WO2009122026A1 - Bypass turbojet engine nacelle - Google Patents

Bypass turbojet engine nacelle Download PDF

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Publication number
WO2009122026A1
WO2009122026A1 PCT/FR2009/000229 FR2009000229W WO2009122026A1 WO 2009122026 A1 WO2009122026 A1 WO 2009122026A1 FR 2009000229 W FR2009000229 W FR 2009000229W WO 2009122026 A1 WO2009122026 A1 WO 2009122026A1
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WO
WIPO (PCT)
Prior art keywords
nozzle
nacelle
section
rod
movable
Prior art date
Application number
PCT/FR2009/000229
Other languages
French (fr)
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 WO2009122026A1 publication Critical patent/WO2009122026A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the invention relates to a turbojet turbojet engine nacelle.
  • An aircraft is driven by several turbojets each housed in a nacelle also housing a set of ancillary actuators related to its operation and providing various functions when the turbojet engine is in operation or stopped.
  • These ancillary actuating devices comprise in particular a mechanical system for actuating thrust reversers.
  • a nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing a thrust reverser means and intended to surround the combustion chamber of the turbojet engine. , and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
  • the modern nacelles are intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air (also called primary flow) from the combustion chamber of the turbojet engine, and a flow of cold air (secondary flow) flowing outside the turbojet through an annular passage, also called vein, formed between a shroud of the turbojet engine and an inner wall of the nacelle.
  • the two air flows are ejected from the turbojet engine from the rear of the nacelle.
  • the invention is not limited to the case of nacelles equipped with an inverter but also applies to the case of said nacelles said smooth, the invention will be described below mainly in the case of a nacelle with inverter.
  • the role of a thrust reverser is, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine.
  • the inverter obstructs the cold flow vein and directs the latter towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft.
  • the movable cowl belongs to the rear section and has a downstream side forming an ejection nozzle for channeling the ejection of the air flows.
  • This nozzle can come in addition to a primary nozzle channeling the hot flow and is then called secondary nozzle.
  • the mobile cowl is thus equipped, as is known from document US Pat. No. 5,806,302, with at least one nozzle movable relative to said movable cowl, so as to adjust the ejection section of the annular channel as a function of the position of said nozzle.
  • the mobile nozzle is also referred to as the movable structure for adjusting the nozzle section.
  • Each moving part namely the reverse thrust cover on the one hand, and the movable nozzle on the other hand, is actuated by a dedicated actuator.
  • the French application FR 06/05512 also describes a variable nozzle system and discloses the use of a telescopic jack whose first rod is intended to actuate the movable cowl while the second rod is intended for adjusting the nozzle.
  • a telescopic jack whose first rod is intended to actuate the movable cowl while the second rod is intended for adjusting the nozzle.
  • the invention aims to remedy this drawback and relates for this purpose to a turbojet engine nacelle comprising a downstream section equipped with a variable nozzle device, comprising a nozzle section mounted movably along a substantially longitudinal axis of the nacelle relative to the latter inside a structure of the downstream section, the nozzle section being adapted to be actuated by at least one actuator comprising a first rod passing through the structure of the downstream section inside which said section is mounted nozzle, characterized in that the structure and the nozzle comprise at least one sealing means arranged to isolate the interior of the nacelle from the outside of the nacelle through the assembly formed by the structure and the section of nozzle.
  • sealing means isolating the entire structure / nozzle greatly limits or even prevent any air leakage from inside the nacelle (high pressure) to the outside of the nacelle (low pressure) to through the downstream section of the latter. This generally improves aeronautical performance by improving the ejection of air flows through the nozzle section and thus the thrust generated by the propulsion unit.
  • the present invention may relate indifferently to a smooth nacelle, or a nacelle equipped with a thrust reverser device, the structure on which is mounted movable the nozzle section may be a fixed structure or a movable hood inverter.
  • the structure inside which the nozzle section is mounted is a movable thrust reverser cowl, said movable cowl being mounted in translation in a direction substantially parallel to a longitudinal axis of the nacelle adapted to pass alternately between a closing position in which it ensures the aerodynamic continuity of the nacelle and covers means of deflection, to an open position in which it opens a passage in the nacelle and discovers the deflection means, the assembly being adapted to be operated by at least one dual action actuator comprising a first rod connected to the movable hood and a second rod passing through the movable hood and connected to the movable nozzle.
  • the sealing means make it possible to greatly reduce, or even completely prevent, a circulation path between the outside and the inside of the nacelle through the assembly formed by the mobile cowl (the structure) and the nozzle. Indeed, the pressure prevailing outside the nacelle being lower than that prevailing inside, there would be air leakage through the hood / nozzle assembly, and loss of a part of the thrust flow, which reduces aeronautical performance.
  • the sealing means comprise a peripheral seal disposed between the base of the rod of the actuator connected to the nozzle section and an internal wall of the structure, upstream of a point of connection between the rod and said structure.
  • the base of the rod connected to the nozzle section is the first rod, linked to the movable cowl.
  • the sealing means comprise a peripheral seal disposed between the base of the rod of the actuator connected to the nozzle section and an internal wall of the structure, downstream of a point of connection between the rod and said structure.
  • the sealing means comprise a nozzle gasket disposed between a face of the nozzle oriented towards the inside of the nacelle and a wall of the structure.
  • the sealing means comprise a nozzle gasket disposed between a face of the nozzle oriented towards the outside of the nacelle and a wall of the structure.
  • Figure 1 is a schematic sectional view of a downstream section of a nacelle smooth according to the invention.
