• 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 defrosting device for a separation spout (8) and aeronautical turbomachine inlet guide vanes (18), comprising a separation spout (8) intended to be positioned at the downstream of a fan (2) of the turbomachine to form a separation between annular flow channels of a primary flow (4) and a secondary flow (6) from the fan, said nozzle having an annular wall outer wall (12) defining the interior of the flow channel of the secondary flow (6) and an inner annular wall (10) defining an inlet of the flow channel of the primary flow (4), said inner annular wall (10) being provided with injection orifices (14) through which hot air is to be blown, and an inner shell (16) to which inlet guide vanes (18) are attached and comprising a hook (22). , said inner ring (16) being locked axially upstream on the annular wall interior (10) by said hook (22). The hook (22) comprises an outer surface facing the outer annular wall (12) forming an angle less than 90 ° to the axis of an injection port (14) so that the outer surface of the hook (22) ) moves progressively closer to the outer annular wall (12) away from said injection port (14), the outer surface of the hook (22) having a minimum clearance J with the outer annular wall (12) such as 0, 2 ≤ J / D ≤ 0.6 where D is the hydraulic diameter of an injection port (14). The invention also relates to a fan module and a turbomachine comprising such a device.
    公开号:FR3047042A1
    申请号:FR1650510
    申请日:2016-01-22
    公开日:2017-07-28
    发明作者:Christophe Scholtes；Antoine Robert Alain Brunet；Simon Amoedo
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to the general field of turbomachines. The invention relates more particularly to a system for deicing a separation spout and fixed inlet vanes of the primary vein of the turbomachine.
    In an aerospace turbomachine of the double-body and double-flow type, the flow veins of the primary flow and the secondary flow are separated downstream of the fan by a separation nozzle. Within the primary vein, at the inlet of the low pressure compressor (also commonly known as "booster"), there is a set of fixed inlet guide vanes (also called IGV for "Inlet Guide Vane").
    In certain phases of flight and on the ground, icing atmospheric conditions may be encountered by the turbomachine, especially when the ambient temperature is sufficiently low and in the presence of high humidity. Under these conditions, ice may form on the separation nozzle and the inlet guide vanes. When this phenomenon occurs, it can lead to partial or complete obstruction of the primary vein, and ingestion of loose blocks of ice in the primary vein. An obstruction of the primary vein causes underfeeding of the combustion chamber which may then be extinguished or prevent acceleration of the engine. In the case of detachment of ice blocks, they can damage the compressor downstream and also lead to the extinction of the combustion chamber.
    To prevent the formation of ice on the separator nozzle, techniques are known to collect hot air in the primary stream at a compressor and inject it into the separator nozzle. The hot air injected into the separation spout can then travel along an inner wall of the spout until holes or grooves configured to inject the hot air into the primary vein towards the vanes to be defrosted. The use of holes in the inner shell carrying the guide vanes makes it possible to form hot air jets which can partially defrost the inlet vanes. However, the holes or grooves of these devices can not be positioned sufficiently upstream of the inlet guide vanes, which leaves little space for the jets to penetrate deep into the primary vein and de-ice the blades to a satisfactory height.
    Finally, the hot air flow required to defrost the separation spout and that the jets of hot air defrosting blades can fight against the flow of cold air entering the primary vein is important. This hot air sampling can reduce the performance and operability of the turbomachine. It would therefore be desirable to be able to increase the efficiency of the deicing of the spout and the inlet guide vanes simultaneously without increasing the hot air intake in the compressor.
    Object and summary of the invention
    The main object of the present invention is therefore to provide a device for deicing a separation spout and inlet guide vanes which allows an improved deicing of the separating nozzle and the guide vanes of the primary vein.
    This object is achieved with a device for deicing a separation nozzle and aerofoil turbine inlet guide vanes, comprising: a separation nozzle intended to be positioned downstream of a fan of the turbomachine to form a separation between annular flow channels of a primary flow and a secondary flow from the fan, said nozzle having an outer annular wall defining the inside of the flow channel of the secondary flow and an inner annular wall delimiting an inlet of the flow channel of the primary flow, said inner annular wall being provided with injection ports through which is intended to be blown hot air, and an inner ring on which are fixed inlet guide vanes and comprising a hook, said inner ferrule being locked axially upstream on the inner annular wall by said hook.
