• 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 (20) for measuring the flow of gases at the outlet of a generally annular turbomachine combustion chamber, said combustion chamber having an axis of revolution, in which a measuring comb is positioned (21). at the outlet of the combustion chamber, in order to take the gases flowing out of the latter, said measuring comb comprising a plurality of measuring orifices whose axes extend in the same plane, characterized in that the measurement comb is inclined (22) at the outlet of said chamber, so that the aforementioned plane of the axes of the measuring orifices and the axis of revolution form a non-zero turning angle, and in that the same angle of gyration (α) is retained for testing under idling and full throttle conditions of the combustion chamber.
    公开号:FR3021741A1
    申请号:FR1454804
    申请日:2014-05-27
    公开日:2015-12-04
    发明作者:Romain Nicolas Lunel；Denis Jean Maurice Sandelis
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] GENERAL TECHNICAL FIELD The present invention relates to a method for measuring the flow of gas at the outlet of a turbomachine combustion chamber, and a measuring comb for the implementation of such a method.
    [0002] STATE OF THE ART It is known from the state of the art measuring combs configured to measure the flow of gas at the outlet of a turbomachine combustion chamber. Such measuring combs are for example described in the document FR 2 952 713 of the Applicant. Such measuring combs typically comprise a comb body extending generally along an axis of orientation and having a profiled bottom portion intended to be positioned facing the outlet of the combustion chamber and an upper soleplate intended to be shifted relatively at the outlet of the combustion chamber so as not to disturb the flow of gases at the outlet of the combustion chamber. The lower part is equipped with measurement ports connected to meters via channels. The measuring orifices are aligned parallel to the axis of orientation of the comb body and are fixed relative to said comb body. During the tests carried out on the combustion chamber, the comb body is rotated about the axis of revolution of the combustion chamber, for example by means of a rotating ring on which the lower sole of the combustion chamber comb body is flanged. The measuring orifices then take the gases flowing out of the combustion chamber, so as to measure the required parameters, such as, for example, the pressure and / or the temperature at the outlet of the combustion chamber. Such measuring combs thus make it possible to measure the flow of gases at the outlet of the combustion chamber. 3021741 2 This flow measurement is however limited. Indeed, it is not possible with such measuring combs to take into account the three-dimensional effects of the gas flow at the outlet of the combustion chamber. However, the taking into account of these three-dimensional effects is essential, especially when the gas flow at the outlet of the combustion chamber is gyratory, that is to say that it has a tangential component relative to the axis of revolution of the combustion chamber. Such a gyration of the gas flow at the outlet of the combustion chamber is for example induced by an inclination of the combustion chamber relative to the axis of the turbomachine. It is also induced by the use of combustion chambers having a dimension in the axis of the reduced turbomachine and / or not including a cooling system, such as dilution orifices, for returning the diluted gases in the axis of the turbomachine. To meet this need, it has been envisaged by the Applicant to develop measuring combs having measuring orifices inclined relative to the axis of orientation of the comb body. However, the Applicant has found by developing such measuring combs that it was necessary to increase the width of the comb body by two, in order to be able to ensure the inclination of the measuring orifices with respect to the axis of orientation. comb body, and thus take into account the gyratory effect of the gas flow at the outlet of the combustion chamber. However, such a comb body could disrupt the flow of gas upstream of the comb body, and thus distort the measurements made by the measuring comb. Such a solution was therefore not retained. PRESENTATION OF THE INVENTION The present invention aims to solve the aforementioned problems by proposing a method for measuring the flow of gas at the outlet of a turbomachine combustion chamber taking into account the gyratory effect of the gas flow. at the outlet of the combustion chamber. More specifically, the subject of the present invention is a method for measuring the flow of gases at the outlet of a generally annular turbomachine combustion chamber, said combustion chamber having an axis of revolution, in which a measuring comb is positioned. at the outlet of the combustion chamber, in order to take the gases flowing out of the latter, said measuring comb comprising a plurality of measuring orifices whose axes extend in the same plane, characterized in that the measuring comb is inclined at the outlet of said chamber, so that the aforementioned plane of the axes of the measurement orifices and the axis of revolution form a non-zero angle of gyration, and in that the same angle of gyration is maintained for testing in idling and full throttle conditions of the combustion chamber. Preferably, a gyration of the gas flow at the outlet of the combustion chamber is calculated under the conditions of idling and full gas of the combustion chamber so as to determine a range of gyration of the gas flow at the outlet of the combustion chamber . More preferably, the measuring orifices have a limit range for detecting the gyration of the gas flow, and in which the angle of gyration is chosen so that the range of gyration of the gas flow at the outlet of the combustion chamber is included in the detection limit range of the measuring ports. Preferably, the measuring comb is inclined at the outlet of the combustion chamber, so that the plane of the axes of the measuring orifices and the axis of revolution form a gyration angle of between 5 and 15 °.
