EP2167798A2 - Turbojet engine for aircraft - Google Patents

Turbojet engine for aircraft

Info

Publication number
EP2167798A2
EP2167798A2 EP08806024A EP08806024A EP2167798A2 EP 2167798 A2 EP2167798 A2 EP 2167798A2 EP 08806024 A EP08806024 A EP 08806024A EP 08806024 A EP08806024 A EP 08806024A EP 2167798 A2 EP2167798 A2 EP 2167798A2
Authority
EP
European Patent Office
Prior art keywords
heat exchanger
bifurcation
turbojet engine
turbojet
nacelle
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Withdrawn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
EP08806024A
Other languages
German (de)
French (fr)
Inventor
Guillaume Bulin
Patrick Oberle
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.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
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 Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP2167798A2 publication Critical patent/EP2167798A2/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Withdrawn legal-status Critical Current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
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
    • F28D2021/0019—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for
    • F28D2021/0021—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for aircrafts or cosmonautics
    • 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 a turbojet engine for aircraft. More specifically, the invention relates to a heat exchanger, also called surface exchanger, housed in a turbojet engine.
  • the heat exchanger according to the invention is intended for cooling a hot fluid of the propulsion system of the turbojet, such as oil, so that it can be reinjected into said at least partially cooled propulsion system.
  • the invention also relates to an aircraft comprising at least one such turbojet engine.
  • the heat exchanger according to the invention finds applications when it is necessary to cool a fluid flowing in or on the periphery of a turbojet engine.
  • the air intake is a direct loss of propulsive efficiency insofar as it does not contribute or little to the thrust of the motor.
  • the matrix of the heat exchanger induces by its internal architecture a high pressure drop in the flow and tends to disturb more or less significantly the downstream aerodynamic flow of the engine.
  • Another known solution is to use a plate heat exchanger locally conforming to the shape of the inner wall of the nacelle to which it is contiguous.
  • An upper face of the heat exchanger is contiguous to the inner wall of the nacelle, while a lower face is located in the cold air flow that passes through the internal volume of the nacelle.
  • the heat transported within the exchanger is transferred by heat conduction to the inner surface of the plate forming the lower face of said heat exchanger thermal.
  • This hot plate is licked by the flow of cold air flowing in the nacelle.
  • the heat stored in the hot plate is thus dissipated by forced convection to the aerodynamic flow of the turbojet engine.
  • a disadvantage of this second embodiment of a heat exchanger of the state of the art is that it reduces the available surfaces for the current systems for reducing noise from the turbojet engine. Indeed, to reduce these noise, it is known to cover at least partially the inner wall of the nacelle of an acoustic coating. More generally, this acoustic coating covers the inner and outer walls of the nacelle and the engine hood when two of these walls are facing one another. The presence of this acoustic coating is incompatible with the joining of the plate heat exchanger on the inner wall of the nacelle. It would be necessary, in order to use such a plate heat exchanger, to locally remove the acoustic coating, which proves difficult in view of the design criteria relating to noise pollution.
  • a heat exchanger adapted to cool a fluid, such as oil or other heat transfer fluid, from the propulsion system of the engine, which can be easily installed in a turbojet engine and adapt to current standards and constraints, especially acoustics. It is also sought to provide a heat exchanger having an increased efficiency compared to the efficiency of heat exchangers of the state of the art, that is to say having greater cooling capacity.
  • the lower bifurcation typically extends in the lower part of the turbojet, between the outer wall of the engine and the inner wall of the nacelle.
  • the lower part of the turbojet engine is meant the part intended to be directed towards the ground when the turbojet engine is mounted on the lower surface of an aircraft wing.
  • the lower bifurcation is disposed downstream of the fan and blades of the fan straightener. Not being directly opposite an inner wall of the nacelle or an outer wall of the engine hood, the lower bifurcation is generally not covered with treatment acoustic.
  • one or more surface heat exchangers are integrated at the level of the lower bifurcation so as to dissipate thermal rejections within the internal flow of the engine while limiting the aerodynamic drag generated and without affecting the treatment.
  • acoustic of the nacelle The lower bifurcation extends most often to the neck of the nacelle and is therefore relatively bulky, so as to accommodate in its internal volume pipes, electrical cables, the transmission shaft of the accessory box etc. which must transit from the engine to a device contained in the body of the nacelle and vice versa.
  • some of the equipment is grouped into the engine itself, which removes some of the pipes and cabling. Therefore, the internal volume of the lower bifurcation, and its overall size, can be reduced.
  • the heat exchanger or heat exchangers according to the invention can advantageously be arranged in the extension of said lower bifurcation. Otherwise, the heat exchanger or heat exchangers can extend on either side of the bifurcation, parallel to said bifurcation. In some cases, it is possible to attach an outer wall of a heat exchanger to the outer wall of the bifurcation so as to reduce the overall size of the assembly. However, in this case, there is only one heat exchange surface per heat exchanger considered.
  • the invention therefore relates to an aircraft turbojet engine comprising a motor housed in a nacelle and at least one heat exchanger for cooling a hot fluid taken from the propulsion system of the turbojet before reinjection of said partially cooled hot fluid into said propulsion system, characterized in that at least one heat exchanger is a radial heat exchanger extending in the lower part of the turbojet engine, at a lower bifurcation of the turbojet engine.
  • the heat exchanger according to the invention extends from the engine to the inner wall of the nacelle and partially passes through the internal volume of said nacelle.
  • at least one radial heat exchanger extends along a side wall of the lower bifurcation.
  • the radial heat exchanger extends parallel to a sidewall or sidewall of the bifurcation, without necessarily being attached to said sidewall.
  • an outer wall of the radial heat exchanger is integral with an outer wall of the lower bifurcation.
