• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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  • 优先权
    • 专利摘要:
    The main object of the invention is a system (1) for supplying pressurized air installed in an aircraft turbine engine, configured to supply pressurizing air with a portion of compressed air using air pressurizing device taken from a compressed air sampling portion (12), characterized in that it comprises a sampling member (32) connected to a sampling port (30) provided with a passage port (38) , a pressurized chamber (33) traversed by the sampling member (32), the system (1) further comprising sealing means (2) for forming a substantially sealed separation between the pressurized chamber (33) and a space free wheel (40) communicating with a turbomachine compartment (ZC) and arranged around the sampling member (32), in order to guard against the introduction of pressurized air from the pressurized chamber (33) inside. of the sampling member (32) in case of breakage of last r.
    公开号:FR3024179A1
    申请号:FR1457192
    申请日:2014-07-25
    公开日:2016-01-29
    发明作者:Francois Gallet
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to the field of aircraft turbomachines, and more particularly to the general field of fuel injection systems. BACKGROUND OF THE INVENTION The present invention relates to the field of aircraft turbomachines, and more particularly to the general field of fuel injection systems. pressurized air provided for such turbomachines, in particular systems for supplying the aircraft fuel tanks with pressurized air taken from a turbomachine compressor. The invention can be applied to all types of aircraft turbomachines, for example such as turbojets and turboprops. More preferentially, the invention can be applied to a double-body and dual-flow turbojet engine. It relates more specifically to a pressurized air supply system installed in an aircraft turbomachine and a method of assembling such a pressurized air supply system. STATE OF THE ART In the general field of aircraft turbomachines, it is known to take hot air under pressure, usually cooled before use, for various tasks, for example to carry out deicing operations of the wings, or for air conditioning requirements, for example of an aircraft cabin during an ascent phase, or even for the pressurizing air supply of the aircraft fuel tanks. In particular, the aircraft fuel tanks require to be supplied with pressurized air to reduce the partial fuel pressure. In practice, the fuel is usually kerosene. By reducing the presence of fuel vapor in and near the tank, it is possible to reduce the risk of fuel self-ignition.
    [0002] For this purpose, it is known to take hot air under pressure from an aircraft turbomachine compressor, for example a low or high pressure compressor. The high temperature of the air sampled is due to the high pressure of the air in the compressor stage where the sampling takes place.
    [0003] FIG. 1 diagrammatically illustrates, in axial semi-section, an example of a turbojet engine 10 with a double flow, of revolution about an axis of rotation T, on which a sample of hot air under pressure is provided for a period of time. compressor stage for supplying pressurized hot air from a fuel tank. The turbojet engine 10 comprises, from upstream to downstream in the direction of flow 10 F of the gases inside the turbojet engine 10, a fan 11, a compressor 12, a combustion chamber 13 and turbines 14, this turbojet engine 10 being intended to be fixed by suitable means under a wing of an airplane or on the rear part of the fuselage of an airplane. The fan 11 comprises a plurality of fan blades 11a which are fixed at their radially inner ends to the periphery of the fan disk 11b of the turbojet engine 10 which is itself attached to the upstream end of a shaft (not shown The fan blades 11a are surrounded externally by a fan casing mounted at the upstream end of the nacelle 15 which is substantially cylindrical and extends downstream around the compressor 12, the chamber combustion 13 and turbines 14 of the turbojet engine 10. This nacelle 15 can channel the air flow 16 entering the turbojet engine 10. A portion 16a of this air flow, forming the primary flow or hot flow, enters the compressor 12, is then mixed with fuel and burned in the combustion chamber 13, to be then injected into the turbines 14 in order to supply energy to the rotor blades of the turbines 14 and lead to rotation of the compressor shaft 12 and the fan 11. The other part 16b of the air stream 16 entering the turbojet engine 10, forming the secondary flow or cold flow, flows around the body of the turbojet engine 10 to the inside an intermediate casing 17 and an outer duct blower 18 (also called OFD for "Outlet Fan Duct" in English) surrounded by hoods of the nacelle 3024179 3 15, to provide an additional boost in addition to that provided by the combustion gases ejected from the turbines 14. The cold air of the secondary flow can be used to cool for example oil or hot air circuits, usually using heat exchangers.
    [0004] The intermediate casing 17 comprises two cylindrical shells 18 and 19 coaxial, respectively internal and external, which are interconnected by radial arms or vanes 20. In addition, the outer blower duct 18 has a substantially cylindrical inner wall 22 which is connected to a coaxial internal casing 21 by at least one tubular radial arm 23, also called "service arm", inside which pass servitudes such as fluid flow conduits and electrical cables. The outer fan duct 18 is fixed at its upstream end to the downstream end of the outer shell 19 of the intermediate casing 17, and at its downstream end to the upstream end of a nozzle (not shown) of the nacelle.
