• 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 device (9) for cooling a turbine casing for a turbomachine, such as for example an airplane turbojet, comprising means for sampling and supplying air (10, 11, 15). , 16), means for distributing the withdrawn air comprising at least one ramp (20a, 20b) extending circumferentially around the axis (X) of the turbomachine, said ramp (20a, 20b) being connected to the means for withdrawing and supplying air (10, 11, 15, 16) via a connection zone (19), said ramp (20a, 20b) having orifices distributed along the ramp (20a, 20b), withdrawn air being intended to escape from said orifices to cool the casing, characterized in that the distribution of the orifices along the ramp (20a, 20b) is such that the density of the orifices is greater in a zone of the ramp (20a, 20b) remote from the connection zone (19) only in a zone of the ramp (20a, 20b) close to the connection zone (19).
    公开号:FR3054000A1
    申请号:FR1656807
    申请日:2016-07-15
    公开日:2018-01-19
    发明作者:Bernard Quelven Damien；Claude Descamps Laurent；Fabien Francois Villard Loic；Alexandre Carlos Pierre-Louis
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Holder (s): SAFRAN AIRCRAFT ENGINES Simplified joint-stock company.
    Extension request (s)
    Agent (s): ERNEST GUTMANN - YVES PLASSERAUD SAS.
    DEVICE FOR COOLING A TURBINE HOUSING FOR A TURBOMACHINE.
    FR 3,054,000 - A1
    The invention relates to a device (9) for cooling a turbine casing for a turbomachine, such as for example an aircraft turbojet, comprising means for taking off and supplying air (10, 11, 15 , 16), means for distributing the extracted air comprising at least one ramp (20a, 20b) extending circumferentially around the axis (X) of the turbomachine, said ramp (20a, 20b) being connected to the means sampling and supplying air (10, 11, 15, 16) via a connection zone (19), said ramp (20a, 20b) having orifices distributed along the ramp (20a, 20b), l the sampled air being intended to escape from said orifices to cool the casing, characterized in that the distribution of the orifices along the ramp (20a, 20b) is such that the density of the orifices is greater in an area of the ramp (20a, 20b) distant from the connection zone (19) than in a zone of the ramp (20a, 20b) close to the connection zone (19).

    Device for cooling a turbine casing for a turbomachine
    The present invention relates to a device for cooling a turbine casing for a turbomachine, such as for example an aircraft turbojet, in particular a turbofan.
    A turbofan engine conventionally comprises a fan downstream of which extends:
    a primary stream in which a primary stream flows, said primary stream passing in particular, in the direction of flow of the primary stream, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a turbine, the primary stream being delimited externally at the level of the turbine by a turbine casing,
    - a secondary vein in which flows a secondary flow distinct from the primary flow.
    The primary air flow from the turbine chamber has a very high temperature and heats the downstream parts, in particular the turbine housing. In order to avoid any premature degradation of said turbine casing, it is necessary to provide efficient cooling means which can be easily integrated into the environment of the turbojet engine.
    Patent application FR 2 867 806, in the name of the Applicant, discloses a device for cooling a turbine casing for a turbomachine comprising means for extracting and supplying air and means for distributing air sampled comprising ramps extending circumferentially around the axis of the turbomachine. The ramps are connected to the sampling and air intake means by connection zones. Each ramp has orifices distributed along the ramp, the sampled air being intended to escape from said orifices to cool the casing.
    The orifices are uniformly distributed along each ramp so as to have a relatively uniform flow over the entire circumference of the casing.
    It has been found that the air circulating in the ramps is heated by its environment as it progresses along the ramp, that is to say as it moves away of the connection zone through which it emerges into the ramp. The temperature differences of the air passing through the area of the ramp located near the connection area and the air passing through the area of the ramp remote from the connection area may be greater than 200 ° C. for example. The areas of the casing located at a distance from the connection areas are thus less well cooled and are subjected to thermal stresses which can cause risks of degradation.
    The object of the invention is in particular to provide a simple, effective and economical solution to this problem.
    To this end, it proposes a device for cooling a turbine casing for a turbomachine, such as for example an airplane turbojet, comprising means for taking off and supplying air, means for distributing the 'sampled air comprising at least one ramp extending circumferentially around the axis of the turbomachine, said ramp being connected to the air intake and intake means by a connection zone, said ramp comprising orifices distributed along from the ramp, the sampled air being intended to escape from said orifices to cool the casing, characterized in that the distribution of the orifices along the ramp is such that the density of the orifices is greater in an area of the ramp distant from the connection area than in an area of the ramp close to the connection area.