  • Figures 2 to 7 are schematic sectional views of several embodiments of the invention on a downstream section of a nacelle equipped with a thrust reversal device.
  • a nacelle is intended to constitute a tubular housing for a turbofan engine (not shown) with a large dilution ratio and serves to channel the air flows it generates through the blades of a blower (not shown), namely a hot air flow through a combustion chamber (not shown) of the turbojet, and a cold air flow flowing outside the turbojet (F).
  • a nacelle generally has a structure comprising a front section forming an air inlet, a central section surrounding the fan of the turbojet, and a downstream section surrounding the turbojet and may include a thrust reversal system.
  • the downstream section comprises an external structure optionally comprising a thrust reversal system and an internal structure
  • Figure 1 illustrates the case of a nacelle smooth, that is to say comprising a downstream section 1 comprising an outer section not equipped with a thrust reverser device.
  • This downstream section comprises a fixed part 11 having a front frame 11a on which is fixed a downstream structure 12 inside which is mounted a nozzle section 13 movable in translation along a substantially longitudinal axis of the nacelle.
  • This nozzle section 13 is driven in translation by a rod 14 of a jack 15 fixed in the fixed part and whose rod 14 passes through the downstream structure 12 through an orifice 18.
  • the nozzle section In the absence of leakage measurement, the nozzle section has an internal surface in communication with the vein 3 and an outer surface in communication with the outside of the nacelle. As a result, there may be a loss of airflow.
  • the downstream section 1 comprises a first seal 20 disposed substantially at level of the front frame 11 around the cylinder 15 upstream of the rod 14 between said cylinder 15 and a wall of the fixed structure 12 upstream of the orifice 18.
  • This first seal 20 thus prevents any loss of air flow to the fixed portion 11 of the downstream section 1.
  • the seal is also ensured by a second seal 21 disposed between an upper surface of the nozzle 13 and an inner wall of the downstream structure 12.
  • the second seal 21 thus prevents any leakage of the air flow to the outside of the nacelle and the interior of the downstream structure 12 is substantially at the outlet pressure of the vein 3.
  • FIG. 2 illustrates the case of a nacelle equipped with a thrust reverser device, that is to say one comprising a downstream section equipped with a cover 30 movable in translation along a substantially longitudinal axis of the nacelle between a closed position in which it ensures the aerodynamic continuity of an external structure 10 of the downstream section and covers means for deflecting the air flow F, and an open position in which it releases an opening in the structure external and activates deflection means (not visible) of the air flow F.
  • the movable cowl 30 then replaces the downstream structure 12 and the nozzle section 13 is then mounted movably in translation inside said movable cowl 30.
  • the assembly is actuated by a double-acting cylinder 115, a base of which is fixed in the fixed part 11 and having, on the one hand, a first rod 116 able to actuate the movable cowl 30 and connected to the latter at a point of attachment. 31, and secondly, a second rod 117, passing through the movable cowl through an orifice 18 and connected to the nozzle section 13.
  • the nozzle section 13 In the absence of leakage measurement, the nozzle section 13 has an internal surface in communication with the vein 3 and an outer surface in communication with the outside of the nacelle. As a result, there may be a loss of airflow.
  • the air flow can also reach an internal space 33 between the movable cover 30 and the fixed part 11 and escape through the interface between the movable cover 30 and said fixed part 11. Conversely, it is possible to lose a portion of the air flow from the thrust reversal system and then through the orifice 18 to the outside of the nacelle.
  • the interface between the movable hood 30 and the fixed part 11 is conventionally sealed with a seal 40 fixed below the actuator 115, either on the front frame 11a or on the movable hood 30 and adapted to come into contact with the movable hood 30 or the front frame 11a, respectively, so as to seal the interface when the movable cover is in the closed position.
  • the leaktightness of the other possible leak paths is ensured, on the one hand, by a first seal 120 disposed inside the movable cowl 30 near the orifice 18 around the first rod 116 of the jack 115 downstream of the fixing point 31 between a wall of the movable cover 30 and the first rod 116, and secondly, by a second seal 121 disposed between an upper surface of the nozzle 13 and an inner wall of the movable cowl 30.
  • FIG. 3 illustrates a variant of the principle of FIG. 2, in which the second seal 121 is replaced by a seal 123 placed between a lower surface of a nozzle 113 and an inner wall of the movable cowl
  • Such an arrangement is more suitable for thicker nozzle sections 1 13 upstream, the thickness available between the upper surface of the nozzle 1 13 and the outside of the movable cowl 30 being then greatly reduced, which makes it difficult to accommodate an additional seal.
  • the inside of the movable cowl 30 is situated substantially at the external pressure at the outlet of the vein 3.
  • this configuration is also adaptable to a fine nozzle 13 which may then have on its face lower a housing 13b adapted to receive the seal 123.
  • FIG. 5 Another solution shown in FIG. 5 also consists in providing a shoulder 13c at an upstream end of the nozzle section 13, shoulder 13c under which the seal 123 may be housed.
  • Figure 6 shows a provision identical to the case of Figure 2 in which the seal 120 has been removed.
  • Figure 7 is a representation identical to Figure 2 but showing the nozzle section 13 in the deployed position. It goes without saying that the invention is not limited to the embodiments of this nacelle, described above as examples, but it embraces all variants. Thus, in particular, the mobile nozzle could be associated with a smooth nacelle and not with a nacelle equipped with a thrust reverser.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a turbojet engine nacelle including a downstream section, fitted with a variable nozzle device, including a nozzle section (13, 113) moveably mounted along a substantially longitudinal axis of the nacelle relative to the latter inside a structure (12, 30) of the downstream section, the nozzle section being actuatable by at least one actuator (15, 115) including a rod (14, 117) extending through the structure of the downstream section wherein said nozzle section is mounted; and characterized in that the structure and the nozzle include at least one sealing means (20, 21, 40, 121, 123) disposed such that the inside of the nacelle is isolated from the outside of the nacelle across the assembly formed by the structure and the nozzle section.