    [0003] Preferably, the rotation comb is rotated about the axis of revolution. Preferably, the temperature and / or the pressure and / or the chemical composition of the gases sampled are measured. Preferably, the same angle of gyration is maintained for testing under idling and full throttle conditions of the combustion chamber.
    [0004] The present invention also relates to a comb for measuring the flow of gases at the outlet of a turbomachine combustion chamber, said combustion chamber extending along an axis of revolution, said measuring comb being characterized by it comprises means for implementing the method as previously described, the measuring comb comprising: a comb body intended to come opposite the outlet of the combustion chamber, and a plurality of measuring orifices whose axes extend in the same plane, the measuring orifices being configured to take off gases flowing out of the combustion chamber; an arm configured to incline the comb body at the outlet of the combustion chamber; combustion chamber, so that the plane of the axes of the measuring orifices and the axis of revolution form a non-zero turning angle. Preferably, the axes of the measuring orifices extend generally in a fan shape. Preferably, the measuring comb further comprises a motor configured to drive the comb body in rotation about the turbomachine axis. Preferably, the measuring orifices are connected to meters 20 configured to measure the temperature and / or the pressure and / or the composition of the gases taken by the measuring orifices. PRESENTATION OF THE FIGURES Other characteristics, objects and advantages of the present invention will appear on reading the detailed description which follows, and with reference to the appended drawings given as non-limiting examples and in which: FIG. 1 is a schematic side view of a measuring comb according to the invention in position for measuring the flow of gas at the outlet of a combustion chamber; FIG. 2 is a schematic top view of the measuring comb and the combustion chamber illustrated in FIG. 1; - Figure 3 shows a perspective view of the comb body of a measuring comb according to the invention; FIG. 4 is a diagrammatic view from above of an orientation of an inadmissible measuring comb; FIG. 5 is a schematic view from above of an orientation of an acceptable measuring comb; FIG. 6 represents a flowchart representing various steps of an exemplary embodiment of the measuring method according to the invention. DETAILED DESCRIPTION FIGS. 1 and 2 each represent a diagrammatic view, respectively in profile and from above, of a measuring comb 10 according to the invention in position for measuring the flow of gases at the outlet of a combustion chamber. 1 of the turbomachine, generally annular and having an axis of revolution 2. The combustion chamber 1 has a gyration range G of the gas flow at its outlet defined between extreme values of gyration respectively corresponding to an operation of the combustion chamber. 1 under idle and full throttle conditions. The measuring comb 10 comprises a comb body 11 designed to face the outlet 3 of the combustion chamber 1. An example of a comb body 11 is shown in FIG.
    [0005] The comb body 11 preferably has a generally elongate shape and shaped so as not to disturb the gas flow upstream of the comb body 11, and thus not to distort the measurements made. The measuring comb 10 further comprises a plurality of measuring orifices 13 formed in the comb body 11 and configured to collect gas flowing at the outlet 3 from the combustion chamber 1. The measuring orifices 13 exhibit axes 12 extending in the same plane P. In the example illustrated in Figure 3, the axes 12 of the measuring orifices 13 are parallel to each other. According to one variant, the axes 12 of the measuring orifices 13 extend generally in a fan shape. In this variant, the axes 12 of the measuring orifices 13 adjacent to the inner and outer radii of the wall of the combustion chamber 1 are for example generally parallel to said wall respectively at the inner and outer radii. The measuring orifices 13 have a detection limit range L of the gyration of the gas flow beyond which the measuring orifices 13 can not take the gases with greater gyration. This detection limit range L is, for example, +/- 15 to 20 ° relative to the axis 12 of each of the measuring orifices 13. When the gyration range G of the gas flow at the outlet of the combustion chamber 1 and the detection limit range L overlap as illustrated in FIG. 4, the orientation of the measurement ports 13 is not permissible. The measuring orifices 13 are connected to meters 14 configured to measure the temperature and / or the pressure and / or the composition of the gases sampled by the measuring orifices 13. The meters 14 may be configured to perform individual measurements. that is to say by measuring orifice 13, or averaged over all the measuring orifices 13. The measuring orifices 13 are for example connected to the measurers 14 via channels 15. The measuring comb 10 further comprises an arm 16 configured to incline the comb body 11 so that the plane P of the axes 12 of the measuring orifices 13 and the axis of revolution 2 form a non-zero angle of turn, the same gyration angle a being maintained for tests under idling and full throttle conditions of the combustion chamber 1. More precisely, the angle of turn a is chosen so that the turning range G of the gas flow at the outlet of the combustion chamber 1 is included in the p detection limit L as illustrated in Figure 5. In this configuration, the orientation of the comb body 11 is permissible.
