• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a turbofan engine (1) comprising: - a low pressure compressor (3); a series of housings (9, 10) downstream of this low-pressure compressor (3) for delimiting a primary circulation flow of a primary flow (6), and comprising an upstream edge (19) delimiting an inlet opening (23); - a high pressure compressor (24) in the primary vein; - a shroud (11) surrounding the series of housings (9, 10) for delimiting a flow stream of an intermediate flow (7), and having an upstream edge (19) delimiting a circular inlet opening (21) located upstream of the high pressure compressor (24); - a secondary vein casing (12) surrounding the fairing (11) for delimiting a secondary flow channel of a secondary flow (8); an exhaust casing (38) comprising radial arms (39) collecting air from the intermediate vein.
    公开号:FR3062678A1
    申请号:FR1700128
    申请日:2017-02-07
    公开日:2018-08-10
    发明作者:Antoine Jean-Philippe BEAUJARD；Tewfik Boudebiza；Catherine PIKOVSKY；Bastien Pierre VERDIER
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    (57) The invention relates to a turbofan engine (1) comprising:
    - a low pressure compressor (3);
    - A series of casings (9, 10) downstream of this low pressure compressor (3) to delimit a primary flow stream of a primary flow (6), and comprising an upstream edge (19) delimiting an inlet opening (23);
    - a high pressure compressor (24) in the primary stream;
    - a fairing (11) surrounding the series of casings (9, 10) to delimit a flow stream of an intermediate flow (7), and having an upstream edge (19) delimiting a circular inlet opening (21) located upstream of the high pressure compressor (24);
    - a secondary vein casing (12) surrounding the fairing (11) to delimit a secondary vein for circulation of a secondary flow (8);
    - An exhaust casing (38) comprising radial arms (39) collecting air from the intermediate stream.

    DOUBLE-FLOW TURBOREACTOR COMPRISING AN INTERMEDIATE VEIN DEDICATED TO
    THE AIR SUPPLY BY RADIAL ARMS OF AN EXHAUST CASING OF THIS
    TURBOJET
    DESCRIPTION
    TECHNICAL AREA
    The invention relates to the supply of air to the radial arms of an exhaust casing fitted to a turbofan engine.
    PRIOR STATE OF THE ART
    A dual-flow turbojet engine has an inlet sleeve that receives air which is drawn in by a low-pressure compressor and then is divided into a central primary flow and a secondary flow surrounding the primary flow.
    The secondary flow circulates in a space called secondary vein which is delimited externally by a secondary vein casing also called engine hull, and internally by an envelope surrounding the primary flow.
    The primary flow circulates in a space called primary vein delimited externally by the envelope and internally by a succession of fixed and rotating internal elements. The fixed internal elements include rectifier and distributor platforms, and inner casing ferrules, and the rotary internal elements include padded rotor wheel platforms.
    As a complement, purges blow air from the internal regions to the primary vein, through each space separating longitudinally a fixed internal element and a rotary internal element. These purges ensure that hot air from the primary vein does not enter the colder interior regions.
    More concretely, the primary flow circulates between an internal casing and an external casing of a high pressure compressor to be compressed in this high pressure compressor before being burned in a combustion chamber. It is then expanded in a high pressure turbine to drive the high pressure compressor, then in a low pressure turbine to drive the low pressure compressor, before being expelled to the rear by generating a thrust.
    The envelope delimiting the primary stream externally is thus formed by a series of casings comprising a high pressure compressor casing, a casing at the level of the combustion chamber and a high pressure turbine casing, as well as by an external casing shell. 'exhaust.
    Each turbine and each compressor is formed of stages each comprising a series of rotary vanes regularly spaced around a longitudinal central axis of the engine, possibly preceded by a distributor in the case of a turbine or possibly followed by a rectifier. in the case of a compressor. Distributors and rectifiers consist of a series of fixed vanes.
    The rear part of such an engine comprises, downstream of the low pressure turbine, an exhaust casing, usually designated by the acronym TRF (Turbine Rear Frame), which carries a bearing supporting a rear end of the engine rotor.
    This exhaust casing comprises an internal ferrule and an external ferrule and radial arms joining these ferrules to one another, crossing radially the primary vein.
