• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a turbomachine combustion module (10), in particular an aircraft, configured for the implementation of constant volume combustion, comprising at least one combustion chamber (12) arranged around an axis ( A), the or each chamber (12) comprising a compressed gas inlet port (16) and a burned gas exhaust port (18), characterized in that each intake port (16) / d ' exhaust (18) is configured to be opened or closed by a corresponding intake rotary valve (28) / exhaust valve (30) coaxial with said axis (A). The invention also relates to a turbomachine comprising a combustion module (10) of the type previously described.
    公开号:FR3032025A1
    申请号:FR1550588
    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] 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 In known manner, the combustion chamber of a conventional aircraft turbine engine operates according to a so-called Brayton cycle, that is to say a constant pressure combustion cycle. Nevertheless, to obtain specific consumption gains, it has been envisaged to replace the combustion chamber operating on a Brayton cycle with a combustion chamber operating on a Humphrey cycle, that is to say a combustion cycle with constant volume 20 or "CVC". Document FR 2 945 316 describes an exemplary embodiment of such an HVAC combustion chamber. The chamber comprises at the inlet a compressed gas inlet valve composed of two rotary elements of substantially ovoid cross section which are rotatably mounted along axes 25 parallel to each other and perpendicular to the axis of the chamber, said elements being capable of determine when they are disjointed an open position of the valve and when they are joined a closed position of the valve. The chamber likewise has at its exit a similar exhaust valve capable of oscillating between an open position and a closed position. The positions of the valves are controlled in a synchronized manner in order to implement the three successive phases of the Humphrey cycle, namely admission / scavenging - exhaust combustion. In this solution, the design of the intake and exhaust valves is perfectible, particularly in terms of robustness and sealing, the latter can be problematic especially during the high pressure observed during the phase of combustion, because of the perfectible sealing of the ovoid section elements. To remedy this drawback, it has been proposed in document WO-2014/020275-A1 an HVAC combustion chamber comprising spherical valves comprising spherical rotors rotatably mounted about axes perpendicular to the axis of the chamber and combined with spherical shells of these rotors, said rotors and said shells having alignable channels and lumens with each other and with combustion chamber exit inlet channels for selectively determining the opening or closing of corresponding intake and exhaust valves. 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.
    [0002] In this solution, the design of the intake and exhaust valves is greatly improved, particularly in terms of sealing, but nevertheless has many disadvantages. 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 improved. Fourth and last, each chamber requires an intake valve and an exhaust valve which are its own, so that a turbomachine comprising several chambers 3032025 3 comprises as many intake valves and exhaust valves as of rooms.
    [0003] DISCLOSURE OF THE INVENTION The object of the invention is therefore to overcome the disadvantages mentioned above, relating to the embodiments of the prior art. For this purpose, the invention generally proposes a combustion chamber of constant volume combustion type aircraft turbomachine, preferably comprising chambers distributed in a radiating structure, in particular in a barrel, and operating in out-of-phase cycles. to ensure a homogeneous supply of at least one turbomachine turbine arranged downstream of the chambers. In addition to this architecture, the invention generally provides an intake valve common to all chambers and an exhaust valve common to all chambers. To this end, the invention proposes a turbomachine combustion module, in particular an aircraft, configured for the implementation of constant volume combustion, comprising at least one combustion chamber arranged around an axis, such as an axis of the turbomachine, the or each chamber comprising a compressed gas inlet port and a burned gas exhaust port, characterized in that each intake / exhaust port is configured to be open or closed by a corresponding intake / exhaust rotary valve coaxial with said axis. According to other features of the module: the module comprises a plurality of combustion chambers angularly distributed regularly around said axis, the intake ports of which are configured to be opened or closed by a common rotary admission valve and whose exhaust ports are 3032025 4 configured to be opened or closed by a common rotary exhaust valve, - the rotary intake / exhaust valves are