  • outer wall is meant the wall directed towards the internal volume of the nacelle and the air passage channel in which they are housed. By internal, we mean therefore directed to the lower bifurcation.
  • the radial heat exchanger then extends downstream of the lower bifurcation in its aerodynamic extension.
  • At least one radial heat exchanger is integral with the engine.
  • the exchanger then being secured and close to the turbomachine, the maintenance actions on the equipment are simplified. This can for example avoid having to disconnect fluid connections between the engine and the exchanger, as can be the case on propulsion systems where the exchanger is not directly attached to the engine.
  • FIG. 1 A representation in longitudinal section of a turbojet engine capable of being provided with at least one radial heat exchanger according to the invention
  • FIG. 2 A sectional representation according to BB of a first embodiment of heat exchangers according to the invention
  • FIG. 3 A sectional representation according to BB of a second embodiment of heat exchangers according to the invention
  • FIG. 1 shows a turbojet engine 1 in longitudinal section along the longitudinal axis A of said turbojet engine 1.
  • the turbojet engine 1 conventionally comprises a nacelle 2 in which a motor 3 is housed.
  • the engine 3 is fixed to an inner wall 4 of the nacelle 2 via, among other things, vanes 5 of a fan straightener.
  • the turbojet engine 1 is provided with a lower bifurcation 6 that can extend in length from the blades 5 to the rear end 7 of the nacelle 2.
  • length we mean the dimension extending parallel to the axis A
  • Forwards and backwards means with respect to the direction of advancement in normal operation of an aircraft equipped with such a turbojet engine 1
  • the lower bifurcation 6 extends in height from the outer wall 12 of the engine 3 to the internal wall 4 of the nacelle 2.
  • height means the dimension extending radially from the longitudinal axis A.
  • the heat exchanger or heat exchangers according to the invention are located in the environment of this lower bifurcation 6, that is to say along the side walls of said bifurcation 6, downstream of said bifurcation 6 and so on.
  • FIGS. 2, 3 and 4 show three nonlimiting examples of embodiments of heat exchangers according to the invention. .
  • the lower bifurcation 6 of Figure 2 extends in length from the rear of the blades 5 to the rear end 7 of the nacelle 2.
  • the lower bifurcation 6 of Figure 2 therefore has a maximum size.
  • Two vertical heat exchangers 8 according to the invention are flanked on either side of the lower bifurcation 6. Said vertical exchangers 8 extend parallel to the lower bifurcation 6, from the outer wall 12 of the engine 3 to the wall external 4 of the nacelle 2.
  • the heat exchangers 8 are secured, at their upper end, the outer wall of the engine.
  • each radial heat exchanger 8 has an internal lateral wall 9 contiguous with an external lateral wall 10 of the lower bifurcation 6. More precisely, the lower bifurcation 6 is dug so that an external general outline of the lower bifurcation assembly 6 and heat exchangers 8 corresponds to the external general outline of a lower bifurcation 6 of the state of the art devoid of heat exchanger. Only the outer wall 11 of the vertical heat exchangers 8 is leached by the flow of cold air passing through the air passage channel in which the lower bifurcation 6 and the vertical heat exchangers 8 extend.
  • the heat exchangers 8 could also be slightly offset relative to the outer wall 10 of the lower bifurcation 6.
  • air passing through the air passage channel could pass between the inner wall 9 of the heat exchangers 8 and the outer wall 10 of the lower bifurcation 6.
  • the heat exchangers 8 would then have two heat exchange surfaces 9, 1 1.
  • the lower bifurcation 16 is reduced, in that it has a smaller footprint than Figure 2. Indeed, the reduced lower bifurcation 16 does not extend in length until the rear end of the nacelle.
  • control systems such as butterfly valves or variable geometry air inlets to control the flow of air passing through said bifurcation 16.
  • the reduced bifurcation 16 of FIG. 3 is flanked by two lateral vertical heat exchangers 13 disposed on either side and downstream of the reduced bifurcation 16.
  • lateral vertical heat exchangers 13 follow an aerodynamic profile of the bifurcation 16.
  • Each lateral heat exchanger 13 has two heat exchange surfaces, respectively at the inner wall 14 and the outer wall 15.
  • the turbojet engine 1 is provided with a central radial heat exchanger 18 extending in the rear extension of the reduced bifurcation 16. More specifically, a rear end 17 of the bifurcation 16 is extended by a central heat exchanger 18.
  • the vertical heat exchangers 8, 13, 18 advantageously have a generally profiled shape, having a leading edge 19, two side walls 9, 11, 14, 15 and a trailing edge 20 In the case of the central radial heat exchanger 18, the leading edge corresponds to the leading edge 21 of the bifurcation 16.
  • the vertical heat exchangers 8, 13, 18 may comprise smooth exchange surfaces, or provided with protuberances that may increase their efficiency, such as fins, disrupters, roughnesses, etc.
  • the heat exchangers according to the invention do not impact the parietal acoustic treatment of the nacelle insofar as they are integrated on areas not traditionally acoustically treated. It is thus possible to use heat exchangers within a propulsion unit without penalizing the level of acoustic treatment.
  • the heat exchangers according to the invention contribute to increasing the efficiency of the propulsion unit by reinjecting within the aerodynamic flow of the turbojet the thermal rejections of the engine and its accessories.
  • this heat energy is not lost by being rejected outside the nacelle or by being dissipated by pressure drop within the matrix of the exchanger.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a turbojet engine for an aircraft that comprises an engine provided in a nacelle and at least one heat exchanger (13) for cooling down a hot fluid collected in the propulsion system of the turbojet engine before re-injecting said partially-cooled hot flow into said propulsion system. The heat exchanger (13) is a radial surface heat exchanger extending in the lower portion of the turbojet engine at a lower branching (16) thereof, parallel to an outer side wall of said lower branching.

