• 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 probe (1) for measuring the gas temperature at the outlet of a gas turbine such as a helicopter turbine. This probe comprises an isothermal box (3) intended to be placed outside the turbine and enclosing a thermal sensor (17), at least one thermocouple (6A, 6B, 6C) comprising a cold junction (11A, 11B, 11C) mounted in the isothermal housing (3) and a hot weld (9A, 9B, 9C) to be placed in the turbine. A connector (2) carried by the isothermal housing (3) makes it possible to electrically connect this probe to a data acquisition apparatus that can be at a distance from the probe itself. The connection between the cold welds can be made in series or in parallel, inside or outside the isothermal housing (3). This probe may comprise N-type thermocouples and sheaths made of Haynes type alloy material.
    公开号:FR3027106A1
    申请号:FR1459652
    申请日:2014-10-08
    公开日:2016-04-15
    发明作者:Jean-Julien Camille Vonfelt；Antoine Moutaux；Jose-Alexandre Pina
    申请人:Turbomeca SA；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The invention relates to the measurement of the temperature of combustion gases expelled at the outlet of a gas turbine, such as in particular at the outlet of a turbine. helicopter, this temperature measurement directly conditioning the power regulation of the turbine. STATE OF THE PRIOR ART In view of the high temperature prevailing at the turbine outlet, the measurement of the temperature of the combustion gases is carried out with a thermocouple connected to a dedicated computer. This thermocouple comprises a hot weld implanted at the turbine outlet, and it is connected to a computer by two cold welds integrated or connected to this computer. This calculator integrates or is connected to an absolute temperature sensor, called reference temperature, which measures the temperature of cold welds. In practice, this thermocouple is of type K, that is to say that it comprises a pair of conductors manufactured respectively in alloys of the type marketed under the brand names Chromel and Alumel. The calculator of such a system thus measures the difference in electrical potential existing between the two cold welds of the thermocouple, which reflects, according to a predetermined law, the temperature difference existing between the hot weld and the cold welds of the thermocouple. The determination of the turbine outlet temperature is performed by this calculator. This determines the temperature difference between the hot weld and the cold welds on the basis of the potential difference and the thermocouple variation law, and the reference temperature from the data provided by the sensor 3027106 2 temperature close to cold welds. The desired temperature is thus the sum of the reference temperature and the temperature difference measured by means of the thermocouple. The robustness of this measurement can be improved by using several thermocouples connected in parallel, instead of just one, which significantly increases the quantity of cables required. But in general, such a measurement system is expensive because of the large length of dedicated and specific cables that are necessary for its implementation. Indeed, these cables must have their conductors manufactured in alloys 10 specific thermocouples they constitute. In addition, cable parts exposed to high temperatures must be protected, for example by a cladding of an alloy of the type marketed under the brand name Nimonic. Thus, the implementation of a thermocouple turbine gas temperature measurement has a significant cost, but since this measurement directly conditions the power regulation of the turbine, it is essential that its accuracy remains high. The object of the invention is therefore to propose a solution for reducing the cost of implementing such a measurement of the temperature of the gases at the turbine outlet without penalizing the measurement accuracy.
    [0002] SUMMARY OF THE INVENTION To this end, the subject of the invention is a probe for measuring the gas temperature at the outlet of a gas turbine, such as a helicopter turbine, this probe comprising a thermocouple comprising a hot solder intended to be placed at the turbine outlet, cold welds and a thermal sensor for measuring the temperature of the cold welds, characterized in that this probe comprises an isothermal housing carrying a connector for connecting the probe to a connection cable to an apparatus for acquiring and processing data, the isothermal housing with its connector being intended to be placed outside the turbine, the isothermal housing enclosing the thermal sensor and each cold thermocouple junction.
    [0003] 3027106 3 The isothermal enclosure keeps the temperatures of the temperature sensor and the cold welds as close as possible to obtain the best measurement accuracy possible. The assembly can thus be connected via its connector to a computer using traditional wiring, that is to say without any specific alloy, such as for example a cable with copper conductors. The invention also relates to a probe thus defined, in which the isothermal housing with its connector is equipped with a flange for attachment to a support. The invention also relates to a probe thus defined, comprising several thermocouples each having cold welds mounted in the isothermal housing 10 and a hot weld to be placed at the turbine outlet. The invention also relates to a probe thus defined, comprising means for connecting together the cold welds to connect the thermocouples out of the isothermal housing. The invention also relates to a probe thus defined, in which the thermocouples are connected in series in the isothermal housing. The invention also relates to a probe thus defined, wherein the thermocouples are connected in parallel in the isothermal housing. The subject of the invention is also a probe thus defined, in which the thermocouples are of type N.