    [0005] In addition, there is also shown in FIG. 1 the compartment or fan zone ZF (also referred to as "Fan Zone" in English) between the hoods of the nacelle 15 and the elements 17 and 18 which delimit externally the vein of the secondary stream. The compartment formed by the inner casing 21 is called the core zone ZC (also called "Core Zone" in English), and is connected to the fan zone ZF by the service arm 23. In an embodiment developed by the applicant , in order to ensure the pressurization of a fuel tank of the aircraft equipped with the turbojet engine 10, there is provided a circuit for drawing hot air under pressure, shown schematically by the arrow path P in FIG. 1, from a stage 12a of the compressor 12. In particular, to ensure the necessary pressure in the fuel tank, there is provided a hot air sample under pressure at a stage 12a of the compressor 12, the access of which requires making a tube sampling device 32 (shown in FIGS. 2A and 2B) which passes through a chamber 33 that can be used for other purposes for extracting air from the turbojet engine 10. The pressure in the chamber 33 is that of a stage 12b of the 3024 4 compressor 12, located downstream of the stage 12a at which is taken the hot air sampling. The sampling tube 32 is intended to be connected to a pipe of the pressurized hot air sampling circuit which circulates inside the service arm 23, as represented by the arrow path P in FIG. 1, so as to connect the ZC core compartment to the ZF fan compartment. Then, once within the blower compartment ZF, the hot air sampling circuit under pressure provides an over-length of pipe, as schematized by the loop of the arrow path P in FIG. 1, which makes it possible to increase the heat exchange surface between the hot air sampling circuit and the ambient air of the fan compartment ZF for cooling the pressurized air before connecting the pressurized hot air sampling circuit to a pylon which connects the turbojet engine 10 to the structure of the plane. For purposes of illustration, the arrow path loop P is shown over the secondary vein, but it should be understood that this loop remains confined within the fan compartment ZF. In addition, the loop is not represented in full; the dotted lines that terminate the arrow path P mean that the loop continues on a path that is not shown and that leads to an exit point where the cooling circuit leaves the fan compartment ZF to supply the aircraft with pressurized air .
    [0006] FIGS. 2A and 2B show enlarged and partial views of FIG. 1 at the level of the compressor 12, and in particular at a pair of successive stages 12a and 12b of the compressor 12 surrounded by a chamber 33 which communicates with the downstream stage 12b by a downstream sampling port 31. For example, the pair of successive stages corresponds to the third and fourth stages of the compressor. FIGS. 2A and 2B correspond respectively to a situation where the hot air sampling circuit under pressure is in nominal operation and to a situation where this circuit is accidentally in communication with the chamber 33 because of a rupture of the tube The compressor 12, which supplies pressurized hot air to the fuel tank, has an upstream intake port 30 for hot pressurized air associated with the upstream stage 12a of the pair of stages. compressor 12, and the above-mentioned downstream sampling port 31 of pressurized hot air, associated with the downstream stage 12b of the compressor 12 and located downstream of the upstream sampling port 30. The temperature of the hot air taken from the the upstream sampling port 30 is, for example, less than 300 ° C., that of the hot air taken at the downstream sampling port 31 being, for example, less than 400 ° C. In addition, the upstream sampling port 30 is for example located at the second stage 12a of the compressor 12, and the downstream sampling port 31 is for example located at the fourth stage 12b of the compressor 12. The hot air under pressure, taken from the compressor 12 can be used for at least two types of pressurizing air supply, and in particular for supplying the fuel tank via the upstream sampling port 30 of the stage 12a of the compressor 12, and for another supply of hot air such as a defrost air supply and / or cabin pressurization air through the downstream sampling port 31 of the stage 12b of the compressor 12.
    [0007] To do this, a pressurized hot air sampling tube 32, connected to the upstream sampling port 30, and a pressurized chamber 33 connected to the downstream sampling port 31 are provided, the sampling tube 32 passing through the chamber 33. along a portion of tube 32a. The sampling tube 32 conveys pressurizing air for the tank according to the arrow 34. Similarly, the chamber 33 20 conveys pressurizing air for another type of supply (defrosting or cabin pressurization, for example ) according to the arrow 35, via a fluid conduit 36. Nevertheless, a major case of degradation identified with respect to this pressurized hot air sampling circuit of the compressor 12 is related to the rupture of the sampling tube 32, having as a consequence of pressurizing the fuel tank with too hot air from the downstream stage 12b of the compressor 12, which can thus generate risks of self-ignition of the fuel. Indeed, with reference to FIG. 2A showing a nominal operating speed configuration of the hot air sampling circuit of the compressor 12, the air in the chamber 33 does not mix with that coming from the port 30 and that is contained in the sampling tube 32. The hot pressurized air that passes through the sampling tube 32 is therefore almost not heated by the warmer air of the chamber 33. In contrast, Referring to Figure 2B, which shows a degrading configuration of the hot air sampling circuit of the compressor 12, the sampling tube 12 is damaged by rupture at the portion 32a near the chamber 33. In this case, a mixing occurs between the air contained in the chamber 33 and the less hot air that passes through the sampling tube 32 from the upstream sampling port 30 of the upstream stage 12a of the compressor 12. In this way excess hot air exiting the downstream stage 12b of the compressor 12 along the arrow 37 is fed to the fuel tanks by the pressurized hot air sampling circuit represented by the arrow path P in FIG. This too hot air creates the risk of self-ignition of the fuel in the tanks. By way of example, it may be imposed a temperature of 232 ° C not to be exceeded for the hot air sent by the sampling circuit at the entrance of the pylon which connects the turbojet to the structure of the aircraft. There is therefore a need to provide a protection system in the compressed air hot air sampling circuit of the compressor 12, to prevent too hot air being injected into the fuel tanks for their pressurization.
    [0008] Solutions have been devised by the Applicant based in particular on the use of sensors or control valves, but they are not entirely satisfactory and have several disadvantages. In particular, such solutions may present difficulties in terms of technical feasibility, high cost or complications for their implementation.