Description

TURBOREACTEUR POUR AERONEF TURBOREACTOR FOR AIRCRAFT
L'invention concerne un turboréacteur pour aéronef. Plus précisément l'invention concerne un échangeur thermique, également appelé échangeur surfacique, logé dans un turboréacteur. L'échangeur thermique selon l'invention est destiné à refroidir un fluide chaud du système propulsif du turboréacteur, tel que de l'huile, afin qu'il puisse être réinjecté dans ledit système propulsif au moins partiellement refroidi. L'invention concerne également un aéronef comportant au moins un tel turboréacteur.The invention relates to a turbojet engine for aircraft. More specifically, the invention relates to a heat exchanger, also called surface exchanger, housed in a turbojet engine. The heat exchanger according to the invention is intended for cooling a hot fluid of the propulsion system of the turbojet, such as oil, so that it can be reinjected into said at least partially cooled propulsion system. The invention also relates to an aircraft comprising at least one such turbojet engine.
D'une manière générale, l'échangeur thermique selon l'invention trouve des applications dès lors qu'il est nécessaire de refroidir un fluide circulant dans ou à la périphérie d'un turboréacteur.In general, the heat exchanger according to the invention finds applications when it is necessary to cool a fluid flowing in or on the periphery of a turbojet engine.
Dans le domaine de l'aviation civile, il est connu d'utiliser un échangeur thermique annexe pour refroidir l'huile qui circule dans le moteur du turboréacteur. L'huile chaude est amenée dans l'échangeur thermique pour y être refroidie avant d'être réinjectée dans le système propulsif.In the field of civil aviation, it is known to use an auxiliary heat exchanger to cool the oil flowing in the turbojet engine. The hot oil is brought into the heat exchanger to be cooled before being reinjected into the propulsion system.
Dans l'état de la technique, il existe de manière générale deux positionnements possibles pour l'échangeur thermique, à savoir au niveau du corps du moteur, ou au niveau de la nacelle.In the state of the art, there are generally two possible positions for the heat exchanger, namely at the engine body, or at the nacelle.
Cependant, dans le cas où l'échangeur thermique est monté dans la nacelle avec sortie d'air vers l'extérieur, le prélèvement d'air constitue une perte directe de rendement propulsif dans la mesure où il ne contribue pas ou peu à la poussée du moteur. Dans le cas où l'échangeur thermique est monté dans le corps du moteur, la matrice de l'échangeur thermique induit de par son architecture interne une forte perte de charge dans l'écoulement et tend à perturber de façon plus ou moins significative l'écoulement aérodynamique aval du moteur.However, in the case where the heat exchanger is mounted in the nacelle with air outlet to the outside, the air intake is a direct loss of propulsive efficiency insofar as it does not contribute or little to the thrust of the motor. In the case where the heat exchanger is mounted in the body of the engine, the matrix of the heat exchanger induces by its internal architecture a high pressure drop in the flow and tends to disturb more or less significantly the downstream aerodynamic flow of the engine.
Une autre solution connue est d'utiliser un échangeur à plaques épousant localement la forme de la paroi interne de la nacelle à laquelle elle est accolée. Une face supérieure de l'échangeur thermique est accolée à la paroi interne de la nacelle, tandis qu'une face inférieure est située dans le flux d'air froid qui traverse le volume interne de la nacelle. La chaleur transportée au sein de l'échangeur est transférée par conduction thermique à la surface interne de la plaque formant la face inférieure dudit échangeur thermique. Cette plaque chaude est léchée par le flux d'air froid s'écoulant dans la nacelle. La chaleur emmagasinée dans la plaque chaude est ainsi dissipée par convection forcée vers l'écoulement aérodynamique du turboréacteur. Un inconvénient de ce deuxième mode de réalisation d'un échangeur thermique de l'état de la technique est qu'il réduit les surfaces disponibles pour les systèmes actuels de réduction des nuisances sonores sortant du turboréacteur. En effet, pour réduire ces nuisances sonores, il est connu de recouvrir au moins partiellement la paroi interne de la nacelle d'un revêtement acoustique. Plus généralement, ce revêtement acoustique recouvre les parois internes et externes de la nacelle et du capot moteur dès lors que deux de ces parois sont en regard l'une de l'autre. La présence de ce revêtement acoustique est incompatible avec l'accolement de l'échangeur thermique à plaques sur la paroi interne de la nacelle. Il serait nécessaire, pour utiliser un tel échangeur thermique à plaques, de supprimer localement le revêtement acoustique, ce qui s'avère difficile au vu des critères de dimensionnement relatifs aux nuisances sonores.Another known solution is to use a plate heat exchanger locally conforming to the shape of the inner wall of the nacelle to which it is contiguous. An upper face of the heat exchanger is contiguous to the inner wall of the nacelle, while a lower face is located in the cold air flow that passes through the internal volume of the nacelle. The heat transported within the exchanger is transferred by heat conduction to the inner surface of the plate forming the lower face of said heat exchanger thermal. This hot plate is licked by the flow of cold air flowing in the nacelle. The heat stored in the hot plate is thus dissipated by forced convection to the aerodynamic flow of the turbojet engine. A disadvantage of this second embodiment of a heat exchanger of the state of the art is that it reduces the available surfaces for the current systems for reducing noise from the turbojet engine. Indeed, to reduce these noise, it is known to cover at least partially the inner wall of the nacelle of an acoustic coating. More generally, this acoustic coating covers the inner and outer walls of the nacelle and the engine hood when two of these walls are facing one another. The presence of this acoustic coating is incompatible with the joining of the plate heat exchanger on the inner wall of the nacelle. It would be necessary, in order to use such a plate heat exchanger, to locally remove the acoustic coating, which proves difficult in view of the design criteria relating to noise pollution.