synchronized in rotation with each other, - each port has a radial opening which is formed in a longitudinal wall of the combustion chamber coaxial with the axis, and each rotary intake / exhaust valve has a tubular member for each port of intake / exhaust of the chamber, mounted to rotate coaxially with said axis and comprising at least one radial slot, arranged substantially in an axial plane of the radial opening of said port, which is adapted to closing or releasing said radial opening during the rotation of said tubular element; the longitudinal wall of the combustion chamber is turned towards the axis, and the tubular element of each valve is rotatably mounted internally to said wall, said tubular element comprising an internal bore delimiting an intake / exhaust gas duct allowing the intake / exhaust gases to be conveyed; the or each combustion chamber comprises two opposite outer and inner walls respectively shaped into sections of cylinders; and each having one of said ports having a radial opening formed in said inner or outer wall, and said module comprises an outer / inner tubular rotary valve associated with each outer / inner wall of the combustion chamber, which comprises a tubular member of diameter corresponding to said outer or inner wall and my rotating coaxially with said corresponding cylinder section, said tubular element having a lumen, arranged substantially in an axial plane of the radial opening of said port, which is adapted to seal or release said radial opening upon rotation of said tubular member; the or each combustion chamber is arranged coaxially around the end of a tubular inner casing element comprising a duct of annular section, the duct having an end opening into the periphery of said tubular inner element, which is arranged facing the opening of the inner wall of the chamber, the internal rotary valve being interposed radially between said tubular inner housing element and the inner wall of the combustion chamber; the combustion chamber is arranged coaxially inside the combustion chamber; a tubular outer casing element comprising an annular duct, the rotary valve e external being arranged around the outer wall of the 10 or each combustion chamber in said annular duct of the tubular outer casing element, the intake port is associated with the outer wall of the or each combustion chamber, the intake gases being conveyed by the annular duct of the tubular outer casing element, and the exhaust port is associated with the inner wall of the or each combustion chamber, the intake gases being evacuated by the conduit of the tubular inner casing element, - the combustion module comprises a common shutter element which comprises the rotating inlet / exhaust valves 20 mutually connected to rotation. The invention also relates to a turbomachine comprising a compressor module, comprising at least one compressor, and a turbine module, comprising at least one turbine, said turbomachine comprising a combustion module of the type described above which is powered by the module. compressor and which feeds the turbine module. For example, in a particularly advantageous and simple embodiment, the turbomachine comprises a tree system that links the compressor module. The compressor module supplies the combustion module via a single intake duct, which combustion module supplies the turbine module through a single exhaust duct, and at least a tree of the tree system forms the drive means of the common shutter element. As a variant, in another particularly advantageous embodiment, since it allows a great possibility of combustion control optimization, said turbomachine comprises a combustion module which is fed by the compressor module and which supplies the turbine module, and which comprises an intake valve and an exhaust valve which can be actively shifted according to the different operating phases of the turbomachine. Thus, the valves may be driven by common drive means and engaged to each other, or selectively disengaged or out of phase, but may also be driven independently of one another while being selectively synchronized, out of sync or out of phase with each other. The invention will be better understood and other details, characteristics and advantages of the present invention will appear 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 of a first embodiment of a combustion module according to the invention; FIG. 2 is a diagrammatic view in axial section of the combustion module of FIG. 1; FIG. 3 is a diagrammatic cross-sectional view of the combustion module of FIG. 2; FIG. 4 is a perspective view of a second embodiment of a combustion module according to the invention; FIG. 5 is a diagrammatic cross-sectional view of the combustion module of FIG. 4; FIG. 6 is a cutaway perspective view of a turbomachine comprising a combustion module according to a third embodiment; FIG. 7 is a diagrammatic view in axial section of the turbomachine of FIG. 6; FIG. 8 is a cross-sectional view of a fourth