    [0004] The subject of the invention is also a probe thus defined, in which each thermocouple comprises a portion covered with a sheath made of Haynes type alloy material. The invention also relates to a gas turbine equipped with a probe thus defined.
    [0005] BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is an overall view of the probe according to the invention; FIG. 2 is a schematic view showing the probe according to the invention with its thermocouples connected in parallel; FIG. 3 is a schematic view showing the probe according to the invention with its thermocouples connected in series. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS The idea underlying the invention is to constitute a thermal probe comprising the thermocouples and their cold welds as well as a cold weld temperature sensor, to connect this probe to a remote computer. by means of normal cables, for example comprising copper conductors.
    [0006] As shown in FIG. 1, the thermal probe 1 according to the invention comprises a connector 2 and an isothermal box 3 mounted on either side of a double flange 4, with three thermocouples 6A, 6B, 6C connected to it. isothermal housing 3. The connector 2 is here a sealed connector, for example of the EN2997 type, having in its inner region non-visible copper plugs. This connector forms with the double flange 4 and the isothermal housing 3 a rigid assembly intended to be fixed to a suitable support, thanks to the flange 4 having two lateral holes 7 and 8 provided to be traversed by two fixing screws. The thermocouple 6A comprises a so-called hot weld 9A corresponding to its free end, and intended to be placed at the outlet of the turbine to measure the temperature of the combustion gases. The opposite end of this thermocouple, indicated by 11A, has two cold welds and is connected in the insulated housing 3. This thermocouple 6A comprises a generally tubular sheath 12A enclosing two non-visible conductors which are connected to each other at the level of its free end to form the hot weld to be located at the turbine outlet. This sheath which is thermally insulating is advantageously manufactured in an alloy of the type marketed under the brand name Haynes, that is to say offering improved creep resistance, in particular in comparison with a 3027106 alloy of the type marketed under the Nimonic brand name usually used to sheath this type of thermocouple. Half of the sheath 12A which is remote from the housing 3 is equipped with a sheath 13A comprising a tubular casing 14A terminated by a flange 16A. This flange 16A also has two holes intended to be traversed by fixing screws to a suitable support located at the turbine outlet. When the probe 1 is in place, the free end 9A is engaged in a suitable opening of the turbine outlet housing, and the flange 16A is plated and fixed to the housing in question. The probe is then connected to an apparatus for acquiring and processing data via its connector 2. The thermocouples 6B and 6C are identical to the thermocouple 6A, and their constituent elements bear in the figures references beginning with the same numbers but followed respectively by the letter B or C instead of the letter A. Complementarily, the housing 3 contains a thermal sensor, 15 marked by 17, to measure the temperature of cold welds. This sensor, which is here a PT100 or PT1000 platinum resistance thermometer, is also connected to the plugs of connector 2. Thus, the cold welds of the three thermocouples and the sensor 17 are connected to the plugs of connector 2. The thermocouples are advantageously thermocouples N type because they have a better behavior in time in terms of drift. This makes it possible to maintain a better performance of the engine over time because the measurement of the gases at the turbine outlet directly conditions the power regulation of the engine. That being so, the invention is equally applicable to thermocouples of any other type such as in particular K, I, E or J.
    [0007] An N-type thermocouple comprises a pair of conductors made respectively of the alloys corresponding to those sold under the trade names Nicrosil and Nisil. As shown in FIGS. 2 and 3, the three thermocouples can be connected to each other in parallel, as is the case in the example of FIG. 2, or in series, which corresponds to the case of FIG. 3.
    [0008] 3027106 6 The parallel or series configuration of the three thermocouples is performed either outside the isothermal housing, for example in the harness, that is to say the wiring harness, which is connected to the connector 2, or in the isothermal housing itself, either in an intermediate housing not shown.
    [0009] The parallel or series configuration can thus be made optionally by the operator according to his operating conditions, while allowing a maintenance operator to be able to test the individual thermocouples in isolation. In general, the fact of the invention to provide an isothermal housing equipped with a connector and containing the temperature sensor as well as the cold welds makes it possible to place the cold welds at a relatively short distance from the hot welds. In practice, the connector with its housing enclosing the cold welds and the sensor are simply placed in the vicinity of the turbine while the hot welds are placed at the turbine outlet. The isothermal enclosure ensures that the temperature measured by the temperature sensor is the same as the temperature of the cold welds to achieve appropriate measurement accuracy with the thermocouples. The fact of deporting the cold junction at the connector limits the lengths of cables in specific thermocouple alloys. This also removes the specific alloy connector pins.
