• 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:
    Speed reducer for a turbomachine, such as a turboprop, comprising intermeshing rotating parts, characterized in that a first rotating part (16 ') comprises a pinion (26') with helical gear meshing with a a helical gear with a second rotating part, said first rotating part being provided with means (34) for measuring the axial forces to which it is subjected due to the transmission of a torque by said second rotating part, said means measuring means being configured to be connected to means (38) for calculating said rotational torque from an output signal of said measuring means.
    公开号:FR3025010A1
    申请号:FR1457872
    申请日:2014-08-19
    公开日:2016-02-26
    发明作者:Antoine Mathieu
    申请人:Hispano Suiza SA；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The present invention relates to a speed reducer for a turbomachine such as a turboprop. STATE OF THE ART A turbomachine may comprise one or more mechanical speed reducers. This is particularly the case of a turboprop engine whose propeller (not faired) is rotated by a turbine shaft via a speed reducer, commonly called PGB which is the acronym for Propeller Gear Box . There are several types of speed reducers such as planetary reduction gearboxes, chain drives, worm gearboxes, intermediate drive trains, etc. All these reducers comprise rotating parts intermeshed with each other. The present invention is preferably but not exclusively applicable to the transmission line intermediate reducer (also called compound reducer). In the present art, such a speed reducer comprises an input line and an output line driven by the input line through two intermediate transmission lines. The power transmitted by the input line is separated between the intermediate lines before being transferred to the output line. The intermediate transmission lines are parallel and each comprise a shaft carrying an input gear engrained with the input line and an output gear engrained with the output line. The input gears of the two intermediate transmission lines are identical and include straight teeth. It has already been proposed to equip a turbomachine gearbox with 30 means for measuring or calculating the torque transmitted to a rotating part by another rotating part. The accuracy of the control of the torque 3025010 2 of rotation influences in particular the accuracy of the power supplied by the turbomachine and makes it possible to optimize the lifetime of the gearbox. However, the currently proposed technologies are complex and cumbersome and therefore difficult to use in the aforementioned type of reducer 5. For example, there is known a technology in which the rotational torque is calculated from torsion forces which are determined from a torsion angle measured between a transmission shaft between two rotating parts, and a control shaft. The twist angle is measured by means of a tone wheel associated with each shaft and an inductive sensor. This technology is complex to implement and cumbersome. SUMMARY OF THE INVENTION The present invention proposes in particular to regulate the power supplied by a turbomachine, by a precise measurement of a torque in a speed reducer. The invention proposes a speed reducer for a turbomachine, such as a turboprop, comprising intermeshing rotating parts, characterized in that a first rotating part comprises a helical gear gear meshing with a pinion gear. helical cut of a second rotating part, said first rotating part being equipped with means for measuring the axial forces to which it is subjected because of the transmission of a torque by said second rotating part, said measuring means being configured to be connected to means for calculating said rotational torque from an output signal of said measuring means. In the present application, the term "rotating part" in particular refers to a part intended for a mechanical power transmission.
    [0002] The invention thus proposes to calculate the rotational torque from a measurement of axial forces. Indeed, as will be explained more in detail below, the axial forces to which a rotating part in operation is directly proportional to the torque applied to it. The axial forces are here generated by the co-operation of the helical teeth of the rotating parts. The invention thus proposes to replace straight teeth of the prior art by helical teeth to ensure the generation of axial forces. Although some prior art gearboxes already include helical gear teeth, they are used for other reasons (efficiency, noise reduction, etc.). During rotation of the second rotating part, the latter causes the first rotating part and applies axial forces due to the cooperation of their helical teeth. In this case, the second rotating part is a driving part and the first rotating part is a driven part. The axial forces are measured by the measuring means which are configured to emit an output signal corresponding to the level of axial forces detected and intended to be transmitted to means for calculating the torque. The gearbox according to the invention may comprise one or more of the following features, taken alone or in combination with each other: said measuring means are mounted on a guide bearing of said first rotating part; said guide bearing is a rolling bearing and said measuring means are mounted on an outer ring of said rolling bearing; Said measuring means are mounted between the outer ring of the rolling bearing and a housing of the gearbox; said measuring means are integrated with said guide bearing; said first rotating part is an input, intermediate or output line of the reducer.
