WO2016027024A1 - Speed reducer for a turbomachine - Google Patents

Speed reducer for a turbomachine Download PDF

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Publication number
WO2016027024A1
WO2016027024A1 PCT/FR2015/052178 FR2015052178W WO2016027024A1 WO 2016027024 A1 WO2016027024 A1 WO 2016027024A1 FR 2015052178 W FR2015052178 W FR 2015052178W WO 2016027024 A1 WO2016027024 A1 WO 2016027024A1
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WIPO (PCT)
Prior art keywords
rotating part
turbomachine
gearbox
line
measuring means
Prior art date
Application number
PCT/FR2015/052178
Other languages
French (fr)
Inventor
Antoine MATHIEU
Original Assignee
Hispano-Suiza
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Publication of WO2016027024A1 publication Critical patent/WO2016027024A1/en

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G01L5/0009—Force sensors associated with a bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H1/00—Toothed gearings for conveying rotary motion
    • F16H1/02—Toothed gearings for conveying rotary motion without gears having orbital motion
    • F16H1/20—Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members
    • F16H1/22—Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with a plurality of driving or driven shafts; with arrangements for dividing torque between two or more intermediate shafts

Definitions

  • the present invention relates to a speed reducer for a turbomachine such as a turboprop.
  • 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 .
  • speed reducers such as planetary, chain, worm gear, intermediate drive gear reducers, and so on. 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).
  • 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.
  • 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 toothed gear. a second rotating part, said first rotating part being equipped with means for measuring the axial forces to which it is subjected due to the transmission of a rotational torque by said second rotating part, said measuring means being mounted on a rolling bearing for guiding said first rotating part and being configured to be connected to means for calculating said rotational torque from an output signal of said measuring means, by the following mathematical relationship: with C: the rotation torque (in Nm), r p : the pitch radius of the bearing toothing of the first rotating part (in m), ⁇ : the helix angle of this toothing (in rad), and Fa: the axial force induced by this toothing (in N).
  • rotating part in particular refers to a part intended for a mechanical power transmission.
  • the invention thus proposes to calculate the rotational torque from a measurement of axial forces. Indeed, as will be explained in more detail in the following, 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.
  • some prior art gearboxes already include helical gear teeth, they are used for other reasons (efficiency, noise reduction, etc.).
  • the second rotating part causes the first rotating part and applies axial forces due to the cooperation of their helical teeth.
  • 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 reducer according to the invention may comprise one or more of the following characteristics, taken separately or in combination with each other:
  • said rolling bearing is a ball bearing
  • 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.
  • 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 an unducted propeller of the turboprop.
  • the turbomachine comprises a computer comprising said calculating means.
  • the turbomachine is preferably an aircraft turboprop.
  • FIG. 1 is a schematic perspective view of a speed reducer with two intermediate transmission lines
  • FIG. 2 is a schematic view of an intermediate transmission line, according to the prior art
  • FIG. 3 is a schematic view of an intermediate transmission line, according to one embodiment of the invention.
  • FIG. 4 is a schematic view of an intermediate transmission line, according to an alternative embodiment of the invention.
  • FIG. 1 schematically represents 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 transmission lines 16 which are driven by the input line 12 and in turn drive the output line 14.
  • the different parts 12, 14, 16 of the gearbox form rotating parts and are generally mounted in a housing of the gearbox which is not shown here, this casing 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 orifice 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 around the same axis noted B.
  • the output line 14 comprises a shaft 22 carrying a pinion 24 with external external 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.
  • 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 a first 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 gears 26, 28 are coaxial and rotate about the same axis noted C, parallel to the axes A and B.
  • Figure 2 shows an intermediate transmission line 16 according to the prior art, the gears 26, 28 are 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 gear (not shown).
  • the bearings 30, 32 are here 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 represents 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.
  • 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.
  • the other pinion 28 of the line 16 ' may have a helical toothing.
  • the transmitted torque is calculated from a measured value of the axial forces applied to the intermediate line 16 '.
  • the intermediate line 16 ' is equipped with means for measuring the aforementioned axial forces.
  • the measurement means In the embodiment of FIG. 3, the measurement means
  • 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
  • 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 calculation means 38, such as a calculator of the turbomachine, for calculating the torque applied to the line 16 '.
  • the calculation means 38 use the following mathematical relationship: r * F

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  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • General Details Of Gearings (AREA)
  • Gear Transmission (AREA)

Abstract

A speed reducer for a turbomachine, such as a turboprop, comprising rotating parts meshed with each other, characterised in that a first rotating part (16') comprises a helical-tooth pinion (26') meshed with a helical-tooth pinion of a second rotating part, said first rotating part being provided with means (34) for measuring the axial forces to which it is subjected as a result of the transmission of a rotational torque by said second rotating part, said measurement means being configured to be linked to means (38) for calculating said rotational torque from an output signal from said measurement means.