Description

Nacelle de turboréacteur à double flux Twin-turbojet engine nacelle
L'invention se rapporte une nacelle de turboréacteur à double flux. Un avion est mu par plusieurs turboréacteurs logés chacun dans une nacelle abritant également un ensemble de dispositifs d'actionnement annexes liés à son fonctionnement et assurant diverses fonctions lorsque le turboréacteur est en fonctionnement ou à l'arrêt. Ces dispositifs d'actionnement annexes comprennent notamment un système mécanique d'actionnement d'inverseurs de poussée. Une nacelle présente généralement une structure tubulaire comprenant une entrée d'air en amont du turboréacteur, une section médiane destinée à entourer une soufflante du turboréacteur, une section aval abritant des moyens d'inversion de poussée et destinée à entourer la chambre de combustion du turboréacteur, et est généralement terminée par une tuyère d'éjection dont la sortie est située en aval du turboréacteur.The invention relates to a turbojet turbojet engine nacelle. An aircraft is driven by several turbojets each housed in a nacelle also housing a set of ancillary actuators related to its operation and providing various functions when the turbojet engine is in operation or stopped. These ancillary actuating devices comprise in particular a mechanical system for actuating thrust reversers. A nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing a thrust reverser means and intended to surround the combustion chamber of the turbojet engine. , and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
Les nacelles modernes sont destinés à abriter un turboréacteur double flux apte à générer par l'intermédiaire des pâles de la soufflante en rotation un flux d'air chaud (également appelé flux primaire) issu de la chambre de combustion du turboréacteur, et un flux d'air froid (flux secondaire) qui circule à l'extérieur du turboréacteur à travers un passage annulaire, également appelé veine, formé entre un carénage du turboréacteur et une paroi interne de la nacelle. Les deux flux d'air sont éjectés du turboréacteur par l'arrière de la nacelle.The modern nacelles are intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air (also called primary flow) from the combustion chamber of the turbojet engine, and a flow of cold air (secondary flow) flowing outside the turbojet through an annular passage, also called vein, formed between a shroud of the turbojet engine and an inner wall of the nacelle. The two air flows are ejected from the turbojet engine from the rear of the nacelle.
Bien que l'invention n'est pas limitée au cas des nacelles équipées d'un inverseur mais s'applique également au cas des nacelles dites lisses, l'invention sera décrite ci-après principalement dans le cas d'une nacelle avec inverseur.Although the invention is not limited to the case of nacelles equipped with an inverter but also applies to the case of said nacelles said smooth, the invention will be described below mainly in the case of a nacelle with inverter.
Le rôle d'un inverseur de poussée est, lors de l'atterrissage d'un avion, d'améliorer la capacité de freinage de celui-ci en redirigeant vers l'avant au moins une partie de la poussée générée par le turboréacteur. Dans cette phase, l'inverseur obstrue la veine du flux froid et dirige ce dernier vers l'avant de la nacelle, générant de ce fait une contre-poussée qui vient s'ajouter au freinage des roues de l'avion.The role of a thrust reverser is, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine. In this phase, the inverter obstructs the cold flow vein and directs the latter towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft.
Les moyens mis en œuvre pour réaliser cette réorientation du flux froid varient suivant le type d'inverseur. Outre sa fonction d'inversion de poussée, le capot mobile appartient à la section arrière et présente un côté aval formant une tuyère d'éjection visant à canaliser l'éjection des flux d'air. Cette tuyère peut venir en complément d'une tuyère primaire canalisant le flux chaud et est alors appelée tuyère secondaire.The means implemented to achieve this reorientation of the cold flow vary according to the type of inverter. In addition to its thrust reversal function, the movable cowl belongs to the rear section and has a downstream side forming an ejection nozzle for channeling the ejection of the air flows. This nozzle can come in addition to a primary nozzle channeling the hot flow and is then called secondary nozzle.
Le capot mobile est ainsi équipé, comme cela est connu du document US 5 806 302, d'au moins une tuyère mobile par rapport audit capot mobile, de manière à régler la section d'éjection du canal annulaire en fonction de la position de ladite tuyère. La tuyère mobile est également appelée structure mobile de réglage de la section tuyère.The mobile cowl is thus equipped, as is known from document US Pat. No. 5,806,302, with at least one nozzle movable relative to said movable cowl, so as to adjust the ejection section of the annular channel as a function of the position of said nozzle. The mobile nozzle is also referred to as the movable structure for adjusting the nozzle section.
Chaque partie mobile, à savoir le capot d'inversion de poussée d'une part, et la tuyère mobile d'autre part, est actionnée par un actionneur dédié. Ceci implique la présence de circuits d'alimentation et de commande des actionneurs s'étendant à l'intérieur du capot mobile, ce qui est handicapant d'un point de vue maintenance et sécurité.Each moving part, namely the reverse thrust cover on the one hand, and the movable nozzle on the other hand, is actuated by a dedicated actuator. This implies the presence of power supply circuits and control actuators extending inside the movable cowl, which is disabling from a maintenance and security point of view.