    The bearing which the exhaust casing supports is supplied with air coming from the secondary stream by being conveyed by the arms of the exhaust casing. This air is used in particular for cooling the radial arms and for externally pressurizing a lubrication enclosure in which the bearing carried by this exhaust casing is housed.
    However, the casings surrounding the primary stream carry on their external faces elements such as fuel rails, variable pitch blade control systems or the like. These elements protrude, so that they introduce significant pressure drops for the secondary flow portion which runs along them and in which the supply air is collected passing through the radial arms of the exhaust casing.
    Because of these pressure drops, the pressure at the collection openings may prove to be insufficient to generate in the radial arms of the exhaust casing a sufficient flow.
    One solution could consist in collecting air by means of a scoop protruding radially from the casings surrounding the primary vein, at the level of the radial arms, but such a scoop would introduce turbulences which are penalizing for the flow of the secondary flow.
    The object of the invention is to provide an architecture making it possible to improve the air supply through the radial arms of the exhaust casing.
    STATEMENT OF THE INVENTION
    To this end, the invention relates to a turbofan engine comprising:
    - a low pressure compressor;
    - A series of casings extending downstream of this low pressure compressor to delimit a primary flow stream of a primary flow, and comprising an upstream edge delimiting a circumferential inlet opening of this primary flow;
    - a high pressure compressor located in the primary stream;
    - a fairing delimiting with the series of casings that it surrounds an intermediate stream of circulation of an intermediate flow, this fairing having an upstream edge delimiting with this series of casings an inlet opening located upstream of the high pressure compressor;
    - a secondary vein casing surrounding the intermediate fairing to delimit with this fairing a secondary vein for circulation of a secondary flow;
    - An exhaust casing comprising an external ferrule extending in the extension of the series of casings as well as radial arms starting from this external ferrule, at least one of these radial arms collecting air coming from the vein intermediate to supply pressurized air to a central region of this exhaust casing.
    With this arrangement, the pressure prevailing at the inlet of the radial feed arms of the casing corresponds to the static pressure increased by the dynamic pressure at the outlet of the low pressure compressor, without the flow of the secondary flow being disturbed.
    The invention also relates to a turbojet engine thus defined, in which the air supplied in the central region of the exhaust casing contributes to pressurizing the seals of a lubrication enclosure in which is housed a bearing carried by this exhaust casing. .
    The invention also relates to a turbojet engine thus defined, in which the air supplied to the central region of the exhaust casing feeds a purge located upstream of the exhaust casing.
    The invention also relates to a turbojet engine thus defined, in which the radial arms of the exhaust casing comprise perforated jackets arranged so that the air passing through these radial arms cools the walls of these arms.
    The invention also relates to a turbojet engine thus defined, in which the inlet opening of the intermediate stream is a circumferential opening surrounding the primary stream.
    The invention also relates to a turbojet engine thus defined, in which the fairing joins the outer shroud of the exhaust casing downstream of the radial arms of this exhaust casing.
    BRIEF DESCRIPTION OF THE DRAWINGS
    Figure 1 is a schematic half-view along a longitudinal sectional plane of the engine according to the invention as a whole;
    Figure 2 is a half-view along a longitudinal sectional plane of a part of the engine according to the invention extending from its combustion chamber to its exhaust casing;
    Figure 3 is a schematic half-sectional view illustrating the path of the air collected at the exhaust casing in the engine according to the invention.
    DETAILED PRESENTATION OF PARTICULAR EMBODIMENTS
    The idea underlying the invention is to collect the air intended to pass through the radial arms of the exhaust casing, directly downstream of the low pressure compressor in order to benefit from the static pressure increased by the dynamic pressure downstream of the low pressure compressor.
    In FIG. 1, a turbofan engine 1 has an inlet sleeve 2 in which the air is sucked in by the blades of a low pressure compressor 3 surrounded by a casing 4 of the low pressure compressor, to then be divided into three flows at an intermediate casing 5 extending longitudinally between the low pressure compressor and a high pressure compressor. These three flows comprise a central primary flow 6, an intermediate flow 7 surrounding the primary flow, and a secondary flow 8 which surrounds the intermediate flow 7.
