• 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 turbomachine (1) characterized in that it comprises: - an exhaust casing (7), comprising a plurality of arms (10), the space separating the arms defining openings (13), - at least one duct (2), ○ configured to withdraw at one of its ends (3) a flow of compressed air, ○ the other end of the duct (2) being connected to at least one opening (13) of the casing ( 7), to insert the air flow taken, said air flow having, when inserted into the opening (13), a Mach number less than or equal to 0.5.
    公开号:FR3016654A1
    申请号:FR1450491
    申请日:2014-01-21
    公开日:2015-07-24
    发明作者:Abdelkader Benyahia；Jean-Michel Boiteux；Maxime Delabriere；Matthieu Fiack；Eddy Stephane Joel Fontanel；Matos Alberto Martin；Helene Orsi；Philippe Rembry；Olivier Renon；Giuliana Elisa Rossi
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to a turbomachine, comprising a sampling of a stream of compressed air from the compressor.
    [0002] Presentation of the Prior Art A turbomachine conventionally comprises a high pressure compressor and a low pressure compressor. Depending on the speed of operation of the turbomachine (for example idle, or full throttle), the compressors have a different operation. When the turbine engine shifts from idling to full throttle, a flow of compressed air with high flow must be removed from the compressor, to avoid the risk of pumping. This is also the case during transient flight phases, or during idle phases, or more generally when the pilot is required to manipulate the throttle control. This flow of compressed air to be evacuated is indicative on some turbomachines, a pressure of about 40 bar and a temperature of about 900K. In general, the airflow is taken at 100 downstream of the high-pressure compressor, but such sampling at high temperature, high speed and expansion rates generates intense noise levels and induces thermal stresses. However, an acoustic constraint of the turbomachine imposes that the additional noise of the aircraft caused by the sampling of the air flow (clean noise of this new flow) and by its subsequent reintroduction is less than 1 EPNdB ("Effective Perceived Noise"). in Decibels ", ie the effective noise perceived in decibels). The prior art solutions proposed to evacuate the withdrawn air flow are unsatisfactory in this respect. According to a solution of the prior art, the air flow taken is reintroduced at the ejection nozzle of the turbomachine. However, this solution degrades the acoustics of the turbomachine. In addition, it is cumbersome to put in place because it requires the installation of large additional openings at the ejection nozzle. Another known solution is to reintroduce the flow of air into a secondary vein of the turbomachine. However, this involves introducing a flow of hot air into the cold stream of the secondary vein, this mixture causing a strong acoustic impact. PRESENTATION OF THE INVENTION In order to overcome the drawbacks of the state of the art, the invention proposes a turbomachine characterized in that it comprises an exhaust casing, comprising a plurality of arms, the space separating the arms defining openings, at least one duct, configured to withdraw at one of its ends a flow of compressed air, the other end of the duct being connected to at least one opening of the exhaust casing, to insert the flow of air taken, said air flow having, when inserted into the opening, a Mach number less than or equal to 0.5. The invention is advantageously completed by the following features, taken alone or in any of their technically possible combination: the duct terminates at its other end by a plurality of secondary ducts, the secondary ducts being connected to the casing openings. exhaust, to insert the flow of air taken; The turbomachine comprises one or more diaphragms disposed in the secondary ducts and making it possible to reduce the pressure of the flow of air taken through them. The diaphragms make it possible to maintain a flow at high pressure in the upstream ducts, which thus makes it possible to maintain a reduced diameter of the ducts over the entire corresponding length. After crossing the diaphragm, the flow is reduced, which contributes to the reduction of the flow velocity and the respect of the aerodynamic and acoustic constraints; the diaphragms have a plurality of holes; the turbomachine comprises one or more outward projecting mouths of the exhaust casing, the end of the secondary ducts being connected to the mouths to insert the flow of air taken to the openings; the turbomachine has a connection fillet