EP2167798A2 - Turbostrahltriebwerk für ein flugzeug - Google Patents

Turbostrahltriebwerk für ein flugzeug

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Withdrawn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
English (en)
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/de
Withdrawn legal-status Critical Current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.

Landscapes

  • 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)
EP08806024A 2007-06-25 2008-06-18 Turbostrahltriebwerk für ein flugzeug Withdrawn EP2167798A2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0755988A FR2917714B1 (fr) 2007-06-25 2007-06-25 Turboreacteur pour aeronef
PCT/FR2008/051089 WO2009007564A2 (fr) 2007-06-25 2008-06-18 Turboreacteur pour aeronef

Publications (1)

Publication Number Publication Date
EP2167798A2 true EP2167798A2 (de) 2010-03-31

Family

ID=39137037

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08806024A Withdrawn EP2167798A2 (de) 2007-06-25 2008-06-18 Turbostrahltriebwerk für ein flugzeug

Country Status (9)

Country Link
US (1) US20100300066A1 (de)
EP (1) EP2167798A2 (de)
JP (1) JP2010531408A (de)
CN (1) CN101730791A (de)
BR (1) BRPI0812818A2 (de)
CA (1) CA2690601A1 (de)
FR (1) FR2917714B1 (de)
RU (1) RU2471682C2 (de)
WO (1) WO2009007564A2 (de)

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FR3006996B1 (fr) * 2013-06-14 2016-12-09 European Aeronautic Defence & Space Co Eads France Ensemble de propulsion electrique pour aeronef
FR3018858B1 (fr) * 2014-03-19 2019-04-05 Airbus Operations (S.A.S.) Ensemble propulsif d'aeronef comprenant un systeme de refroidissement
CN103982302B (zh) * 2014-05-23 2016-02-17 中国航空动力机械研究所 用于燃气轮机发电机组的冷却机构及燃气轮机发电机组
FR3024495B1 (fr) * 2014-07-31 2019-07-12 Safran Aircraft Engines Dispositif de circulation d'air a debit ajustable pour turbomachine
DE102015110615A1 (de) * 2015-07-01 2017-01-19 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufel eines Gasturbinentriebwerks, insbesondere eines Flugtriebwerks
US10036318B2 (en) 2015-12-22 2018-07-31 Snecma Air circulation device for turbomachine
FR3047270B1 (fr) * 2016-01-29 2019-03-29 Safran Aircraft Engines Echangeur thermique surfacique et traitement acoustique
CN107054698B (zh) * 2017-03-07 2021-04-06 沈武云 航天器外表面除热装置
CN110159358B (zh) * 2018-02-14 2022-02-08 中国航发商用航空发动机有限责任公司 级间机匣
GB201817153D0 (en) * 2018-10-22 2018-12-05 Rolls Royce Plc Gas turbine engine
FR3093540B1 (fr) * 2019-03-07 2021-04-23 Safran Aircraft Engines Turbomachine double flux a gaz a bras echangeur thermique
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GB202017401D0 (en) * 2020-11-03 2020-12-16 Rolls Royce Plc Gas turbine engine with cabin blower system
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Also Published As

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

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