    According to the invention, the hook comprises an outer surface facing the outer annular wall forming an angle less than 90 ° with the axis of an injection orifice so that the outer surface of the hook is progressively closer to the outer annular wall away from said injection port, the outer surface of the hook having a minimum clearance J with the outer annular wall such that: 0.2 <J / D <0.6; where D is the hydraulic diameter of the injection port.
    In the present description, the terms "upstream" and "downstream" are defined with respect to the direction of flow of the air inside the turbomachine; the terms "inner" and "outer", "axial" and "radial", and their derivatives, are defined with respect to the longitudinal axis of the turbomachine.
    The device according to the invention makes it possible to ensure simultaneously and with the same flow of hot air, the defrosting of the separation nozzle and the inlet guide vanes. The angle less than 90 ° between the outer surface of the hook and the axis of an injection orifice, and the orientation of said surface allows the existence of a minimum clearance between the hook and the outer annular wall of the separation spout. This minimum clearance makes it possible to accelerate the flow of hot air that arrives inside the separation spout upstream. This acceleration of the hot air flow inside the spout increases the rate of impact of the hot air flow on the end of the spout, which improves its defrosting. In addition, the shape of the hook according to the invention allows a better distribution of hot air flow in azimuth, that is to say along the separation nozzle and around the longitudinal axis of the turbomachine. Conversely, with the devices of the prior art, the flow of hot air is generally concentrated around the holes which results in an inhomogeneous deicing of the separation nozzle. The inequality presented above for the minimum clearance J and the diameter of the injection ports D makes it possible to correctly ensure the deicing of the nozzle in all the operating conditions of the turbomachine.
    In the device according to the invention, the bores can be separated and remote from the hook and can thus be positioned further upstream of the inlet guide vanes than in the devices of the prior art. Thus, the hot air jets have more distance to enter the vein and defrost the inlet guide vanes to a greater depth in the vein.
    Generally speaking, the device according to the invention makes it possible, for the same flow of hot air taken from the engine, to obtain better deicing of the separation nozzle and better penetration of the hot air jets into the vein than with the devices of the prior art. Indeed, the studies have in particular shown an increase in the penetration of the jets in the vein up to 50% more than with the devices of the prior art based on hot air jets.
    The hook may be axisymmetric about a longitudinal axis of the turbomachine.
    Preferably, the outer surface of the hook forms an angle of between 40 ° and 70 ° with the axis of an injection orifice. When the hook is made in this way, the angle with which each jet of hot air enters the primary vein is such that the jet is tilted upstream than at an angle outside this range of values. This arrangement further increases the penetration of the jet of hot air into the vein and improves the defrosting of the inlet guide vanes.
    Also preferably, the hydraulic diameter D_ of an injection orifice respects the following inequality: 2% <D / H <6%, where H is the distance between the injection orifice and an inner wall of the injection channel. flow of the primary flow. The distance H also corresponds to the height of the flow vein of the primary flow at the injection ports. This range of values makes it possible to ensure that the jet of hot air in the vein is adapted to the dimensions of the compressor. Indeed, for values of D / H <2%, the flow of hot air leaving the orifice is too low to ensure proper defrosting. For values of D / H> 6%, the section of an orifice is larger and the generated jet is characterized by a low Mach number, which results in a rapid shear of the jet by the flow of the primary flow in the vein.
    According to one embodiment, each injection orifice may have a circular section.
    The device may further include hot air delivery means configured to deliver hot air upstream within the partition spout. The invention also relates to an aeronautical turbomachine blower module comprising: a blower, a low pressure compressor, inlet guide vanes located upstream of the low pressure compressor and downstream of the blower, and a blower device; defrosting such as that presented above, the injection orifices being positioned on the inner annular wall of the separation spout so that in operation, the hot air delivered by each injection orifice in the flow channel of the primary flow is ejected to a leading edge of an inlet guide vane.