between the mouths and the outer portion of the exhaust casing; the ends of the secondary ducts, inserting the flow of air taken, are arranged on the underside of the arms; the secondary ducts have a progressive inclination at their end whose slope is an angle 0 constantly less than or equal to 45 ° over the entire inclination with respect to a longitudinal axis of the turbomachine; the angle between the flow of air drawn introduced into the openings and the primary flow flowing in the turbomachine is less than 45 °, preferably less than 35 °; the ends of the secondary ducts connected to the openings of the exhaust casing are arranged at an azimuth angle between 3H and 9H. An advantage of the invention is to reduce the acoustic impact caused by the withdrawal of the flow and its reintroduction. Another advantage of the invention is to maximize the length of the conduits of the discharge system, for which they have a reduced diameter. The overall size of these ducts is reduced. In particular, the invention makes it possible to optimize a compromise between: the length of the ducts for which they have a reduced diameter; obtaining an air flow having a desired Mach number at the outlet of the ducts. Another advantage of the invention is to propose a simple and effective solution, in which a single piece makes it possible to influence both the pressure in the ducts, and therefore the length of the ducts for which a reduced diameter is obtained. as well as the acoustic impact induced by the withdrawal of the compressed air flow. Finally, another advantage of the invention is to provide a system with reduced space, and furthermore to preserve the secondary flow. Other features and advantages of the invention will become apparent from the description which follows, which is purely illustrative and non-limiting, and should be read with reference to the accompanying drawings, in which: FIG. a turbomachine of the prior art; - Figure 2 is a representation of a turbomachine portion according to one embodiment of the invention; Figures 3 and 4 show an exhaust housing including a plurality of arms ("TRF" arm, in side view and rear view); Figure 5 is a diagram showing a conduit terminating in secondary conduits including diaphragms, in accordance with a possible embodiment of the invention; - Figure 6 illustrates a possible positioning of the diaphragms; - Figure 7 shows the effect of the pressure drop at the outlet of the diaphragm on the flow of the air flow; Figure 8 shows a diaphragm having a plurality of holes; - Figure 9 shows an angle condition to improve the acoustic performance; - Figure 10 shows a sectional view of the mouth projecting from the outer shell of the exhaust casing and connected to the end of ducts; - Figure 11 shows a three-dimensional view of the protruding mouth on the outer shell of the exhaust casing. DETAILED DESCRIPTION As illustrated in FIG. 2, the turbofan engine 1 conventionally comprises a low pressure turbine 14, a high pressure turbine 19, and a high pressure compressor 38. The flow direction of the sampled flow is represented by an arrow in FIG. 1. The turbomachine 1 furthermore comprises an exhaust casing 7 disposed at the outlet of the low-pressure turbine 14. This exhaust casing 7 is designated by the English expression "Turbine Rear 15 Frame" by the skilled person, and is revolutionary. This exhaust casing 7 is conventionally arranged before the exhaust nozzle. It serves in particular to maintain the structure of the turbomachine. As illustrated in FIGS. 3 and 4, the exhaust casing 7 is substantially of revolution. It comprises a plurality of arms 10, the space 20 separating the arms defining openings 13. The arms 10 extend in particular between an inner hub 20 of the part and an outer shell 21 of the part. The ferrule 21 is for example polygonal. The hub 20 is manufactured in one piece and is cast. The arms 10 extend in a radial direction, or in a direction tangential to the hub, or in a direction intermediate between these two directions. Their summit is sunk. Radial is understood to mean the radial axis of the turbomachine 1, which extends radially with respect to the longitudinal axis of the turbomachine 1 (which is the axis of flow of the primary stream 29 of the turbomachine 1). The casing 7 generally comprises a plurality of sectors bonded together by welding.
    [0003] Suspension screeds 36 are generally provided in outer projection of the exhaust casing 7, and have one or more ears. Where appropriate, the exhaust casing 7 comprises at least one external flange 37, for example forged and attached.