    In this way, the cooling air flow in the area of the ramp remote from the connection area is greater than in the area of the ramp close to the connection area, so as to compensate for the increase in temperature. air as the air progresses along the ramp.
    Preferably, the orifices are distributed in such a way that a constant convective air exchange is observed over the entire length of the ramp, so as to ensure uniform cooling of the turbine casing.
    According to the invention, in order to adjust the air flow, one acts on the density of the orifices as a function of their position along the ramp, rather than on the diameter of said orifices. Indeed, the fact of increasing the diameter of the orifices, if it makes it possible to increase the air flow rate, does not necessarily make it possible to significantly increase the convective heat exchange.
    The ramp may extend over the entire circumference, that is to say 360 ° or almost 360 °, or over only part of the periphery, for example at an angle of the order of 180 ° or around 90 °. A ramp can extend circumferentially on each side of the connection zone. Thus, the same connection zone can supply two opposite ramps each extending over 90 ° for example, so as to cover and cool an area of the housing extending to 180 °.
    The air intake and intake means make it possible to take air from one or more areas of the turbomachine where the air is relatively cold, in comparison with the temperature of the turbine casing in operation, for example at the level a flow stream for the secondary flow, in the context of a turbofan engine, or at the compressor, for example at the low-pressure compressor.
    The sampling and air intake means can be equipped with a valve making it possible to regulate the flow of sampled air, for example as a function of the engine speed and / or the flight conditions.
    The ramp may include at least one row of orifices spaced apart from each other, the pitch or spacing between the orifices being smaller in the zone remote from the connection zone than in the zone close to the connection zone.
    The distance between the centers of two consecutive or adjacent orifices is defined by step or distance between centers.
    The ramp may include a first zone close to the connection zone and a second zone distant from the connection zone, the orifices being separated by a first step in the first zone and by a second step in the second zone, the second not being less than the first step.
    In this way, the ramp has two types of center distance, which remains relatively simple to achieve in terms of machining range for example.
    In this case, the first zone of the ramp may extend over a length between 50 and 80% of the length of the ramp, preferably between 60 and 75% of the length of the ramp, even more preferably between 64 and 70% of the length of the ramp.
    As a variant, the pitch or the spacing between the orifices can vary continuously along the ramp, so that the pitch or spacing is progressively reduced as one moves away from the connection zone . In such a case, the pitch can be constant over a part of the ramp close to the connection zone, then be gradually reduced as one moves away from the connection zone.
    Such an alternative embodiment, if it is more complex to produce, makes it possible to more finely control the distribution of air along the ramp, as required.
    The orifices of the ramp can be located on the same radial plane.
    The orifices are then arranged in a circumferential line along the ramp.
    The orifices of the ramp can be distributed over at least two radial planes spaced axially from one another, the orifices of the two radial planes being staggered.
    In this case, the orifices are arranged along at least two circumferential lines along the ramp.
    The orifices can be cylindrical and have substantially the same diameter.
    The device can include at least two connecting zones, located for example diametrically opposite.
    Two ramps can extend on either side of each connection zone. The ramps located on the same radial plane can cover the entire circumference of the housing, that is to say extend substantially over 360 °.
    The device can comprise at least two ramps extending circumferentially in two radial planes offset axially from one another, the two ramps being connected to the same connection zone.
    The connection zone thus forms a manifold capable of receiving the air from the air intake and intake means and of distributing it in each of the ramps.
    The invention also relates to a turbofan engine, comprising a fan downstream of which extends:
    a primary stream in which a primary stream flows, said primary stream passing in particular, in the direction of flow of the primary stream, a compressor, a combustion chamber and a turbine comprising a turbine casing,
    - a secondary stream in which flows a secondary stream distinct from the primary stream, characterized in that it comprises a cooling device of the aforementioned type, the ramp extending circumferentially around the axis of the turbojet engine and being located radially outside the turbine casing, the orifices being turned in the direction of said turbine casing, the air intake and intake means being able to take air from the secondary stream.
    The secondary air flow does not pass through the compressor and the combustion chamber, so that it is at a relatively low temperature. This air can therefore be taken and used to effectively cool the turbine housing.