    [0009] SUMMARY OF THE INVENTION Accordingly, there is a need to provide an alternative solution for preventing, or at least limiting, the penetration of pressurized air that is too hot, for example contained in a pressurized chamber, within a pressure chamber. a pressurizing air sampling tube of a part of an aircraft turbomachine, for example a turbomachine compressor stage, this pressurizing air being intended for example to supply a fuel tank. Such a need exists especially in the case where the sampling tube is damaged, and in particular a rupture. In other words, there is a need to prevent, or at least limit, the increase in temperature in a fuel tank supplied with hot air under pressure through such a sampling tube, damage to the sampling tube, especially in case of breakage. There is also a need to provide such a solution which is simple to implement, and for which the increase in weight and bulk is minimized. The invention aims to at least partially address the needs mentioned above and the disadvantages relating to the previous designs of the applicant. The invention thus has, according to one of its aspects, a system 15 for supplying pressurized air for an aircraft turbomachine, configured to supply pressurizing air with a portion of compressed air use. the aircraft from pressurizing air taken from a compressed air sampling portion of the aircraft turbomachine, characterized in that it comprises: a pressurization air sampling port formed on a crankcase; the compressed air sampling portion of the aircraft turbomachine, - a sampling member connected to the sampling port to allow the removal and the conveyance of the pressurizing air taken to the air utilization part. compressed, - a port for passage of the sampling member formed on a casing of a compartment of the turbomachine, said casing being subject to slight movements relative to the casing of the compressed air sampling portion, sampling member passing through the port of passage with a freedom of movement relative to the latter during said slight displacements, a pressurized chamber through which the sampling member is located between the casing of the compressed air sampling part and the housing of the compartment 3024179 8 of the turbomachine, and comprising air under a pressure greater than that of the pressurization air taken, the pressurized air supply system further comprising sealing means located substantially between the casing of the compressed air sampling portion 5 and the compartment casing to form a substantially sealed separation between the pressurized chamber and a free space communicating with the compartment and arranged around the sampling member, in order to guard against the introduction of pressurized air from the pressurized chamber inside the sampling member in the event of failure of this ernier.
    [0010] Thanks to the invention, it is possible to allow the supply of pressurizing air to a part of an aircraft, for example an aircraft fuel tank, via a sampling member. pressurized air, for example a turbomachine compressor stage, without the risk of introduction of pressurizing air at too high a temperature, which can in particular cause risks of self-ignition of the fuel, even in case of rupture of the sampling organ. In addition, the invention can provide a simple and compact solution for the protection of the hot air intake member under pressure, compatible with the environments in which it can be implemented. The pressurized air supply system according to the invention may further comprise one or more of the following features taken singly or in any possible technical combinations. The sampling member is advantageously constituted by a sampling tube. Similarly, the protection member, described below, is advantageously constituted by a protective tube. Thus, the sampling member may constitute an inner tube, located inside the protective tube which may constitute an outer tube. In particular, the protection tube may constitute a locknut for fixing the sampling tube on the pressurizing air sampling port. The supply system may include a device for supplying pressurized air to at least one fuel tank of the aircraft to which the sampling member is connected.
    [0011] The compressed air sampling part of the aircraft turbomachine may consist of a compressor stage of the turbomachine, in particular a high pressure compressor. In particular, the sampling member can be connected to a sampling port of an upstream stage of the compressor of the turbomachine, and the pressurized chamber can have the pressure of a downstream stage of the compressor, which is higher than that of the compressor. upstream stage of the compressor. The sampling member may be connected to a pressurized hot air pipe located inside a service arm of the turbomachine, connecting the core compartment to the fan chamber of the turbomachine.
    [0012] The sealing means may comprise a first sealing part arranged around the sampling member and in the passage port with a freedom of movement relative to the latter, this first sealing part being connected to the housing of the compressed air sampling portion by a sealed connection so as to prevent significant air leakage from the pressurized chamber at said connection. Furthermore, the leaktight connection may be formed by a second sealing piece comprising an annular outer surface forming a spherical surface portion, and the first sealing piece may have a free end comprising a cylindrical inner surface which forms a line of circular contact 20 with said spherical surface portion, so that the first sealing member is hinged sealingly to the second sealing member. As a variant, it may be possible to dispense with such a second sealing piece comprising an annular outer surface forming a spherical surface portion. In particular, it may be possible to form a spherical surface portion on the peripheral surface of the boss, described later, forming the sampling port. The system may further comprise a holding cap fixed on the casing of the turbomachine compartment and traversed by the sampling member, this holding cap being arranged to seal the casing and the sealing means 3024179 10 allowing a freedom of movement of the sealing means relative to the housing. The first sealing piece may comprise a sliding traversing soleplate having a flat portion adapted to bear against a corresponding flat portion of the holding cap with the possibility of sliding on it, the freedom of movement of the first piece of sealing effected in a plane parallel to the flat portion with prevention of displacement perpendicular to this plane. The sampling port may be formed by a boss on the housing of the compressed air sampling portion, an inner surface of which is formed by a threaded bore configured to cooperate with a thread of the outer surface of a first end of the the sampling member to allow the attachment of the sampling member on the boss of the sampling port. The second sealing member may moreover be a substantially annular sealing washer. It may be mounted on the housing boss of the compressed air bleeding portion, and may include a passage opening for insertion of the sampling member. The supply system may further comprise a clamping gasket placed between the sampling member, in particular a first external boss of the sampling member, and the second sealing piece.
