambers 6a,
6b, 6c ont une « rigidité » qui varie en fonction de leur pression interne et par conséquent une réponse en déformation différente en fonction de la pression interne et de l'action de l'écoulement d'air 10. Dans ce cas de figure précis, le moteur à air comprimé (non représenté) et l'écoulement d'air 10 jouent le rôle de moyens 8 de réglage de la position des caissons gonflables par rapport à la tuyère 2. En référence à la figure 4, une tuyère 2 comprend un dispositif 3 de régulation de la pression d'un écoulement d'air 4 en sortie 5 de la tuyère 2 tel que divulgué dans les figures 2a et 2b et la description qui y est associée, le dispositif 3 comprenant ici en sus de ce mode de réalisation des figures 2a et 2b un moyen d'injection d'air 13 permettant de réguler l'écoulement d'air 1 0 entrant dans la zone 9 de convergence 9a selon le mode de réalisation des figures 2a et 2b. 6b, 6c have a "rigidity" which varies according to their internal pressure and therefore a different deformation response depending on the internal pressure and the action of the air flow 10. In this specific case , the compressed air motor (not shown) and the air flow 10 act as means 8 for adjusting the position of the air chambers with respect to the nozzle 2. With reference to FIG. 4, a nozzle 2 comprises a device 3 for regulating the pressure of an air flow 4 at the outlet 5 of the nozzle 2 as disclosed in FIGS. 2a and 2b and the description associated therewith, the device 3 comprising here in addition to this mode embodiment of FIGS. 2a and 2b an air injection means 13 making it possible to regulate the flow of air 1 0 entering the zone 9 of convergence 9a according to the embodiment of FIGS. 2a and 2b.
Ce moyen d'injection d'air 13 comprend un moteur à air comprimé (non représenté) et un orifice d'éjection de l'air comprimé dans la zone 9 de convergence 9a. Une fois injecté, le dit air comprimé a une influence variable en fonction de la pression à laquelle il est injecté dans la zone 9 de convergence 9a sur les caractéristiques de l'écoulement d'air 10.  This air injection means 13 comprises a compressed air motor (not shown) and an outlet orifice for the compressed air in the zone 9 of convergence 9a. Once injected, said compressed air has a variable influence as a function of the pressure at which it is injected into the zone 9 of convergence 9a on the characteristics of the air flow 10.
Un moyen d'injection d'air 13 est disposé en amont de chaque volet rigide 6a, 6b, 6c au voisinage de la section d'entrée 1 1 des dits volets rigides 6a, 6b, 6c permettant ainsi un réglage dès l'amont de l'écoulement d'air 10. En référence à la figure 5, une tuyère 2 comprend un dispositif 3 de régulation de la pression d'un écoulement d'air 4 en sortie 5 de la tuyère 2 tel que divulgué dans les figures 1 a et 1 b, l'élément annulaire 6 présentant des dimensions telles que la section d'entrée 1 1 de la partie convergente de la zone 9 de convergence 9a - divergence 9b présente une aire d'une valeur au voisinage de ou supérieure à celle de la section de sortie 5 de la tuyère 2. An air injection means 13 is disposed upstream of each rigid flap 6a, 6b, 6c in the vicinity of the inlet section 1 1 of said rigid flaps 6a, 6b, 6c thus allowing adjustment upstream of the air flow 10. With reference to FIG. 5, a nozzle 2 comprises a device 3 for regulating the pressure of an air flow 4 at the outlet 5 of the nozzle 2 as disclosed in FIGS. 1a and 1b, the annular element 6 having dimensions such that the inlet section 1 1 of the convergent portion of the convergence zone 9a-divergence 9b has an area of a value in the vicinity of or greater than that of the outlet section 5 of the nozzle 2.
Dans ce cas précis, l'effet de trompe est utilisé pour accroître la poussée lors du décollage. En croisière l'élément annulaire 6 peut être déplacé grâce aux moyens 8 pour rendre cet effet plus modeste et retrouver sensiblement la ligne de fonctionnement de la nacelle 1 sans élément annulaire 6.  In this case, the horn effect is used to increase the thrust during take-off. In cruising the annular element 6 can be moved by the means 8 to make this effect more modest and substantially find the operating line of the nacelle 1 without annular element 6.
Il va de soi que l'invention n'est pas limitée aux modes de réalisation décrits ci-dessus à titre d'exemples mais qu'elle comprend tous les équivalents techniques et les variantes des moyens décrits ainsi que leurs combinaisons possibles. It goes without saying that the invention is not limited to the embodiments described above as examples but that it includes all technical equivalents and variants of the means described and their possible combinations.

