• 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:

    公开号:FR3017693A1
    申请号:FR1451321
    申请日:2014-02-19
    公开日:2015-08-21
    发明作者:Nicolas Savary；Patrick Berteau；Bernard Carrere；Jean-Marc Dubourdieu；Ludovic Naudot
    申请人:Turbomeca SA；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to the field of turbomachine combustion chambers, and more particularly to the field of turbomachine annular combustion chambers and in particular, but not exclusively, helicopter turboshaft engines. The term "turbomachine" refers to all gas turbine engines producing a motive power, among which are distinguished in particular turbojet engines providing thrust required for propulsion by reaction to the high speed ejection of hot gases, and Turbomotors in which the motive power is provided by the rotation of a motor shaft. For example, turboshaft engines are used as engines for helicopters, ships, trains, or as an industrial engine. Turboprops (turbine engine driving a propeller) are also turboshaft engines used as aircraft engines. STATE OF THE PRIOR ART A conventional annular turbomachine combustion chamber has an axial direction, a radial direction and an azimuthal direction, and generally comprises five annular walls, each annular wall delimiting at least a portion of the chamber of the chamber. combustion. These annular walls are conventionally assembled by welding or bolting. Joining by welding makes it impossible to dismantle the first and second walls, for example for maintenance or for the replacement of one of these walls. The bolting assembly has the disadvantage of favoring the appearance of cracks and fissures in the vicinity of the bolt bolt engagement holes because of the generated blockages, which weakens the combustion chamber. In addition, these types of assemblies are complex, long and expensive. PRESENTATION OF THE INVENTION One embodiment relates to an annular turbomachine combustion chamber having an axial direction, a radial direction and an azimuthal direction, comprising a first annular wall and a second annular wall, each wall delimiting at least a portion of the enclosure of the annular combustion chamber, the first and second walls having complementary interlocking elements, the first wall having at least one first through-hole, while the second wall having at least one second through-hole; combustion further comprising at least one pin engaged in a pair of holes comprising a first hole and a second hole, said pin interlocking the interlocking of the first and second walls. It will be understood that the first annular wall comprises first interlocking elements while the second annular wall comprises second interlocking elements, the first and second interlocking elements being respectively complementary to one another so as to be able to interlocking in the axial and / or azimuth direction of the combustion chamber. In other words, the first and second interlocking elements are nested or engaged with each other by moving them relative to each other in the axial and / or azimuth direction of the combustion chamber. .
    [0002] The combustion chamber may comprise two or more annular walls. In the latter case, the assembly of these several annular walls can be locked by the spindle. For example, the same pin can lock the assembly of three or more separate walls. In another example, a pin can lock the assembly of two walls, namely a first and a second wall, while another pin locks the assembly of the first or second wall with a third wall. It is understood that the first wall has one or more first hole (s), the second wall has one or more second hole (s). Of course, according to one variant, there are as many first holes as second holes, each first hole forming a pair of holes with a second hole (or vice versa). Subsequently, and unless otherwise indicated, the first hole or set of first holes and the only second hole or set of second holes respectively denote by "the first hole" and "the second hole" respectively. The combustion chamber comprises one or more pins. Subsequently, and unless otherwise indicated, the "pin" designates the single pin or set of pins. The pin is for example a rod or staple configured to engage simultaneously in a first hole and second hole forming a pair of holes. The spindle is engaged, with or without play, in a pair of first and second holes.