La demande française FR 06/05512 décrit également un système de tuyère variable et divulgue l'utilisation d'un vérin téléscopique dont une première tige est destinée à actionner le capot mobile tandis que la deuxième tige est destinée au réglage de la tuyère. Un tel système permet de répondre à la problématique de la centralisation des moyens d'alimentation et de commande au niveau d'un cadre avant sur lequel est fixé la base de l'actionneur double action.The French application FR 06/05512 also describes a variable nozzle system and discloses the use of a telescopic jack whose first rod is intended to actuate the movable cowl while the second rod is intended for adjusting the nozzle. Such a system makes it possible to respond to the problem of the centralization of the supply and control means at a front frame on which is fixed the base of the double action actuator.
Les demandes FR 07/04343, FR 07/06963 et FR 07/06964 décrivent également des actionneurs double effet pour tuyère variable. Un des inconvénients de l'utilisation des actionneurs double effet par rapport à des actionneurs distincts isolés pour chaque élément mobile provient de l'étanchéité de l'intérieur de la tuyère et de l'intérieur du capot mobile par rapport à l'extérieur de la nacelle et à la veine de circulation du flux d'air. En effet, dans un actionneur double effet, la tige destinée à l'actionnement de la tuyère variable traverse également le capot mobile. Ceci peut entraîner la présence de flux d'air parasites qui vont impacter sur les performances aéronautiques de l'ensemble.Applications FR 07/04343, FR 07/06963 and FR 07/06964 also describe double-acting actuators for variable nozzle. One of the drawbacks of the use of double acting actuators with respect to separate actuators isolated for each movable element comes from the sealing of the inside of the nozzle and the inside of the movable cowl with respect to the outside of the nozzle. nacelle and the flow vein of the air flow. Indeed, in a double-acting actuator, the rod for actuating the variable nozzle also passes through the movable cowl. This can cause the presence of parasitic air flows that will impact the aeronautical performance of the whole.
Lorsque l'inverseur de poussée est en position fermée, notamment, de l'air circulant dans la veine peut s'échapper par l'espace existant entre le capot mobile et un cadre avant puis par l'orifice de passage de la tige de l'actionneur vers la tuyère avant de rejoindre l'extérieur de la nacelle.When the thrust reverser is in the closed position, in particular, air flowing in the vein can escape through the space existing between the moving cowl and a front frame and then through the passage opening of the rod of the actuator to the nozzle before reaching the outside of the nacelle.
Ainsi, il existe un besoin pour une solution permettant d'isoler convenablement ces différentes zones de manière à limiter les fuites d'air à travers le corps de la nacelle.Thus, there is a need for a solution to properly isolate these different areas so as to limit air leakage through the body of the nacelle.
L'invention vise à remédier à cet inconvénient et se rapporte pour ce faire à une nacelle de turboréacteur comprenant une section aval équipée d'un dispositif de tuyère variable, comprenant une section de tuyère montée mobile selon un axe sensiblement longitudinal de la nacelle relativement à cette dernière à l'intérieur d'une structure de la section aval, la section de tuyère étant apte à être actionnée par au moins un actionneur comprenant une première tige traversant la structure de la section aval à l'intérieur de laquelle est montée ladite section de tuyère, caractérisée en ce que la structure et la tuyère comprennent au moins un moyen d'étanchéité disposé de manière à isoler l'intérieur de la nacelle de l'extérieur de la nacelle à travers l'ensemble formé par la structure et la section de tuyère.The invention aims to remedy this drawback and relates for this purpose to a turbojet engine nacelle comprising a downstream section equipped with a variable nozzle device, comprising a nozzle section mounted movably along a substantially longitudinal axis of the nacelle relative to the latter inside a structure of the downstream section, the nozzle section being adapted to be actuated by at least one actuator comprising a first rod passing through the structure of the downstream section inside which said section is mounted nozzle, characterized in that the structure and the nozzle comprise at least one sealing means arranged to isolate the interior of the nacelle from the outside of the nacelle through the assembly formed by the structure and the section of nozzle.
Ainsi, La présence de moyens d'étanchéité isolant l'ensemble structure / tuyère permet de grandement limiter voire empêcher toute fuite d'air depuis l'intérieur de la nacelle (pression élevée) vers l'extérieur de la nacelle (pression faible) à travers la section aval de cette dernière. Ceci améliore de manière générale les performances aéronautiques en améliorant l'éjection des flux d'air par la section de tuyère et donc la poussée générée par l'ensemble propulsif.Thus, the presence of sealing means isolating the entire structure / nozzle greatly limits or even prevent any air leakage from inside the nacelle (high pressure) to the outside of the nacelle (low pressure) to through the downstream section of the latter. This generally improves aeronautical performance by improving the ejection of air flows through the nozzle section and thus the thrust generated by the propulsion unit.
Bien évidemment, on notera que la présente invention peut concerner indifféremment une nacelle lisse, ou une nacelle équipée d'un dispositif d'inversion de poussée, la structure sur laquelle est montée mobile la section de tuyère pouvant être une structure fixe ou un capot mobile d'inverseur.Of course, it should be noted that the present invention may relate indifferently to a smooth nacelle, or a nacelle equipped with a thrust reverser device, the structure on which is mounted movable the nozzle section may be a fixed structure or a movable hood inverter.
