• 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:
    Turbomachine combustion module (10), in particular an aircraft turbomachine, configured for the implementation of a constant volume combustion comprising at least two combustion chambers (12A, 12B) arranged around an axis, each chamber (12A, 12B, 12C) comprising an intake port (16) for compressed gas and an exhaust port (18) for burnt gases, and ignition means for igniting combustion in the combustion chambers (12A, 12B , 12C). The module (10) comprises at least one duct (80) capable of placing a first of the combustion chambers (12A) in communication with at least one second of the combustion chambers (12B) for injecting flue gases from the first chamber of combustion. combustion (12A) in said second combustion chamber (12B) to initiate combustion in said second combustion chamber (12B).
    公开号:FR3032024A1
    申请号:FR1550587
    申请日:2015-01-26
    公开日:2016-07-29
    发明作者:Matthieu Leyko
    申请人:Safran SA；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to the field of combustion chambers 5 of aircraft turbomachines, of the constant-volume combustion type. The invention applies to any type of turbomachine, in particular turbojet engines, turboprop engines, and turbomachines with unducted fans, also known by the Anglo-Saxon term "Open Rotor". STATE OF THE PRIOR ART A conventional aircraft turbine engine comprises, in a known manner, one or more combustion chambers. Such a combustion chamber is supplied with pressurized air by a compressor module and comprises a fuel injector which is capable of injecting fuel into the flow of air admitted to burn it and thus causing the emission of hot gases. which are used on the one hand to drive a turbine, which drives the compressor module and can also drive a fan of the turbomachine, and on the other hand which are used to be ejected at high speed out of the turbomachine so as to propel the aircraft which is equipped with said turbomachine by reaction. In such a chamber, the fuel flow is continuous and the combustion operates according to a so-called Brayton cycle, that is to say according to a constant pressure combustion cycle. Nevertheless, in order to obtain specific consumption gains, it has been envisaged to replace the Brayton-cycle combustion chamber with a plurality of Humphrey-type combustion chambers, i.e. constant volume combustion cycle or "HVAC". WO-2014/020275-A1 discloses an HVAC combustion chamber comprising spherical valves comprising rotatable rotors rotatably mounted about axes perpendicular to the axis of the chamber and combined with spherical envelopes of these rotors, said rotors and said envelopes having alignable channels and lumens with each other and with combustion chamber exit inlet channels for selectively determining the opening or closing of the intake and outlet valves; corresponding exhaust. Each chamber has a spherical valve at each of its ends, and said valves are synchronized with each other to implement the three successive phases of the Humphrey cycle. In this solution, the design of the intake and exhaust valves has drawbacks. In the first place, the movements of the spherical rotors in the envelopes cause numerous friction, detrimental to the longevity of such valves. Second, the valves are difficult to manufacture, because of the spherical shape of their elements. Thirdly, in this design, the valves remain independent and must be synchronized, and therefore the complexity of the combustion chamber is not optimal. Fourth and last, each chamber requires an intake valve and an exhaust valve which are its own, so that a turbomachine comprising several chambers comprises as many intake valves and exhaust valves as chambers .
    [0002] SUMMARY OF THE INVENTION A Humphrey cycle combustion chamber comprises a compressed gas inlet port having an inlet valve arranged at the chamber inlet and a flue gas exhaust port having a exhaust valve 3032024 3 arranged at the outlet of the combustion chamber. These valves are able to oscillate each between an open position and a closed position and are controlled in a synchronized manner to implement the three successive phases of the Humphrey cycle, namely admission / sweep - combustion - exhaust. In such an engine, it is desirable that the cycles of the chambers are offset relative to each other inversely proportional to the number of chambers. This makes it possible, by generating a succession of exhaust phases, to smooth the flow of the exhaust gases supplied to the turbine module, and consequently to smooth the pulsation phenomena inherent in constant volume combustion cycles. In fact, if all the chambers were operating simultaneously at the same times in the Humphrey cycle, the exhaust phases would all be simultaneous and this would result in an irregular exhaust gas flow, because subjected to the simultaneous pulsation of the gases coming from the bedrooms. Such a flow would be detrimental to the longevity of the turbine module. On the other hand, a combustion module comprising staggered chamber cycles makes it possible to smooth these pulsations. The exhaust gas intake of the turbine module is all the more homogeneous and free of pulsations as the number of chambers is high. Thus, preferably, a combustion module comprising a determined number of chambers sees preferably, between two consecutive chambers, the cycles of its chambers offset by a fraction of the number of determined chambers.