embodiment of a combustion module according to the invention; - Figure 9 is an axial sectional view of the combustion module of Figure 8 and a casing of an associated turbine engine; FIGS. 10 to 14 are schematic views of different turbine engine architectures employing a combustion module according to the invention. In the following description, like reference numerals designate like or similar parts. FIGS. 1 to 5 and FIG. 8 show a combustion module 10 produced in accordance with the invention. In a known manner, the module 10 is configured to implement a constant-volume combustion taking place according to the Humphrey cycle, that is to say having a combustion time, an exhaust time, and a combustion time. fresh air intake and flue gas scavenging. In known manner the module 10 comprises at least one combustion chamber 12 arranged around an axis "A". Such a configuration has been shown in FIG. 6, which shows a turbomachine 14 comprising ten combustion chambers 12 arranged around the "A" axis of the turbomachine. In a nonlimiting manner of the invention, the axis "A" may for example coincide with an axis of rotation of the turbomachine. As illustrated in FIGS. 1 and 2, each chamber 12 comprises a compressed gas inlet port 16 and an exhaust port 18 for the flue gases. In a turbomachine of the type of that shown in FIGS. 6 and 7, 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 exhaust gas feeds at least one turbine module 24 comprising at least one turbine 26. According to the invention, each intake port 16 or exhaust port 18 is configured to be opened or closed by a valve rotary admission 28 or by a corresponding exhaust valve 30, coaxial with the axis A of the turbomachine 14. In its simplest configuration which has been shown in Figures 1 to 3, the module 10 has only one chamber 12 of combustion. This configuration corresponds to a first embodiment of the module 10. However, in the preferred embodiment of the invention, the module 10 comprises 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 common intake rotary valve 28 and whose exhaust ports 18 are configured to be opened or closed by a common exhaust rotary valve 30. Inlet valve 28 and exhaust valve 30 may rotate together or may be rotatable parts.
    [0004] FIG. 5 shows, by way of example, a second embodiment of the module 10 comprising a common intake rotary valve 28 which supplies the three intake ports 16 with three combustion chambers 12 of the same type. Likewise, in FIG. 6 there is shown the example of a third embodiment of the module 10 comprising a common rotary valve 28 for supplying the intake ports with ten combustion chambers 12. a same module 10 and an exhaust rotary valve 30 which is fed by the ten exhaust ports of the ten combustion chambers 12 of said module 10.
    [0005] This configuration is particularly advantageous since it makes it possible to feed several chambers 12 with a single inlet valve 28 and to discharge the gases with a single exhaust valve 30, which considerably simplifies the flow of gas. architecture of a turbomachine comprising such a combustion module 10 with respect to the previously known prior art designs The combustion chambers 12 are angularly distributed regularly around the axis A, and each has a direction preferably oriented in a substantially axial direction, so as to form a barrel-shaped structure, however, this configuration is not limiting of the invention, and the chambers could be arranged in another orientation, for example substantially radial. Thus it will be understood that a main feature of the invention is that the chambers 12 can be arranged in a manner Also preferably, the combustion cycles of the chambers 12 are shifted by 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 to constant volume combustion cycles. Indeed, if all the chambers 12 were operating simultaneously at the same times in the Humphrey cycle, the exhaust phases would all be simultaneous and the result would be an irregular exhaust gas flow, because subjected to the simultaneous pulsation of the gases from On the contrary, a combustion module 10 comprising offset chamber cycles 12 smooths these pulsations. Note that the exhaust gas inlet of the turbine module 24 will be 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 see the cycles of its shifted chambers. For a number of "n" chambers, it will be necessary to operate a number of chambers less than the "n / 2" half of the "n" number of chambers at the same time to balance the loads on the rotating valves. In particular, two opposite chambers will be on the same cycle phase considering for example for four rooms at a given time two rooms in combustion and two rooms without combustion.
    [0006] In the preferred embodiment of the invention, the rotary intake and exhaust valves 30 are synchronized in rotation with each other, rotating at the same rotational speed. This synchronization can be achieved by any means known from the state of the art, especially mechanically.
