• 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 method and a device ventilation circuit of a turbojet engine, the turbojet engine (10) comprising a cold zone (ZF) having a fan (14) upstream of a hot zone (Zc), the equipment (32) of the turbojet to be ventilated being disposed in a ventilation space (30) available around the hot zone between a primary air flow stream (26) and a secondary air flow vein (28) from the turbojet engine , the method comprising withdrawing ventilation air into one of the airflow streams to convey it to the ventilation space and the forced circulation of the ventilation air through at least an electric fan (36) positioned within the ventilation space and supplied with electric current by a plurality of thermoelectric generators (38) positioned in a wall (40) separating the ventilation space from the flow stream; secondary air.
    公开号:FR3027958A1
    申请号:FR1460426
    申请日:2014-10-30
    公开日:2016-05-06
    发明作者:Pache Gwenole Yann Le；Lise Domecq
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to the general field of equipment ventilation arranged in the vicinity of the hot zone of a turbojet engine. A turbojet engine includes a large number of ancillary equipment. These are in particular the various accessories of the AGB ("Accessory Gearbox"), such as pumps for the production of hydraulic energy, fuel supply, lubrication, electric generators for the production of electrical power. , etc., as well as the hydromechanical unit of the turbojet engine (or HMU for "Hydromechanical Unit") which makes it possible to control the servovalves used to measure the flow of fuel sent to the hydraulic cylinders for actuating variable geometries of the turbojet engine and the valves air circuit of the engine air. Such equipment is sensitive to heat and must therefore preferably be placed in the vicinity of the cold zone of the turbojet, that is to say around the fan of the latter, in order to avoid having their reliability affected by the strong thermal stresses to which they are subjected. However, for turbojet engines having a high dilution ratio, having the equipment around the fan would contribute to increasing the turbojet engine drag. Also, it has become commonplace to position certain equipment in the vicinity of the hot zone of the turbojet engine. This hot zone, which is typically located downstream of the cold zone (around the high pressure body of the turbojet engine - called "core" - including the high-pressure compressor and the combustion chamber) offers space to accommodate turbojet engine equipment.
    [0002] To limit the temperature of the equipment during the operation of the turbojet, it is known to have heat shields around the high-pressure body of the turbojet engine and to ventilate the space where the equipment is arranged by removing fresh air from the fan.
    [0003] However, after stopping the engine, there is more fresh air that is routed to the equipment to ventilate while the body 302 7 9 5 8 2 high-pressure turbojet is still very hot and continues to radiate so that the equipment rises in temperature before cooling very gradually. This phenomenon (called "soakback") which sees the ambient temperature in the engine increase may last for a long time after the engine has stopped, the peak temperature being generally reached up to several hours after stopping. In an attempt to remedy this drawback, one solution is to size the equipment to maintain the temperatures reached during this phenomenon of "soakback". However, the arrival in the available space around the turbojet's high-pressure body of many additional equipment that is not usually designed to withstand such temperatures renders this solution ineffective. Another known solution is to provide a forced ventilation of air in the space in which the equipment is housed after stopping the engine until their temperature drops. It will be possible to refer in particular to documents FR 2,955,896 and FR 2,955,896 which describe ventilation circuits using a variable speed fan which is driven from the cockpit or the electronic computer of the turbojet engine and supplied with electric power by means of the groups auxiliaries (or APU for Auxiliary Power Unit), either by the ground power unit provided by the airport, or by the batteries of the aircraft. In order to operate, this solution therefore requires that one of the above-mentioned electrical sources for the supply of the fans be available after the engine has been stopped. However, when the engine is stopped, it is preferable that the aircraft, and therefore the APU, are also extinguished. In addition, for reasons of system independence, aircraft manufacturers are generally reluctant to provide auxiliary power to the engine when it is stopped. In addition, the supply of the fans 30 by batteries of the aircraft requires sizing them accordingly, which necessarily increases their mass. Finally, feeding by the ground feeding group is operationally constraining as it monopolizes the aircraft, personnel and equipment. SUMMARY OF THE INVENTION The subject of the present invention is therefore a method and an active ventilation circuit of the equipment of a turbojet engine which do not have the abovementioned disadvantages. According to the invention, this object is achieved by means of a device ventilation process of a turbojet engine, the turbojet engine comprising a cold zone having a fan upstream of a hot zone, the equipment of the turbojet engine to be ventilated being disposed in a ventilation space available around the hot zone between a primary air flow vein and a secondary air flow stream coming from the turbojet engine, the method comprising extracting ventilation air in one of the veins of airflow to convey it to the ventilation space and the forced circulation of the ventilation air via at least one electric fan positioned inside the ventilation space and fed electric current by a plurality of thermoelectric generators positioned in a wall separating the ventilation space from the secondary air stream. Correlatively, the invention also relates to a device ventilation circuit of a turbojet, the turbojet comprising a cold zone having a fan upstream of a hot zone, the equipment of the turbojet to be ventilated being arranged in a space ventilation system available around the hot zone between a primary air flow vein and a secondary air flow stream from the turbojet, the circuit comprising means for drawing ventilation air in one of the veins of airflow and convey it into the ventilation space and at least one electric fan positioned inside the ventilation space and supplied with electric current by a plurality of thermoelectric generators positioned in a wall separating the Ventilation space of the secondary air flow vein. The method according to the invention can advantageously be implemented after stopping