    The invention will be better understood and other details, characteristics and advantages of the invention will appear on reading the following description given by way of nonlimiting example with reference to the appended drawings in which:
    FIG. 1 is a view in axial section of a part of a double-flow reactor according to an embodiment of the invention,
    FIG. 2 is a perspective view of the cooling device according to the invention,
    - Figure 3 is a schematic view of part of a ramp,
    FIG. 4 is a front view of part of the cooling device,
    - Figure 5 is a diagram illustrating the evolution of the air temperature along a ramp, as a function of the angular position relative to the corresponding connection area, in the case of the prior art and in the case of the invention,
    - Figure 6 is a schematic view of part of a ramp, according to an alternative embodiment of the invention.
    FIG. 1 illustrates a part of a turbofan engine according to the invention, in particular the low pressure turbine 1. This comprises a rotor comprising wheels 2 assembled axially to each other by annular flanges 3 and each comprising a disc 4 carrying blades 5.
    Between the movable wheels 2 are annular rows of fixed blades 6 which are mounted by suitable means at their radially external ends on a casing 7 of the low pressure turbine. The fixed blades 6 of each row are joined together at their radially internal ends by annular sectors placed circumferentially end to end.
    As previously indicated, the flow of primary air F1 from the combustion chamber 5 and flowing in the primary stream 8 heats the casing 7 considerably.
    In order to ensure the cooling of the casing 7, the turbojet engine includes a cooling device 9, better visible in FIG. 2.
    This includes means for removing and supplying air comprising:
    a scoop 10 comprising an opening 10a opening for example into the secondary stream of the turbojet engine in order to take cold air there,
    a connecting member 11 having a general shape of Y comprising an upstream part 12 connected to the scoop 10, and a downstream part comprising a first branch 13 whose function will not be detailed here, and a second branch 14,
    a regulating valve 15 mounted downstream of the second branch 14 and capable of being controlled as a function of the engine speed and / or the flight conditions for example, so as to adjust the flow rate withdrawn,
    - A distribution member 16 formed of one or more parts and comprising an upstream part 17 connected at the outlet of the regulating valve 15, and two downstream branches 18 extending circumferentially around the axis of the turbojet engine, on both sides and d 'other of the downstream end of the upstream part 17. Each branch 18 extends for example over about 90 °.
    The device 9 further comprises collectors or connecting zones 19, here two in number, connected to the corresponding ends of the branches 18, each collector 19 forming a channel extending axially.
    The device 9 further comprises ramps 20a, 20b (or more generally denoted 20) formed by curved pipes of circular section, each ramp 20a, 20b extends at an angle of approximately 90 °, more precisely of the order 90 ° here.
    Each ramp 20 has a proximal end 21 opening into the channel of the corresponding collector 19 and a distal end 22 closed. Each ramp 20 further comprises orifices 23 (FIG. 3) facing the casing 7 so that the air taken through the scoop 10, the member 11, the valve 15 and the distribution member 16, enters the manifolds 19 and then into the ramps 20 before opening through the orifices 23 facing the casing 7, so as to cool it.
    The two manifolds 19 are diametrically opposite, each manifold 19 being associated with several pairs of ramps 20, namely ramps 20a extending circumferentially on one side and ramps 20b extending circumferentially on the opposite side. Thus, each manifold 19 and the associated opposite ramps 20a, 20b cover an angular range of approximately 180 °. In the embodiment shown in the figures, each manifold 19 is associated with several pairs of ramps, for example 9 pairs of ramps 20a, 20b. The ramps 20a, 20bd of the same pair are located on the same radial plane, the ramps 20a, 20b of different pairs being offset from one another along the axis X of the turbomachine, as can be seen in FIG. 2.
    The two collectors 19 and the pairs of ramps 20 associated have substantially identical structures and are arranged in diametrically opposite manner.
    In this way, the ramps 20 are located on several radial planes offset axially from one another, the ramps 20 of the same radial plane forming a cooling ring surrounding the casing 7 substantially the entire periphery, that is to say that is, substantially 360 °.
    The orifices 23 of each ramp are distributed in such a way that the density of the orifices 23 is greater in an area Z2 of the ramp 20 remote from the connection area 19 than in an area of the ramp Z1 close to the connection area 19 .
    In particular, each ramp 20 comprises a row of orifices 23 spaced apart from each other, the pitch or spacing between the orifices 23 being smaller in the zone Z2 remote from the connection zone 19 than in the zone Z1 close to the zone of connection 19. The distance between the centers of two consecutive or adjacent orifices 23 is defined by step or center distance.