    [0004] The turbomachine 1 further comprises at least one duct 2, configured to withdraw at one of its ends 3 a flow of compressed air. The sampling can for example be performed downstream of the compressor 38 high pressure. The other end of the duct 2 is connected to an opening 13 of the exhaust casing 7, to insert the flow of air taken. In other words, the duct 2 provides a fluid connection between the stream of compressed air taken and the opening 13. The air flow has, when inserted into the opening 13, a lower Mach number or equal to 0.5, which limits the acoustic impact.
    [0005] The duct 2 also comprises a valve 22 making it possible to control the flow rate of the air flow taken by the duct 2. The opening and the closing of this valve 22 are conventionally controlled by the computer of the aircraft, according to the orders of the pilot. This valve 22 is conventionally called TBV by those skilled in the art, for "Transient Bleed Valve". In the embodiment illustrated in the figures, the duct 2 terminates at its other end by a plurality of secondary ducts 6, the secondary ducts 6 being connected to openings 13 of the exhaust casing 7, to transmit the flow air taken.
    [0006] According to one possible embodiment, the other end of the conduit 2 terminates in at least two separate branches 17 each carrying a portion of the secondary ducts 6. In the example, each branch 17 carries three secondary ducts 6. According to one embodiment, the end 31 of the secondary ducts 6 pass through the outer shell 21 of the exhaust casing 7 to discharge into the openings 13 the flow of air taken. For this purpose, holes may be provided in the outer shell 21 to allow the passage of the end 31 of the ducts 6. The exhaust casing 7 typically comprises six holes symmetrically distributed: three holes on one side, and three holes of the other, so as to limit the thermomechanical distortion. According to another embodiment, illustrated in FIGS. 10 and 11, the turbomachine comprises one or more mouths 34 projecting from the shell 21, the end of the secondary ducts 6 being connected, for example by assembly, to the mouths 34 for insert the air flow taken to the openings 13. The mouths 34 may in particular be arranged on the collar 21 between the arms 10, and preferably between the weld zones. According to one possible embodiment, connection fillets are present between the lateral parts of the mouths 34 and the outer part (ferrule 21) of the exhaust casing 7. Furthermore, as explained below, it has been discovered that the fact that arranging the ends of the ducts 6 (ie ends which discharge the flow of air taken from the casing 7) from the intrados side of the arms 10 improves the aerodynamic performance.
    [0007] In the embodiment using mouths 34, they are therefore advantageously arranged on the underside of the arms 10. It is the same for the embodiment cited above using holes in the shell 21 external to allow the passage of the end 31 of the ducts 6, which are advantageously arranged on the underside of the arms 10. The azimuthal positioning of the ends of the ducts 6 has been defined in order to optimize the losses of the arms 10 of the casing 7 in the duct configuration. non-debiting.
    [0008] Due to the lift phenomenon, the Mach level at the lower surface of the arms of the casing 7 is lower compared to the Mach level at the upper surface.
    [0009] The presence of a conduit mouth in the vein in a non-flowable configuration is comparable to the presence of a discontinuity, or a wall that locally stops the flow of the vein at the housing 7.
    [0010] Local flow stop causes flow energy dissipation which results in increased losses and reduced aerodynamic performance. The energy dissipation generated decreases with the local Mach level of the flow, which explains the favorable properties of azimuthal positioning of the ends of the ducts 6 close to the intrados. In order to improve the acoustics, and as illustrated in FIG. 10, the secondary ducts 6 have a progressive inclination at their end whose slope is at an angle θ constantly lower than or equal to 45 ° with respect to a longitudinal axis 40. of the turbomachine.
    [0011] This smooths the evolution of the slope of the end of the secondary ducts 6 to the casing 7, and therefore not to have a too abrupt break in the slope of the ducts. Such a break-up would have the effect of causing massive boundary layer detachments, and hence an increase in noise.