    Finally, the invention also relates to an aerospace turbomachine comprising a fan module such as that presented above.
    BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures: FIG. 1 is a partial view in longitudinal section of an aeronautical turbomachine equipped with a deicing device according to the invention; FIG. 2 is an enlarged view of the turbine engine of FIG. of the separation spout, and - Figure 3 is an enlarged view of Figure 2 at the hook of the inner ring.
    Detailed description of the invention
    FIG. 1 partially represents an aeronautical turbomachine 1 of the double-body and double-flow type to which the invention can be applied.
    In a manner known per se, the turbomachine 1 is axisymmetric with respect to a longitudinal axis XX and comprises an inlet at its upstream end which receives external air, this air supplying a fan 2. Downstream of the fan 2, the air is distributed between a flow vein (or channel) of a primary flow 4 (or hot flow) and a flow vein of a secondary flow 6 (or cold flow). These two veins 4, 6 are separated from each other at their inlet by a separation spout 8. Once entered into the flow channel of the primary flow 4, the air then passes through a low pressure compressor 3 ( or "booster"), a high-pressure compressor, a combustion chamber and turbines (the latter elements are not shown in the figures), before being ejected outside the turbomachine.
    As shown in FIGS. 2 and 3, the separation spout 8 has a U- or V-shaped longitudinal section rounded at its upstream end, and comprises an inner annular wall 10 delimiting the inlet of the flow passage of the primary flow. 4, and an outer annular wall 12 defining inside the flow channel of the secondary flow 6. The outer annular wall 12 has a dimension in the longitudinal direction greater than that of the inner annular wall 10.
    The inner annular wall 12 of the partition spout 8 comprises bores forming hot air injection orifices 14 in the flow passage of the primary flow 4 having a drilling axis A. The injection orifices 14 are distributed circumferentially around the inner annular wall 10. The axis A of each orifice 14 is here substantially radial with respect to the axis XX of the turbomachine, that is to say that the axis A is substantially perpendicular to the axis XX. As can be seen in FIG. 2, the injection orifices 14 are separated by a distance H from the wall delimiting the flow vein of the primary flow inside (the distance H also corresponds to the vein height to the right of the injection ports 14). The injection orifices 14 may be circular, as in the example illustrated, or for example oval. In all cases, they may have a hydraulic diameter D respecting the inequality 0.02 <D / H <0.06. The hydraulic diameter is, in a manner known per se, defined for air as the ratio between four times the area of the passage section of an orifice and the perimeter of this orifice. In the case of an injection orifice 14 of circular section, the hydraulic diameter is equal to the diameter of the orifice.
    The inner annular wall 10 of the partition nozzle 8 is extended downstream by an inner shell 16. The inner shell 16 carries the fixed inlet vanes 18 of the turbomachine. Note that the position of the injection orifices 14 may be chosen so that in operation, the hot air jets delivered by said orifices 14 impart the leading edge of the inlet guide vanes 18 into the flow duct primary flow. The inner and outer annular walls 12 and the inner ferrule 16 define an annular cavity 20 inside the partition spout 8. The inner ferrule 16 is mounted and blocked upstream on the inner annular wall 10 of the spout. separation 8 by a hook 22 integrated in said ferrule 16, and downstream on a structural housing 24 of the turbomachine.
    In the illustrated example, the structural housing 24 comprises an inner casing 26 extending the inner ferrule 16 downstream, and on which the inner ferrule 16 comes to rest; and an outer housing 28 provided with a flange 30 intended to cooperate with a flange 32 present at the downstream end of the inner shell 16. The inner casings 26 and outer 28 delimit between them an annular channel for conveying hot air 34 opening into the cavity 20 of the partition nozzle 8 through openings 36 present in the flange 32 of the inner shell 16. Hot air injectors (not shown) to introduce the hot air sampled for example in a compressor of the turbomachine inside the annular channel for conveying hot air 34.