    [0003] According to the current state of the art, the combustion in this type of combustion chamber is triggered conventionally at each combustion stage by a spark plug housed in each chamber. Such a design, in the context of a multi-chamber engine, involves a management of particularly rigorous ignition times, and the implementation on the assembly 3032024 4 of the engine of a complex ignition circuit that is detrimental to the accessibility of the engine. However, another solution to trigger the ignition of a constant volume chamber is to inject hot burnt gases, the high temperature of these gases sufficient to trigger combustion. The invention proposes a combustion module implementing this solution to trigger ignition successively in the combustion chambers. For this purpose, the invention proposes a combustion module of the type 10 configured for the implementation of constant volume combustion, comprising at least two combustion chambers, each chamber comprising a compressed gas intake port and a exhaust port of burnt gases, and ignition means initiating combustion in the combustion chambers. The module has its chambers 15 arranged around an axis, and it comprises at least one duct capable of putting into communication a first of the combustion chambers with at least one second of the combustion chambers for injecting flue gas from the first chamber combustion in said second combustion chamber to initiate combustion in said second combustion chamber. The rooms are for example radially mounted around the axis. According to other characteristics of the combustion module: the module comprises a shutter for opening / closing of the duct able to selectively allow the passage of the flue gases from the first combustion chamber towards said second combustion chamber; the duct is a fixed duct and the shutter comprises at least one pressure-calibrated valve means, which is located in the duct, and which is able to open when the pressure of the flue gases in the first chamber exceeds a predetermined threshold, the module comprises at least one group of combustion chambers angularly arranged regularly around said axis, said group comprising at least one clean ignition circuit which comprises communication conduits which are each arranged between two 5 chambers of said group and which are able to inject flue gas from a first of the two chambers in the second of the two chambers in order to trigger a in the second combustion chamber, the module comprises at least two groups of combustion chambers angularly arranged in a regular manner around said axis, each group comprising at least one clean ignition circuit which comprises communication ducts which are each arranged between two chambers of said group and which are capable of injecting flue gases from a first of the two chambers into the second of the two chambers in order to trigger combustion in said second combustion chamber of said group, and at least one circuit of additional ignition, which is interposed between two groups and which comprises additional communication conduits which are each arranged between a first chamber of a group and a second chamber of the other group and which are capable of injecting burnt gases from the first first group chamber in the second chamber of the second group to initiate combustion in said second combustion chamber of said second group, in order to maintain the ignition of the chambers of the two groups in case of failure of a clean ignition circuit, the combustion chamber inlet / outlet ports are configured to being open or closed by respective synchronized and rotatably mounted common intake / exhaust valves about said axis, said valves having a radial opening which is formed in a wall shaped as a cylinder section of the combustion chamber facing the axis, each corresponding rotary valve inlet or exhaust comprising a tubular element, of diameter corresponding to said cylinder section 3032024 6 rotatably mounted coaxially with said cylinder section, said tubular element having a bore allowing the routing of the gases of intake / exhaust, and at least one radial lumen, arranged substantially in an axial plane of the radial opening Ie of said port, and which is 5 able to close or release said radial opening during the rotation of said tubular element and at least one of the rotary valves comprises on its periphery a throat section which extends over a given angular sector of the periphery of the rotary valve for determining a leakage duct which is intended to put into communication a first of the combustion chambers and a second of the combustion chambers close to said first chamber, in a position of said rotary valve corresponding to an end of combustion in the first chamber prior to an evacuation of the burnt gases and a filling end of the second chamber prior to combustion, the rotary valve 15 forming the shutter according to its angular position, - the throat section is formed in the periphery of the the tubular element of the rotary exhaust valve, - the module comprises a common rotary element which com carries rotational mutually related inlet / exhaust valves. The invention also relates to a turbomachine comprising a compressor module comprising at least one compressor, a combustion module of the type described above, and a turbine module comprising at least one turbine, the compressor module being connected to the turbine module by a tree system. According to the invention, this turbomachine is characterized in that the compressor module feeds the combustion module via a single intake duct, and in that the combustion module supplies the turbine module with the combustion engine. intermediate of a single exhaust duct.