    The primary flow 6 circulates in a primary vein which is delimited internally by a succession of internal fixed elements and internal rotary elements. The fixed internal elements include rectifier and distributor platforms, and inner casing ferrules, and the rotary internal elements include padded rotor wheel platforms.
    This primary stream is delimited externally by a series of casings which surround it and which include a high pressure compressor casing 9, a casing surrounding the combustion chamber and a casing surrounding the high pressure turbine identified jointly by 10, as well as by a external casing of the exhaust casing.
    The intermediate flow circulates between on the one hand the series of casings delimiting the primary vein, and on the other hand an intermediate fairing 11 which surrounds them over all their lengths.
    The secondary flow circulates in a secondary vein delimited internally by the intermediate fairing 11 and externally by a secondary vein casing 12 surrounding the intermediate fairing 11.
    The intermediate casing 5 comprises an external ferrule and an internal ferrule connected by radial arms, and it is located between the low pressure compressor 3 and the high pressure compressor 24. Its external ferrule connects the casing 4 of the low pressure compressor to the vein casing secondary 12, and its internal ferrule and supports the bearings of these compressors.
    An upstream circular edge 18 of the external casing of the high pressure compressor, and an upstream circular edge 19 of the intermediate casing 11 are located at the level of this intermediate casing 5. The upstream circular edge 18 of the high pressure compressor casing internally delimits an opening circumferential entry 23 of the primary vein.
    The upstream circular edge 19 of the fairing 11 defines with the edge 18 a circumferential inlet opening 21 of the intermediate vein, and it defines with the secondary vein casing 12 a circumferential inlet opening 22 of the secondary vein. These inlet openings have both crown shapes and they both receive air having undergone low pressure compression and circulating in the intermediate casing 5.
    The edges 18 and 19 can if necessary be formed directly in the intermediate casing in the form of corresponding spouts extended respectively by the high pressure compressor casing and by the intermediate fairing 11.
    After the intermediate casing 5, the primary flow 6 passes through a high pressure compressor 24 before reaching a combustion chamber 26 to be then expanded in a high pressure turbine 28 then in a low pressure turbine 29.
    As can be seen more clearly in FIG. 2, the high pressure turbine 28 comprises a disc 31 carrying corresponding vanes, this disc being secured to a high pressure body 25 extending upstream to the compressor 24 of which this high pressure body 25 carries also the vanes.
    The low pressure turbine 29 comprises two discs 32, 33 carrying corresponding blades, and which are secured to a low pressure journal 34 having a downstream end received in a bearing 36. This bearing 36 is located in the central region of a casing exhaust 38 which surrounds it while ensuring its maintenance.
    This exhaust casing 38 includes an internal ferrule and an external ferrule which externally delimits the primary stream, as well as radial arms 39 joining these ferrules to one another. The outer shell extends in continuity with the series of casings 9, 10 and the radial arms radially cross the primary stream, the assembly being located downstream of the low pressure turbine 29.
    This exhaust casing 38 also carries an outlet cone 41 which is surrounded by a confluence wall 42, downstream of the low pressure turbine 29 and radial arms 39. This confluence wall which is fixed to a flange of the casing exhaust extends in the extension of the outer shell of the exhaust casing to guide the secondary flow so that it has the most regular flow possible, that is to say without disturbances.
    One or more of the radial arms 39 is hollow, so as to convey, in a central region of this exhaust casing 38, air coming from the intermediate stream, in particular for pressurizing the seals of the lubrication enclosure of the bearing carried by this casing, along a path F shown in dotted lines in FIGS. 1 and 2.
    The intermediate fairing 11 surrounds the series of casings externally delimiting the primary stream from the intermediate casing corresponding to the outlet of the low pressure compression portion, up to the rear of the engine downstream of the radial arms 39. As can be seen in particular on the FIG. 1, the series of casings 9 and 10 carries on its external face various pieces of equipment, such as flanges, fuel rails, variable-pitch blade control systems or the like, identified by 37. The intermediate fairing 11 begins when the high pressure compressor is fitted.
    In other words, the various pieces of equipment 37 are all located in the intermediate vein instead of being located in the secondary vein, so that they do not introduce a pressure drop in the secondary vein. Over its entire length, this fairing 11 surrounds the series of casings 9, 10 in order to delimit therewith an annular space for circulation of the air flow from the intermediate stream.