    [0007] We will now describe a preferred embodiment of the chambers 12 and valves 28, 30. Preferably of the invention, each combustion chamber 12 comprises at least one wall 32, 34 in a coaxial cylinder section to the axis.
    [0008] In the first to third embodiments of the invention, the chambers 12 comprise a first longitudinal wall 32 in cylinder section, facing the axis A, ie an inner wall 32, which comprises the two ports. intake 16 and exhaust 18, and incidentally a second longitudinal wall 34, turned away from the axis A, that is to say an outer wall, which is devoid of intake ports or exhaust. In the fourth embodiment which has been shown in FIGS. 8 and 9, each combustion chamber 12 also comprises, extending longitudinally, a first wall 32 in cylinder section, coaxial with the axis A and turned to the opposite said axis A, that is to say an outer wall, which has the intake port 16 and a second wall 34 in longitudinally extending cylinder section, coaxial with the axis A and turned towards the axis A, that is to say an inner wall, which has the exhaust port 18.
    [0009] It will be understood that other configurations are possible without changing the nature of the invention, for example a configuration according to which the intake and exhaust ports 18 and 18 would be arranged on a wall coaxial with the axis A. and facing away from said axis A, or a substantially opposite configuration of the fourth embodiment. Each port 16, 18 comprises, in the configuration chosen, a radial opening 36, 38 which is formed in the corresponding longitudinal wall 32, 34 of the combustion chamber coaxial with the axis A. Each rotary admission valve 28 / exhaust pipe 30 comprises a corresponding tubular element 40, 42, of diameter corresponding to said cylinder section, and mounted to rotate coaxially with said cylinder section. This tubular element 40, 42 constitutes, opposite the combustion chamber 12, an intake / exhaust gas conduit 44, 46, and it comprises at least one radial slot 50, 52, arranged substantially in a axial plane of the radial opening 36, 38 of said port 16, 18, which is able to close or release said radial opening 36, 38 during rotation 15 of said tubular element 40, 42. Thus, in the first to third embodiments which have been shown in Figures 1 to 7, the wall 32 in cylinder section of the combustion chamber 12 is facing the axis A, and the tubular member 40, 42 of each valve 28, 30 is mounted internally rotating auditing 20 cylinder section. Each tubular element 40 or 42 has an internal bore 44, 46 defining the intake / exhaust gas duct, which is therefore formed in the tubular element 40, 42, and which allows the delivery of the inlet gases. and evacuation of exhaust gases in the direction of flow of these gases, as shown by the arrow of FIG. 1. In the fourth embodiment which has been shown in FIGS. 8 and 9, each chamber the combustion chamber 12 has two opposite outer walls 32 and 34, respectively, which are in the form of cylinder sections and each of which has a port 16, 18 having a radial opening 36, 38 formed in said outer wall 32 or inner wall 34. combustion 10 comprises an outer tubular rotary valve 28 and an inner tubular rotary valve 30, associated with each outer wall 32 and outer 34 of the combustion chamber 12, which comprises each of them has a respective tubular element 40, 42 of diameter corresponding to said outer or inner wall and which is mounted to rotate coaxially with said corresponding cylinder section. Each tubular element 40, 42 comprises at least one lumen 50, 52 arranged substantially in an axial plane of the radial opening 36, 38 of the port 16, 18, which is capable of closing or releasing said radial opening 36, 38 during the rotation of said tubular element 40, 42.