Dans l'invention, on cherche à fournir un échangeur thermique, apte à refroidir un fluide, tel que de l'huile ou autre fluide caloporteur, en provenance du système propulsif du moteur, qui puisse s'installer aisément dans un turboréacteur et s'adapter aux normes et contraintes actuelles, notamment acoustiques. On cherche également à fournir un échangeur thermique ayant un rendement accru par rapport au rendement des échangeurs thermiques de l'état de la technique, c'est-à-dire ayant des capacités de refroidissement plus importantes.In the invention, it is sought to provide a heat exchanger, adapted to cool a fluid, such as oil or other heat transfer fluid, from the propulsion system of the engine, which can be easily installed in a turbojet engine and adapt to current standards and constraints, especially acoustics. It is also sought to provide a heat exchanger having an increased efficiency compared to the efficiency of heat exchangers of the state of the art, that is to say having greater cooling capacity.
Pour cela, dans l'invention, on propose de disposer un ou plusieurs échangeurs thermiques au niveau de la bifurcation inférieure du turboréacteur. La bifurcation inférieure s'étend classiquement en partie basse du turboréacteur, entre la paroi externe du moteur et la paroi interne de la nacelle. Par partie basse du turboréacteur, on entend la partie destinée à être dirigée vers le sol lorsque le turboréacteur est monté sur l'intrados d'une aile d'aéronef. La bifurcation inférieure est disposée en aval de la soufflante et des aubes du redresseur de fan. N'étant pas directement en regard avec une paroi interne de la nacelle ou une paroi externe du capot moteur, la bifurcation inférieure n'est généralement pas recouverte de traitement acoustique. Ainsi, selon l'invention, on intègre au niveau de la bifurcation inférieure un ou plusieurs échangeurs thermiques surfaciques de manière à dissiper au sein de l'écoulement interne du moteur les réjections thermiques tout en limitant les traînées aérodynamiques engendrées et sans influer sur le traitement acoustique de la nacelle. La bifurcation inférieure s'étend le plus souvent jusqu'au col de la nacelle et est de ce fait relativement encombrante, de manière à pouvoir loger dans son volume interne des canalisations, des câbles électriques, l'arbre de transmission de la boîte à accessoires etc. qui doivent transiter depuis le moteur jusqu'à un équipement contenu dans le corps de la nacelle et inversement. Dans certains turboréacteurs une partie de l'équipement est regroupée dans le moteur lui-même, ce qui supprime une partie des canalisations et du câblage. Dès lors, le volume interne de la bifurcation inférieure, et son encombrement général, peut être réduit. Dans le cas où la bifurcation inférieure est réduite, le ou les échangeurs thermiques selon l'invention peuvent avantageusement être disposés dans le prolongement de ladite bifurcation inférieure. Autrement, le ou les échangeurs thermiques peuvent s'étendre de part et d'autre de la bifurcation, parallèlement à ladite bifurcation. Dans certains cas, il est possible d'accoler une paroi externe d'un échangeur thermique à la paroi externe de la bifurcation de manière à réduire l'encombrement de l'ensemble. Cependant, dans ce cas, il n'existe qu'une surface d'échange thermique par échangeur thermique considéré.For this, in the invention, it is proposed to have one or more heat exchangers at the lower bifurcation of the turbojet engine. The lower bifurcation typically extends in the lower part of the turbojet, between the outer wall of the engine and the inner wall of the nacelle. By the lower part of the turbojet engine is meant the part intended to be directed towards the ground when the turbojet engine is mounted on the lower surface of an aircraft wing. The lower bifurcation is disposed downstream of the fan and blades of the fan straightener. Not being directly opposite an inner wall of the nacelle or an outer wall of the engine hood, the lower bifurcation is generally not covered with treatment acoustic. Thus, according to the invention, one or more surface heat exchangers are integrated at the level of the lower bifurcation so as to dissipate thermal rejections within the internal flow of the engine while limiting the aerodynamic drag generated and without affecting the treatment. acoustic of the nacelle. The lower bifurcation extends most often to the neck of the nacelle and is therefore relatively bulky, so as to accommodate in its internal volume pipes, electrical cables, the transmission shaft of the accessory box etc. which must transit from the engine to a device contained in the body of the nacelle and vice versa. In some turbojet engines some of the equipment is grouped into the engine itself, which removes some of the pipes and cabling. Therefore, the internal volume of the lower bifurcation, and its overall size, can be reduced. In the case where the lower bifurcation is reduced, the heat exchanger or heat exchangers according to the invention can advantageously be arranged in the extension of said lower bifurcation. Otherwise, the heat exchanger or heat exchangers can extend on either side of the bifurcation, parallel to said bifurcation. In some cases, it is possible to attach an outer wall of a heat exchanger to the outer wall of the bifurcation so as to reduce the overall size of the assembly. However, in this case, there is only one heat exchange surface per heat exchanger considered.
L'invention a donc pour objet un turboréacteur pour aéronef comportant un moteur logé dans une nacelle et au moins un échangeur thermique destiné à refroidir un fluide chaud prélevé dans le système propulsif du turboréacteur avant réinjection dudit fluide chaud partiellement refroidi dans ledit système propulsif, caractérisé en ce qu'au moins un échangeur thermique est un échangeur thermique radial s'étendant en partie basse du turboréacteur, au niveau d'une bifurcation inférieure du turboréacteur.The invention therefore relates to an aircraft turbojet engine comprising a motor housed in a nacelle and at least one heat exchanger for cooling a hot fluid taken from the propulsion system of the turbojet before reinjection of said partially cooled hot fluid into said propulsion system, characterized in that at least one heat exchanger is a radial heat exchanger extending in the lower part of the turbojet engine, at a lower bifurcation of the turbojet engine.