    This fairing 11 has a downstream end 43 located after the radial arms 39 which tightens to join the outer shell of the exhaust casing so that the intermediate stream is closed at its rear end.
    The intermediate flow 7 is thus evacuated mainly by the internal channel or channels of the radial arms 39, in particular for cooling these arms, pressurizing the seals of the lubrication enclosure of the bearing carried by this casing, as well as for supplying a purge.
    In general, the pressure prevailing in the whole of the intermediate vein corresponds to the total pressure at its inlet 21, that is to say to the static pressure of the air which has been compressed by the compressor low pressure 3 increased by dynamic pressure. Indeed, the flow rate of the intermediate flow being relatively low, the pressure drops introduced by the elements 37 are reduced.
    Under these conditions, the pressure prevailing at the inlet of the radial arms 39 is equal to the total pressure prevailing at the inlet 21, that is to say the static pressure resulting from the compression delivered by the low pressure compressor increased by dynamic pressure.
    The invention thus makes it possible, despite the presence of the elements 37 protruding from the external face of the series of housings 9, 10, to maintain a sufficiently high pressure of the flow along the external face of this series of housings. It also makes it possible to limit the turbulence of the secondary flow which no longer follows the irregularities that constitute the elements 37.
    As shown diagrammatically in FIG. 3, the intermediate flow 7 which passes through the radial arms of the exhaust casing, cools these arms, pressurizes the lubrication enclosure containing the bearing which this exhaust casing carries, and it also supplies a drain located between the last rotary stage of the low pressure turbine and the exhaust casing.
    To improve the cooling of the radial arms 39, these are fitted with internal perforated jackets arranged to improve thermal convection along the walls of these arms.
    As shown in FIG. 3, the flow 7 passes through the arms 39 of the casing to cool them, and a first part of the remaining air is directed towards the environment of the lubrication enclosure carried by the exhaust casing, to contribute to its pressurization, which is represented by arrow 46.
    The air from flow 7, supplemented by another pressurization air 47, coming from upstream of the low-pressure turbine, is moreover reintroduced into the primary vein by passing through a passage 48 formed in the internal shell of the casing d exhaust 38.
    A second part of the remaining air is directed to the bleed 49 located between the last stage of the low pressure turbine and the exhaust casing 38. The bleed is supplemented by air 47 from the upstream of the turbine .
    Furthermore, the intermediate flow can also be used to cool a high pressure turbine housing in order to reduce the play existing between the blade ends of the high pressure turbine and this housing.
    权利要求:
    Claims (6)
    [1" id="c-fr-0001]
    1. Double-flow turbojet (1) comprising:
    - a low pressure compressor (3);
    - A series of casings (9, 10) extending downstream of this low pressure compressor 5 (3) to delimit a primary flow stream of a primary flow (6), and comprising an upstream edge (18) delimiting a circumferential inlet opening (23) of this primary flow (6);
    - a high pressure compressor (24) located in the primary stream;
    - a fairing (11) delimiting with the series of casings (9, 10) that it surrounds an intermediate flow stream of an intermediate flow (7), this fairing having an upstream edge (19) delimiting with this series of housings (9, 10) an inlet opening (21) located upstream of the high pressure compressor (24);
    - a secondary vein casing (12) surrounding the intermediate fairing (11) to delimit with this fairing (11) a secondary vein of
    15 circulation of a secondary flow (8);
    - an exhaust casing (38) comprising an external ferrule extending in the extension of the series of casings (9, 10) as well as radial arms starting from this external ferrule, at least one of these radial arms ( 39) collecting air from the intermediate vein to supply pressurized air to a central region
    20 of this exhaust casing (38).
    [2" id="c-fr-0002]
    2. Turbojet engine according to claim 1, in which the air supplied in the central region of the exhaust casing (38) contributes to pressurizing the joints of a lubrication enclosure in which is housed a bearing carried by this casing.
    25 exhaust (38).
    [3" id="c-fr-0003]
    3. Turbojet engine according to claim 1 or 2, wherein the air supplied to the central region of the exhaust casing (38) feeds a purge (49) located upstream of the exhaust casing (38).