    The hook 22 upstream of the inner shell 16 is shown in more detail in FIG. 3. The hook 22 comprises an inner surface 220 resting on the inner annular wall 10 of the partition spout 8, and an outer surface 221 facing the outer annular wall 12 of the spout 8. The hook 22 further comprises an upstream surface 222 and a downstream surface 223 which are here substantially parallel to each other, and which here extend in a substantially radial direction. The upstream surface 222 of the hook 22 provides the connection between the inner surface 220 and the outer surface 221 upstream. The upstream surface 222 is here smaller than the downstream surface 223. In longitudinal section the surfaces 220, 221, 222 and 223 of the hook 22 are here substantially straight.
    The hook 22 is preferably axisymmetric about the axis XX, and positioned downstream of the injection ports 14 without obstructing them, that is to say that the hook 22 is not located radially above the orifices. 14. The hook 22 is offset from the injection orifices 14 so that the upstream surface 222 corresponding to the upstream end of the hook is located downstream of the injection orifices 14.
    According to the invention, the outer surface 221 of the hook 22 opposite the outer annular wall 12 of the partition nozzle 8 forms an angle α less than 90 ° with the axis A of an injection orifice (FIG. 3) . The angle may be between 40 ° and 70 ° to improve the penetration of the hot air jet into the flow path of the primary flow. Thus, the outer surface 221 of the hook 22 is inclined and progressively approaches the outer annular wall 12 of the spout 8 when moving from upstream to downstream on the outer surface 221, that is to say in its away from the injection orifice 14. The inclination of the outer surface 221 also makes it possible to define a variable clearance between this surface 221 and the outer annular wall 12 having a minimum value J. In the example illustrated, the set J is the distance between a point on the circular edge 224 between the surfaces 221 and 223, and the outer annular wall 12. According to the invention, the minimum clearance J and the hydraulic diameter D of the injection ports satisfy the inequality: 0.2 <J / D <0.6.
    In operation, hot air is conveyed, for example through the channel 34, into the cavity 20 inside the separation spout. The possible outputs for this flow of hot air (the flow of air being represented by dashed arrows in FIG. 2) are constituted by the injection orifices 14. The flow of hot air is thus directed towards the upstream of the separation nozzle 8 in the direction of the hook 22. When the air flow approaches the hook 22 it is deflected outwards by the downstream surface 223 of the hook 22. It must then travel over the hook by the narrowing where the clearance J is minimal between the outer surface 221 of the hook 22 and the outer annular wall 12 of the spout 8. When passing through the narrowing, the flow of hot air accelerates to impact the end of the spout 8 and warm it up. Finally, the air flow can follow the wall of the spout 8 at its upstream end and reach the injection ports 14 which project it into the vein in the form of jets of hot air. The jets of hot air thus generated can impact the inlet guide vanes at their leading edge to defrost them.
    The studies carried out showed a good distribution of the hot air flow in the azimuthal direction along the separation nozzle, but also a uniformity of the penetration depth of the jets created by the injection orifices in the vein. The device according to the invention thus makes it possible to perform more effectively the two functions of deicing the separating nozzle 8 and the inlet guide vanes 18, without the need to increase the hot air intake in the compressor compared to the devices. of the prior art.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1. Device for de-icing a separation spout (8) and aerobatic turbine engine inlet guide vanes (18), comprising: a separation spout (8) intended to be positioned downstream of a fan (2) of the turbomachine to form a separation between annular flow channels of a primary flow (4) and a secondary flow (6) from the fan, said nozzle having an outer annular wall ( 12) delimiting the interior of the flow channel of the secondary flow (6) and an inner annular wall (10) delimiting an inlet of the flow channel of the primary flow (4), said inner annular wall (10) being provided with injection ports (14) through which is intended to be blown hot air, and an inner shell (16) on which are fixed inlet guide vanes (18) and comprising a hook (22), said inner ferrule (16) being axially locked upstream on the inner annular wall (10) by r said hook (22), characterized in that the hook (22) comprises an outer surface (221) facing the outer annular wall (12) forming an angle (a) less than 90 ° with the axis (A) an injection port (14) so that the outer surface (221) of the hook (22) is progressively closer to the outer annular wall (12) away from said injection port (14), the surface outer (221) hook (22) having a minimum clearance J with the outer annular wall (12) such that: 0.2 <J / D <0.6 where D is the hydraulic diameter of the injection port ( 14).