    [0004] According to another characteristic of the turbomachine, at least one shaft of the shaft system forms the driving means of the common rotary element linking the mutually rotatable inlet and exhaust rotary valves. Finally, the invention relates to a method for controlling a combustion engine of a turbomachine of the type described above, comprising at least one step of successively igniting at least a first and a second combustion chamber, each of which operates successively. according to a cycle comprising: a first phase during which the intake and exhaust ports are closed, comprising a first sub-phase of confinement of a fresh fuel mixture and then a second sub-phase of combustion of said mixture carburettor in each corresponding chamber, - a second phase during which the intake port is closed and the exhaust port is open, to cause the escape of the flue gas from each corresponding chamber, then 15 - a third phase to during which the ports of admission and intake and exhaust are open, to cause the flue gas to be scanned with fresh gases through each chamber. e, in which, during the successive ignition step, the inlet and the outlet of the first and second chambers are expanded so that the first chamber can be subjected to the second sub-phase when the second chamber is subjected to the first sub-phase, and in that the successive ignition step comprises a control sub-step, intervening when the first chamber is subjected to the second sub-phase, during which communicates the first chamber and the second chamber to initiate combustion in the second chamber. The invention will be better understood and other details, features and advantages of the present invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings, in which: Figure 1 is a perspective view intersected by an axial plane illustrating the principle of a constant volume combustion module; FIG. 2 is a diagrammatic view in axial section of the combustion module of FIG. 1; Figure 3 is a schematic cross-sectional view of the combustion module of Figure 2; FIG. 4 is a perspective view of a combustion module with three combustion chambers; Figure 5 is a diagrammatic cross-sectional view of the combustion module of Figure 4; FIG. 6 is a cutaway perspective view of a turbomachine comprising a plurality of constant volume combustion modules; FIG. 7 is a perspective view of a combustion module with three combustion chambers according to the invention; FIG. 8 is a schematic cross-sectional view of the combustion module of FIG. 6; FIG. 9 is a schematic view of an ignition circuit of the combustion module of FIGS. 7 and 8; FIG. 10 is a schematic view of a first variant of an ignition circuit for the combustion module of FIGS. 7 and 8; FIG. 11 is a schematic view of a second variant of an ignition circuit for the combustion module of FIGS. 7 and 8; FIG. 12 is a perspective view of a rotating element for an ignition circuit of a combustion module according to FIGS. 4 to 6; FIGS. 13A, 14A and 15A are schematic views showing three successive positions of a combustion module comprising a rotary element according to FIG. 11, in cross section in the axial plane of its intake valve; and FIGS. 13B, 14B and 15B are schematic views showing three successive positions of a combustion module 3032024 9 having a rotary element according to FIG. 11 in section in the axial plane of its exhaust valve. In the following description, like reference numerals designate like or similar parts. FIGS. 1 to 3 show the principle of a combustion module 10 configured to implement a constant-volume combustion taking place according to the Humphrey cycle, that is to say comprising a combustion phase, a phase exhaust, and a phase 10 of fresh air intake and flue gas scavenging. Figures 1 to 3 illustrate the principle of a combustion module 10 having a combustion chamber 12 arranged around an axis "A", which corresponds for example to an axis of rotation of a turbomachine. FIGS. 1 to 3 have been simplified to a single chamber 12, for the understanding of the operation of such a chamber 12. However, the invention relates to a module comprising at least two combustion chambers 12, that is to say say for example a module of the type that has been shown in Figures 4 and 5, which has three combustion chambers. The combustion module 10 may comprise a greater number of chambers 12, as illustrated in FIG. 6, which represents a turbomachine 14 comprising ten combustion chambers 12 arranged around the "A" axis. As illustrated in FIGS. 1 and 2, each chamber 12 includes a compressed gas inlet port 16 and an exhaust gas port 18. In a turbomachine of the type of that shown in FIG. 6, the compressed gas inlet port 16 is supplied by a compressor module 20 of the turbomachine 14 comprising at least one compressor 22, and the port 18 of exhaust gas feeds at least one turbine module 24 comprising at least one turbine 26.
    [0005] The invention is described with reference to preferred embodiments of the combustion module, but it will be understood that this configuration is not limiting of the invention. Preferably, each intake port 16 or exhaust port 18 is configured to be opened or closed by a rotary admission valve 28 or by a corresponding exhaust valve 30, coaxial with the axis A of the turbomachine 14. The combustion module 10 which has been shown in Figures 1 to 3 has only a combustion chamber 12. In this configuration, the ignition of the combustion chamber 12 is necessarily carried out by an ignition means, for example a spark plug, which is specifically associated with the chamber 12. In order to homogenize the combustion gases, Exhaust provided to the turbine module 24 of the turbomachine, there is provided a module 10 15 having a plurality of combustion chambers 12. Thus, it is preferable to have a module 10 comprising at least two combustion chambers 12 angularly distributed regularly around the axis A, whose intake ports 16 are configured to be opened or closed by a rotary valve. common intake 28 and whose exhaust ports 18 are configured to be opened or closed by a common exhaust rotary valve 30. The inlet valve 28 and the exhaust valve 30 can rotate together or can rotate be parts that can turn differently. FIG. 5 illustrates a combustion module 10 of this type, comprising a common rotary valve 28 for admission which supplies the three intake ports 16 with three combustion chambers 12 of the same module 10. FIG. 6 shows a turbomachine whose module 10 includes a common intake rotary valve 28 which supplies the intake ports with ten combustion chambers 12 of the same module 10 and an exhaust rotary valve 30. which is supplied by the ten exhaust ports of the ten combustion chambers 12 of said module 10. This configuration is particularly advantageous since it makes it possible to feed several chambers 12 with a single intake valve 28 and to exhaust gas with a single exhaust valve 30, which greatly simplifies the architecture of a turbomachine 14 comprising such a combustion module 10 compared to previously known designs of the state of the tec hnical.
    [0006] The combustion chambers 12 are angularly distributed uniformly about the axis A, and they each have a direction preferably oriented in a substantially axial direction parallel to the axis A, so as to form a barrel-shaped structure. . However, this configuration is not limiting, and the chambers 15 could be arranged according to another orientation as long as they are disposed radially around the axis A to be able to be supplied with compressed air in a common manner by a valve. 28 common intake and to evacuate the gases burned in common by a common exhaust valve.