    [0003] Such a pin cooperates only by engagement or fitting with the pair of holes so as to couple the first and second walls according to certain degrees of freedom, for example in axial translation and / or in rotation around the axial direction of the combustion chamber, without however blocking all degrees of freedom. Such a spindle makes it possible to avoid, or significantly reduce the risk of the appearance of cracks or fissures compared to the conventional use of bolts. Thus, such a pin makes it possible to assemble the walls of the combustion chamber without the need to weld and / or to crimp the two walls, as is done within the combustion chambers of the state of the art. Of course, when the combustion chamber has several pairs of first and second holes, said combustion chamber may have several pins, each pin being engaged in a pair of holes. Alternatively, when a pin is provided in a pair of holes, this pair of holes receives a single pin. According to one variant, there are as many pins as pairs of first and second holes. According to one variant, the pins are similar. The pin blocks axial and / or azimuth relative displacements between the first and second walls. Thus, when the one or more pins are engaged in the one or more pairs of holes, the interlocking of the first and second walls is locked. To dislodge the first and second walls from each other, it is necessary first to remove the pin (s) of the pair or pairs of first and second holes. Thus, the combustion chamber can be assembled easily, quickly, and at low cost compared to the combustion chambers of the state of the art, and without the need for welding operation. Moreover, such a combustion chamber can be just as easily disassembled, thus facilitating maintenance operations. In some embodiments, the first hole and the second hole of the pair of holes are arranged substantially facing each other. It is also understood that by "opposite" is meant that the first hole is aligned axially and Azimuthally with the second hole, having the same angular position. In other words, the first and second holes of the pair of holes are not diametrically opposed. Such a configuration vis-à-vis allows the use of single pins, and allows easy and efficient assembly. In some embodiments, the spindle is formed by an injector. Of course, the combustion chamber may have other pins formed by other elements. According to a variant, the combustion chamber has several pins, each pin being formed by an injector. Using an injector as a spindle optimizes the mass of the combustion chamber, a constant problem in turbomachines used in aeronautics. The structure of the combustion chamber is also simplified, which contributes to facilitating its assembly / disassembly. In addition, using the injectors as pins, one can fix and position the combustion chamber directly through this in a turbomachine. In some embodiments, the pin extends substantially radially. By "substantially radial direction" means a direction parallel to a radial plane and forming an angle of between 60 ° and 120 ° relative to the axis of the combustion chamber. Such orientation of the pin (s) makes it easy to assemble the combustion chamber while interlocking is even more satisfactory. In some embodiments, the complementary interlocking elements comprise a plurality of axial tabs extending from one of the first wall and the second wall and a plurality of days in the other wall of the first and second walls. said days receiving the tabs. In this case, the complementary interlocking elements form complementary elements of axial interlocking. It is understood that the first wall and / or the second wall 30 comprises one or more tongues. Thus, the first wall may have tabs while the second wall has no tab, the first wall may have no tab while the second wall has tabs, or the first wall may have a plurality of first tabs while the second wall has a plurality of second tabs. The other wall has days arranged opposite the tongues, so as to receive and cooperate by axial interlocking with the tongues. Thus, if only the first wall has tongues then the second wall has days, if only the second wall has tongues then the first wall has days, whereas if the first wall has first tongues and the second wall presents second tongues, then the first wall has first days receiving the second tongues while the second wall has second days receiving the first tongues. According to one variant, the tongues and the days are regularly distributed (or spaced) azimuthally. It is therefore understood that the angular spacing between the adjacent tabs / adjacent days is equal. Such a distribution makes it possible to obtain a certain symmetry of revolution of the complementary interlocking elements, which facilitates the interlocking operations of the walls, and therefore the assembly of the combustion chamber. In some embodiments, the hole of one wall of the first and second walls is formed in a protruding blade.
    [0004] It is understood that the blade is a projecting portion of the first wall if the hole is the first hole while the blade is a projecting portion of the second wall if the hole is the second hole. Such a configuration reduces the mass of a wall while reducing the size of the combustion chamber in the vicinity of the blade.
    [0005] Moreover, this configuration makes it possible to confine the location of the hole to a very particular and controlled position within the combustion chamber, thus reducing the risks of leaks, these leaks being disadvantageous from the point of view of the performance of the combustion chamber. .