    [0010] Thus, the main difference between, on the one hand, the first to third embodiments of the invention, and the fourth mode on the other hand, is that in the first to third embodiments of the invention the elements tubular elements 40, 42 constituting the valves 28, 30 are coaxial and axially offset, whereas in the third embodiment of the invention the tubular elements 40, 42 constituting the valves 28, 30 are coaxial and offset radially, it is to say concentric. As illustrated in FIG. 9, in the fourth embodiment of the invention, each combustion chamber 12 is arranged coaxially around the end 54 of a tubular inner casing element 56 comprising a channel 58 of annular section. . The duct 58 has an end 60, which opens into the periphery of said tubular inner member 56, which is arranged facing the opening 38 of the inner wall 34 of the chamber 12, and the internal rotary valve 30 is radially interposed between said inner tubular housing member 56 and the inner wall 34 of the combustion chamber 12. Similarly, the combustion chamber 12 is arranged coaxially within a tubular outer casing member 62 having an annular duct 64, and the outer rotary valve 28 is arranged around the outer wall 32 of the chambers. 12 of combustion 3032025 13 inside said annular duct 64 of the tubular outer casing element 62. Preferably, in this fourth embodiment of the invention, the intake port 16 is associated with the outer wall 32 of the combustion chambers 12, the inlet gases then being conveyed by the annular conduit 64 of the outer casing 62, and correspondingly the exhaust port 30 is associated with the inner wall 34 of the combustion chambers 12, the inlet gases being then discharged through the conduit 58 of the inner tubular element 56 of casing.
    [0011] It will be understood that this configuration is not limiting of the invention and could be reversed. Furthermore, for example, the inlet and the exhaust could be axially offset, with a longer length of the combustion chamber. A particularly advantageous feature of the invention is that the combustion module 10 may comprise a common shutter element 66 which includes the rotary intake and exhaust valves 30 and which is driven for example by a single drive means , the valves being thus mutually connected to rotation. This configuration makes it possible in a very simple manner to synchronize the intake and exhaust valves 30. The drive of this shutter element 66 can be made in different ways. For example, the shutter member 66 may be driven by a motor 68 and a bevel gear coupling 70, as shown in FIG. 1, but more simply, the shutter member 66 may be coupled to a system. of trees of the associated turbomachine via a suitable reduction. Alternatively, the intake valves 28 and exhaust 30 can naturally be driven by separate drive means, for example synchronized.
    [0012] The invention therefore naturally applies to a turbomachine used in aeronautical propulsion, comprising a compressor module 20 comprising at least one compressor 22 and a turbine module 24 comprising at least one turbine 26. Such a turbomachine comprises a combustion module 10 of the type described above, supplied by the compressor module 20 and supplying the turbine module 24. An example of such a turbomachine 14, as shown in FIGS. 6 and 7, comprises, for example, as previously seen, a compressor module 20 comprising at least one compressor 22, a combustion module 10 of the type described above, and a turbine module 24 comprising at least one turbine 26. In this configuration, the module 22 is connected to the turbine module 24 by a system of shafts 72. In this configuration, as represented in FIGS. 6 and 7, the module compressor 22 supplies the combustion module 10 with, for example, a single intake duct 15, the combustion module 10 supplies the turbine module 24 with exhaust gas through the engine. An example of a single exhaust duct 58, and at least one shaft of the shaft system 22, forms the drive means of the common shutter element 66. Alternatively, in another particularly advantageous embodiment that has a great possibility of combustion control optimization, said turbomachine could comprise a combustion module comprising an intake valve and an exhaust valve 10 which could be actively shifted according to the different phases of operation of the turbine engine.
    [0013] Thus, the valves could be driven by common drive means and engaged with each other, or selectively disengaged or out of phase, but could also be driven independently of each other while being selectively synchronized, desynchronized or out of phase with each other.
    [0014] The invention thus makes it possible to simply and reliably provide the admission and exhaust of the chambers 12 of a constant volume type combustion module 10. Figures 10 to 14 illustrate different possibilities of application to different types of propulsion systems. FIG. 10 represents a first type of system in which a turbomachine 14 drives directly or via a gearbox a load 74, such as for example a turboprop propeller. In this case the turbine module 24 is directly coupled to the load 74.
    [0015] FIG. 11 shows a second type of system in which a turbomachine 14 drives a free turbine 76, which in turn directly drives a load 74, such as for example a turboprop propeller. In this case, the gases at the outlet of the turbine module 24 drive the free turbine 76.