    [0007] Also preferably, the combustion cycles of the chambers 12 are shifted according to an offset depending on the number of chambers 12. This smooths the flow of the exhaust gases supplied to the turbine module 24, smoothing the pulsation phenomena inherent in the constant volume combustion cycles. Indeed, if all the chambers 12 were operating simultaneously according to the same times of the Humphrey cycle, the exhaust phases would all be simultaneous and this would result in an irregular exhaust gas flow, because subjected to the simultaneous pulsation of the gases from 12. Such a flow rate could damage the turbine module 24. On the contrary, a combustion module 10 operating in cycles of shifted chambers 12 smooths these pulsations. Note that the exhaust gas inlet 3032024 12 of the turbine module 24 is even more homogeneous and free of pulsations that the number of chambers 12 will be high. Thus, preferably, a combustion module having a determined number "n" of chambers 12 will it see the cycles of its 5 staggered chambers For a number of "n" rooms, it will be necessary to operate a number of chambers less than half "n / 2" of the number "n" of chambers at the same time to balance the loads on the rotary valves. In particular, two opposite chambers will be on the same cycle phase considering for example for four rooms at a given instant two rooms in combustion and two rooms without combustion. In the embodiment considered, the rotary intake valves 28 and exhaust valves 30 are synchronized in rotation with each other, rotating at the same speed of rotation. This synchronization can in general be carried out by any means known from the state of the art, in particular mechanically. The multiplication of the number of combustion chambers 12 raises the problem of ignition means intended to cause combustion in these chambers 12.
    [0008] In such an architecture comprising several chambers 12, it is of course possible to reproduce the configuration which has been mentioned in FIG. 1, according to which each chamber 12 comprises an independent ignition means. However, this configuration is inappropriate because it requires synchronized management of ignition times. Moreover, this configuration further increases the complexity of the combustion module 10 that it comprises more rooms 12. However, it is possible to cause the ignition of a fuel mixture of a non-combustion chamber not by means of a spark plug, but by injections of hot gases, such as for example gases at a temperature close to that of a combustion.
    [0009] Also, as illustrated in FIGS. 6 to 15B, the invention proposes a combustion module 10 of the type described above, comprising at least one duct 80 capable of placing a first combustion chamber 12A in communication with at least a second combustion chamber 12B for injecting flue gases from the first combustion chamber 12A into said second combustion chamber 12B to initiate combustion in said second combustion chamber 12B. Thus, it will be understood that the combustion module 10 according to the invention comprises at least one conduit 80 adapted to put into communication two combustion chambers 12A, 12B whose combustion cycles are offset. For this purpose all the steps of admission / scanning - combustion - exhaust chambers 12A, 12B are offset. This shift involves not only the injection of the burnt gases from the first combustion chamber 12A into said second combustion chamber 12B to ignite combustion in said second combustion chamber 12B, but also that the intake and the exhaust gases from the two chambers 12A 12B, through the intake valves 28 and exhaust valves 30 occur in a staggered manner, so that the injection of flue gas from the first chamber 12A occurs in the chamber 12B filled with fuel mixture. fresh. Furthermore, more generally, this configuration is generalized to all the combustion chambers of the combustion module 10, the flue gas injections being made from a chamber to a successive chamber 25 in the order of ignition of the chambers. In the following of the present invention, the operation of a combustion module 10 comprising at least one group of three chambers 12A, 12B, and 12C intended to be subjected to successive combustions will be described, it being understood that the combustion module 10 may comprise a greater number of chambers 12.
    [0010] According to the invention, the module 10 comprises a shutter 30, 82 which constitutes an opening / closing means of the conduit 80 capable of selectively allowing the passage of the flue gases from the first combustion chamber 12A to said second chamber 12B combustion.
    [0011] According to a first embodiment of the invention which has been represented in FIGS. 6 and 7, each duct 80 is a fixed duct which connects a wall 84A, 84B, 84C to a wall 86A, 86B, 86C of two successive chambers the chambers 12A, 12B, 12C and which may be opened or closed by a shutter 82.
    [0012] The shutter 82 constituting the opening means of each duct 80 may take any form known from the state of the art. For example, the shutter 82 could include a solenoid valve. However, for the sake of simplification, the shutter 82 comprises at least one valve means 84 pressure calibrated, which is located in the conduit 80, and which is able to open 15 when the pressure of the burnt gases in the first chamber 12A, 12B, 12C exceeds a determined threshold. As soon as this threshold is crossed, the valve means 84 opens, and allows the supply of the next chamber. Thus, the chamber 12A supplies burnt gas to the chamber 12B, which then supplies the chamber 12C with burnt gas, which then supplies the chamber 12A with burnt gases, and then this cycle is repeated. This configuration is particularly suitable for a module 10 comprising at least one group of combustion chambers 12A, 12B, 12C angularly arranged regularly around the axis A, the ignition sequence being repeatable cyclically. Each group of chambers 12A, 12B, 12C comprises at least one clean ignition circuit 90, consisting of ducts 80 and shutters 82, said communication ducts 80 being each arranged between two chambers of the same group of chambers 12A, 12B, 12C. Figure 8 and Figure 9 schematically illustrate the simplest of configurations of this type of ignition system.