    [0006] In some embodiments, a projection disposed in the vicinity of the other hole of the first hole and the second hole extends substantially parallel to the axis of said other hole so as to cooperate by snapping with the blade. For example, the vicinity of a hole comprises the annular portion of the wall that extends around the hole over three times the diameter (or the maximum dimension) of the hole. For example, the projection is formed by a boss machined directly on the wall, for example by stamping, or by an insert and fixed on the wall. The clipping (or clipping) is a method of assembling two parts by engagement and elastic deformation (generally local deformation, for example of the blade, or by deformation of all the parts involved in the assembly). When both parts are engaged in the latching position, the parts have generally returned to their original shape and no longer exhibit elastic deformation (or less elastic deformation). When the two parts are engaged with each other in the latching position, they cooperate with each other so as to oppose, or even block, the relative movements of said parts in the direction of disengagement ( opposite meaning to the meaning of the commitment). In the latching position, the two parts can also cooperate to oppose, or even block, their relative movements in the direction of the extension of the engagement, beyond the latching position. Such snapping makes it possible to maintain the first and second nested walls before locking the interlocking using the spindle.
    [0007] In some embodiments, the edge of said other hole forms a projection extending substantially parallel to the axis of said other hole so as to cooperate by snapping with the blade. In some embodiments, a wall of the first wall and the second wall has an axial annular shoulder cooperating abutting with the other wall of the first wall and the second wall. Such a shoulder allows to form a joint plane between the first and the second wall, whereby the leaks within the combustion chamber are minimized or even zero. In certain embodiments, the combustion chamber comprises only two annular walls defining the chamber of the combustion chamber, namely the first annular wall and the second annular wall. The first and second walls therefore alone define enclosure of the combustion chamber. Such a combustion chamber has a particularly small number of walls, which makes assembly easier, faster and cheaper. Moreover, disassembly operations for maintenance are also facilitated. In addition, a combustion chamber having such a reduced number of walls presents risks of leakage in the vicinity of the joints between the various particularly weak walls. One embodiment relates to a turbomachine comprising a combustion chamber according to any one of the embodiments described in the present description. BRIEF DESCRIPTION OF THE DRAWINGS The invention and its advantages will be better understood on reading the detailed description given below of various embodiments of the invention given as non-limiting examples. This description refers to the pages of appended figures, in which: FIG. 1 represents a turbomachine equipped with a combustion chamber, FIG. 2 represents the annular walls of the combustion chamber of FIG. 1, seen in perspective, Figure 3 shows a detail view of the annular walls of Figure 1, and Figure 4 shows the annular walls of Figure 1 assembled. DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS FIG. 1 represents a turbomachine 100 equipped with an annular combustion chamber 10 while FIGS. 2 to 4 represent in more detail the two annular walls 12 and 14 of this combustion chamber 10. this combustion chamber 10 is an annulus of the inverted flow type, but the invention is not limited to this particular type of combustion chamber.
    [0008] The combustion chamber 10 has an axial direction (along the X axis), a radial direction R and an azimuthal direction Y. The combustion chamber 10 has a symmetry of revolution along the axis X. In this example, the first wall 12 forms a flame tube defining the enclosure where the fuel ignites, ie where the combustion takes place. The second wall 14 forms an outer bend and serves as a deflector for guiding the flow of gases from the flame tube. This example of a combustion chamber 10 comprises only the two annular walls 12 and 14 for delimiting the chamber 10a of the combustion chamber 10. More particularly, the first wall 12 and the second wall 14 each have a general shape substantially of half torus, the torus being cut perpendicularly to its axis of revolution, or mold "donut", the two half-toruses being arranged opposite one another. Thus, each wall 12 and 14 comprises a substantially axial outer portion 12a and 14a, a substantially axial inner portion 12b and 14b, and a substantially radial bottom 12c and 14c respectively connecting the outer portions 12a and 12b inner portion of the first wall 12 and the outer portions 14a and inner 14b of the second wall 14. As a reminder, generally and unless otherwise stated, the adjectives "inside" and "outside" are used with reference to a radial direction so that the inner portion (ie radially inner ) an element is closer to the X axis than the outer (ie radially outer) part of the same element. In this example, the radius of the outer portion 12a of the first wall 12 is substantially equal to, but less than, the radius of the outer portion 14a of the second wall 14 while the radius of the inner portion 12b of the first wall 12 is greater than the radius 14b of the second wall 14. Thus, one can assemble the first wall 12 with the second wall 14 by their outer wall 12a and 14a, the outer portion 12a of the first wall 21 being disposed inside the portion external 14a of the second wall 14, while the radius difference of the inner portions 12b and 14b creates a flue gas exhaust duct. The first wall 12 has a plurality of axial tongues 12d while the second wall 14 has a plurality of days 14d configured to receive the tabs 12d of the first wall 12. The tabs 12d and 14d days form in this example complementary elements d axial interlocking of the first and second walls 12 and 14. Of course, according to a variant not shown, tabs may form complementary elements of azimuthal engagement, or axial and azimuthal interlocking.