    [0013] Such a clamping joint may in particular be constituted by a substantially annular spring washer, with or without a brake. For example, it can be selected from the washers of the "Belleville" type or the "Grower" type with teeth. The sampling member may also comprise a second external boss, situated at a distance from the first external boss, so that the portion of the sampling member situated between the first and second external bosses constitutes a weak zone mechanically, it is that is to say an area of mechanical weakness, preferred in case of rupture (ie breakage) of the sampling member. The second external boss of the sampling member may also make it possible to limit (or calibrate) a pressurization air flow rate in the event of leakage, for example in the event of rupture of the sampling member and / or first piece 3024179 11 sealing. In this case, the second outer boss may be formed on the sampling member substantially facing an outer boss of the end of the first sealing piece from which extends the sliding bushing. The second external boss of the sampling member and the external boss of the first sealing member can thus define between them a restricted channel for the flow of pressurizing air flow in the event of leakage. A protective member forming at least a partial envelope around the sampling member may be located between the sampling member and the first sealing piece, and may comprise an insertion cavity for the introduction at least partially. the sampling member inside the protection member, said protective member being arranged to bear against the second sealing member once the sampling member fixed on the boss of the sampling port. The protective member may comprise a first end mounted on the first end of the sampling member, the first end of the protection member comprising in particular a threaded portion intended to cooperate with a thread of the outer surface of the first part. end of the sampling organ. The protective member may further comprise a second free end located at a distance from the sampling member and the first sealing piece. The integrity of the protective member can be guaranteed by the fact that the protective member 20 comprises a second free end, without contact with the elements of its environment, the first sealing piece being in abutment against the second piece seal and not against the protection element. As a result, the protection member does not undergo any stress and therefore can never break. In particular, the protection member may be arranged in the supply system so as to provide a clearance between the second end of the protection member and the sampling member, this second end being thus free of any solicitation mechanical. Advantageously, the threading of the outer surface of the first end of the sampling member, the threaded bore of the inner surface of the boss of the housing of the compressed air withdrawal part, and the threaded portion of the first end of the protective member, do not mechanically weaken the feed system so that they can not break because they stand to each other. Also, even in case of rupture of the sampling member and / or the protective member, the assembly between the thread, the threaded bore and the tapped portion will be maintained.
    [0014] Furthermore, the first end of the protective member may bear against the second sealing member and screwed onto the first end of the sampling member so as to constitute a lock nut for fixing the sampling member on the boss of the sampling port. Finally, the invention also relates, in another of its aspects, to a method 10 of assembling a pressurized air supply system as defined above, comprising the successive steps of: a) positioning the second sealing piece resting on the boss of the housing of the compressed air sampling portion, b) placing the first sealing part in sealed engagement with the second sealing member, c) securing the protection on the sampling member, in particular by screwing the threaded portion of the protective member on the thread of the outer surface of the first end of the sampling member, d) fixing the assembly formed by the member protection and the sampling member on the sampling port, in particular by screwing the thread of the outer surface of the first end of the sampling member into the threaded bore of the inner surface of the boss, up to that the protection member comes into contact with the second sealing member, e) optionally, re-tighten the protective member on the sampling member in order to secure the assembly. Thus, advantageously, the fixing of the protective member on the turbomachine is carried out by means of the sampling member, on which the protective member has been previously fixed. It could be envisaged to have specific tools allowing the simultaneous fixing of the protection and sampling organs.
    [0015] The pressurized air supply system and the assembly method according to the invention may comprise any of the features set forth in the description, taken alone or in any technically possible combination with other features.
    [0016] BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood on reading the following detailed description, non-limiting examples of implementation thereof, as well as on the examination of the figures, diagrammatic and partial. of the accompanying drawings, in which: FIG. 1 illustrates, in axial semi-section, an example of an aircraft turbojet engine on which a hot air sample is taken under pressure from a compressor stage, FIGS. 2A. and 2B are enlarged and partial views of the turbojet engine of FIG. 1 at the compressor, respectively when the hot air sampling circuit under pressure is in nominal operation and in the event of degradation of this circuit, FIG. , in axial and partial section, a first exemplary embodiment of a pressurized air supply system according to the invention, - Figures 4A, 4B, 4C and 4D illustrate, in partial views in axial section, four e steps of the method of assembly of the pressurized air supply system of FIG. 3; FIG. 5 represents, in axial and partial section, a second exemplary embodiment of a pressurized air supply system; according to the invention, and - Figure 6 shows, in axial and partial section, an alternative embodiment of the example of Figure 5.
    [0017] In all of these figures, identical references may designate identical or similar elements. In addition, the different parts shown in the figures are not necessarily in a uniform scale, to make the figures more readable.
    [0018] DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS Throughout the description, it is noted that the terms upstream and downstream are to be considered with respect to a main direction F of normal gas flow (from upstream to downstream) for a turbomachine 10. Furthermore, the T-axis of the turbomachine 10 is called the radial axis of symmetry of the turbomachine 10. The axial direction of the turbomachine 10 corresponds to the axis of rotation of the turbines, which is also the direction of the T-axis of the turbomachine 10. A radial direction of the turbomachine 10 is a direction perpendicular to the axis T of the turbomachine 10. In addition, unless otherwise stated, the adjectives and adverbs axial, radial, axially and radially are used with reference to the aforementioned axial and radial directions. In addition, unless otherwise stated, the terms inner and outer are used with reference to a radial direction so that the inner portion of an element is closer to the T-axis of the turbomachine 10 than the outer portion of the same element. FIGS. 1, 2A and 2B have already been described previously in part 15 relating to the technical context of the invention. With reference to FIGS. 3 and 5, there is shown respectively, in axial and partial section, first and second exemplary embodiments of pressurized air supply systems 1 according to the invention. FIGS. 4A, 4B, 4C and 4D, for their part, show, in partial axial section views, four steps in the assembly process of the pressurized air supply system of FIG. 3. In all these examples, considers that the aircraft turbine engine 10 may be such as that described above with reference to Figure 1, so that the elements described with reference to Figure 1 are not repeated in this detailed description. However, the turbomachine 10 could be of any type, and in particular 25 correspond to a turbojet engine double body and dual flow. Moreover, for each of the embodiments described below, it is considered that the pressurized hot air circulating in the feed system 1 according to the invention is intended to feed at least one fuel tank of the aircraft. , in order to pressurize it and thus avoid the risk of auto-ignition of the fuel.
    [0019] In addition, it is considered that the supply system 1 comprises a tube 32 for drawing hot air under pressure from an upstream stage 12a of a compressor 12, in particular a high-pressure compressor, of the turbine engine 10, as shown in FIG. has previously been described with reference to FIG. 1. The sampling tube 32 passes through a pressurized chamber 33 whose pressure is that of a downstream stage 12b of the compressor 12 of higher pressure than the upstream stage 12a of the compressor 12. Also, the sealing means of the feed system 1 described hereinafter are intended to overcome a case of failure resulting from a rupture of the sampling tube 32.