    [0013] In this configuration, the module 10 comprises a single group G1 of combustion chambers 12A, 12B, 12C angularly arranged in a regular way of the axis, which comprises its own ignition circuit 90 which comprises its communication conduits 80 which are each arranged between the successive chambers 12A, 12B, 12C of said group in the direction of ignition which has been represented by the arrows of FIG. 8. The conduits 80 are capable of injecting flue gas from a first of the two chambers 12A, 12B, 12C in the second of the two successive chambers 12B, 12C, 12A to initiate combustion in said second combustion chamber 12B, 12C, 12A. This configuration assumes, in order to function properly continuously, that the combustion is initiated correctly in each chamber 12A, 12B, 12C by an injection of burnt gases from the previous chamber 12C, 12A, 12B in the firing order. However, if combustion is not initiated, the cycle is interrupted and must be restarted by conventional ignition means such as a spark plug. FIG. 10 illustrates a first variant of this configuration according to which the module comprises two groups G1 and G2 of combustion chambers 12A, 12B, 12C and 12D, 12E, 12F respectively arranged angularly in regular manner about the axis A, each group G1 and G2 comprising at least one clean ignition circuit 901 and 902 respectively which comprises communication ducts 801 and 802 which are each arranged between two chambers of said group G1 and G2 and which are capable of injecting flue gases with a gas. first of two chambers of the same group G1 or G2 in the second of two chambers of the same group G1 or G2. In this way, if one of the groups G1 or G2 is extinguished, the other group continues to operate, which avoids stopping, or at least a degraded operation, of the associated turbine engine . It is possible to provide a conventional ignition means such as a spark plug 3032024 16 on one of the chambers of each group G1 or G2, in order to be able to restart a group G1 or G2 in case of extinction. In FIG. 10, the combustion module 10 which has been shown has two groups G1 and G2, but it will be understood that the combustion module 10 could have a larger number of groups. Note that the chamber groups 12A, 12B, 12C and 12D, 12E, 12F can be angularly offset, as shown schematically in Figure 9, but it will be understood that they could also be axially offset along the axis A.
    [0014] FIG. 11 illustrates a second variant of the combustion module 10 according to which the module 10 similarly has two groups G1 and G2 of combustion chambers 12A, 12B, 12C and 12D, 12E, 12F respectively angularly arranged in a regular manner around the preceding case. of the axis A, each group G1 and G2 having at least one respective own ignition circuit 901 and 902 which comprises communication ducts 801 and 802 which are each arranged between two chambers of said group G1 and G2 and which are fit injecting burnt gases from a first of the two chambers of the same group G1 or G2 into the second of the two chambers of the same group G1 or G2. The module 10 comprises at least one additional ignition circuit 903, which is interposed between two groups G1 and G2 and which comprises additional communication conduits 803 which are each arranged between a first chamber 12A, 12B, 12C of a group G1 and a second chamber 12D, 12E, 12F of the other group G2 and which are capable of injecting flue gas from the first chamber 12A, 12B, 12C of the first group G1 into the second chamber 12D, 12E, 12F of the second group G2 in order to trigger a combustion in said second combustion chamber 12D, 12E, 12F of said second group G2, in order to maintain the ignition of the chambers of the two groups G1 and G2 in case of failure of a clean ignition circuit 30 .
    [0015] It will be understood that this configuration is preferably reciprocal, and that each chamber can make it possible to light two chambers and to be turned on by two other chambers. Thus, each chamber 12A, 12B, 12C illuminates a chamber 12B, 12C, 12A of the same group G1 and a chamber 12D, 12E, 12F of the other group G2, while each chamber 12D, 12E, 12F ignites a chamber 12E , 12F, 12D of the same group G2 and a chamber 12A, 12B, 12C of the other group G2. In this configuration, the risks of extinction are reduced. The extinction probability in its entirety of a combustion module having N groups is pN, where p is the extinction probability of a chamber. According to a second embodiment of the invention which has been shown in FIGS. 12 to 15B, it is possible to take advantage of a particular configuration of the intake and exhaust valves 30 to obtain the duct 80. FIG. 1 illustrates the principle of a combustion module 10 comprising such intake valves 28 and exhaust valves 30. Preferably, each combustion chamber 12 comprises at least one wall 32, 34 in section. The chambers 12 comprise at least a first longitudinal wall 32 in cylinder section, facing the axis A, that is to say an inner wall 32, which comprises the two ports of the cylinder. intake 16 and exhaust 18, and incidentally a second longitudinal wall 34, 25 facing away from the axis A, that is to say an outer wall 34, which is devoid of intake ports or exhaust. Each port 16, 18 has a radial opening 36, 38 which is formed in the inner wall 32 in the cylinder section of the combustion chamber coaxial with the axis A. Each rotary intake valve 28/30 exhaust 30 comprises a tubular element 40, 42 corresponding, of diameter corresponding to said cylinder section, and rotatably mounted internally 3032024 18 said cylinder section. This tubular element 40, 42 constitutes, opposite the combustion chamber 12, an intake / exhaust gas conduit 44, 46 formed in an internal bore of the tubular element 40, 42, and comprises at least one radial slot 50, 52 arranged substantially in an axial plane of the radial opening 36, 38 of said port 16, 18, which is adapted to close or release said radial opening 36, 38 during the rotation of said tubular member 40 , 42. The intake gas flow and the exhaust gas evacuation were represented by the arrow in Figure 1.