    [0010] The use of Haynes type alloy-coated thermocouples makes it possible to have better creep resistance of the thermocouples in order to provide better measurement reliability over time, and hence better motor performance over time. The use of N-type hot welds reduces the effects of aging on measurement accuracy. The ability to parallel or serial cold welds outside the sensor allows the reuse of the sensor on different applications and improve fault detection and localization procedures. 30
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A probe (1) for measuring the gas temperature at the outlet of a gas turbine, such as a helicopter turbine, said probe comprising at least one thermocouple (6A, 6B, 6C) comprising a hot weld (9A, 9B, 9C) intended to be placed at the turbine outlet, cold welds (11A, 11B, 11C) and a thermal sensor (17) for measuring the temperature of the cold welds (11A, 11B, 11C), characterized in that this probe comprises an insulated housing (3) carrying a connector (2) for connecting the probe (1) to a connection cable to a data acquisition and processing equipment, the isothermal housing (3) with its connector (2) being intended to be placed out of the turbine, the isothermal housing (3) enclosing the thermal sensor (17) and each thermocouple cold junction (11A, 11B, 11C).
    [0002]
    2. Probe (1) according to claim 1, wherein the isothermal housing (3) with its connector (2) is equipped with a flange (4) for attachment to a support.
    [0003]
    A probe according to claim 1 or 2 comprising a plurality of thermocouples (6A, 6B, 6C) each having cold welds (11A, 11B, 11C) mounted in the isothermal housing (3) and a hot weld (9A, 9B, 9C). intended to be placed at the outlet of the turbine.
    [0004]
    4. Probe (1) according to claim 3, comprising means for connecting together the cold welds (11A, 11B, 11C) for connecting the thermocouples (6A, 6B, 6C) out of the isothermal housing (3). 25
    [0005]
    5. Probe (1) according to claim 3, wherein the thermocouples (6A, 6B, 6C) are connected in series in the isothermal housing (3).
    [0006]
    6. Probe (1) according to claim 3, wherein the thermocouples (6A, 6B, 6C) are connected in parallel in the isothermal housing (3). 20 3027106 8
    [0007]
    7. Probe (1) according to claims 1 to 6, wherein the thermocouples (6A, 6B, 6C) are of type N.
    [0008]
    The probe (1) according to claims 1 to 7, wherein each thermocouple comprises a portion covered with a sheath (12A, 12B, 12C) of Haynes type alloy material.
    [0009]
    9. Gas turbine equipped with a probe (1) according to one of claims 1 to 8.
    [0010]
    10
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    同族专利:
    公开号 | 公开日
    FR3027106B1|2016-12-09|
    WO2016055726A1|2016-04-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    WO2018158541A1|2017-02-28|2018-09-07|Safran Helicopter Engines|Thermometric measurement by meshing of probes, particularly in turbine engines|
    RU2676237C1|2018-02-13|2018-12-26|Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова"|Device for determining temperature of gaseous media in gas turbine engines|
    FR3075877A1|2017-12-21|2019-06-28|Safran Aircraft Engines|SYSTEM FOR DETECTING A TEMPERATURE FAULT IN THE INTER-VEIN COMPARTMENT OF A DOUBLE FLOW TURBOREACTOR|
    CN106932112A|2017-02-08|2017-07-07|中国航发沈阳发动机研究所|One kind is without cooling down high-temperature thermocouple preparation method and without cooling down high-temperature thermocouple|
    法律状态:
    2015-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-15| PLSC| Search report ready|Effective date: 20160415 |
    2016-10-13| PLFP| Fee payment|Year of fee payment: 3 |
    2017-09-01| CD| Change of name or company name|Owner name: SAFRAN HELICOPTER ENGINES, FR Effective date: 20170727 |
    2018-07-27| ST| Notification of lapse|Effective date: 20180629 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1459652A|FR3027106B1|2014-10-08|2014-10-08|PROBE FOR MEASURING THE TEMPERATURE REGULATING AT THE OUTPUT OF THE HELICOPTER TURBINE|FR1459652A| FR3027106B1|2014-10-08|2014-10-08|PROBE FOR MEASURING THE TEMPERATURE REGULATING AT THE OUTPUT OF THE HELICOPTER TURBINE|
    PCT/FR2015/052672| WO2016055726A1|2014-10-08|2015-10-06|Sensor for measuring the prevailing temperature at the outlet of a helicopter turbine|
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