    [0020] Of course, these choices are in no way limiting. In particular, the supply system 1 could be provided to allow the drawing of air under pressure on another part of the turbine engine 10, and could also allow to feed another part of the aircraft a fuel tank and, for example, be used for wing de-icing operations, or for air-conditioning purposes, for example the cabin of the aircraft during an ascent phase. In Figure 3, there is shown partially a first embodiment of a system 1 for supplying air under pressure according to the invention. The system 1 thus comprises first a pressurization air sampling port 30 formed on the casing 12c of the compressor 12.
    [0021] A sampling tube 32 (inner tube) is also connected to the sampling port 30 to allow the collection and delivery of the pressurizing air from the upstream stage 12a of the compressor 12 to the fuel tank of the compressor. aircraft. In addition, the pressurized air supply system 1 comprises a passage port 38 of the sampling tube 32. The passage port 38 is formed on the casing 39 of the core compartment ZC of the turbomachine 10, this casing 39 being subject to slight displacements relative to the housing 12c of the compressor 12. By the expression "weak displacements" is meant in particular a relative displacement of the housing 39 of the core compartment ZC with respect to the compressor housing 12c 12, caused by the 30 dilations and the mechanical stresses to which the housings are subjected. For example, the housing 12c of the compressor 12 may be subjected to higher temperatures than the housing 39 of the core compartment ZC. In addition, during the operation of the turbomachine 10, the thrust and torque forces generated by the turbine cause temporary deformations of each casing which imply small relative displacements between the casings. Due to these relative displacements, the sampling port 30 and the passage port 38, which extend substantially along the same axis corresponding to the axis of the sampling tube 32, may be slightly misaligned in operation. The distance between the two ports 30 and 38, as well as the angle between the two casings 12c and 39, may also vary slightly. For these reasons, it is desired that the sampling tube 32, which is attached to the sampling port 30 of the housing 12c and thus follows the movement of this port 30, passes through the passage port 38 with a freedom of movement relative to that port. last so as not to come into contact with the housing 39 during said low displacements. A bearing of the sampling tube 32 on the housing 39 would indeed cause stress on the tube which could cause its rupture. In addition, the sampling tube 32 passes through a pressurized chamber 33 along a portion 32a of sampling tube, the pressurized chamber 33 being located between the housing 12c of the compressor 12 and the housing 39 of the core compartment ZC. The pressurized chamber 33 comprises air at a pressure greater than that of the pressurizing air taken from the upstream stage 12a of the compressor 12. According to the invention, the system 1 for supplying pressurized air comprises advantageously sealing means 2 located substantially between the housing 12c of the compressor 12 and the housing 39 of the core compartment ZC to form a substantially sealed separation between the pressurized chamber 33 and a free space 40 communicating with the core compartment ZC and arranged around the sampling tube 32, this free space 40 along a mechanically weak zone Zf of the sampling tube 32, so as to guard against the introduction of pressurized air from the pressurized chamber 33 inside the tube sampling 32 in case of breakage thereof.
    [0022] In addition, a first sealing piece in the form of a sliding bushing 2 (also sometimes called "yoyo") is arranged around the sampling tube 32 and in the passage port 38 while having a relative freedom of movement to the latter. This sliding bushing 2 is connected to the compressor housing 12c 12c by a sealed connection so as to prevent significant air leakage from the pressurized chamber 33 at the connection. This sealed connection is formed by a second sealing member 5, which has a passage opening 5a for the passage of the sampling tube 32. This second sealing member 5 is in the form of a sealing washer 10 , comprising an annular outer surface forming a spherical surface portion. The sliding bushing 2 has a free end 2c comprising a cylindrical inner surface which forms a circular line of contact with this spherical surface portion, so that the sliding bushing 2 is articulated with sealing on the sealing washer 5. L articulation of the sliding bushing 2 on the second sealing member 5 makes it possible not to generate stresses on these parts during the relative displacements of the housing 39 of the core compartment ZC with respect to the housing 12c of the compressor 12, in particular when the angle and / or the distance between the two housings are varied. Indeed, the sliding bushing 2 is designed to slide, that is to say slide locally, on an integral surface of the housing 39 while remaining perpendicular to this surface. Furthermore, the system 1 further comprises a holding cap 3 fixed on the casing 39 of the core compartment ZC of the turbomachine 10 and traversed by the sampling tube 32, this holding cap 3 being arranged to sealingly connect the casing 39 and the sliding bushing 2 while allowing freedom of movement of the sliding bushing 2 relative to the casing 39. The holding cap 3 comprises a second passage opening 3a for the insertion of the sampling tube 32. The sliding bushing 2 further comprises a sliding traversing sole 2a which has a flat portion adapted to abut against a corresponding flat portion of the holding cap 3 with the possibility of sliding thereon. The freedom of movement of the sliding bushing 2 takes place in a plane parallel to the plane portion with movement prevention perpendicular to this plane. Thus, the sliding bushing 2a is disposed against the housing 39 of the core compartment ZC and a first passage opening 2b for the insertion of the sampling tube 32.