Avantageusement, la structure à l'intérieur de laquelle est montée la section de tuyère est un capot mobile d'inverseur de poussée, ledit capot mobile étant monté en translation selon une direction sensiblement parallèle à un axe longitudinal de la nacelle apte à passer alternativement d'une position de fermeture dans laquelle il assure la continuité aérodynamique de la nacelle et couvre des moyens de déviation, à une position d'ouverture dans laquelle il ouvre un passage dans la nacelle et découvre les moyens de déviation, l'ensemble étant apte à être actionné par au moins un actionneur double action comprenant une première tige liée au capot mobile et une deuxième tige traversant le capot mobile et liée à la tuyère mobile.Advantageously, the structure inside which the nozzle section is mounted is a movable thrust reverser cowl, said movable cowl being mounted in translation in a direction substantially parallel to a longitudinal axis of the nacelle adapted to pass alternately between a closing position in which it ensures the aerodynamic continuity of the nacelle and covers means of deflection, to an open position in which it opens a passage in the nacelle and discovers the deflection means, the assembly being adapted to be operated by at least one dual action actuator comprising a first rod connected to the movable hood and a second rod passing through the movable hood and connected to the movable nozzle.
Par isoler, on entend de manière générale que les moyens d'étanchéité permettent de réduire fortement, voire empêcher totalement, un chemin de circulation entre l'extérieur et l'intérieur de la nacelle à travers l'ensemble formé par le capot mobile (la structure) et la tuyère. En effet, la pression régnant à l'extérieur de la nacelle étant inférieure à celle régnant à l'intérieur, il y aurait fuite d'air à travers l'ensemble capot/tuyère, et perte d'une partie du flux de poussée, ce qui réduit les performances aéronautiques.By isolating, it is generally understood that the sealing means make it possible to greatly reduce, or even completely prevent, a circulation path between the outside and the inside of the nacelle through the assembly formed by the mobile cowl (the structure) and the nozzle. Indeed, the pressure prevailing outside the nacelle being lower than that prevailing inside, there would be air leakage through the hood / nozzle assembly, and loss of a part of the thrust flow, which reduces aeronautical performance.
Avantageusement, les moyens d'étanchéité comprennent un joint périphérique disposé entre la base de la tige de l'actionneur liée à la section de tuyère et une paroi interne de la structure, en amont d'un point de liaison entre la tige et ladite structure. Dans le cas d'un actionneur double effet, la base de la tige liée à la section de tuyère est la première tige, liée au capot mobile.Advantageously, the sealing means comprise a peripheral seal disposed between the base of the rod of the actuator connected to the nozzle section and an internal wall of the structure, upstream of a point of connection between the rod and said structure. . In the case of a double acting actuator, the base of the rod connected to the nozzle section is the first rod, linked to the movable cowl.
Alternativement, les moyens d'étanchéité comprennent un joint périphérique disposé entre la base de la tige de l'actionneur liée à la section de tuyère et une paroi interne de la structure, en aval d'un point de liaison entre la tige et ladite structure.Alternatively, the sealing means comprise a peripheral seal disposed between the base of the rod of the actuator connected to the nozzle section and an internal wall of the structure, downstream of a point of connection between the rod and said structure. .
Selon une première variante de réalisation, les moyens d'étanchéité comprennent un joint de tuyère disposé entre une face de la tuyère orientée vers l'intérieur de la nacelle et une paroi de la structure.According to a first variant embodiment, the sealing means comprise a nozzle gasket disposed between a face of the nozzle oriented towards the inside of the nacelle and a wall of the structure.
Selon un deuxième mode de réalisation, les moyens d'étanchéité comprennent un joint de tuyère disposé entre une face de la tuyère orientée vers l'extérieur de la nacelle et une paroi de la structure.According to a second embodiment, the sealing means comprise a nozzle gasket disposed between a face of the nozzle oriented towards the outside of the nacelle and a wall of the structure.
La présente invention sera mieux comprise à l'aide de la description qui suit en référence au dessin schématique annexé sur lequel : La figure 1 est une vue schématique en coupe d'une section aval d'une nacelle lisse selon l'invention.The present invention will be better understood from the description which follows with reference to the attached schematic drawing in which: Figure 1 is a schematic sectional view of a downstream section of a nacelle smooth according to the invention.
Les figures 2 à 7 sont des vues schématiques en coupe de plusieurs modes de réalisation de l'invention sur une section aval d'une nacelle équipée d'un dispositif d'inversion de poussée.Figures 2 to 7 are schematic sectional views of several embodiments of the invention on a downstream section of a nacelle equipped with a thrust reversal device.
Une nacelle est destinée à constituer un logement tubulaire pour un turboréacteur (non représenté) double flux à grand taux de dilution et sert à canaliser les flux d'air qu'il génère par l'intermédiaire des pâles d'une soufflante (non représentée), à savoir un flux d'air chaud traversant une chambre de combustion (non représentée) du turboréacteur, et un flux d'air froid circulant à l'extérieur du turboréacteur (F).A nacelle is intended to constitute a tubular housing for a turbofan engine (not shown) with a large dilution ratio and serves to channel the air flows it generates through the blades of a blower (not shown), namely a hot air flow through a combustion chamber (not shown) of the turbojet, and a cold air flow flowing outside the turbojet (F).
Une nacelle possède de manière générale une structure comprenant une section avant formant une entrée d'air, une section médiane entourant la soufflante du turboréacteur, et une section aval entourant le turboréacteur et pouvant comprendre un système d'inversion de poussée.A nacelle generally has a structure comprising a front section forming an air inlet, a central section surrounding the fan of the turbojet, and a downstream section surrounding the turbojet and may include a thrust reversal system.
La section aval comprend une structure externe comprenant éventuellement un système d'inversion de poussée et une structure interneThe downstream section comprises an external structure optionally comprising a thrust reversal system and an internal structure
2 de carénage du moteur définissant avec la surface externe une veine 3 destinée à la circulation d'un flux froid F dans le cas d'une nacelle de turboréacteur double flux tel qu'ici discutée.2 of the motor fairing defining with the outer surface a vein 3 for the circulation of a cold flow F in the case of a turbojet engine nacelle as discussed herein.