the engine. After a shutdown, the temperature of the turbojet engine's high-pressure body significantly exceeds the ambient temperature it makes inside the secondary air stream. A large thermal gradient is therefore available between the high pressure body and the secondary air stream. The method and the circuit according to the invention are thus remarkable in that they use this thermal gradient as a source of energy to effect a forced circulation of the ventilation air in the ventilation space in which are arranged the equipments. Indeed, the thermoelectric generators are devices that convert the heat (here the available thermal gradient between the high-pressure body and the secondary flow stream) into electrical energy supplying a fan positioned inside the space of ventilation. Thus fed with electric current, the ventilator makes it possible to ventilate the space of ventilation and thus to cool the equipment. The thermal gradient between the high pressure body and the secondary air stream decreases accordingly. Since the electric energy produced by the thermoelectric generators is proportional to the thermal gradient to which they are subjected, the reduction of the latter causes a decrease in the electrical energy produced and therefore a decrease in the ventilation of the equipment. The fan then stops by itself when the thermal gradient between the high-pressure body and the secondary air stream reaches a certain threshold. At this point, the ventilation space has been sufficiently cooled and has reached a thermal equilibrium with the secondary air stream. The method and the circuit according to the invention thus have the advantage of effectively regulating the temperature in the ventilation space in which the equipment is arranged without requiring a supply of electrical energy outside the turbojet engine. The ventilation circuit according to the invention is thus completely autonomous and self-regulating without the need to resort to a temperature sensor or any other control system. Finally, this ventilation circuit is reliable and simple to implement. The electric fan may be stopped as soon as the temperature inside the ventilation space becomes lower than a predetermined threshold temperature. Correlatively, the circuit may include means for stopping the electric fan below a predetermined threshold temperature within the ventilation space. This feature aims at stopping the ventilation of the equipment before a thermal equilibrium is established between the ventilation space and the secondary air stream. This limits the overuse of the ventilation circuit when it is not necessary to raise the equipment temperature to such a low temperature. The operation of the electric fan can be monitored to detect any malfunction. Correlatively, the circuit may include means for detecting any malfunction of the fan. The electric fan can be supplied with electric current during an operating phase of the turbojet engine so as to ventilate the equipment during the flight. Each thermoelectric generator of the ventilation circuit may comprise a plurality of semiconductor elements with thermoelectric properties connected to two conductive plates, each of which is covered by an electrical insulating substrate, one of the substrates being disposed on the the secondary air stream and the other substrate being disposed on the ventilation space side. The invention further relates to a turbojet comprising a ventilation circuit as defined above. BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures: - Figure 1 is a schematic sectional view of a turbojet engine equipped with a ventilation circuit according to the invention; FIG. 2 is a schematic view of a thermoelectric generator used for the ventilation circuit of FIG. 1; and FIG. 3 is a functional view of the ventilation circuit of FIG. 1. DETAILED DESCRIPTION OF THE INVENTION FIG. 1 is a diagrammatic longitudinal sectional view of an aircraft turbojet engine of the double and double-body type. flow and surrounded by a nacelle 12. In a manner known per se, the turbojet engine 10 comprises, from upstream to downstream, a fan 14, a low-pressure compressor 16, a high-pressure compressor 18, a chamber 302 7 9 5 8 6 combustion 20, a high pressure turbine 22 and a low pressure turbine 24 which are centered on a longitudinal axis XX. The turbojet engine 10 also comprises a primary air flow stream 26 (or hot stream) and a secondary air flow stream 28 (or cold stream) formed around the primary flow vein. The turbojet engine 10 also comprises a cold zone ZF (including in particular the fan 14 and the low-pressure compressor 16) upstream of a hot zone Zc (corresponding to the high-pressure body and including in particular the high-pressure compressor 18 and the combustion chamber. combustion 20). Within the hot zone Zc, is delimited a ventilation space 30 where are arranged different equipment 32 of the turbojet engine (such as accessories of the AGB, the HMU, etc.). In the example of Figure 1, this ventilation space is located around the high-pressure compressor 18 and the combustion chamber 20 and communicates with the outside of the turbojet engine (that is to say, it is subject to at ambient pressure). Since the ventilation space 30 is positioned at the hot zone Zc of the turbojet engine, the equipment 32 disposed inside it is exposed to the high temperatures prevailing in this hot zone. Also, in order to ventilate the equipment 32 in order to limit their rise in temperature, it is envisaged, in accordance with the invention, to provide a ventilation circuit for withdrawing ventilation air in the secondary air flow duct 28. downstream of the fan 14 to convey it inside the ventilation space 30. According to the invention, this ventilation circuit comprises in particular at least one scoop 34 opening in the vein of secondary air flow 28 downstream of the blower 14 and opening into the ventilation space 30 30 where are the equipment 32. The ventilation circuit according to the invention also comprises at least one electric fan 36 positioned inside the space of 30. ventilation 30 downstream of the scoop 34 and upstream of the equipment 32 to ventilate. This fan 36 has the function of maintaining, after stopping the turbojet engine or even during its operation, a forced circulation of the ventilation air in the ventilation space 30 so that the temperature of the equipment 32 decreases. The ventilation circuit according to the invention further comprises a plurality of thermoelectric generators 38 which are intended to supply the fan 36 with electric current. These thermoelectric generators 38 are interconnected and are positioned on all or part of a wall 40 separating the ventilation space 30 from the secondary air stream 28, this wall 40 also being able to accommodate a thermal protection coating ( not shown in the figures).