    [0016] The tubular elements 40, 42 are synchronized in rotation in a very simple manner. Advantageously, the combustion module 10 comprises a common rotary element 66 which comprises the rotary intake and exhaust valves 30 and which is driven for example by a single drive means. This configuration therefore makes it possible to achieve, in a very simple manner, the synchronization of the intake and exhaust valves 30. Separate drive means may be provided, for example by being synchronized with each other. The driving of this rotary element 66 can be achieved in different ways. For example, the rotatable member 66 may be driven by a motor 68, and by a bevel gear gear coupling 70, as shown in FIG. 1, but more simply, the rotatable member 66 can be coupled to a shaft system of the associated turbomachine via a suitable reduction. Such a shaft system 72, connecting the compressor module 20 to the turbine module 24, has been shown by way of example in FIG. 6. It will be noted that this configuration allows a simplified feed of the module intake gas. 10 combustion and exhaust also simplified burned gases in said combustion module 10. The compressor module 22 supplies the combustion module 10 with intake gas via a single intake duct opening into the bore 44 of the rotary element 66 and the combustion module 10 supplies the combustion element 10. the exhaust gas turbine module 24 via a single exhaust duct fed by the bore 46 of the rotary element 66. In this principle, the invention proposes, in this second embodiment embodiment, to realize the duct directly in the rotary element 66. For this purpose, at least one of the rotary valves 28, 30 comprises on its periphery a groove portion 92 which extends over a given angular sector of the periphery of the rotary valve 28, 30 for determining a leakage duct which is intended to put in communication a first 10 of the combustion chambers 12A and a second of the combustion chambers 12B adjacent to said first chamber, in a position of said valve ro tative corresponding to an end of combustion in the first chamber 12A prior to a discharge of burnt gases and a filling end of the second chamber 12B prior to combustion. FIG. 12 thus represents the groove section 92 which has been formed on an angular sector of the exhaust valve 30, said angular sector being arranged at the periphery of the tubular element 42 in the same axial plane as the light of the exhaust 52.
    [0017] In this case, it is therefore the valve 30 of the rotary element 66 which itself forms the shutter according to its angular position relative to the chambers 12A, 12B, 12C. It will be understood that this provision is not limiting of the invention and that the throat section 92 could be formed in the periphery of the tubular element 40 of the inlet valve 28. The throat section 92 has an angular opening greater than the gap between the radial openings 38 of the two chambers 12A, 12B. For example, in FIGS. 13A to 15B, the angular difference between two successive chambers 12A, 12B is 60 °, and it will be understood that the throat section 30 has an opening greater than 60 °.
    [0018] The groove section 92 may be partially covered to protect the cavity in which the rotary element 66 is housed. This makes it possible, for example, to avoid degrading the sealing system of the rotary element 66, constituted for example by abradable materials during the circulation of the hot gas in the groove 92. In this way, the throat section 92 constitutes some of the delimiting walls of the duct 80 between the two chambers 12A, 12B only according to certain angular positions of the element As illustrated in FIGS. 13A to 15B, each combustion chamber 12A, 12B, 12C operates in a cycle having a first phase during which the intake port 16 and the exhaust port 18 are closed. This first phase comprises a first sub-phase of confinement of a fresh fuel mixture and then a second sub-phase of combustion of said fuel mixture. Then, the cycle 15 comprises a second phase during which the intake port 16 is closed and the exhaust port 18 is open, to cause the escape of the flue gases. Then the cycle comprises a third phase during which the intake ports 16 and intake 18 and exhaust ports are open, to ensure the flue gas is scanned with fresh gases. The relative angular position of the radial slots 50, 52 of the element determines the execution of the method according to which the admission and the exhaust of the first chamber 12A and second chamber 12B, and subsequent chambers in the order of ignition, are out of phase so that the first chamber 12A can be subjected to the second sub-phase when the second chamber 12B is subjected to the first sub-phase. Furthermore, the angular position of the throat section 92 determines a control substep, occurring when the first chamber 30 is subjected to the second sub-phase, during which the first chamber 12A is placed in communication with the second chamber 12B for 3032024 21 start the combustion in the second chamber 12B. In this case, the groove section 92 determines in this angular position of the tubular element 42 a leakage duct 80 between the chambers 12A and 12B, which makes it possible to convey part of the burnt gases from the chamber 12A to the chamber 12B. to trigger combustion in chamber 12B. In the position of FIGS. 13A and 13B, the chamber 12C is at the end of the second combustion sub-phase, the chamber 12A at the beginning of the second combustion sub-phase, and the chamber 12B is in the third scanning phase of the burnt gas.