Claims

REVENDICATIONS
1 . Tuyère (2) de sortie de flux secondaire d'un turboréacteur double flux comprenant un dispositif (3) de régulation de la pression d'un écoulement d'air (4) en sortie (5) de la tuyère (2) caractérisée en ce que le dit dispositif (3) comprend un élément annulaire (6) entourant l'extrémité aval (7) de la tuyère (2) et à distance de celle-ci, et des moyens (8) de réglage de la position d'au moins une partie de l'élément annulaire (6) par rapport à l'extrémité aval (7) de la tuyère (2), et en ce que l'élément annulaire (6) forme avec l'extrémité aval (7) de la tuyère (2) une zone (9) de striction dont la partie la plus évasée (1 1 ) se situe en amont de sa partie la plus étrécie (12), et dont le profil est variable en fonction de la position de l'élément annulaire (6).  1. Secondary flow outlet nozzle (2) for a turbofan engine comprising a device (3) for regulating the pressure of an air flow (4) at the outlet (5) of the nozzle (2), characterized in that said device (3) comprises an annular element (6) surrounding the downstream end (7) of the nozzle (2) and at a distance therefrom, and means (8) for adjusting the position of the least part of the annular element (6) with respect to the downstream end (7) of the nozzle (2), and in that the annular element (6) forms with the downstream end (7) of the nozzle (2) a necking zone (9), the widest part (1 1) of which is upstream of its narrowest part (12), and whose profile is variable as a function of the position of the element annular (6).
2. Tuyère (2) selon l 'u ne q uelconq ue des revend ications précédentes caractérisée en ce que la paroi intérieure de l'élément annulaire (6) forme avec la tuyère une zone (9) de convergence (9a) - divergence (9b) au regard du sens d'écoulement d'air.  2. A nozzle (2) according to the above-mentioned prior art, characterized in that the inner wall of the annular element (6) forms with the nozzle a zone (9) of convergence (9a) - divergence ( 9b) with regard to the direction of air flow.
3. Tuyère (2) selon la revendication 2caractérisée en ce que la ligne de frontière entre les zones de convergence (9a) et de divergence (9b) de l'élément annulaire (6) peut être située dans le plan dans lequel s'inscrit l'extrémité aval (7) de la tuyère (2) dans au moins une des positions de l'élément annulaire (6).  3. nozzle (2) according to claim 2characterized in that the boundary line between the convergence zones (9a) and divergence (9b) of the annular element (6) can be located in the plane in which is inscribed the downstream end (7) of the nozzle (2) in at least one of the positions of the annular element (6).
4. Tuyère (2) selon l 'u ne q uelconq ue des revend ications précédentes caractérisée en ce que l'élément annulaire (6) est constitué d'une pluralité de volets rigides (6a, 6b, 6c).  4. nozzle (2) according to u uconq ue previous revendications characterized in that the annular element (6) consists of a plurality of rigid flaps (6a, 6b, 6c).
5. Tuyère (2) selon la revendication 4 caractérisée en ce que l'élément annulaire (6) est mobile en rotation selon des axes (Δ') tangents à la tuyère (2) et sensiblement orthogonaux à l'axe (Δ) de la tuyère (2).  5. nozzle (2) according to claim 4 characterized in that the annular element (6) is rotatable along axes (Δ ') tangent to the nozzle (2) and substantially orthogonal to the axis (Δ) of the nozzle (2).
6. Tuyère (2 ) selon l 'u ne q uelconq ue des revend ications précédentes caractérisée en ce que l'élément annulaire (6) est mobile en translation.  6. nozzle (2) according to the uuelconq ue previous revendications characterized in that the annular element (6) is movable in translation.
7. Tuyère (2 ) selon l 'u ne q uelconq ue des revend ications précédentes caractérisée en ce que l'élément annulaire (6) comprend des caissons gonflables (6a, 6b, 6c).  7. nozzle (2) according to u uconq ue any preceding revendications characterized in that the annular element (6) comprises inflatable caissons (6a, 6b, 6c).
8. Tuyère (2) selon la revendication 7 caractérisée en ce que la pression interne des caissons gonflables (6a, 6b, 6c) est régulée à l'aide d'un dispositif de type moteur à air comprimé. 8. nozzle (2) according to claim 7 characterized in that the internal pressure of the inflatable chambers (6a, 6b, 6c) is controlled by means of a device type compressed air motor.
9. Tuyère (2) selon l'une quelconque des revendications précédentes caractérisée en ce que la section d'entrée (11 ) dans la zone (9) de striction présente une aire voisine ou supérieure à la section de sortie (5) de la tuyère (2). 9. nozzle (2) according to any one of the preceding claims characterized in that the inlet section (11) in the zone (9) of necking has an area close to or greater than the outlet section (5) of the nozzle (2).
10. Tuyère (2) selon l'une quelconque des revendications précédentes caractérisée en ce qu'elle comprend un dispositif d'injection d'air sous pression modulable située au niveau de la tuyère (2).  10. nozzle (2) according to any one of the preceding claims characterized in that it comprises a device for injection of pressurized air pressure located at the nozzle (2).
11. Nacelle (1) équipée d'une tuyère (2) selon l'une quelconque des revendications précédentes.  11. Nacelle (1) equipped with a nozzle (2) according to any one of the preceding claims.
EP14705821.8A 2013-01-16 2014-01-16 Nacelle jet pipe with devices for regulating pressure Withdrawn EP2946101A1 (en)

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WO2014111663A1 (en) 2014-07-24
RU2015133708A (en) 2017-02-22
CN104937250A (en) 2015-09-23
US20160040624A1 (en) 2016-02-11
CA2897266A1 (en) 2014-07-24
FR3000994A1 (en) 2014-07-18
BR112015015166A2 (en) 2017-07-11

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