    [0016] FIG. 12 shows a third type of system in which a combustion module 10 drives a turbine module 24, which in turn directly drives a load 74, such as for example a turboprop propeller. In this case, it is the gases at the outlet of the combustion module 10 which drive the turbine module 24.
    [0017] FIG. 13 represents a fourth type of system in which a turbomachine 14 of the type previously described ejects gases in a nozzle 78. In this case the propulsion is provided by reaction. Finally, FIG. 14 represents a fifth type of system in which a combustion module 10 directly ejects gases in a nozzle 78. In this case, the system is reduced to its simplest expression and is very close in operation to a ramjet. with the difference that it has a higher number of combustion chambers 12 synchronized in their operating cycles. The operating pressure is then higher. Propulsion is also provided by reaction.
    [0018] The invention thus proposes a new type of propulsion system which is particularly advantageous in that, at equal thrust, it has been estimated that such a system is likely to allow a consumption gain of 10% to 20% compared with a conventional turbomachine. 5 10
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Turbomachine combustion module (10), in particular an aircraft, configured for the implementation of a constant volume combustion, comprising at least one combustion chamber (12) arranged around an axis (A), the each chamber (12) comprising a compressed gas inlet port (16) and a burned gas exhaust port (18), characterized in that each intake (16) / exhaust port (18) is configured to be opened or closed by a corresponding intake (28) / exhaust rotary valve (30) coaxial with said axis (A).
    [0002]
    2. Module (10) of combustion according to the preceding claim, characterized in that it comprises a plurality of combustion chambers (12) regularly distributed angularly about said axis (A), whose intake ports (16). are configured to be opened or closed by a common intake rotary valve (28) and whose exhaust ports (18) are configured to be opened or closed by a common exhaust rotary valve (30).
    [0003]
    3. Module (10) of combustion according to the preceding claim, characterized in that the rotary intake valves (28) / exhaust (30) are synchronized in rotation to one another.
    [0004]
    4. Module (10) for combustion according to one of the preceding claims, characterized in that each port (16, 18) has a radial opening (36, 38) which is formed in a longitudinal wall (32, 34) of the combustion chamber (12) coaxial with the axis (A), and in that each rotary intake (28) / exhaust valve (30) has a tubular element (40, 42) for each port of intake (16) / exhaust (18) of the chamber, rotatably mounted coaxially with said axis (A) and having 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 rotation of said tubular member (40, 42). 3032025 18
    [0005]
    5. Combustion module (10) according to the preceding claim, characterized in that the longitudinal wall (32) of the combustion chamber (10) is turned towards the axis (10), and in that the tubular element (40) 42) of each valve is rotatably mounted internally to said wall, said tubular member (40, 42) having an internal bore (44, 46) defining an intake / exhaust gas conduit for the delivery of gases intake / exhaust.
    [0006]
    6. Module (10) of combustion according to one of claims 1 to 3, characterized in that the or each combustion chamber (12) has two walls respectively outer (32) and inner (34) opposite shaped into sections of cylinders and each having one of said ports (16, 18) having a radial opening (36, 38) formed in said inner (34) or outer (32) wall, and in that said module (10) comprises a rotary valve outer tubular (32) / inner (34) associated with each outer wall (32) / inner (34) of the combustion chamber, which comprises a tubular element (40, 42) of diameter corresponding to said outer wall (32) or inner (34) and mounted to rotate coaxially with said corresponding cylinder section, said tubular member (40, 42) having a lumen (50, 52) arranged substantially in an axial plane of the radial opening of said port (16, 18). ), which is able to close or release r said radial opening (36, 38) during rotation of said tubular member (40, 42).
    [0007]
    7. Combustion module (10) according to the preceding claim, characterized in that the or each combustion chamber (12) is arranged coaxially around the end (54) of a tubular inner casing element (56) comprising a duct (58) of annular section, the duct (58) having an end (60) opening into the periphery of said tubular inner member (56), which is arranged facing the opening (38) of the inner wall (34); ) of the chamber (12), the inner rotary valve (30) being interposed radially between said inner tubular housing member (56) and the inner wall (34) of the combustion chamber.