    [2" id="c-fr-0002]
    2. Device according to claim 1, wherein the hook (22) is axisymmetric about a longitudinal axis (X-X) of the turbomachine.
    [3" id="c-fr-0003]
    3. Device according to any one of claims 1 and 2, wherein the outer surface (221) of the hook (22) forms an angle (a) between 40 ° and 70 ° with the axis (A) of a injection port (14).
    [4" id="c-fr-0004]
    4. Device according to any one of claims 1 to 3, wherein the hydraulic diameter D of an injection port (14) respects the following inequality: 2% <D / H <6%, where H is the distance between the injection port (14) and an inner wall (15) of the flow channel of the primary flow (4).
    [5" id="c-fr-0005]
    5. Device according to any one of claims 1 to 4, wherein each injection port (14) has a circular section.
    [6" id="c-fr-0006]
    6. Device according to any one of claims 1 to 5, further comprising means for conveying hot air (34, 36) configured to deliver hot air upstream inside the beak of separation (8).
    [7" id="c-fr-0007]
    Aeronautical turbomachine blower module comprising: a blower (2), a low pressure compressor (3), inlet guide vanes (18) located upstream of the low pressure compressor and downstream of the blower (2), and a de-icing device according to any one of claims 1 to 6, the injection ports (14) being positioned on the inner annular wall (10) of the separating spout (8) so that In operation, the hot air delivered from each injection port (14) in the flow channel of the primary flow (4) is ejected to a leading edge of an inlet guide vane (18).
    [8" id="c-fr-0008]
    Aeronautical turbomachine (1) comprising a fan module according to claim 7.
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    同族专利:
    公开号 | 公开日
    US20190024533A1|2019-01-24|
    EP3405656B1|2019-12-25|
    US10738650B2|2020-08-11|
    EP3405656A1|2018-11-28|
    CN108495977B|2020-10-02|
    WO2017125663A1|2017-07-27|
    FR3047042B1|2018-02-16|
    CN108495977A|2018-09-04|
    引用文献:
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    法律状态:
    2017-01-05| PLFP| Fee payment|Year of fee payment: 2 |
    2017-07-28| PLSC| Publication of the preliminary search report|Effective date: 20170728 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 6 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1650510|2016-01-22|
    FR1650510A|FR3047042B1|2016-01-22|2016-01-22|DEVICE FOR DEFROSTING A SEPARATION SPOUT AND INPUT DIRECTION GUIDES OF AERONAUTICAL TURBOMACHINE|FR1650510A| FR3047042B1|2016-01-22|2016-01-22|DEVICE FOR DEFROSTING A SEPARATION SPOUT AND INPUT DIRECTION GUIDES OF AERONAUTICAL TURBOMACHINE|
    CN201680056016.1A| CN108138582B|2015-07-30|2016-07-27|Anti-icing system for turbine engine blades|
    US15/748,252| US10683805B2|2015-07-30|2016-07-27|Anti-icing system for a turbine engine vane|
    EP16757306.2A| EP3329101A1|2015-07-30|2016-07-27|Anti-icing system for a turbine engine blade|
    PCT/FR2016/051953| WO2017017378A1|2015-07-30|2016-07-27|Anti-icing system for a turbine engine blade|
    US16/071,524| US10738650B2|2016-01-22|2017-01-10|Device for deicing a splitter nose and inlet guide vanes of an aviation turbine engine|
    CN201780007734.4A| CN108495977B|2016-01-22|2017-01-10|Device for deicing the splitter nose and inlet guide vanes of an aircraft turbine engine|
    PCT/FR2017/050048| WO2017125663A1|2016-01-22|2017-01-10|Aircraft turbomachine fan module with a device for de-icing a splitter nose and inlet guide vanes|
    EP17702678.8A| EP3405656B1|2016-01-22|2017-01-10|Aircraft turbomachine fan module with a device for de-icing a splitter nose and inlet guide vanes|
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