    [0004] In known manner, a thermoelectric generator (called "Seebeck generator" in English) is a device that converts heat (ie a thermal gradient) directly into electrical energy, using the Seebeck effect (ie by difference electrical potential). An exemplary embodiment of a thermoelectric generator 38 is shown in FIG. 2. Typically, this comprises a plurality of semiconductor elements 42 with thermoelectric properties and respectively doped N type and P type which are connected to two conductive plates 44, these conductive plates being each covered by a substrate 46 forming an electrical insulator. The conductive plates 44 are also connected to electrical terminals 48 connected to the fan 36 for supplying electric current. The operation of such a thermoelectric generator 38 is known per se and will not be described in detail. Briefly, when the two substrates 46 are subjected to a thermal gradient (one of the substrates 25 being positioned here on the side of the secondary air stream 28 and the other substrate being positioned on the side of the ventilation space 30), the heat displacement induces a charge difference sufficient to induce a potential difference for supplying an electric current. FIG. 3 diagrammatically shows the operation of such a ventilation circuit after stopping the turbojet engine. Typically, after the shutdown of the turbojet, the temperature of the high-pressure body of the turbojet engine (and in particular of the combustion chamber 20) significantly exceeds the ambient temperature 35 Tambiante it does inside the flow stream of Secondary air 28. A large thermal gradient AT is then available between the high-pressure body and the secondary air flow vein. This thermal gradient AT is used as a source of energy by the thermoelectric generators 38 to induce a difference in AV potential proportional to the temperature gradient AT which is used to supply the electric fan 36. The latter will therefore ventilate the ventilation space 30 by carrying out a forced circulation of air inside it (the ventilation air is reinjected downstream in the secondary air stream 28 through openings 50 made in the wall 40 - see FIG. 1). This ventilation thus makes it possible to cool the equipment 32. As the ventilation space 30 is thus ventilated by the fan 36, the thermal gradient AT between the high pressure body and the secondary air stream of the turbojet decreases accordingly. Since the potential difference AV induced by the thermoelectric generators 38 is proportional to this thermal gradient AT, the electrical energy produced also decreases, which leads to a decrease in the ventilation. Thus, the fan 36 stops by itself when the thermal gradient AT is no longer high enough to induce a potential difference AV. At this stage, the equipment 32 present in the ventilation space 30 have been cooled and the ventilation space has reached a thermal equilibrium with the secondary air flow stream 28. In this way, a ventilation of the ventilation space 30 is obtained. ventilation space which is self-regulating and therefore does not require the presence of temperature sensors and control device (the fan 36 is triggered and stops alone) with the certainty that the fan stop corresponds to a thermal equilibrium between the ventilation space and the vein of secondary airflow no longer requiring such ventilation. In addition, this ventilation does not require that the turbojet engine or the supply of external electrical energy. Note that the operation of the ventilation circuit according to the invention is just as valid during operation of the turbojet engine (especially in flight). Indeed, when the turbojet engine is running, the thermal gradient AT between the primary air flow vein and the secondary air stream is also available.