    [0003] The present invention also relates to a turbomachine, characterized in that it comprises at least one gear as described above. The reducer may include an output line configured to drive a non-faired turbo propeller. Preferably, the turbomachine comprises a computer comprising said calculating means. The turbomachine is preferably an aircraft turboprop. DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1 is a diagrammatic perspective view of a gear reducer with two intermediate transmission lines; FIG. 2 is a diagrammatic view of an intermediate transmission line, according to the prior art; FIG. a schematic view of an intermediate transmission line, according to one embodiment of the invention, and FIG. 4 is a schematic view of an intermediate transmission line, according to an alternative embodiment of the invention. DETAILED DESCRIPTION FIG. 1 is a schematic representation of a speed reducer with two intermediate transmission lines, this reducer comprising essentially four parts: an input line 12, an output line 14 and two intermediate lines of transmission. transmission 16 which are driven by the input line 12 and in turn drive the output line 14. The various parts 12, 14, 16 of the gearbox form rotating parts and are generally mounted in a housing of the reducer which n is not shown here, this housing having a first port for the passage of the input line and its connection to a first element of a turbomachine for example, and a second port for the passage of the output line and its connection to a second element of the turbomachine. The first element is for example a turbine shaft of the turbomachine and the second element is a drive shaft of a propeller of this turbomachine in the case where the latter is a turboprop. The input line 12 comprises a shaft 18 carrying a pinion 20 with external external teeth. The pinion 20 and the shaft 18 are coaxial and rotate about the same axis denoted B. The exit line 14 comprises a shaft 22 carrying a pinion 24 with external right teeth. The pinion 24 and the shaft 22 are coaxial and rotate about the same axis noted A. They rotate here in the same direction of rotation as the pinion 20 and the shaft 18 of the input line.
    [0004] The input and output lines 12, 14 are parallel. Their axes of rotation A, B are therefore parallel. The intermediate transmission lines 16 are substantially parallel and identical. Each line 16 has a shaft 25 which carries an input gear 26 at one end and an output gear 28 at a second end. The output gears 28 are meshed with the pinion 24 of the output line 14. The input gears 26 are meshing with the pinion 20 of the input line 12. The pinions 26, 28 are with straight external gears. Each shaft 25 and its pinions 26, 28 are coaxial and rotate about the same axis C, parallel to the axes A and B. FIG. 2 shows an intermediate transmission line 16 according to the prior art, whose gears 26, 28 have straight teeth. References 30 and 32 denote guide bearings of the transmission line, which are mounted between the shaft 25 of the line and the housing of the gearbox (not shown). The bearings 30, 32 here are rolling bearings, the bearing 30 being a ball bearing located at one end of the shaft 25 and the bearing 32 being a roller bearing located at the opposite end of the shaft. . FIG. 3 shows an embodiment of the invention which is here applied to an intermediate transmission line 16 'but which can be applied to any rotating part of the gearbox. The intermediate line 16 'differs from that 16 of Figure 2 essentially in that at least one of its teeth is helical and in that it is further associated with means for measuring the axial forces during transmission a couple of rotation.
    [0005] In the example shown, it is the toothing of the pinion 26 'which cooperates with the input line 12, which is helical. The teeth of the pinion 20 of the input line 12 must have a shape complementary to that of the pinion 26 'of the intermediate line 16' and therefore has a helical shape. Alternatively or additional feature, the other pinion 28 of the line 16 '15 may have a helical toothing. When transmitting a torque from the input line 12 to the intermediate line 16, the pinion 20 of the input line applies axial forces to the toothing of the pinion 26 'of the intermediate line, by the intermediate helical teeth. These axial forces are directly proportional to the transmitted torque. According to the invention, the transmitted torque is calculated from a measured value of the axial forces applied to the intermediate line 16 '. For this purpose, the intermediate line 16 'is equipped with means for measuring the aforementioned axial forces.
    [0006] In the embodiment of FIG. 3, the measuring means 34 are integrated in the guide bearing 30 which is thus of the instrumented type. These measuring means 34 are for example configured to measure the axial forces applied to the line 16 'from the relative axial displacements between the outer and inner rings of the bearing 30.
    [0007] In the variant embodiment of FIG. 4, the measuring means 34 are mounted between the outer ring of the guide bearing 30 and the casing 36 of the gearbox. The measuring means 34 comprise, for example, a strain gauge type strain sensor (extensometric or piezoresistive), of the displacement measuring type, of the optical fiber type, etc. They are for example configured to measure the axial forces applied to the line 16 'from the relative axial displacements between the outer ring of the bearing 30 and the housing 36. The measuring means 34 are configured to emit an output signal which is transmitted to computing means 38, such as a calculator of the turbomachine, for calculating the rotational torque applied to the line 16 '. For this purpose, the calculating means 38 can use the following mathematical relation: r * Fa 15 CP tan (f3) with C: the torque transmitted by the toothing (in Nm), rp: the pitch radius of the pinion (in m), p: the helix angle of the toothing (in rad), and Fa: the axial force induced by the toothing (in N).