    [0009] The axial tongues 12d extend axially from the outer portion 12a of the first wall 12. The days 14d are formed in an annular shoulder 14e extending radially and connecting the outer portion 14a and the bottom 14c of the second wall 14.
    [0010] In this example, there are as many tabs 12d as days 14d, each day 14d receiving a tab 12d. When the first wall 12 is nested axially with the second wall 14, the tongues 12d are penetrated in the days 14d while the axial free end of the outer portion 12a of the first wall cooperates axially in abutment with the shoulder. 14th. The first wall 12 has a plurality of first through holes 12f, the axis of these holes 12f being oriented radially. These holes 12f are formed in the outer portion 12a of the wall 12. The second wall 14 has second through holes 14f whose axis is oriented radially. The holes 14f are formed in blades 14g projecting axially from the outer portion 14a of the second wall 14. In this example, the holes 12f and 14f are substantially circular, but may of course have another shape. When the first and second walls 12 and 14 are nested, the holes 12f and 14f face each other. In this example, there are as many first holes 12f as second holes 14f. A sleeve 16 configured to receive an injector 18 is fixed, for example by welding or crimping, in each first hole 12f. This sleeve 16 forms an outwardly projecting rim along the axis of each first hole 12f. The maximum radius of the sleeves 16 is smaller than the radius of the second holes 14f. Thus, during the engagement of the first and second walls 12 and 14, each blade 14g cooperates by snapping with a sleeve 16. To lock the blades 14g snapped with the sleeves 16, 30 a spoiler 20 is reported after the interlocking of the first and second walls 12 and 14 on the outside of the outer portion 12a of the first wall 12. For example the spoiler 20 is welded. Such a spoiler 20 allows intermediate locking of the engagement of the walls 12 and 14 as the injectors 18 described below forming locking pins of the interlocking are not installed. One or more spoilers can be provided. In this example, there are as many spoil 20 as there are blades 14g. Of course these spikes 20 are optional and are not present in some variants of the combustion chamber. When the first and second walls 12 and 14 are axially nested, the first holes 12f are in facing relation with the second holes 14f. Then introduced into each pair of first and second holes 12f and 14f vis-à-vis an injector 18 forming a pin, thereby locking the interlocking of the first and second walls 12 and 14. The injectors 18 extend radially in each pair of holes 12f and 14f. The injectors 18 are fitted with clearance in each pair of holes so as to allow relative displacements between each of the elements due to the thermal expansion differentials, but nevertheless couple the first and second walls 12 and 14 in translation along the axial direction X and in rotation in the azimuthal direction Y. Of course, the sleeves 16 also participate in the coupling of the first and second walls 12 and 14, but this coupling is relatively fragile, in particular because of thermal expansion differentials which in certain circumstances can cause the blades 14g no longer cooperate effectively with the sleeves 16, and this despite the spurs 20. Thus, most of the locking of the interlocking of the first and second walls 12 and 14 is provided by the pins formed by the injectors 18. Although the the present invention has been described with reference to specific embodiments, it is obvious that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various embodiments illustrated / mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.30
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine annular combustion chamber (10) having an axial direction (X), a radial direction (R) and an azimuthal direction (Y), comprising a first annular wall (12) and a second annular wall (14) , each wall delimiting at least a portion of the enclosure (10a) of the annular combustion chamber (10), the first and second walls (12, 14) having complementary interlocking elements (12d, 14d), the first wall (12) having at least one first through hole (12f) while the second wall (14) has at least one second through hole (14f), the combustion chamber (10) further comprising at least one spindle (18) engaged in a pair of holes comprising a first hole (12f) and a second hole (14f), said pin (18) locking the engagement of the first and second walls (12, 14).