La figure 1 illustre le cas d'une nacelle lisse, c'est-à-dire comprenant une section aval 1 comprenant une section externe non équipée d'un dispositif d'inversion de poussée.Figure 1 illustrates the case of a nacelle smooth, that is to say comprising a downstream section 1 comprising an outer section not equipped with a thrust reverser device.
Cette section aval comprend une partie fixe 11 présentant un cadre avant 11a sur lequel est fixée une structure aval 12 à l'intérieur de laquelle est montée une section de tuyère 13 mobile en translation le long d'un axe sensiblement longitudinal de la nacelle.This downstream section comprises a fixed part 11 having a front frame 11a on which is fixed a downstream structure 12 inside which is mounted a nozzle section 13 movable in translation along a substantially longitudinal axis of the nacelle.
Cette section de tuyère 13 est entraînée en translation par une tige 14 d'un vérin 15 fixé dans la partie fixe et dont ladite tige 14 traverse la structure aval 12 par un orifice 18.This nozzle section 13 is driven in translation by a rod 14 of a jack 15 fixed in the fixed part and whose rod 14 passes through the downstream structure 12 through an orifice 18.
En l'absence de mesure d'étanchéité, la section de tuyère présente une surface interne en communication avec la veine 3 et une surface externe en communication avec l'extérieur de la nacelle. Il peut donc y avoir perte de flux d'air par ce biais.In the absence of leakage measurement, the nozzle section has an internal surface in communication with the vein 3 and an outer surface in communication with the outside of the nacelle. As a result, there may be a loss of airflow.
Le flux d'air peut également parvenir jusqu'à l'intérieur de la partie fixe 11 à travers la structure aval 12. Afin de pallier ce problème, et selon l'invention, la section aval 1 comprend un premier joint 20 disposé sensiblement au niveau du cadre avant 11 autour du vérin 15 en amont de la tige 14 entre ledit vérin 15 et une paroi de la structure fixe 12 en amont de l'orifice 18.The air flow can also reach the inside of the fixed part 11 through the downstream structure 12. In order to overcome this problem, and according to the invention, the downstream section 1 comprises a first seal 20 disposed substantially at level of the front frame 11 around the cylinder 15 upstream of the rod 14 between said cylinder 15 and a wall of the fixed structure 12 upstream of the orifice 18.
Ce premier joint 20 empêche ainsi toute perte du flux d'air vers la partie fixe 11 de la section aval 1. L'étanchéité est également assurée par un deuxième joint 21 disposé entre une surface supérieure de la tuyère 13 et une paroi interne de la structure aval 12.This first seal 20 thus prevents any loss of air flow to the fixed portion 11 of the downstream section 1. The seal is also ensured by a second seal 21 disposed between an upper surface of the nozzle 13 and an inner wall of the downstream structure 12.
Le deuxième joint 21 empêche donc toute fuite du flux d'air vers l'extérieur de la nacelle et l'intérieur de la structure aval 12 se situe sensiblement à la pression en sortie de la veine 3.The second seal 21 thus prevents any leakage of the air flow to the outside of the nacelle and the interior of the downstream structure 12 is substantially at the outlet pressure of the vein 3.
La figure 2 illustre le cas d'une nacelle équipée d'un dispositif d'inversion de poussée, c'est-à-dire dont comprenant une section aval équipée d'un capot 30 mobile en translation selon un axe sensiblement longitudinal de la nacelle entre une position de fermeture dans laquelle il assure la continuité aérodynamique d'une structure externe 10 de la section aval et recouvre des moyens de déviation du flux d'air F, et une position d'ouverture dans laquelle il dégage une ouverture dans la structure externe et active des moyens de déviation (non visibles) du flux d'air F. Le capot mobile 30 remplace alors la structure aval 12 et la section de tuyère 13 est alors montée mobile en translation à l'intérieur dudit capot mobile 30.FIG. 2 illustrates the case of a nacelle equipped with a thrust reverser device, that is to say one comprising a downstream section equipped with a cover 30 movable in translation along a substantially longitudinal axis of the nacelle between a closed position in which it ensures the aerodynamic continuity of an external structure 10 of the downstream section and covers means for deflecting the air flow F, and an open position in which it releases an opening in the structure external and activates deflection means (not visible) of the air flow F. The movable cowl 30 then replaces the downstream structure 12 and the nozzle section 13 is then mounted movably in translation inside said movable cowl 30.
L'ensemble est actionné par un vérin 115 double action dont une base est fixé dans la partie fixe 11 et présentant, d'une part, une première tige 116 apte à actionner le capot mobile 30 et liée à ce dernier en un point de fixation 31 , et d'autre part, une deuxième tige 117, traversant le capot mobile par un orifice 18 et liée à la section de tuyère 13.The assembly is actuated by a double-acting cylinder 115, a base of which is fixed in the fixed part 11 and having, on the one hand, a first rod 116 able to actuate the movable cowl 30 and connected to the latter at a point of attachment. 31, and secondly, a second rod 117, passing through the movable cowl through an orifice 18 and connected to the nozzle section 13.
En l'absence de mesure d'étanchéité, la section de tuyère 13 présente une surface interne en communication avec la veine 3 et une surface externe en communication avec l'extérieur de la nacelle. Il peut donc y avoir perte de flux d'air par ce biais.In the absence of leakage measurement, the nozzle section 13 has an internal surface in communication with the vein 3 and an outer surface in communication with the outside of the nacelle. As a result, there may be a loss of airflow.