    [4" id="c-fr-0004]
    4. A turbojet engine according to one of claims 1 to 3, in which the radial arms (39) of the exhaust casing (38) comprise perforated liners arranged so that the air passing through these radial arms (39) cools the walls of these arms.
    [5" id="c-fr-0005]
    5. A turbojet engine according to one of claims 1 to 4, wherein the inlet opening (21) of the intermediate vein is a circumferential opening surrounding the primary vein.
    [6" id="c-fr-0006]
    10 6. Turbojet engine according to one of claims 1 to 5, wherein the fairing (11) joins the outer shell of the exhaust casing downstream of the radial arms (39) of this exhaust casing (38).
    S.61698
    1/2
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    同族专利:
    公开号 | 公开日
    WO2018146405A1|2018-08-16|
    US20200032664A1|2020-01-30|
    FR3062678B1|2019-04-19|
    EP3580443A1|2019-12-18|
    CN110268152A|2019-09-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB695482A|1950-11-28|1953-08-12|Rolls Royce|Improvements in or relating to gas-turbine engines|
    FR2824598A1|2001-05-10|2002-11-15|Snecma Moteurs|Ventilation of turbojet nacelle is obtained by means of cavities in structural arms of enclosure in turbine rear and orifices in exhaust casing external scroll and in enclosure walls|
    FR2897655A1|2006-02-13|2007-08-24|Gen Electric|TURBOPROPULSEUR DOUBLE FLUX|
    WO2013165281A1|2012-05-02|2013-11-07|Gkn Aerospace Sweden Ab|Supporting structure for a gas turbine engine|FR3088955A1|2018-11-27|2020-05-29|Safran Aircraft Engines|Double-flow turbojet engine comprising an outlet cone cooled by its secondary flow|
    FR3101379A1|2019-09-30|2021-04-02|Safran Aircraft Engines|TURBOMACHINE ENCLOSURE PRESSURIZATION WITH AIR FROM THE SECONDARY VEIN|GB938247A|1962-03-26|1963-10-02|Rolls Royce|Gas turbine engine having cooled turbine blading|
    US9004849B2|2012-01-10|2015-04-14|United Technologies Corporation|Gas turbine engine forward bearing compartment architecture|FR3062681B1|2017-02-07|2020-11-20|Safran Aircraft Engines|TURBOREACTOR WITH OPTIMIZED BEARING ARCHITECTURE FOR THE SUPPORT OF A LOW PRESSURE SHAFT|
    法律状态:
    2018-01-22| PLFP| Fee payment|Year of fee payment: 2 |
    2018-08-10| PLSC| Publication of the preliminary search report|Effective date: 20180810 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 4 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 5 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1700128|2017-02-07|
    FR1700128A|FR3062678B1|2017-02-07|2017-02-07|DOUBLE FLOW TURBOREACTOR COMPRISING AN INTERMEDIATE VEHICLE DEDICATED TO AIR SUPPLY BY RADIAL ARMS OF AN EXHAUST CASE OF THIS TURBOJET ENGINE|FR1700128A| FR3062678B1|2017-02-07|2017-02-07|DOUBLE FLOW TURBOREACTOR COMPRISING AN INTERMEDIATE VEHICLE DEDICATED TO AIR SUPPLY BY RADIAL ARMS OF AN EXHAUST CASE OF THIS TURBOJET ENGINE|
    US16/483,526| US20200032664A1|2017-02-07|2018-02-05|Double flow turbojet including an intermediate flow path dedicated to supplying with air via radial arms an exhaust casing of this turbojet|
    PCT/FR2018/050275| WO2018146405A1|2017-02-07|2018-02-05|Turbofan comprising an intermediate stream for the supply of air via radial arms to an exhaust housing of said turbofan|
    EP18706791.3A| EP3580443A1|2017-02-07|2018-02-05|Turbofan comprising an intermediate stream for the supply of air via radial arms to an exhaust housing of said turbofan|
    CN201880010503.3A| CN110268152A|2017-02-07|2018-02-05|Turbofan including the intermediate flow for supplying air to the exhaust holding part of turbofan by radial arm|
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