    [0023] The sliding bushing 2 is mounted relatively movably between the sampling tube 32 and the casing 39 of the core compartment ZC of the turbomachine 10. In particular, it is mounted so as to bear against the holding cap 3 with possibility to slide on the latter. In addition, a clearance J is formed between the sliding traversing sole 2a and an annular shoulder inside the holding cap 3 10 resting on the casing 39. The holding cap 3 thus allows axial retention of the sliding bushing 2 relative to to the casing 39. Nevertheless, a small game not shown in FIG. 3 is provided between the outer surface of the casing 39 and the sliding traversing sole 2a, so as to avoid clamping of this sole 2a between the holding cap 3 and the As a matter of fact, the pressure in the pressurized chamber 33 is greater than that in the core compartment ZC and thus pushes the sliding bushing 2 outwards, which has the effect of pressing the soleplate 2a against the bonnet. 3. There is then no contact between the sole 2a and the housing 39. The sampling port 30 is formed by a boss 30a of the housing 12c, this boss having an opening through the housing 12c and extends. nt along a port axis which corresponds to the axis of the sampling tube 32. The inner surface Si which defines the opening of the boss is formed by a threaded bore 30b cooperating with a screw thread 32c of the external surface Se of the first end 32b of the sampling tube 32. In this way, the attachment of the sampling tube 32 on the boss 30a is made possible by screwing the thread 32c in the threaded bore 30b.
    [0024] The sealing washer 5 is mounted on the boss 30a of the housing 12c of the compressor 12. In addition, in this first example of FIG. 3, the sealing means also comprise a protective tube 4 (outer tube) forming a partial envelope around the sampling tube 32.
    [0025] The protective tube 4 is located between the sampling tube 32 and the sliding bushing 2. It has an insertion cavity 4a for the partial introduction of the sampling tube 32 inside thereof. Moreover, as can be seen in this FIG. 3 and in FIGS. 4B to 4D, the protective tube 4 has a first end 4b fixed to the first end 32b of the sampling tube 32. This first end 4b of the tube protection 4 comprises a threaded portion 4d (against-nut) cooperating with the thread 32c of the outer surface Se of the first end 32b of the sampling tube 32.
    [0026] In addition, the protective tube 4 is located radially away from the sliding bushing 2, and has a second free end 4c located radially away from the sampling tube 32. Thus, during relative movements of the housing 39 of the core compartment ZC with respect to the housing 12c of the compressor 12, the protective tube 4 is no longer in axial alignment with the sliding bushing 2, 15 but does not normally come into contact with the sliding bushing 2. Moreover, even if the sampling tube 32 undergoes constraints imposing a slight bending, it does not normally come into contact with the second end 4c. The integrity of the protection tube 4 is thus guaranteed in particular by this second end 4c free. The protection tube 4 is not stressed and therefore can never break.
    [0027] Furthermore, as can be seen in FIG. 3, the first end 4b of the protection tube 4 is in contact with the sealing washer 5 so as to ensure a certain degree of tightness at the level of the contact surface. Advantageously, if the inner sampling tube 32 were to break, the leak pressurizing air materialized by the arrow R1 would thus escape to the core compartment ZC. Similarly, if the sliding bushing 2 were to break, leakage pressurizing air materialized by the arrow R2 would thus escape to the core compartment ZC, but in no case to the fuel tank pressurization circuit, c that is to say inside the sampling tube 32.
    [0028] With reference to FIGS. 4A to 4D, steps will now be described of a method for assembling the pressurized air supply system 1 of the first example of FIG. 3. In first a) and second b 4A, the sealing washer 5 and the sliding bushing 2 are respectively introduced into the turbomachine 10, by positioning the sealing washer 5 on the boss 30a of the compressor housing 12c 12, and then by placing the sliding bushing 2 in sealing engagement with the sealing washer 5. Furthermore, as illustrated in FIG. 4B, the protection tube 4 forming a counter-nut is screwed onto the sampling tube in a step c), in progressing along the arrows F1 shown in FIG. 4B, by cooperation between the threaded portion 4d of the protection tube 4 on the thread 32c of the outer surface Se of the first end 32b of the sampling tube 32. illustrated in FIG. 4C, an assembly formed by the protection tube 4 and the sampling tube 32, screwed on one another, is then obtained. Then, as illustrated in FIG. 4D, is introduced according to a step d) this assembly in the turbomachine 10, by screwing the thread 32c of the sampling tube 32 in the threaded bore 30b of the inner surface Si of the boss 30a of the port of sampling 30, progressing according to the arrow F3 with rotation according to the arrow F2. This is done until the protective tube 4 comes into contact with the sealing washer 5. Finally, in a step e), the protective tube (4) forming a counter-nut is tightened again. the sampling tube 32 to secure the assembly. FIG. 5 partially shows a second exemplary embodiment of a system 1 for supplying pressurized air according to the invention. In this second example, the elements common with those described with reference to FIG. 3 will not be repeated. This second embodiment differs essentially from the first embodiment described with reference to FIG. 3 in that the means for fixing the sampling tube 32 to the pressurization air sampling port 30 do not here comprise counter-pressure. nut, which makes it possible to dispense with the protection tube 4. In particular, the sealing means are formed by the sealing washer 5 and the sliding bushing 2.
    [0029] However, in this example, the supply system 1 also comprises a substantially annular clamping gasket 6 placed between a first external boss 32d of the sampling tube 32 and the sealing washer 5. This clamping joint 6 can for example be chosen from the washers of the type "Belleville" or type "Grower" teeth.