    [0002]
    The combustion chamber (10) of claim 1, wherein the first hole (12f) and the second hole (14f) of the pair of holes are disposed substantially facing each other.
    [0003]
    Combustion chamber (10) according to claim 1 or 2 wherein the pin is formed by an injector (18).
    [0004]
    4. Combustion chamber (10) according to any one of claims 1 to 3, wherein the pin (18) extends substantially radially.
    [0005]
    5. Combustion chamber (10) according to any one of claims 1 to 4, wherein the complementary interlocking elements comprise a plurality of axial tongues (12d) extending from a wall of the first wall (12) and the second wall (14) and a plurality of days (14d) formed in the other wall of the first wall (12) and the second wall (14), said days (14d) receiving the tongues (12d).
    [0006]
    The combustion chamber (10) according to any of claims 1 to 5, wherein one of the first hole (12f) and the second hole (14f) is formed in a protruding blade (14g).
    [0007]
    The combustion chamber (10) according to claim 6, wherein a projection (16) disposed in the vicinity of the other one of the first hole (12f) and the second hole (14f) extends substantially parallel to the axis of said other hole so as to cooperate by snapping with the blade (14g).
    [0008]
    8. Combustion chamber (10) according to any one of claims 1 to 7, wherein a wall of the first wall (12) and the second wall (14) has an annular shoulder (14e) cooperating axially in abutment with the another wall among the first wall (12) and the second wall (14).
    [0009]
    9. Combustion chamber (10) according to any one of claims 1 to 8, comprising only two annular walls defining the enclosure (10a) of the combustion chamber (10), namely the first annular wall (12) and the second annular wall (14).
    [0010]
    10. Turbomachine (100) comprising a combustion chamber (10) according to any one of claims 1 to 9.20
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    法律状态:
    2016-02-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-02-10| PLFP| Fee payment|Year of fee payment: 4 |
    2017-09-01| CD| Change of name or company name|Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170727 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 5 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 8 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1451321|2014-02-19|
    FR1451321A|FR3017693B1|2014-02-19|2014-02-19|TURBOMACHINE COMBUSTION CHAMBER|FR1451321A| FR3017693B1|2014-02-19|2014-02-19|TURBOMACHINE COMBUSTION CHAMBER|
    US15/120,015| US9933164B2|2014-02-19|2015-01-27|Annular turbomachine combustion chamber|
    PL15706859T| PL3114409T3|2014-02-19|2015-01-27|Annular turbine engine combustion chamber|
    EP15706859.4A| EP3114409B1|2014-02-19|2015-01-27|Annular turbine engine combustion chamber|
    CA2940099A| CA2940099C|2014-02-19|2015-01-27|Annular turbine engine combustion chamber|
    RU2016137127A| RU2669435C2|2014-02-19|2015-01-27|Annular combustion chamber of turbo-machine|
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    ES15706859.4T| ES2670697T3|2014-02-19|2015-01-27|Turbomachine annular combustion chamber|
    CN201580008108.8A| CN106415131B|2014-02-19|2015-01-27|The turbomachinery combustion chamber of annular|
    PCT/FR2015/050179| WO2015124840A1|2014-02-19|2015-01-27|Annular turbine engine combustion chamber|
    KR1020167025649A| KR102265942B1|2014-02-19|2015-01-27|Annular turbine engine combustion chamber|
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