    [0012] According to one embodiment, the ends 31 of the secondary ducts 6 are arranged on the lower part of the exhaust casing 7, as illustrated in FIG. 4, in order to respect installation and mechanical impact constraints on the casing 7. 'exhaust. Indeed, the upper part of the exhaust casing 7 is already mechanically loaded.
    [0013] The term "lower part" means that the ends 31 of the ducts 6 are arranged at an azimuth angle (1) (angle in the plane orthogonal to the longitudinal axis of the turbomachine) between 3H (H for Hours) and 9H . The air flow sampled typically has a pressure of about 40 bar. At the outlet of the valve 22 of the duct 2, the air flow typically has a pressure of approximately 10 bars. At the openings 13 in which the flow of air taken must be discharged, the pressure is about 1 bar. Therefore, an adaptation of the pressure of the air flow must be realized.
    [0014] The turbomachine 1 comprises diaphragms 15 arranged in the secondary ducts 6 and making it possible to reduce the pressure of the flow of air passing through them. The position of the diaphragms 15 influences the Mach at the outlet of the secondary ducts 6.
    [0015] The diaphragms 15 comprise a plate 25 having at least one hole 18. After passing through the diaphragm 15, the pressure of the air flow taken is for example, but not limited to, about 1 bar. At the passage of the diaphragm 15, the pressure drop of the air flow taken leads to the appearance of shock waves and a zone 30 where the flow is supersonic. In addition to the constraint on the Mach number less than 0.5 at the outlet of the secondary ducts 6, it is advantageous to have ducts with a reduced diameter.
    [0016] For this purpose, it is desirable for the flow of air taken to maintain a high pressure in the ducts 2, 6 over the highest possible distance, because this high pressure makes it possible to maintain a reduced diameter of the ducts 2, 6. therefore desirable to be able to arrange the diaphragms 15 as far downstream as possible from the ducts 6, in order to maximize the length over which the duct 2 and the secondary ducts 6 have a reduced diameter, for example of a value of less than 3 inches, while retaining a Mach number less than 0.5 at the outlet of the ducts 6. These two constraints are contradictory, the first imposing to arrange the diaphragms 15 as far downstream as possible from the ducts 6, the second imposing to arrange the diaphragms 15 as far upstream as possible from the ducts 6.
    [0017] In order to optimize this compromise, the diaphragms 15 have in one embodiment a plurality of holes 18. The use of multi-perforated diaphragms in place of conventional single-hole diaphragms allows for better mixing of the flow. at the exit of the diaphragm and a faster dissipation of shocks. Thus the extent of the zone 30 downstream of the diaphragm 15 where the flow is supersonic is reduced compared with the use of a conventional diaphragm.
    [0018] A single piece therefore allows both to respond to mechanical (duct diameter) and acoustic (Mach number out) constraints. By way of non-limiting example, the ducts have a diameter of 2 inches upstream of the diaphragms and 2.25 inches downstream of the diaphragms. According to an exemplary embodiment, the diaphragms 15 are arranged in the secondary ducts 6 at a position making it possible to obtain an air flow having a Mach number of less than 0.5 at the outlet of the secondary ducts and to maximize the length. on which the duct 2 and the secondary ducts 6 have a diameter of less than 3 inches. The position of the diaphragm can be found by simulations, or through experiments, or by a combination of both methods. Other constraints may be imposed on the sampled flow to improve acoustic performance. According to one embodiment, illustrated in Figure 9, the ducts 6 have, at their ends 31 connected to the openings 13, an angle with the longitudinal axis of the turbine engine lower than 45 °. This makes it possible to require that the stream of air drawn introduced into the openings 13 has an angle 13 less than 45 ° with the primary flow 29 flowing in the openings 13 of the turbomachine. Preferably, the angle 13 is less than 35 °.