Par radial, on entend perpendiculaire à l'axe longitudinal du turboréacteur. Autrement dit, l'échangeur thermique selon l'invention s'étend depuis le moteur jusqu'à la paroi interne de la nacelle et traverse partiellement le volume interne de ladite nacelle. Selon des exemples de réalisation du turboréacteur selon l'invention, il est possible de prévoir qu'au moins un échangeur thermique radial s'étend le long d'une paroi latérale de la bifurcation inférieure.Radial means perpendicular to the longitudinal axis of the turbojet engine. In other words, the heat exchanger according to the invention extends from the engine to the inner wall of the nacelle and partially passes through the internal volume of said nacelle. According to embodiments of the turbojet according to the invention, it is possible to provide that at least one radial heat exchanger extends along a side wall of the lower bifurcation.
L'échangeur thermique radial s'étend parallèlement à un flanc, ou paroi latérale, de la bifurcation, sans être forcément accolé à ladite paroi latérale.The radial heat exchanger extends parallel to a sidewall or sidewall of the bifurcation, without necessarily being attached to said sidewall.
Dans le cas où l'échangeur thermique radial est accolé, on diminue les perturbations aérodynamiques engendrées par la présence de l'échangeur thermique radial. Par exemple une paroi externe de l'échangeur thermique radial est solidaire d'une paroi externe de la bifurcation inférieure. Par paroi externe, on entend la paroi dirigée vers le volume interne de la nacelle et le canal de passage d'air dans lequel ils sont logés. Par interne, on entend donc dirigé vers la bifurcation inférieure.In the case where the radial heat exchanger is attached, the aerodynamic disturbances generated by the presence of the radial heat exchanger are reduced. For example, an outer wall of the radial heat exchanger is integral with an outer wall of the lower bifurcation. By outer wall is meant the wall directed towards the internal volume of the nacelle and the air passage channel in which they are housed. By internal, we mean therefore directed to the lower bifurcation.
A l'inverse, dans le cas où on dispose l'échangeur thermique radial à distance de la bifurcation, on augmente les surfaces d'échange et donc les performances de refroidissement dudit échangeur thermique radial.Conversely, in the case where the radial heat exchanger is arranged at a distance from the bifurcation, the exchange surfaces and thus the cooling performance of said radial heat exchanger are increased.
Préférentiellement, l'échangeur thermique radial s'étend alors en aval de la bifurcation inférieure dans son prolongement aérodynamique.Preferably, the radial heat exchanger then extends downstream of the lower bifurcation in its aerodynamic extension.
Dans un exemple particulier de réalisation du turboréacteur selon l'invention, on prévoit qu'au moins un échangeur thermique radial est solidaire du moteur.In a particular embodiment of the turbojet engine according to the invention, it is expected that at least one radial heat exchanger is integral with the engine.
L'échangeur étant alors solidaire et à proximité de la turbomachine, les actions de maintenance sur l'équipement sont simplifiées. Cela peut par exemple éviter d'avoir à déconnecter des connections fluidiques entre le moteur et l'échangeur, comme cela peut être le cas sur des ensembles propulsifs où l'échangeur n'est pas directement fixé sur le moteur.The exchanger then being secured and close to the turbomachine, the maintenance actions on the equipment are simplified. This can for example avoid having to disconnect fluid connections between the engine and the exchanger, as can be the case on propulsion systems where the exchanger is not directly attached to the engine.
L'invention sera mieux comprise à la lecture de la description qui suit et à l'examen des figures qui l'accompagnent. Celles-ci sont présentées à titre indicatif et nullement limitatif de l'invention. Les figures représentent : - Figure 1 : Une représentation en coupe longitudinale d'un turboréacteur pouvant être muni d'au moins un échangeur thermique radial selon l'invention ;The invention will be better understood on reading the description which follows and on examining the figures which accompany it. These are presented as an indication and in no way limitative of the invention. The figures represent: FIG. 1: A representation in longitudinal section of a turbojet engine capable of being provided with at least one radial heat exchanger according to the invention;
- Figure 2 : Une représentation en coupe selon B-B d'un premier exemple de réalisation d'échangeurs thermiques selon l'invention ; - Figure 3 : Une représentation en coupe selon B-B d'un deuxième exemple de réalisation d'échangeurs thermiques selon l'invention ;- Figure 2: A sectional representation according to BB of a first embodiment of heat exchangers according to the invention; - Figure 3: A sectional representation according to BB of a second embodiment of heat exchangers according to the invention;
- Figure 4 : Une représentation en coupe selon B-B d'un troisième exemple de réalisation d'échangeurs thermiques selon l'invention. La figure 1 montre un turboréacteur 1 en coupe longitudinale selon l'axe longitudinal A dudit turboréacteur 1.- Figure 4: A representation in section along B-B of a third embodiment of heat exchangers according to the invention. FIG. 1 shows a turbojet engine 1 in longitudinal section along the longitudinal axis A of said turbojet engine 1.