Le flux d'air peut également parvenir jusqu'à un espace interne 33 entre le capot mobile 30 et la partie fixe 11 et s'échapper par l'interface entre le capot mobile30 et ladite partie fixe 11. Inversement, il est possible de perdre une partie du flux d'air depuis le système d'inversion de poussée puis à travers l'orifice 18 vers l'extérieur de la nacelle.The air flow can also reach an internal space 33 between the movable cover 30 and the fixed part 11 and escape through the interface between the movable cover 30 and said fixed part 11. Conversely, it is possible to lose a portion of the air flow from the thrust reversal system and then through the orifice 18 to the outside of the nacelle.
L'interface entre le capot mobile 30 et la partie fixe 11 est classiquement rendu étanche à l'aide d'un joint 40 fixé en dessous de l'actionneur 115, soit sur le cadre avant 11a soit sur le capot mobile 30 et apte à venir au contact avec le capot mobile 30 ou le cadre avant 11a, respectivement, de manière à assurer l'étanchéité de l'interface lorsque le capot mobile est en position de fermeture.The interface between the movable hood 30 and the fixed part 11 is conventionally sealed with a seal 40 fixed below the actuator 115, either on the front frame 11a or on the movable hood 30 and adapted to come into contact with the movable hood 30 or the front frame 11a, respectively, so as to seal the interface when the movable cover is in the closed position.
L'étanchéité des autres chemins de fuite possibles est assurée, d'une part, par un premier joint 120 disposé à l'intérieur du capot mobile 30 à proximité de l'orifice 18 autour de la première tige 116 du vérin 115 en aval du point de fixation 31 entre une paroi du capot mobile 30 et la première tige 116, et d'autre part, par un deuxième joint 121 disposé entre une surface supérieure de la tuyère 13 et une paroi interne du capot mobile 30.The leaktightness of the other possible leak paths is ensured, on the one hand, by a first seal 120 disposed inside the movable cowl 30 near the orifice 18 around the first rod 116 of the jack 115 downstream of the fixing point 31 between a wall of the movable cover 30 and the first rod 116, and secondly, by a second seal 121 disposed between an upper surface of the nozzle 13 and an inner wall of the movable cowl 30.
Ainsi, les fuites possible du flux d'air F sont limitées et l'intérieur du capot mobile 30 se situe sensiblement à la pression en sortie de la veine 3.Thus, the possible leakage of the air flow F is limited and the inside of the movable cowl 30 is substantially at the pressure at the outlet of the vein 3.
La figure 3 illustre une variante du principe de la figure 2, dans laquelle le deuxième joint 121 est remplacé par un joint 123 disposé entre une surface inférieur d'une tuyère 113 et une paroi interne du capot mobile 30FIG. 3 illustrates a variant of the principle of FIG. 2, in which the second seal 121 is replaced by a seal 123 placed between a lower surface of a nozzle 113 and an inner wall of the movable cowl
Une telle disposition convient mieux à des sections de tuyère 1 13 plus épaisses en amont, l'épaisseur disponible entre la surface supérieure de la tuyère 1 13 et l'extérieur du capot mobile 30 étant alors fortement réduit ce qui rend difficile le logement d'un joint supplémentaire.Such an arrangement is more suitable for thicker nozzle sections 1 13 upstream, the thickness available between the upper surface of the nozzle 1 13 and the outside of the movable cowl 30 being then greatly reduced, which makes it difficult to accommodate an additional seal.
Dans un tel cas, l'intérieur du capot mobile 30 se situe sensiblement à la pression extérieure en sortie de la veine 3. Comme représenté sur la figure 4, cette configuration est également adaptable à un tuyère 13 fine qui pourra alors présenter sur sa face inférieure un logement 13b apte à recevoir le joint 123.In such a case, the inside of the movable cowl 30 is situated substantially at the external pressure at the outlet of the vein 3. As shown in FIG. 4, this configuration is also adaptable to a fine nozzle 13 which may then have on its face lower a housing 13b adapted to receive the seal 123.
Une autre solution représentée sur la figure 5 consiste également à prévoir un épaulement 13c au niveau d'une extrémité amont de la section de tuyère 13, épaulement 13c sous lequel pourra être logé le joint 123.Another solution shown in FIG. 5 also consists in providing a shoulder 13c at an upstream end of the nozzle section 13, shoulder 13c under which the seal 123 may be housed.
La figure 6 montre une disposition identique au cas de la figure 2 dans laquelle le joint 120 a été supprimé.Figure 6 shows a provision identical to the case of Figure 2 in which the seal 120 has been removed.
En effet, il est possible de supprimer le joint 120 puisque l'extérieur de la nacelle est isolé grâce aux joints 40 et 121. L'expace 33 et l'intérieur du capot mobile sont donc tous deux sensiblement à la pression de la veine 3 et il n'est donc pas nécessaire d'isoler l'orifice 18 entre eux.Indeed, it is possible to remove the seal 120 since the outside of the nacelle is isolated through the seals 40 and 121. The expace 33 and the inside of the movable cowl are both substantially at the pressure of the vein 3 and it is therefore not necessary to isolate the orifice 18 between them.
La figure 7 est une représentation identique à la figure 2 mais montrant la section de tuyère 13 en position déployée. Comme il va de soi l'invention ne se limite pas aux seules formes de réalisation de cette nacelle, décrites ci-dessus à titre d'exemples, mais elle embrasse au contraire toutes les variantes. C'est ainsi notamment que la tuyère mobile pourrait être associée à une nacelle lisse et non à une nacelle équipée d'un inverseur de poussée. Figure 7 is a representation identical to Figure 2 but showing the nozzle section 13 in the deployed position. It goes without saying that the invention is not limited to the embodiments of this nacelle, described above as examples, but it embraces all variants. Thus, in particular, the mobile nozzle could be associated with a smooth nacelle and not with a nacelle equipped with a thrust reverser.