    [0019] In the position of FIGS. 14A and 14B, the chamber 12C is in the second exhaust phase, the chamber 12A is in the second combustion sub-phase, and the chamber 12B is at the end of the third exhaust gas scavenging phase. . In the position of FIGS. 15A and 15B, the chamber 12C is in the third scavenging phase of the burned gases, the chamber 12A is at the end of the second combustion sub-phase, and the chamber 12B is in the first sub-phase of combustion. combustion. In this position, the throat section 92 defines a leakage duct 80 between the chamber 12A and the chamber 12B. The burning gases travel through the leakage duct 80 and allow the mixture to ignite in the chamber 12B. The invention thus makes it possible to simply and reliably carry out the ignition control of the chambers 12 of a constant volume type combustion module 10 with radiating combustion chambers.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Turbomachine combustion module (10), in particular an aircraft turbomachine, configured for the implementation of a constant volume combustion, comprising at least two combustion chambers (12A, 12B), each chamber (12A, 12B, 12C) comprising an intake port (16) of compressed gas and an exhaust port (18) of burnt gases, and ignition means initiating combustion in the combustion chambers (12A, 12B, 12C), characterized in that, the chambers (12A, 12B, 12C) being arranged around an axis (A), the module (10) comprises at least one duct (80) able to put in communication a first of the combustion chambers (12A ) with at least one second of the combustion chambers (12B) for injecting flue gases from the first combustion chamber (12A) into said second combustion chamber (12B) to initiate combustion in said second combustion chamber (12B) ).
    [0002]
    2. Module (10) of combustion according to the preceding claim, characterized in that it comprises a shutter 30, 82) for opening / closing the conduit (80) adapted to selectively allow the passage of the flue gases of the first combustion chamber (12A) towards said second combustion chamber (12B).
    [0003]
    3. Module (10) of combustion according to the preceding claim, characterized in that the duct (80) is a fixed duct and in that the shutter (82) comprises at least one valve means (84) pressure calibrated which is located in the duct (80) and is able to open when the pressure of the flue gases in the first chamber (12A) exceeds a predetermined threshold.
    [0004]
    4. Module (10) of combustion according to one of claims 1 to 3, characterized in that it comprises at least one group (G1, G2) of combustion chambers (12A, 12B, 12C) arranged angularly in a regular manner about said axis (A), said group (G1, G2) having at least one own ignition circuit (90, 901, 902) which comprises communication conduits (80, 801, 802) which are each arranged between two chambers (12A, 12B, 12C, 12D, 12E, 12F) of said group (G1, G2) and which are capable of injecting flue gas from a first of the two chambers 5 second combustion chamber.
    [0005]
    5. Module (10) of combustion according to one of claims 1 to 3, characterized in that it comprises at least two groups (G1, G2) of combustion chambers (12A, 12B, 12C, 12D, 12E, 12F ) angularly arranged regularly about said axis (A), each group (G1, G2) having at least one clean ignition circuit (90, 901, 902) which comprises communication ducts (80, 801, 802) which are each arranged between two chambers of said group (G1, G2) and which are capable of injecting flue gases from a first of the two chambers (12A, 12B, 12C, 12D, 12E, 12F) into the second of the two chambers (12A, 12B, 12C, 12D, 12E, 12F) to initiate combustion in said second combustion chamber of said group (G1, G2), and at least one additional ignition circuit (903), which is interposed between two groups (G1, G2) and which has additional communication conduits (803) which are each arranged between a first chamber (12A, 12B, 12C) a group (G1) and a second chamber (12D, 12E, 12F) of the other group (G2) and which are capable of injecting flue gas from the first chamber (12A, 12B, 12C) of the first group ( G1) in the second chamber (12D, 12E, 12F) of the second group (G2) to initiate combustion in said second combustion chamber (12D, 12E, 12F) of said second group (G2), in order to maintain the lighting the chambers (12A, 12B, 12C, 12D, 12E, 12F) of the two groups (G1, G2) in the event of a failure of a clean ignition circuit (901, 902).
    [0006]
    The combustion module (10) according to claim 1 or 2, characterized in that the intake (16) / exhaust (18) ports of the combustion chambers (12A, 12B, 12C) are configured to be open or (12A, 12B, 12C, 12D, 12E, 12F) in the second of the two chambers (12A, 12B, 12C, 12D, 12E, 12F) to initiate combustion in said closed 3032024 by common valves of intake (28) / exhaust (30) respectively synchronized and rotatably mounted about said axis (A), said valves (28, 30) cooperating with a radial opening (36, 38) which is formed in a shaped wall (32) in a cylinder section of the combustion chamber (12) facing towards the axis (A), each corresponding rotary intake valve (28) or exhaust valve (30) comprising a tubular element (40, 42), diameter corresponding to said cylinder section mounted to rotate coaxially with said cylinder section, said tubular element (40, 42) comprising a the bore (44, 46) for conveying the intake / exhaust gases, and at least one radial slot (50, 52) arranged substantially in an axial plane of the radial opening (36, 38) of said port (16, 18), and which is adapted to close or release said radial opening (36, 38) during the rotation of said tubular element (40, 42) and in that at least one of the rotary valves (30) 15 comprises on at its periphery a throat section (92) which extends over a given angular sector of the periphery of the rotary valve (30) to determine a leakage duct (80) which is intended to put in communication a first of the combustion chambers (12A, 12B, 12C) and a second one of the combustion chambers (12B, 12C, 12A) adjacent said first chamber (12A, 12B, 12C), in an angular position of said rotary valve (30) corresponding to an end in the first chamber (12A; 12B, 12C) prior to evacuation of the flue gases and a filling end of the second chamber -12B, 12C, 12A) prior to combustion, the rotary valve (30) forming the shutter according to its angular position
    [0007]
    7. Module (10) of combustion according to the preceding claim, characterized in that the throat section (92) is formed in the periphery of the tubular element (42) of the rotary exhaust valve (30).