Le turboréacteur 1 comporte classiquement une nacelle 2 dans laquelle est logé un moteur 3. Le moteur 3 est fixé à une paroi interne 4 de la nacelle 2 par l'intermédiaire entre autre d'aubes 5 de redresseur de fan. Le turboréacteur 1 est muni d'une bifurcation inférieure 6 pouvant s'étendre en longueur depuis les aubes 5 jusqu'à l'extrémité arrière 7 de la nacelle 2. Par longueur, on entend la dimension s'étendant parallèlement à l'axe A. Par avant et arrière, on entend par rapport au sens d'avancement en fonctionnement normal d'un aéronef muni d'un tel turboréacteur 1 La bifurcation inférieure 6 s'étend en hauteur depuis la paroi externe 12 du moteur 3 jusqu'à la paroi interne 4 de la nacelle 2. Par hauteur, on entend la dimension s'étendant radialement depuis l'axe longitudinal A.The turbojet engine 1 conventionally comprises a nacelle 2 in which a motor 3 is housed. The engine 3 is fixed to an inner wall 4 of the nacelle 2 via, among other things, vanes 5 of a fan straightener. The turbojet engine 1 is provided with a lower bifurcation 6 that can extend in length from the blades 5 to the rear end 7 of the nacelle 2. By length, we mean the dimension extending parallel to the axis A Forwards and backwards means with respect to the direction of advancement in normal operation of an aircraft equipped with such a turbojet engine 1 The lower bifurcation 6 extends in height from the outer wall 12 of the engine 3 to the internal wall 4 of the nacelle 2. By height means the dimension extending radially from the longitudinal axis A.
Le ou les échangeurs thermiques selon l'invention se situent dans l'environnement de cette bifurcation inférieure 6, c'est-à-dire le long des parois latérales de ladite bifurcation 6, en aval de ladite bifurcation 6 etc.The heat exchanger or heat exchangers according to the invention are located in the environment of this lower bifurcation 6, that is to say along the side walls of said bifurcation 6, downstream of said bifurcation 6 and so on.
Sur les figures 2, 3 et 4 sont représentés trois exemples non limitatifs de réalisation d'échangeurs thermiques selon l'invention. .FIGS. 2, 3 and 4 show three nonlimiting examples of embodiments of heat exchangers according to the invention. .
La bifurcation inférieure 6 de la figure 2 s'étend en longueur depuis l'arrière des aubes 5 jusqu'à l'extrémité arrière 7 de la nacelle 2. La bifurcation inférieure 6 de la figure 2 a donc un encombrement maximal. Deux échangeurs thermiques verticaux 8 selon l'invention sont flanqués de part et d'autre de la bifurcation inférieure 6. Lesdits échangeurs verticaux 8 s'étendent parallèlement à la bifurcation inférieure 6, depuis la paroi externe 12 du moteur 3 jusqu'à la paroi externe 4 de la nacelle 2. Avantageusement, les échangeurs thermiques 8 sont solidaires, par leur extrémité haute, de la paroi externe du moteur.The lower bifurcation 6 of Figure 2 extends in length from the rear of the blades 5 to the rear end 7 of the nacelle 2. The lower bifurcation 6 of Figure 2 therefore has a maximum size. Two vertical heat exchangers 8 according to the invention are flanked on either side of the lower bifurcation 6. Said vertical exchangers 8 extend parallel to the lower bifurcation 6, from the outer wall 12 of the engine 3 to the wall external 4 of the nacelle 2. Advantageously, the heat exchangers 8 are secured, at their upper end, the outer wall of the engine.
De manière à ne pas augmenter l'encombrement des installations dans le canal de passage d'air, chaque échangeur thermique radial 8 a une paroi latérale interne 9 accolée à une paroi latérale externe 10 de la bifurcation inférieure 6. Plus précisément, la bifurcation inférieure 6 est creusée de manière à ce qu'un contour général externe de l'ensemble bifurcation inférieure 6 et échangeurs thermiques 8 corresponde au contour général externe d'une bifurcation inférieure 6 de l'état de la technique dépourvue d'échangeur thermique. Seule la paroi externe 11 des échangeurs thermiques verticaux 8 est léchée par le flux d'air froid f transitant par le canal de passage d'air dans lequel s'étend la bifurcation inférieure 6 et les échangeurs thermiques verticaux 8.In order not to increase the overall size of the installations in the air passage channel, each radial heat exchanger 8 has an internal lateral wall 9 contiguous with an external lateral wall 10 of the lower bifurcation 6. More precisely, the lower bifurcation 6 is dug so that an external general outline of the lower bifurcation assembly 6 and heat exchangers 8 corresponds to the external general outline of a lower bifurcation 6 of the state of the art devoid of heat exchanger. Only the outer wall 11 of the vertical heat exchangers 8 is leached by the flow of cold air passing through the air passage channel in which the lower bifurcation 6 and the vertical heat exchangers 8 extend.
Bien entendu, les échangeurs thermiques 8 pourraient également être légèrement décalés par rapport à la paroi externe 10 de la bifurcation inférieure 6. Ainsi, de l'air transitant par le canal de passage d'air pourrait passer entre la paroi interne 9 des échangeurs thermiques 8 et la paroi externe 10 de la bifurcation inférieure 6. Les échangeurs thermiques 8 auraient alors deux surfaces d'échanges thermiques 9, 1 1.Of course, the heat exchangers 8 could also be slightly offset relative to the outer wall 10 of the lower bifurcation 6. Thus, air passing through the air passage channel could pass between the inner wall 9 of the heat exchangers 8 and the outer wall 10 of the lower bifurcation 6. The heat exchangers 8 would then have two heat exchange surfaces 9, 1 1.
Sur les figures 3 et 4, la bifurcation inférieure 16 est réduite, en ce sens qu'elle a un encombrement moins important qu'à la figure 2. En effet, la bifurcation inférieure réduite 16 ne s'étend pas en longueur jusqu'à l'extrémité arrière de la nacelle.In Figures 3 and 4, the lower bifurcation 16 is reduced, in that it has a smaller footprint than Figure 2. Indeed, the reduced lower bifurcation 16 does not extend in length until the rear end of the nacelle.
Dans un exemple de réalisation particulier de la bifurcation réduite, il est possible de prévoir des systèmes de régulation tels que des vannes papillon ou des entrées d'air à géométrie variable afin de contrôler le débit d'air traversant ladite bifurcation 16.In a particular embodiment of the reduced bifurcation, it is possible to provide control systems such as butterfly valves or variable geometry air inlets to control the flow of air passing through said bifurcation 16.