    [0006] The angle of gyration is preferably between 5 and 15 °. In the illustrated example, the angle of turn a is between 8 and 9 °. The measuring comb 10 thus makes it possible to incline the measuring orifices 13 with respect to the axis of revolution 2, so as to take into account the gyratory effect of the gas flow at the outlet of the combustion chamber 1, and this also for tests in idling or full throttle conditions of the combustion chamber 1. Thus, it is possible to perform a series of tests between the idle and the full gas of the combustion chamber 1 without modifying the angle of gyration has measuring ports 13.
    [0007] In the example illustrated in FIG. 1, the arm 16 comprises a first portion 17 extending along the axis of revolution 2, and a second portion 18 extending generally radially from the first portion 17 and connecting the first portion. 17 to the comb body 11. According to a variant, the arm 16 comprises a ring extending the axis of revolution 2, on which the comb body 11 is clamped. The arm 16 may be connected to a plurality of comb bodies 11 whose measurement orifices 13 have the same inclination relative to the axis of revolution 2. The arm 16 may for example comprise a plurality of second portions 18 extending radially from the first portion. 17, each of the second portions 18 being connected to a comb body 11. Alternatively, a plurality of comb bodies 11 may be clamped on the ring. The comb bodies 11 are advantageously distributed equidistantly in a plane generally perpendicular to the axis of revolution 2. The measuring comb 10 also comprises a motor 19 configured to drive the comb body 11 in rotation about the axis of rotation. revolution 2. The motor 19 is for example connected to the first portion 17 of the arm 16 or to the ring on which the comb body 11 is clamped. Fig. 6 is a flowchart illustrating a method for measuring the flow of gas at the outlet 3 of the combustion chamber 1. The method 20 comprises the steps of: positioning the comb body 11 opposite the output 3 of the combustion chamber 1, inclination 22 of the comb body 11 at the outlet of the combustion chamber 1 so that the plane P of the axes 12 of the measuring orifices 13 and the axis of revolution 2 form the angle of gyration a non-zero, the same angle of gyration being maintained for tests in conditions of idling and full throttle of the combustion chamber 1, - rotating 23 of the comb body 11 around the axis of revolution 2, 10 - sampling 24 of the gases flowing at the outlet 3 of the combustion chamber 1 through the measuring orifices 13, and - measurement 25 of the temperature and / or the pressure and / or the chemical composition of the gases sampled . The angle of turn a is defined so that it can perform with the same angle of gyration tests under idling conditions and full throttle of the combustion chamber 1. For this, a gyration of the output gas flow of the combustion chamber 1 is calculated under idling and full throttle conditions of the combustion chamber 1 so as to determine the gyration range G of the gas flow at the outlet of the combustion chamber 1, and the angle of Gyration a 20 is chosen so that the gyration range G of the gas flow at the outlet of the combustion chamber 1 is included in the limit range of detection of the measuring orifices 13. The method 20 thus makes it possible to incline the orifices of measuring 13 with respect to the axis of revolution 2, so as to take into account the gyratory effect of the gas flow at the outlet 3 of the combustion chamber 1, and this as well for operating conditions of idling or full combustion chamber gas 1. Ain if, it is possible to carry out a series of tests between the idle and the full gas of the combustion chamber 1 without modifying the angle of gyration with measuring orifices 13.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A method (20) for measuring the flow of gases at the outlet of a generally annular turbomachine combustion chamber (1), said combustion chamber having an axis of revolution (2), in which (21) is positioned a comb of measuring (10) at the outlet of the combustion chamber (1), in order to take the gases flowing out of the latter, said measuring comb (10) comprising a plurality of measurement orifices (13) whose axes (12) extend in the same plane (P), characterized in that the measuring comb (11) is inclined (22) at the outlet of said chamber, so that the aforementioned plane (P) of the axes (12) ) measuring orifices (13) and the axis of revolution (2) form a non-zero turning angle (a), and that the same turning angle (a) is maintained for tests under idle conditions and full gas of the combustion chamber (1).