Claims

REVENDICATIONS
1. Nacelle de turboréacteur comprenant une section aval, équipée d'un dispositif de tuyère variable, comprenant une section de tuyère (13, 113) montée mobile selon un axe sensiblement longitudinal de la nacelle relativement à cette dernière à l'intérieur d'une structure (12, 30) de la section aval, la section de tuyère étant apte à être actionnée par au moins un actionneur (15, 1 15) comprenant une tige (14, 1 17) traversant la structure de la section aval à l'intérieur de laquelle est montée ladite section de tuyère, caractérisée en ce que la structure et la tuyère comprennent au moins un moyen d'étanchéité (20, 21 , 40, 121 , 123) disposé de manière à isoler l'intérieur de la nacelle de l'extérieur de la nacelle à travers l'ensemble formé par la structure et la section de tuyère.1. turbojet engine nacelle comprising a downstream section, equipped with a variable nozzle device, comprising a nozzle section (13, 113) mounted movable along a substantially longitudinal axis of the nacelle relative to the latter inside a structure (12, 30) of the downstream section, the nozzle section being adapted to be actuated by at least one actuator (15, 1 15) comprising a rod (14, 1 17) passing through the structure of the downstream section to the interior of which said nozzle section is mounted, characterized in that the structure and the nozzle comprise at least one sealing means (20, 21, 40, 121, 123) arranged so as to isolate the interior of the nacelle from the outside of the nacelle through the assembly formed by the structure and the nozzle section.
2. Nacelle selon la revendication 1 , caractérisée en ce que la structure à l'intérieur de laquelle est montée la section de tuyère (13, 113) est un capot mobile (30) d'inverseur de poussée, ledit capot mobile étant monté en translation selon une direction sensiblement parallèle à un axe longitudinal de la nacelle apte à passer alternativement d'une position de fermeture dans laquelle il assure la continuité aérodynamique de la nacelle et couvre des moyens de déviation, à une position d'ouverture dans laquelle il ouvre un passage dans la nacelle et découvre les moyens de déviation, l'ensemble étant apte à être actionné par au moins un actionneur double action (1 15) comprenant une première tige (1 16) liée au capot mobile et une deuxième tige (1 17) traversant le capot mobile et liée à la tuyère mobile.Nacelle according to claim 1, characterized in that the structure inside which the nozzle section (13, 113) is mounted is a movable thrust reverser cowl (30), said movable cowl being mounted in translation in a direction substantially parallel to a longitudinal axis of the nacelle adapted to pass alternately from a closed position in which it ensures the aerodynamic continuity of the nacelle and covers means of deflection, to an open position in which it opens a passage in the nacelle and discovers the deflection means, the assembly being able to be actuated by at least one double action actuator (1 15) comprising a first rod (1 16) connected to the movable hood and a second rod (1 17 ) passing through the movable hood and connected to the movable nozzle.
3. Nacelle selon l'une quelconque des revendications 1 ou 2, caractérisée en ce que les moyens d'étanchéité comprennent un joint périphérique (20, 120) disposé entre la base de la tige (14, 117) de l'actionneur (15, 115) liée à la section de tuyère (13, 113) et une paroi interne de la structure (12, 30), en amont d'un point de liaison (31 ) entre la tige et ladite structure. 3. The nacelle according to any one of claims 1 or 2, characterized in that the sealing means comprise a peripheral seal (20, 120) disposed between the base of the rod (14, 117) of the actuator (15). , 115) connected to the nozzle section (13, 113) and an inner wall of the structure (12, 30), upstream of a connection point (31) between the rod and said structure.
4. Nacelle selon l'une quelconque des revendications 1 ou 2, caractérisée en ce que les moyens d'étanchéité comprennent un joint périphérique disposé entre la base de la tige (14, 117) de l'actionneur (15, 115) liée à la section de tuyère (13, 113) et une paroi interne de la structure, en aval d'un point de liaison entre la tige et ladite structure.4. Platform according to any one of claims 1 or 2, characterized in that the sealing means comprise a peripheral seal disposed between the base of the rod (14, 117) of the actuator (15, 115) connected to the nozzle section (13, 113) and an inner wall of the structure, downstream of a connection point between the rod and said structure.
5. Nacelle selon l'une quelconque des revendications 1 à 4, caractérisée en ce que les moyens d'étanchéité comprennent un joint de tuyère (123) disposé entre une face de la tuyère (13, 113) orientée vers l'intérieur de la nacelle et une paroi de la structure (12, 30).5. Platform according to any one of claims 1 to 4, characterized in that the sealing means comprise a nozzle gasket (123) disposed between a face of the nozzle (13, 113) facing the inside of the nacelle and a wall of the structure (12, 30).
6. Nacelle selon l'une quelconque des revendications 1 à 4, caractérisée en ce que les moyens d'étanchéité comprennent un joint de tuyère (31 , 121) disposé entre une face de la tuyère (13) orientée vers l'extérieur de la nacelle et une paroi de la structure (12, 30). 6. Platform according to any one of claims 1 to 4, characterized in that the sealing means comprise a nozzle gasket (31, 121) disposed between a face of the nozzle (13) facing outwardly of the nacelle and a wall of the structure (12, 30).
PCT/FR2009/000229 2008-04-02 2009-03-04 Bypass turbojet engine nacelle WO2009122026A1 (en)

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