La bifurcation réduite 16 de la figure 3 est flanquée de deux échangeurs thermiques verticaux latéraux 13 disposés de part et d'autre et en aval de la bifurcation réduite 16. De manière à ne pas perturber l'écoulement du flux d'air f dans le canal de passage d'air, les échangeurs thermiques verticaux latéraux 13 suivent un profil aérodynamique de la bifurcation 16. Chaque échangeur thermique latéral 13 présente deux surfaces d'échanges thermiques, respectivement au niveau de la paroi interne 14 et de la paroi externe 15. Dans l'exemple représenté à la figure 4, en plus des deux échangeurs thermiques verticaux latéraux 13, Le turboréacteur 1 est muni d'un échangeur thermique radial central 18 s'étendant dans le prolongement arrière de la bifurcation réduite 16. Plus précisément, une extrémité arrière 17 de la bifurcation 16 est prolongée par un échangeur thermique central 18. Les trois échangeurs thermiques 13, 18 de la figure 4 sont munis de deux surfaces d'échange thermique. La partie basse du flux secondaire f entraîné par la soufflante, traverse le plan des redresseurs 5, contourne la bifurcation réduite 16 et tangente les faces internes et externes de chaque échangeur thermique 13, 18. Le transfert d'énergie calorifique se produit alors par convection forcée entre les parois chaudes des échangeurs thermiques 13, 18 et l'écoulement d'air frais f.The reduced bifurcation 16 of FIG. 3 is flanked by two lateral vertical heat exchangers 13 disposed on either side and downstream of the reduced bifurcation 16. In order not to disturb the flow of the air flow f in the air passage channel, lateral vertical heat exchangers 13 follow an aerodynamic profile of the bifurcation 16. Each lateral heat exchanger 13 has two heat exchange surfaces, respectively at the inner wall 14 and the outer wall 15. In the example shown in FIG. 4, in addition to the two lateral vertical heat exchangers 13, the turbojet engine 1 is provided with a central radial heat exchanger 18 extending in the rear extension of the reduced bifurcation 16. More specifically, a rear end 17 of the bifurcation 16 is extended by a central heat exchanger 18. The three heat exchangers 13, 18 of FIG. 4 are provided with two heat exchange surfaces. The lower part of the secondary flow f driven by the fan, passes through the plane of the rectifiers 5, bypasses the reduced bifurcation 16 and tangents the inner and outer faces of each heat exchanger 13, 18. The transfer of heat energy then occurs by convection forced between the hot walls of the heat exchangers 13, 18 and the fresh air flow f.
D'une manière générale, les échangeurs thermiques verticaux 8, 13, 18 selon l'invention ont avantageusement une forme générale profilée, présentant un bord d'attaque 19, deux parois latérales 9, 11 , 14, 15 et un bord de fuite 20. Dans le cas de l'échangeur thermique radial central 18, le bord d'attaque correspond au bord d'attaque 21 de la bifurcation 16.In general, the vertical heat exchangers 8, 13, 18 according to the invention advantageously have a generally profiled shape, having a leading edge 19, two side walls 9, 11, 14, 15 and a trailing edge 20 In the case of the central radial heat exchanger 18, the leading edge corresponds to the leading edge 21 of the bifurcation 16.
Bien entendu, d'autres types de positionnement des échangeurs thermiques 8, 13, 18 peuvent être envisagés de manière à plus ou moins augmenter la surface d'échange et de manière à plus ou moins limiter l'encombrement et l'impact aérodynamique sur l'écoulement interne du turboréacteuM .Of course, other types of positioning of the heat exchangers 8, 13, 18 may be envisaged so as to increase the exchange surface to a greater or lesser extent and to more or less limit the space requirement and the aerodynamic impact on the surface. internal flow of the turboreaccessor.
Bien entendu, les échangeurs thermiques verticaux 8, 13, 18 peuvent comporter des surfaces d'échange lisses, ou munies de protubérances susceptibles d'en augmenter l'efficacité, telles que des ailettes, des perturbateurs, des rugosités etc.Of course, the vertical heat exchangers 8, 13, 18 may comprise smooth exchange surfaces, or provided with protuberances that may increase their efficiency, such as fins, disrupters, roughnesses, etc.
De même, il peut être envisagé d'intégrer en aval de la bifurcation inférieure 6, 16 des échangeurs thermiques verticaux 8, 13, 18 munis sur leur paroi externe d'une surface parfaitement lisse de manière à limiter des turbulences sur l'écoulement aérodynamique du turboréacteur 1 à la périphérie de la bifurcation 6, 16, et munis entre les parois internes d'ailettes et de protubérances augmentant l'efficacité d'échange au sein de l'écoulement aérodynamique apparaissant entre les échangeurs thermiques 8, 13, 18. Les échangeurs thermiques selon l'invention étant de type échangeur surfacique et étant disposés dans le prolongement de la bifurcation inférieure ils ne génèrent qu'un niveau limité de perturbations aérodynamiques susceptibles d'impacter les performances de l'ensemble propulsif. Les échangeurs thermiques selon l'invention ne comportent pas de conduit courbé et compliqué susceptible de générer des perturbations aérodynamiques internes et externes à l'échangeur thermiqueSimilarly, it is possible to integrate downstream of the lower bifurcation 6, 16 vertical heat exchangers 8, 13, 18 provided on their outer wall with a perfectly smooth surface so as to limit turbulence on the aerodynamic flow. of the turbojet engine 1 at the periphery of the bifurcation 6, 16, and provided between the inner walls with fins and protuberances increasing the exchange efficiency within the aerodynamic flow occurring between the heat exchangers 8, 13, 18. The heat exchangers according to the invention being of the surface exchanger type and being arranged in the extension of the lower bifurcation they generate only a limited level of aerodynamic disturbances likely to impact the performance of the propulsion unit. The heat exchangers according to the invention do not comprise ducts curved and complicated, which can generate aerodynamic disturbances inside and outside the heat exchanger
De plus, les échangeurs thermiques selon l'invention n'impactent pas le traitement acoustique pariétal de la nacelle dans la mesure où ils sont intégrés sur des zones traditionnellement non munies de traitement acoustique. Il est ainsi possible d'utiliser des échangeurs thermiques au sein d'un ensemble propulsif sans pénaliser le niveau de traitement acoustique.In addition, the heat exchangers according to the invention do not impact the parietal acoustic treatment of the nacelle insofar as they are integrated on areas not traditionally acoustically treated. It is thus possible to use heat exchangers within a propulsion unit without penalizing the level of acoustic treatment.