    [0002]
    2. Method (20) according to claim 1, wherein a gyration of the gas flow at the outlet of the combustion chamber (1) is calculated under the conditions of idling and full gas of the combustion chamber (1) so determining a turning range (G) of the gas flow at the outlet of the combustion chamber (1).
    [0003]
    3. Method (20) according to claim 2, wherein the measuring orifices (13) have a limit detection range (L) of the gyration of the gas flow, and wherein the angle of gyration (a) is chosen. so that the turning range (G) of the gas flow at the outlet of the combustion chamber (1) is included in the detection limit range (L) of the measuring orifices (13).
    [0004]
    4. Method (20) according to one of claims 1 to 3, wherein the measuring comb (10) is inclined (22) at the outlet of the combustion chamber (1), so that the plane (P) of the axes (12) of the measuring orifices (13) and the axis of revolution (2) form a gyration angle (a) of between 5 and 15 °.
    [0005]
    5. Method (20) according to one of claims 1 to 4, wherein the measuring comb (10) is rotated (23) about the axis of revolution (2).
    [0006]
    6. Process (20) according to one of claims 1 to 5, wherein the temperature and / or the pressure and / or the chemical composition of the gases taken are measured (25).
    [0007]
    7. Measuring comb (10) of the flow of gas at the outlet of a combustion chamber (1) of a turbomachine, said combustion chamber (1) extending along an axis of revolution (2), said comb of measurement (10) being characterized in that it comprises means for implementing the method (20) according to one of claims 1 to 6, the measuring comb (10) comprising: - a comb body (11) intended to come opposite the outlet of the combustion chamber (1), and - a plurality of measuring orifices (13) whose axes (12) extend in the same plane (P), the orifices of measuring device (13) being configured to collect gases flowing out of the combustion chamber (1), - an arm (16) configured to incline the comb body (11) at the outlet of the combustion chamber (2) , so that the plane (P) of the axes (12) 25 measuring orifices (13) and the axis of revolution (2) form a non-zero gyration angle (a).
    [0008]
    8. Measuring comb (10) according to claim 7, wherein the axes (12) of the measuring orifices (13) extend generally fanwise. 30 3 0 2 1 74 1 11
    [0009]
    9. Measuring comb (10) according to claim 7 or claim 8, further comprising a motor (19) configured to drive the comb body (11) in rotation about the turbomachine axis (2).
    [0010]
    Measuring comb (10) according to one of Claims 7 to 9, in which the measuring orifices (13) are connected to measuring devices (14) configured for measuring the temperature and / or the pressure and / or the composition. gases taken from the measuring ports (13).
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    引用文献:
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    US4498347A|1983-03-31|1985-02-12|Rockwell International Corporation|Fluid flow measuring|
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    US6595062B1|2000-10-16|2003-07-22|Lockheed Martin Corporation|High temperature rake for suspersonic flow|
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    法律状态:
    2015-05-12| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-04| PLSC| Publication of the preliminary search report|Effective date: 20151204 |
    2016-05-13| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-26| 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 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
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    FR1454804A|FR3021741B1|2014-05-27|2014-05-27|METHOD FOR MEASURING THE FLOW OF GAS AT THE EXIT OF A TURBOMACHINE COMBUSTION CHAMBER|FR1454804A| FR3021741B1|2014-05-27|2014-05-27|METHOD FOR MEASURING THE FLOW OF GAS AT THE EXIT OF A TURBOMACHINE COMBUSTION CHAMBER|
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    PCT/FR2015/051400| WO2015181499A1|2014-05-27|2015-05-27|Measuring comb for measuring parameters of the gases exiting a turbomachine working section|
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    US15/314,043| US10190946B2|2014-05-27|2015-05-27|Measuring comb for measuring parameters of the gases exiting a turbomachine working section|
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