    The orifices 23 are cylindrical and have substantially the same diameter. The diameter of the orifices 23 is for example between 0.5 and 1.5 mm, for example of the order of 0.8 mm.
    Each ramp 20 thus comprises a first zone Z1 close to the connection zone and a second zone Z2 distant from the connection zone, the orifices 23 being separated by a first step P1 in the first zone Z1 and by a second step P2 in the second zone Z2, the second step P2 being less than the first step P1. In this way, each ramp 20 comprises two types of spacing P1, P2. The P1 / P2 ratio is for example between 1 and 3, for example of the order of 2.
    The first zone Z1 of the ramp 20 extends over a length of between 64 and 70% of the length of the ramp 20, here 68% of the length of the ramp 20, the second zone Z2 of the ramp 20 extending so on the rest of the length of the ramp 20.
    As shown in Figure 4, we define by:
    - a1 the angle over which the whole of each ramp 20 extends,
    - a2 the angle over which the first zone Z1 extends,
    - a3 the angle over which the second zone Z2 extends.
    a1 is between 45 and 90 °, preferably around 90 °. a2 is between 0 and 90 °, preferably around 61 °. a3 is between 0 and 90 °, preferably around 29 °.
    In this way, in operation, the cooling air flow in the second zone Z2 is greater than in the first zone Z1 of the ramp 20, so as to compensate for the increase in the air temperature as and as the air progresses along the ramp 20. The orifices 23 are distributed in such a way that an almost constant convective air exchange is observed over the entire length of the ramp 20, so as to ensure cooling homogeneous housing 7.
    According to a variant not shown, the pitch between the orifices 23 can vary continuously along the ramp 20, so that said pitch or spacing is gradually reduced as one moves away from the zone of link 19. In such a case, the pitch can be constant over an area of the ramp 20 close to the link area 19, then be gradually reduced as one moves away from the link area 19 .
    Such an alternative embodiment, if it is more complex to produce, makes it possible to more finely refine the distribution of the air along the ramp 20, as required.
    FIG. 5 is a diagram illustrating the evolution of the air temperature along a ramp 20, as a function of the angular position a with respect to the corresponding connection zone 19, in the case of the prior art having orifices 23 uniformly distributed (curve C1) and in the case of the embodiment shown in FIGS. 1 to 4 having a non-uniform distribution of orifices 23 (curve C2).
    It can be seen that, in the case of the prior art (curve C1), the temperature of the air increases exponentially as it travels along the ramp 20, that is to say as and as the angle a increases, this temperature being very important at the end of the ramp 20, that is to say for a large angle a. Consequently, the casing 7 is poorly cooled in the zones situated opposite the zones Z2 of the ramps 20 which are distant from the collectors 19, in the case of the prior art.
    On the contrary, in the case of the invention (curve C2), it can be seen that the temperature at the level of zone Z2 which is far from the corresponding collector 19 (that is to say for a large angle a) is lower than in the case of the prior art, which allows better cooling of the casing 7 in this zone Z2.
    FIG. 6 illustrates another embodiment, which differs from that previously explained in that each ramp 20 has orifices 23 distributed on two radial planes R1, R2 spaced apart axially from one another, the orifices 23 in the two planes radial R1, R2 being staggered.
    In this case, the orifices 23 are arranged in two circumferential lines along the ramp 20.
    The orifices 23 of the same line or of the same radial plane R1, R2 are thus spaced apart by a step denoted y, the two radial planes R1, R2 being spaced apart by an axial distance denoted by x. The orifices 23 arranged in staggered rows are thus spaced two by two by a distance denoted d.
    In this embodiment, it is possible to vary the distance y so as to adjust the pitch between the orifices 23, as a function of the zones Z1, Z2 of the ramp 20
    The first zone Z1 can thus comprise a first step y1 and the second zone Z2 can comprise a second step y2, y2 being less than y1.