    [0005] Note also that it is possible to stop the operation of the fan 36 before the thermal equilibrium between the ventilation space and the secondary air flow vein (that is, as soon as the temperature inside the ventilation space becomes lower than a predetermined threshold temperature higher than the temperature prevailing in the secondary air stream 28). This operating option limits the overuse of the ventilation circuit. For this purpose, one solution is to adjust the starting voltage of the fan so that it stops working as soon as a determined thermal gradient is reached (ie under a threshold of potential difference AV induced by thermoelectric generators). Another solution is to resort to a non-controlled switching of the fan power supply. Yet another solution may be based on an electronic fan control device that is not connected to the electronic engine computer and that would be present in the ventilation space. According to an advantageous arrangement, the ventilation circuit also comprises means for monitoring the operation of the fan 36 in order to detect any possible malfunction thereof. This monitoring can be performed by a suitable sensor mounted on the fan or by a temperature sensor already present in the ventilation space. It will also be noted that the thermoelectric generators 38 may be redundant and / or distributed in several independent fan supply channels 36 to reduce the risk of occurrence of a malfunction of these generators. Finally, in a variant embodiment not shown, the ventilation circuit may further comprise a forced ventilation of a cold zone of the ventilation space by the same fan 36. This additional ventilation makes it possible to improve the efficiency of the cooling circuit. ventilation of the equipment 38 and to avoid the formation of a harmful boundary layer for ventilation between this cold zone and the hot zone of the ventilation space. In practice, this additional ventilation requires adding a dedicated fan inside the ventilation space and directed to the cold zone thereof.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A method of ventilating equipment of a turbojet, the turbojet engine (10) comprising a cold zone (ZF) having a fan (14) upstream of a hot zone (Zc), the equipment (32) of the turbojet to be ventilated being arranged in a ventilation space (30) available around the hot zone between a primary air flow duct (26) and a secondary air flow duct (28) coming from the turbojet engine, the method comprising the removal of ventilation air in one of the air flow veins for conveying it to the ventilation space and the forced circulation of the ventilation air via at least one electric fan (36) positioned at the interior of the ventilation space and supplied with electric current by a plurality of thermoelectric generators (38) positioned in a wall (40) separating the ventilation space from the secondary air stream.
    [0002]
    2. Method according to claim 1, wherein the electric fan is supplied with electric current after stopping the turbojet engine.
    [0003]
    3. Method according to one of claims 1 and 2, wherein the electric fan is stopped as soon as the temperature inside the ventilation space becomes less than a predetermined threshold temperature.
    [0004]
    4. Method according to any one of claims 1 to 3, wherein the operation of the electric fan is monitored to detect any malfunction.
    [0005]
    5. Method according to any one of claims 1 to 4, wherein the electric fan is supplied with electric current during an operating phase of the turbojet engine.
    [0006]
    6. Equipment ventilation circuit of a turbojet engine, the turbojet engine (10) comprising a cold zone (ZF) having a fan (14) upstream of a hot zone (Zc), the equipment (32) of the 3 0 2 7 9 5 8 11 turbofan engine being arranged in a ventilation space (30) available around the hot zone between a primary air flow duct (26) and a secondary air flow duct (28) from the turbojet engine, the circuit comprising means (34) for collecting ventilation air 5 in one of the airflow streams and conveying it into the ventilation space and at least one electric fan (36). ) positioned within the ventilation space and supplied with electric current by a plurality of thermoelectric generators (38) positioned in a wall (40) separating the ventilation space from the secondary airflow duct.
    [0007]
    The circuit of claim 6, further comprising means for stopping the electric fan below a predetermined threshold temperature within the ventilation space. 15
    [0008]
    8. Circuit according to one of claims 6 and 7, further comprising means for detecting a possible malfunction of the fan. 20
    [0009]
    9. Circuit according to any one of claims 6 to 8, wherein each thermoelectric generator comprises a plurality of semiconductor elements (42) with thermoelectric properties connected to two conductive plates (44), these being each covered by a substrate (46) forming an electrical insulator, one of the substrates being disposed on the side of the secondary air stream and the other substrate being disposed on the side of the ventilation space.
    [0010]
    10. Turbeactor comprising a ventilation circuit according to any one of claims 6 to 9.
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    同族专利:
    公开号 | 公开日
    US20160123185A1|2016-05-05|
    FR3027958B1|2016-12-23|
    引用文献:
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    法律状态:
    2015-10-09| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-06| PLSC| Search report ready|Effective date: 20160506 |
    2016-10-03| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-21| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1460426A|FR3027958B1|2014-10-30|2014-10-30|METHOD AND CIRCUIT FOR VENTILATING EQUIPMENT OF A THERMO-ELECTRICITY TURBOKINACTOR|FR1460426A| FR3027958B1|2014-10-30|2014-10-30|METHOD AND CIRCUIT FOR VENTILATING EQUIPMENT OF A THERMO-ELECTRICITY TURBOKINACTOR|
    US14/926,628| US20160123185A1|2014-10-30|2015-10-29|Method and a circuit for ventilating equipment of a turbojet by thermoelectricity|
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