Par ailleurs, les échangeurs thermiques selon l'invention contribuent à augmenter le rendement de l'ensemble propulsif en réinjectant au sein de l'écoulement aérodynamique du turboréacteur les réjections thermiques du moteur et de ses accessoires. Ainsi, cette énergie calorifique n'est pas perdue en étant rejetée à l'extérieur de la nacelle ou en étant dissipée par perte de charge au sein de la matrice de l'échangeur.Moreover, the heat exchangers according to the invention contribute to increasing the efficiency of the propulsion unit by reinjecting within the aerodynamic flow of the turbojet the thermal rejections of the engine and its accessories. Thus, this heat energy is not lost by being rejected outside the nacelle or by being dissipated by pressure drop within the matrix of the exchanger.
En parallèle, il est à noter que le positionnement des échangeurs thermiques au niveau de la bifurcation inférieure tend à en simplifier l'accessibilité et la maintenance. In parallel, it should be noted that the positioning of heat exchangers at the lower bifurcation tends to simplify accessibility and maintenance.

Claims

REVENDICATIONS
1 - Turboréacteur (1 ) pour aéronef comportant un moteur (3) logé dans une nacelle (2) et au moins un échangeur thermique (8, 13, 18) destiné à refroidir un fluide chaud prélevé dans le système propulsif du turboréacteur avant réinjection dudit fluide chaud partiellement refroidi dans ledit système propulsif, caractérisé en ce qu'au moins un échangeur thermique surfacique (8, 13, 18) est un échangeur thermique radial s'étendant en partie basse du turboréacteur, au niveau d'une bifurcation inférieure (6, 16) du turboréacteur disposée en aval de la soufflante et des aubes du redresseur de fan dudit turboréacteur, l'échangeur thermique s'étendant parallèlement à une paroi latérale externe (10) de la bifurcation inférieure.1 - Turbeactor (1) for an aircraft comprising a motor (3) housed in a nacelle (2) and at least one heat exchanger (8, 13, 18) for cooling a hot fluid taken from the propulsion system of the turbojet before reinjection of said hot fluid partially cooled in said propulsion system, characterized in that at least one surface heat exchanger (8, 13, 18) is a radial heat exchanger extending in the lower part of the turbojet engine, at a lower bifurcation (6 , 16) of the turbojet arranged downstream of the fan and the blades of the fan rectifier of said turbojet, the heat exchanger extending parallel to an outer side wall (10) of the lower bifurcation.
2- Turboréacteur selon la revendication 1 , caractérisé en ce que l'échangeur thermique radial s'étend le long d'une paroi latérale (10) de la bifurcation inférieure.2- turbojet engine according to claim 1, characterized in that the radial heat exchanger extends along a side wall (10) of the lower bifurcation.
3- Turboréacteur selon la revendication 2, caractérisé en ce qu'une paroi interne (9) de l'échangeur thermique radial est solidaire d'une paroi latérale externe (10) de la bifurcation inférieure. 4- Turboréacteur selon l'une des revendications 1 à 3, caractérisé en ce que l'échangeur thermique radial s'étend en aval de la bifurcation inférieure réduite (16).3. Turbojet engine according to claim 2, characterized in that an inner wall (9) of the radial heat exchanger is secured to an outer side wall (10) of the lower bifurcation. 4- Turbojet engine according to one of claims 1 to 3, characterized in that the radial heat exchanger extends downstream of the reduced lower bifurcation (16).
5- Turboréacteur selon l'une des revendications 1 à 4, caractérisé en ce que l'échangeur thermique radial est solidaire du moteur. 5- turbojet engine according to one of claims 1 to 4, characterized in that the radial heat exchanger is integral with the engine.
EP08806024A 2007-06-25 2008-06-18 Turbojet engine for aircraft Withdrawn EP2167798A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0755988A FR2917714B1 (en) 2007-06-25 2007-06-25 TURBOREACTOR FOR AIRCRAFT
PCT/FR2008/051089 WO2009007564A2 (en) 2007-06-25 2008-06-18 Turbojet engine for aircraft

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JP (1) JP2010531408A (en)
CN (1) CN101730791A (en)
BR (1) BRPI0812818A2 (en)
CA (1) CA2690601A1 (en)
FR (1) FR2917714B1 (en)
RU (1) RU2471682C2 (en)
WO (1) WO2009007564A2 (en)

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CA2690601A1 (en) 2009-01-15
CN101730791A (en) 2010-06-09
RU2010102057A (en) 2011-07-27
US20100300066A1 (en) 2010-12-02
WO2009007564A3 (en) 2009-04-30
BRPI0812818A2 (en) 2014-12-09
FR2917714B1 (en) 2009-11-27
RU2471682C2 (en) 2013-01-10
JP2010531408A (en) 2010-09-24
WO2009007564A2 (en) 2009-01-15
FR2917714A1 (en) 2008-12-26

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