    [0008]
    Combustion module (10) according to the preceding claim, characterized in that the combustion chamber (12) is arranged coaxially inside a tubular outer casing element (62) comprising an annular duct (64). the external rotary valve (28) being arranged around the outer wall (32) of the or each combustion chamber (12) in said annular duct (64) of the tubular outer casing element. 10
    [0009]
    9. Combustion module (10) according to claim 8, characterized in that the intake port (28) is associated with the outer wall (32) of the or each combustion chamber (12), the inlet gases being conveyed through the annular conduit (64) of the tubular outer crankcase member (62), and in that the exhaust port (30) is associated with the inner wall (34) of the or each combustion chamber (12), the inlet gases being discharged through the conduit (58) of the inner tubular housing member (56).
    [0010]
    10. Module (10) for combustion according to one of the preceding claims, characterized in that it comprises a common valve member (66) which comprises the rotary valves intake (28) / 20 exhaust (30) related mutually rotating.
    [0011]
    11. A turbomachine (14) comprising a compressor module (20) comprising at least one compressor (22) and a turbine module (24) comprising at least one turbine (26), characterized in that it comprises a module (10) ) of combustion according to any one of the preceding claims fed by the compressor module (20) and supplying the turbine module (24).
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    BE342262A|
    同族专利:
    公开号 | 公开日
    RU2714386C2|2020-02-14|
    CA2974294A1|2016-08-04|
    RU2017126145A3|2019-08-07|
    RU2017126145A|2019-02-28|
    CN107208553B|2020-08-28|
    CN107208553A|2017-09-26|
    BR112017015809A2|2018-03-27|
    WO2016120551A1|2016-08-04|
    US10662874B2|2020-05-26|
    EP3250858B1|2021-03-03|
    US20180274440A1|2018-09-27|
    EP3250858A1|2017-12-06|
    FR3032025B1|2018-06-15|
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    FR3068074B1|2017-06-23|2019-08-09|Safran|CONSTANT VOLUME COMBUSTION SYSTEM WITH CLOISONNE EXHAUST MANIFOLD|
    FR3068075B1|2017-06-23|2019-08-09|Safran|CONSTANT VOLUME COMBUSTION SYSTEM COMPRISING A SEGMENTED LIGHTING ROTATING ELEMENT|
    FR3083823B1|2018-07-12|2020-09-25|Safran|FUEL INJECTION SYSTEM OF A CONSTANT VOLUME COMBUSTION SYSTEM FOR TURBOMACHINE|
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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
    FR1550588|2015-01-26|
    FR1550588A|FR3032025B1|2015-01-26|2015-01-26|COMBUSTION MODULE WITH CONSTANT VOLUME FOR A TURBOMACHINE|FR1550588A| FR3032025B1|2015-01-26|2015-01-26|COMBUSTION MODULE WITH CONSTANT VOLUME FOR A TURBOMACHINE|
    EP16705231.5A| EP3250858B1|2015-01-26|2016-01-25|Constant-volume combustion module for a turbine engine|
    CA2974294A| CA2974294A1|2015-01-26|2016-01-25|Constant-volume combustion module for a turbine engine|
    RU2017126145A| RU2714386C2|2015-01-26|2016-01-25|Combustion module at constant volume for gas turbine engine|
    BR112017015809-4A| BR112017015809A2|2015-01-26|2016-01-25|constant volume combustion module for a turbomachine|
    CN201680006989.4A| CN107208553B|2015-01-26|2016-01-25|Constant volume combustion module for a turbine engine|
    PCT/FR2016/050142| WO2016120551A1|2015-01-26|2016-01-25|Constant-volume combustion module for a turbine engine|
    US15/545,992| US10662874B2|2015-01-26|2016-01-25|Constant-volume combustion module for a turbine engine|
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