    [0008] Although the invention has been described above in connection with an intermediate line of the gearbox, it could be applied in the same way to the input line or the output line of the gearbox. 25
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Speed reducer (10) for a turbomachine, such as a turboprop, comprising interengaging rotating parts (12, 14, 16 '), characterized in that a first rotating part (16') comprises a pinion (26 ') with helical gear meshing with a helical gear with a second rotating part (12), said first rotating part being equipped with means (34) for measuring the axial forces to which it is subjected due to the transmission a rotational torque by said second rotating part, said measuring means being configured to be connected to means (38) for calculating said rotational torque from an output signal of said measuring means.
    [0002]
    2. Gearbox (10) according to claim 1, characterized in that said measuring means (34) are mounted on a bearing (30) for guiding said first rotating part (16 ').
    [0003]
    3. Gearbox (10) according to claim 2, characterized in that said guide bearing (30) is a rolling bearing and in that said measuring means (34) are mounted on an outer ring of said rolling bearing.
    [0004]
    4. Gearbox (10) according to claim 3, characterized in that said measuring means (34) are mounted between the outer ring of the rolling bearing and a housing (36) of the gear.
    [0005]
    5. Gearbox (10) according to claim 2 or 3, characterized in that said measuring means (34) are integrated with said guide bearing (30).
    [0006]
    6. gearbox (10) according to one of the preceding claims, characterized in that said first rotating part is an input line (12), intermediate (16 ') or output (14) of the reducer.
    [0007]
    7. Turbomachine, characterized in that it comprises at least one gear (10) according to one of the preceding claims. 3025010 9
    [0008]
    8. The turbomachine according to claim 7, characterized in that the gearbox (10) comprises an output line (14) configured to drive an unducted propeller turboprop.
    [0009]
    9. A turbomachine according to claim 7 or 8, characterized in that it comprises a computer comprising said calculating means (38).
    [0010]
    10. Turbomachine according to one of claims 7 to 9, characterized in that it is a turboprop.
    类似技术:
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    同族专利:
    公开号 | 公开日
    WO2016027024A1|2016-02-25|
    FR3025010B1|2021-10-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2899822A|1959-08-18|Matthews |
    US6490935B1|1999-09-28|2002-12-10|The Timken Company|System for monitoring the operating conditions of a bearing|FR3106155A1|2020-01-09|2021-07-16|Safran Aircraft Engines|GEAR LUBRICATION SYSTEM FOR AN AIRCRAFT TURBOMACHINE|DE2648192C2|1976-10-25|1985-08-01|Wolfhard Dipl.-Ing. 6108 Weiterstadt Sack|Device for measuring and / or monitoring the axial force on a tool spindle|
    FR2736979B1|1995-07-21|1997-08-14|Roulements Soc Nouvelle|DYNAMOMETRIC SENSOR DEVICE AND METHOD FOR BEARINGS AND BEARINGS|
    US6988420B2|2003-11-17|2006-01-24|Lufkin Industries, Inc.|Method and apparatus for applying dynamic loads to a locked gear train for testing power transmission components|DE102016221357A1|2016-10-28|2018-05-03|Deere & Company|wheel gear|
    CN106774482B|2016-11-17|2020-06-19|深圳市旗客智能技术有限公司|Rotating shaft rotating state detecting and controlling device|
    EP3330493B1|2016-12-02|2019-05-01|Rolls-Royce Deutschland Ltd & Co KG|Control system and method for a gas turbine engine|
    法律状态:
    2015-08-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-26| PLSC| Search report ready|Effective date: 20160226 |
    2016-06-20| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-17| PLFP| Fee payment|Year of fee payment: 4 |
    2017-08-25| CD| Change of name or company name|Owner name: HISPANO-SUIZA, FR Effective date: 20170725 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1457872A|FR3025010B1|2014-08-19|2014-08-19|SPEED REDUCER FOR A TURBOMACHINE|FR1457872A| FR3025010B1|2014-08-19|2014-08-19|SPEED REDUCER FOR A TURBOMACHINE|
    PCT/FR2015/052178| WO2016027024A1|2014-08-19|2015-08-07|Speed reducer for a turbomachine|
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