    [0019] In the case where mouths 34 are used, this implies that the mouths 34 are inclined relative to the ferrule 21 with an angle less than or equal to 45 °, or 35 ° as appropriate. According to a possible aspect of the invention, each secondary duct 6 is connected to an opening 13 different from the exhaust casing 7, to transmit to it the flow of air taken. Since the openings 13 do not communicate with each other, this makes it possible to improve the acoustics of the outlet flow of the ducts 6 more advantageously, since the air flows leaving the ducts 6 do not mix. .10
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine (1) characterized in that it comprises: an exhaust casing (7), comprising a plurality of arms (10), the space separating the arms defining openings (13), at least one duct (2) , o configured to withdraw at one of its ends (3) a flow of compressed air, o the other end of the duct (2) being connected to at least one opening (13) of the exhaust casing (7), for inserting the sampled air flow therein, said airflow having, when inserted into the opening (13), a Mach number less than or equal to 0.5.
    [0002]
    2. A turbomachine according to claim 1, wherein the duct (2) terminates at its other end by a plurality of ducts (6) secondary, the ducts (6) being connected to the secondary openings (13) of the casing (7) d exhaust, to insert the flow of air taken.
    [0003]
    3. The turbomachine according to claim 2, comprising one or more diaphragms (15) disposed in the ducts (6) and secondary reducing the pressure of the flow of air taken through them.
    [0004]
    4. Turbomachine according to claim 3, wherein the diaphragms (15) have a plurality of holes (18).
    [0005]
    5. Turbomachine according to one of claims 2 to 4, comprising one or more mouths (34) projecting from the outside of the exhaust housing (7), the end of the conduits (6) being connected to the secondary mouths (34) for insert the air flow taken to the openings (13).
    [0006]
    6. The turbomachine according to claim 5, having a fillet (35) connection between the mouths (34) and the outer portion of the exhaust housing (7).
    [0007]
    7. A turbomachine according to one of claims 2 to 6, wherein the ends of the ducts (6) secondary, inserting the air flow taken, are disposed on the underside of the arms (10).
    [0008]
    8. The turbomachine according to one of claims 2 to 7, wherein the ducts (6) have a secondary slope inclined at their end whose slope is an angle 0 constantly less than or equal to 45 ° throughout the inclination by relative to a longitudinal axis (40) of the turbomachine.
    [0009]
    9. The turbomachine according to one of claims 1 to 8, wherein the angle (13) between the air flow taken introduced into the openings (13) and the primary flow (29) flowing in the turbomachine (1) is less than 45 ° or 35 °.
    [0010]
    10. A turbomachine according to one of claims 2 to 9, wherein the ends (31) of the conduits (6) secondary connected to the openings of the exhaust housing (7) are disposed at an azimuth angle between 3H and 9H.
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    引用文献:
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    法律状态:
    2016-01-12| PLFP| Fee payment|Year of fee payment: 3 |
    2017-01-13| PLFP| Fee payment|Year of fee payment: 4 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 8 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450491A|FR3016654B1|2014-01-21|2014-01-21|TURBOMACHINE WITH COMPRESSED AIR FLOW|
    FR1450491|2014-01-21|FR1450491A| FR3016654B1|2014-01-21|2014-01-21|TURBOMACHINE WITH COMPRESSED AIR FLOW|
    US15/112,952| US10316688B2|2014-01-21|2015-01-20|Turbomachine with collection of a compressed air flow|
    CN201580005407.6A| CN105934563B|2014-01-21|2015-01-20|Turbine with the collection to compressed air stream|
    RU2016134087A| RU2666928C2|2014-01-21|2015-01-20|Gas turbine engine with collection of compressed air flow|
    PCT/FR2015/050131| WO2015110748A1|2014-01-21|2015-01-20|Turbomachine with collection of a compressed air flow|
    EP15704347.2A| EP3097276B1|2014-01-21|2015-01-20|Turbomachine with compressed air bleeding|
    CA2937491A| CA2937491C|2014-01-21|2015-01-20|Turbomachine with collection of a compressed air flow|
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