    As a variant, each ramp 20 may comprise a first zone Z1, close to the connection zone or to the manifold 19, comprising orifices 23 which are all arranged on the same radial plane, and a second zone Z2, distant from the connection zone or of the manifold 19, comprising orifices 23 which are arranged in staggered rows.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Device (9) for cooling a casing (7) of a turbine (1) for a turbomachine, such as for example an airplane turbojet engine, comprising means for taking off and supplying air (10, 11, 15, 16), means for distributing the withdrawn air comprising at least one ramp (20) extending circumferentially around the axis (X) of the turbomachine, said ramp (20) being connected to the means of sampling and supplying air (10, 11, 15, 16) via a connection zone (19), said ramp (20) comprising orifices (23) distributed along the ramp (20), the air sampled being intended to escape from said orifices (23) to cool the casing (7), characterized in that the distribution of the orifices (23) along the ramp (20) is such that the density of the orifices (23) is more important in a second zone (Z2) of the ramp (20) distant from the connection zone (19) than in a first zone (Z1) of the ramp (20) close to the zo link (19).
    [2" id="c-fr-0002]
    2. Device (9) according to claim 1, characterized in that the ramp (20) comprises at least one row of orifices (23) spaced from each other, the pitch or center distance (P1, P2) between the orifices ( 23) being weaker in the second zone (Z2) remote from the connection zone (19) than in the first zone (Z1) close to the connection zone (19).
    [3" id="c-fr-0003]
    3. Device (9) according to claim 1 or 2, characterized in that the first zone (Z1) of the ramp (20) extends over a length between 50 and 80% of the length of the ramp (20) , preferably between 60 and 75% of the length of the ramp (20).
    [4" id="c-fr-0004]
    4. Device (9) according to one of claims 1 to 3, characterized in that the orifices (23) of the ramp (20) are located on the same radial plane.
    [5" id="c-fr-0005]
    5. Device (9) according to one of claims 1 to 3, characterized in that the orifices (23) of the ramp (20) are distributed on at least two radial planes (R1, R2) axially spaced one of the other, the orifices (23) of the two radial planes (R1, R2) being arranged in staggered rows.
    [6" id="c-fr-0006]
    6. Device (9) according to one of claims 1 to 5, characterized in that the orifices (23) are cylindrical and have substantially the same diameter.
    [7" id="c-fr-0007]
    7. Device (9) according to one of claims 1 to 6, characterized in that it comprises at least two connecting zones (19), located for example diametrically opposite.
    [8" id="c-fr-0008]
    8. Device (9) according to one of claims 1 to 7, characterized in that it comprises at least two ramps (20) extending circumferentially in two radial planes offset axially from one another, both ramps (20) being connected to the same connection zone (19).
    [9" id="c-fr-0009]
    9. Double-flow turbojet engine, comprising a fan downstream of which extends:
    - a primary stream (8) in which a primary stream (F1) flows, said primary stream (8) passing in particular, in the direction of flow of the primary stream (F1), a compressor, a combustion chamber and a turbine (1) comprising a turbine casing (7),
    - a secondary stream in which flows a secondary flow distinct from the primary flow, characterized in that it comprises a cooling device (9) according to one of claims 1 to 8, the ramp (20) extending circumferentially around the axis (X) of the turbojet engine and being located radially outside the turbine casing (7), the orifices (20) being turned in the direction of said turbine casing (7), the means for taking off and air supply (10, 11, 15, 16) being able to take air from the secondary vein.
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    CIM
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    同族专利:
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5399066A|1993-09-30|1995-03-21|General Electric Company|Integral clearance control impingement manifold and environmental shield|
    EP2551467A1|2011-07-26|2013-01-30|United Technologies Corporation|Gas turbine engine active clearance control system and corresponding method|FR3079874A1|2018-04-09|2019-10-11|Safran Aircraft Engines|COOLING DEVICE FOR TURBINE OF A TURBOMACHINE|
    FR3081911A1|2018-06-04|2019-12-06|Safran Aircraft Engines|DEVICE FOR COOLING A TURBINE HOUSING FOR A TURBOMACHINE|
    FR3101105A1|2019-09-23|2021-03-26|Safran Aircraft Engines|Housing for turbomachine and turbomachine equipped with such a housing|
    法律状态:
    2017-04-27| PLFP| Fee payment|Year of fee payment: 2 |
    2018-01-19| PLSC| Search report ready|Effective date: 20180119 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 3 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 4 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 5 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1656807A|FR3054000B1|2016-07-15|2016-07-15|DEVICE FOR COOLING A TURBINE HOUSING FOR A TURBOMACHINE|
    FR1656807|2016-07-15|FR1656807A| FR3054000B1|2016-07-15|2016-07-15|DEVICE FOR COOLING A TURBINE HOUSING FOR A TURBOMACHINE|
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