    [0008]
    Combustion module (10) according to claim 6 or 7, characterized in that it comprises a common rotary element (66) which comprises the rotary intake (28) / exhaust valves (30). mutually related to rotation.
    [0009]
    9. A turbomachine (10) comprising a compressor module (20) comprising at least one compressor (22), a combustion module (10) according to one of claims 1 to 8, and a turbine module (24) comprising at least one turbine (26), the compressor module (20) being connected to the turbine module (24) by a shaft system (72), characterized in that the compressor module (20) supplies the combustion module (10) via a single inlet duct and in that the combustion module (10) feeds the turbine module (24) through a single exhaust duct.
    [0010]
    10. A turbomachine (10) according to the preceding claim, the combustion module being as defined in claim 8, characterized in that at least one shaft of the shafts system (72) forms a drive means 15. common rotary member (66) linking the rotatable inlet / outlet exhaust valves (30).
    [0011]
    11. A method of controlling a combustion engine of a turbomachine according to one of claims 9 or 10, comprising at least one step of successive ignition of at least a first and a second chamber 20 (12A, 12B). each of which operates successively in a cycle comprising: a first phase during which the intake and exhaust ports are closed, comprising a first sub-phase of confinement of a fresh fuel mixture and then a second combustion sub-phase of said fuel mixture in each corresponding chamber (12A, 12B); - a second phase during which the intake port (16) is closed and the exhaust port (18) is open; to cause the escape of the flue gases from each corresponding chamber (12A, 12B) 30, then 3032024 26 - a third phase during which the intake ports (16, 18) and exhaust ports are open, to cause the flue gas scavenging with g a fresh charge through each corresponding chamber (12A, 12B), in which, during the successive ignition step, the intake and exhaust of the first chamber (12A) and the second chamber (12B) are expanded so that the first chamber (12A) can be subjected to the second sub-phase when the second chamber (12B) is subjected to the first sub-phase, and wherein the successive ignition step comprises a sub-step control, occurring when the first chamber (12A) is subjected to the second sub-phase, during which the first chamber (12A) and the second chamber (12B) are communicated to trigger combustion in the second chamber ( 12B). 15
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    同族专利:
    公开号 | 公开日
    US20180010517A1|2018-01-11|
    BR112017015622A2|2018-03-13|
    CA2974296A1|2016-08-04|
    RU2720868C2|2020-05-13|
    RU2017127534A|2019-02-28|
    CN107250510B|2020-04-10|
    CN107250510A|2017-10-13|
    FR3032024B1|2018-05-18|
    WO2016120555A1|2016-08-04|
    US11066990B2|2021-07-20|
    RU2017127534A3|2019-08-13|
    EP3250859A1|2017-12-06|
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    法律状态:
    2016-01-22| PLFP| Fee payment|Year of fee payment: 2 |
    2016-07-29| PLSC| Publication of the preliminary search report|Effective date: 20160729 |
    2017-01-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-12-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1550587A|FR3032024B1|2015-01-26|2015-01-26|COMBUSTION MODULE WITH CONSTANT VOLUME FOR TURBOMACHINE COMPRISING COMMUNICATION IGNITION|
    FR1550587|2015-01-26|FR1550587A| FR3032024B1|2015-01-26|2015-01-26|COMBUSTION MODULE WITH CONSTANT VOLUME FOR TURBOMACHINE COMPRISING COMMUNICATION IGNITION|
    PCT/FR2016/050151| WO2016120555A1|2015-01-26|2016-01-26|Constant-volume combustion module for a turbine engine, comprising communication-based ignition|
    US15/545,287| US11066990B2|2015-01-26|2016-01-26|Constant-volume combustion module for a turbine engine, comprising communication-based ignition|
    EP16705236.4A| EP3250859A1|2015-01-26|2016-01-26|Constant-volume combustion module for a turbine engine, comprising communication-based ignition|
    CN201680009561.5A| CN107250510B|2015-01-26|2016-01-26|Constant volume combustion module for a turbine engine including a communication-based ignition device|
    BR112017015622-9A| BR112017015622A2|2015-01-26|2016-01-26|constant volume combustion module for a turbocharger comprising a communication ignition|
    CA2974296A| CA2974296A1|2015-01-26|2016-01-26|Constant-volume combustion module for a turbine engine, comprising communication-based ignition|
    RU2017127534A| RU2720868C2|2015-01-26|2016-01-26|Constant volume combustion module for a gas turbine engine comprising an ignition system by means of a communication line|
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