    [0030] Furthermore, the sampling tube 32 also comprises a second external boss 32e, in the vicinity of the end of the tube 32 at which the tube is connected in the core compartment ZC to a duct (not shown) of the control circuit. extraction of pressurized hot air, represented by the arrow path P in FIG. 1. The connection of the tube 32 to the pipe in the core compartment ZC 15 generates stresses on the tube. As a result, the risk of rupture (ie of breaking) of the tube 32 can not be ruled out completely in operation. The external boss 32e is situated at a distance from the first external boss 32d, so that the portion of the sampling tube 32 located between the first 32d and second 32nd external bosses constitutes a mechanically weak zone Zf, that is to say a zone of mechanical weakness, preferred in case of rupture of the sampling tube 32. These first 32d and second 32nd bosses are also present on the sampling tube 32 of the embodiment of Figure 3. They define the mechanically weak zone Zf at which it could occur a break of the sampling tube 32 in case of abnormally intense mechanical stress . Moreover, the second external boss 32e also makes it possible to calibrate the pressurization air flow in the event of leakage, for example in the event of breakage of the sampling tube 32 and / or of the sliding bushing 2. To do this, as illustrated on FIG. 5, this second external boss 32e is formed on the sampling tube 32 substantially facing an external boss 2d of the end of the sliding bushing 2 from which extends the sliding bushing sole 2a. These two bosses 32e and 2d then define between them a restricted channel of pressurizing air flow in case of leakage. In the embodiment of FIG. 3, a similar restricted channel is formed between the second boss 32e and the free end 4c of the protection tube 4. The air passage section of this restricted channel can be adjusted to mounting by adjusting the position of the protective tube 4 on the sampling tube 32, as shown in Figure 4C. Advantageously, the space surrounding the mechanically weak zone Zf of the sampling tube 32 is no longer at the pressure of the pressurized chamber 33, but at a pressure lower than that present inside the sampling tube 32. namely the pressure of the heart compartment ZC. If the sampling tube 32 or the sliding bushing 2 were to break, in other words to break, the pressurized air leak would then escape to the core compartment ZC, but never in the pressurizing circuit of the tube 15 sampling 32 to the fuel tank. Thus, advantageously in each of the embodiments described in the foregoing, the sealing means of the pressurized air supply system 1 according to the invention make it possible to ensure that the pressurizing air contained in the pressurized chamber 33 will not circulate inside the sampling tube 32 20 towards the fuel tank in case of leakage. As a result, any leak will flow into the core compartment ZC, and not into the fuel tank pressurization circuit. In addition, the presence of the protective tube 4, as in the example of FIG. 3, or the particular arrangement of the sliding bushing 2 and of the sealing member 5, as in the example of FIG. 5, can make it possible to calibrate the pressurization air flow rate in the event of a leak, and therefore to limit the efficiency losses of the compressor 12, and thus the specific fuel consumption penalties (or SFC for "Specific Fuel Consumption") in case of failure of the sampling tube.
    [0031] Naturally, the invention is not limited to the embodiments which have just been described. Various modifications may be made by the skilled person. In particular, in the examples previously described with reference to FIGS. 3, 4A, 4D and 5, the sealing washer 5 has an annular outer surface forming a spherical surface portion. This spherical portion is included in the surface of the same sphere. However, according to an alternative embodiment of the invention, for example according to an alternative embodiment of the example of Figure 5 as shown in Figure 6, it could be possible to dispense with such a washer 10 d sealing 5 and forming a spherical portion directly on the peripheral surface of the boss 30a forming the sampling port 30. The expression "comprising a" must be understood as being synonymous with "comprising at least one", unless the contrary is specified.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A system (1) for supplying pressurized air to an aircraft turbine engine (10) configured to supply pressurizing air to a portion of compressed air use of the aircraft from pressurizing air taken since a compressed air sampling portion (12) of the aircraft turbomachine (10), characterized in that it comprises: a pressurization air sampling port (30) formed on a casing (12c) of the compressed air sampling portion (12) of the aircraft turbomachine (10), - a sampling member (32) connected to the sampling port (30) to allow the sampling and the transport of the air from pressurization withdrawn towards the part of use of compressed air, - a passage port (38) of the sampling member (32) formed on a casing (39) of a compartment (ZC) of the turbomachine (10) , said housing (39) being subject to slight displacements relative to the housing (12c) of the bleed portion ir compressed (12), the sampling member (32) passing through the port of passage (38) with a freedom of movement relative to the latter during said low displacements, - a pressurized chamber (33) traversed by the organ of sample (32), located between the casing (12c) of the compressed air sampling portion (12) and the casing (39) of the compartment (ZC), and comprising air under a pressure greater than that of the pressurizing air taken off, the system (1) for supplying pressurized air further comprising sealing means (2) located substantially between the casing (12c) of the compressed air sampling part (12) and the housing (39) of the compartment (ZC) for forming a substantially sealed separation between the pressurized chamber (33) and a free space (40) communicating with the compartment (ZC) and arranged around the sampling member (32), in order to guard against the introduction of pressurized air from the pressurized chamber Isée (33) inside the sampling member (32) in case of rupture of the latter. 3024179 25
    [0002]
    2. System according to claim 1, characterized in that the sealing means comprise a first sealing piece (2) arranged around the sampling member (32) and in the passage port (38) having a freedom of movement relative to the latter, this first sealing member (2) being connected to the casing (12c) of the compressed air sampling portion (12) by a sealed connection so as to prevent air leakage significantly from the pressurized chamber (33) at said connection.
    [0003]
    3. System according to claim 2, characterized in that the tight connection is formed by a second sealing piece (5) comprising an annular outer surface forming a spherical surface portion, and in that the first sealing piece. (2) has a free end (2c) comprising a cylindrical inner surface which forms a circular nip with said spherical surface portion, so that the first sealing member (2) is hinged with sealing on the second sealing piece (5).
    [0004]
    4. System according to one of the preceding claims, characterized in that it comprises a holding cap (3) fixed on the housing (39) of the compartment (ZC) of the turbomachine (10) and traversed by the body of sampling (32), this holding cap (3) being arranged to seal the casing (39) and the sealing means (2) while allowing freedom of movement of the sealing means (2) relatively to the housing (39).
    [0005]
    5. System according to claim 4, taken in combination with claim 2 or 3, characterized in that the first sealing part (2) comprises a sliding traversing sole (2a) having a flat portion adapted to bear in abutment. against a corresponding flat portion of the holding cap (3) with the possibility of sliding on it, the freedom of movement of the first sealing piece (2) taking place in a plane parallel to the flat portion with movement prevention perpendicular to this plane. 3024179 26
    [0006]
    6. System according to any one of the preceding claims, characterized in that the sampling port (30) is formed by a boss (30a) on the casing (12c) of the compressed air withdrawal portion (12), an inner surface (Si) 5 of which is formed by a threaded bore (30b) configured to cooperate with a thread (32c) of the outer surface (Se) of a first end (32b) of the sample member (32) to allow the attachment of the sampling member (32) on the boss (30a) of the sampling port (30). 10
    [0007]
    7. System according to claim 6, in combination with claim 3, characterized in that the second sealing member (5) is mounted on the boss (30a) of the housing (12c) of the compressed air withdrawal portion. (12) and has a passage opening (5a) for insertion of the sampling member (32). 15
    [0008]
    8. System according to claim 6 or 7, in combination with claim 3, characterized in that a protective member (4) forming an at least partial envelope around the sampling member (32) is located between the sampling member (32) and the first sealing member (2) and comprises an insertion cavity (4a) for the at least partial introduction of the sampling member (32) into the interior of the protection member (4), said protective member (4) being arranged to bear against the second sealing member (5) once the sampling member (32) is fixed on the boss (30a) of the port of sampling (32).
    [0009]
    9. System according to claim 8, characterized in that the protection member (4) comprises a first end (4b) mounted on the first end (32b) of the sampling member (32), the first end ( 4b) of the protection member (4) comprising in particular a threaded portion (4d) intended to cooperate with a thread (32c) of the outer surface (Se) of the first end (32b) of the sampling member (32). ), and in that the protective member (4) comprises a free second end (4c) located at a distance from the sampling member (32) and the first sealing piece (2).
    [0010]
    10. System according to claim 9, characterized in that the first end (4b) of the protective member (4) bears on the second sealing member (5) and is screwed on the first end (32b ) of the sampling member (32) so as to form a locknut for fixing the sampling member (32) on the boss (30a) of the sampling port (30). 10
    [0011]
    11. A method of assembling a system (1) for supplying pressurized air according to any one of claims 7 to 10, comprising the successive steps of: a) positioning the second sealing member (5) resting on the boss (30a) of the casing (12c) of the compressed air sampling portion (12), b) placing the first seal piece (2) in sealing engagement with the second sealing piece ( 5), c) fixing the protection member (4) on the sampling member (32), in particular by screwing the threaded portion (4d) of the protection member (4) onto the thread (32c) of the outer surface (Se) of the first end (32b) of the sampling member (32), d) fixing the assembly formed by the protection member (4) and the sampling member (32) on the sampling port (30), in particular by screwing the thread (32c) of the outer surface (Se) of the first end (32b) of the sampling member (32) into the random threaded bore (30b) of the inner surface (Si) of the boss (30a), until the protective member (4) comes into contact with the second sealing member (5), e) optionally tighten again the protection member (4) on the sampling member (32) to secure the assembly.
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    同族专利:
    公开号 | 公开日
    EP3172411A1|2017-05-31|
    RU2680910C2|2019-02-28|
    JP2017524863A|2017-08-31|
    FR3024179B1|2016-08-26|
    CA2955739A1|2016-01-28|
    CN106661953A|2017-05-10|
    CN106661953B|2017-12-26|
    RU2017105631A|2018-08-27|
    WO2016012715A1|2016-01-28|
    JP6585699B2|2019-10-02|
    RU2017105631A3|2019-01-09|
    BR112017001321A2|2018-01-30|
    CA2955739C|2017-07-04|
    EP3172411B1|2018-06-20|
    US9995224B2|2018-06-12|
    US20170204789A1|2017-07-20|
    WO2016012715A9|2016-07-07|
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    法律状态:
    2015-08-10| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-29| PLSC| Publication of the preliminary search report|Effective date: 20160129 |
    2016-07-26| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-26| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-10| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20200304 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 7 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1457192A|FR3024179B1|2014-07-25|2014-07-25|PRESSURIZED AIR SUPPLY SYSTEM INSTALLED IN AN AIRCRAFT TURBOMACHINE HAVING SEALING MEANS|FR1457192A| FR3024179B1|2014-07-25|2014-07-25|PRESSURIZED AIR SUPPLY SYSTEM INSTALLED IN AN AIRCRAFT TURBOMACHINE HAVING SEALING MEANS|
    RU2017105631A| RU2680910C2|2014-07-25|2015-07-22|System for supplying pressurised air installed in an aircraft turbine engine included sealing means|
    JP2017503124A| JP6585699B2|2014-07-25|2015-07-22|System for supplying pressurized air installed in an aircraft turbine engine including a sealing means|
    PCT/FR2015/052012| WO2016012715A1|2014-07-25|2015-07-22|System for supplying pressurised air installed in an aircraft turbine engine including sealing means|
    US15/327,719| US9995224B2|2014-07-25|2015-07-22|System for supplying pressured air installed in an aircraft turbine engine including sealing means|
    CN201580041223.5A| CN106661953B|2014-07-25|2015-07-22|The system for pressurised air for including sealing device in aircraft turbine engines|
    EP15759859.0A| EP3172411B1|2014-07-25|2015-07-22|System for supplying pressurised air installed in an aircraft turbine engine including sealing means|
    CA2955739A| CA2955739C|2014-07-25|2015-07-22|System for supplying pressurised air installed in an aircraft turbine engine including sealing means|
    BR112017001321A| BR112017001321A2|2014-07-25|2015-07-22|pressurized air supply system for an aircraft turbine engine and method for mounting a pressurized air supply system|
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