Description

Réducteur de vitesse pour une turbomachine  Speed reducer for a turbomachine
DOMAINE TECHNIQUE TECHNICAL AREA
La présente invention concerne un réducteur de vitesse pour une turbomachine telle qu'un turbopropulseur.  The present invention relates to a speed reducer for a turbomachine such as a turboprop.
ETAT DE L'ART  STATE OF THE ART
Une turbomachine peut comprendre un ou plusieurs réducteurs mécaniques de vitesse. C'est notamment le cas d'un turbopropulseur dont l'hélice (non carénée) est entraînée en rotation par un arbre de turbine par l'intermédiaire d'un réducteur de vitesse, appelé couramment PGB qui est l'acronyme de Propeller Gear Box.  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 .
Il existe plusieurs types de réducteur de vitesse tels que les réducteurs à trains épicycloïdaux, à chaînes, à vis sans fin, à lignes intermédiaires d'entraînement, etc. Tous ces réducteurs comprennent des parties tournantes engrenées les unes avec les autres. La présente invention s'applique de préférence mais non exclusivement au réducteur à lignes intermédiaires de transmission (aussi appelé réducteur composé ou « compound »).  There are several types of speed reducers such as planetary, chain, worm gear, intermediate drive gear reducers, and so on. 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).
Dans la technique actuelle, un réducteur de vitesse de ce type comprend une ligne d'entrée et une ligne de sortie entraînée par la ligne d'entrée par l'intermédiaire de deux lignes intermédiaires de transmission. La puissance transmise par la ligne d'entrée est séparée entre les lignes intermédiaires avant d'être transférée à la ligne de sortie. Les lignes intermédiaires de transmission sont parallèles et comportent chacune un arbre portant un pignon d'entrée engrainé avec la ligne d'entrée et un pignon de sortie engrainé avec la ligne de sortie. Les pignons d'entrée des deux lignes intermédiaires de transmission sont identiques et comprennent des dentures droites.  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.
On a déjà proposé d'équiper un réducteur de turbomachine de moyens de mesure ou de calcul du couple de rotation transmis à une pièce tournante par une autre pièce tournante. La précision du contrôle du couple de rotation influe notamment sur la précision de la puissance fournie par la turbomachine et permet d'optimiser la durée de vie du réducteur. Cependant, les technologies actuellement proposées sont complexes et encombrantes et donc difficilement utilisables dans le type de réducteur précité. It has already been proposed to equip a turbomachine gearbox means for measuring or calculating the torque transmitted to a rotating part by another rotating part. The accuracy of the torque control of rotation influences in particular the precision 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.
On connaît par exemple une technologie dans laquelle le couple de rotation est calculé à partir d'efforts de torsion qui sont déterminés à partir d'un angle de torsion mesuré entre un arbre de transmission entre deux parties tournantes, et un arbre témoin. L'angle de torsion est mesuré au moyen d'une roue phonique associée à chaque arbre et d'un capteur inductif. Cette technologie est complexe à mettre en œuvre et encombrante. EXPOSE DE L'INVENTION  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 torsion 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
La présente invention propose notamment de réguler la puissance fournie par une turbomachine, par une mesure précise d'un couple de rotation dans un réducteur de vitesse.  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.
L'invention propose un réducteur de vitesse pour une turbomachine, telle qu'un turbopropulseur, comprenant des parties tournantes engrenées les unes avec les autres, caractérisé en ce qu'une première partie tournante comprend un pignon à denture hélicoïdale engrenée avec un pignon à denture hélicoïdale d'une seconde partie tournante, ladite première partie tournante étant équipée de moyens de mesure des efforts axiaux auxquels elle est soumise du fait de la transmission d'un couple de rotation par ladite seconde partie tournante, lesdits moyens de mesure étant montés sur un palier à roulement de guidage de ladite première partie tournante et étant configurés pour être reliés à des moyens de calcul dudit couple de rotation à partir d'un signal de sortie desdits moyens de mesure, par la relation mathématique suivante :
Figure imgf000003_0001
avec C : le couple de rotation (en N.m), rp : le rayon primitif de la denture du palier de la première partie tournante (en m), β : l'angle d'hélice de cette denture (en rad), et Fa : l'effort axial induit par cette denture (en N). 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 toothed gear. a second rotating part, said first rotating part being equipped with means for measuring the axial forces to which it is subjected due to the transmission of a rotational torque by said second rotating part, said measuring means being mounted on a rolling bearing for guiding said first rotating part and being configured to be connected to means for calculating said rotational torque from an output signal of said measuring means, by the following mathematical relationship:
Figure imgf000003_0001
with C: the rotation torque (in Nm), r p : the pitch radius of the bearing toothing of the first rotating part (in m), β: the helix angle of this toothing (in rad), and Fa: the axial force induced by this toothing (in N).
Dans la présente demande, on entend par partie tournante notamment une partie destinée à une transmission de puissance mécanique.  In the present application, the term "rotating part" in particular refers to a part intended for a mechanical power transmission.
L'invention propose ainsi de calculer le couple de rotation à partir d'une mesure d'efforts axiaux. En effet, comme cela sera expliqué plus en détail dans ce qui suit, les efforts axiaux auxquels est soumise une partie tournante en fonctionnement sont directement proportionnels au couple de rotation appliqué à celle-ci. Les efforts axiaux sont ici générés par la coopération des dentures hélicoïdales des parties tournantes. L'invention propose ainsi de remplacer des dentures droites de la technique antérieure par des dentures hélicoïdales pour assurer la génération des efforts axiaux. Bien que certains réducteurs de la technique antérieure comprennent déjà des dentures hélicoïdales, elles sont utilisées pour d'autres raisons (rendement, réduction du bruit, etc.). Lors de la rotation de la seconde partie tournante, celle-ci entraîne la première partie tournante et lui applique des efforts axiaux du fait de la coopération de leurs dentures hélicoïdales. Dans ce cas, la seconde partie tournante est une partie menante et la première partie tournante est une partie menée. Les efforts axiaux sont mesurés par les moyens de mesure qui sont configurés pour émettre un signal de sortie correspondant au niveau d'efforts axiaux détecté et destiné à être transmis à des moyens de calcul du couple de rotation.  The invention thus proposes to calculate the rotational torque from a measurement of axial forces. Indeed, as will be explained in more detail in the following, 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, it 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.
Dans le document US-B1 -6,490,935, c'est la composante axiale d'une force de résistance qui est mesurée. Cette composante axiale est obtenue grâce à un palier à rouleaux coniques. Le document permet ainsi de déterminer les efforts axiaux sur un roulement et non pas les efforts axiaux auxquels un arbre est directement soumis du fait de la transmission d'un couple de rotation. Dans le document US-A-2,899,822, les moyens de mesure ne sont pas situés sur un palier à roulement et n'utilisent pas la relation mathématique ci-dessus. In US Pat. No. 6,490,935, it is the axial component of a resistance force which is measured. This axial component is obtained thanks to a tapered roller bearing. The document thus makes it possible to determine the axial forces on a bearing and not the axial forces to which a shaft is directly subjected because of the transmission of a torque. In US-A-2,899,822, the measuring means are not located on a rolling bearing and do not use the mathematical relationship above.
Le réducteur selon l'invention peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément ou en combinaison les unes avec les autres :  The reducer according to the invention may comprise one or more of the following characteristics, taken separately or in combination with each other:
- ledit palier à roulement est un palier à billes,  said rolling bearing is a ball bearing,
- lesdits moyens de mesure sont montés sur une bague externe dudit palier à roulement ;  said measuring means are mounted on an outer ring of said rolling bearing;
- lesdits moyens de mesure sont montés entre la bague externe du palier à roulement et un carter du réducteur ; said measuring means are mounted between the outer ring of the rolling bearing and a housing of the gearbox;
- lesdits moyens de mesure sont intégrés audit palier de guidage ;  said measuring means are integrated with said guide bearing;
- ladite première partie tournante est une ligne d'entrée, intermédiaire ou de sortie du réducteur.  said first rotating part is an input, intermediate or output line of the reducer.
La présente invention concerne également une turbomachine, caractérisée en ce qu'elle comporte au moins un réducteur tel que décrit ci- dessus.  The present invention also relates to a turbomachine, characterized in that it comprises at least one gear as described above.
Le réducteur peut comprendre une ligne de sortie configurée pour entraîner une hélice non carénée du turbopropulseur.  The reducer may include an output line configured to drive an unducted propeller of the turboprop.
De préférence, la turbomachine comprend un calculateur comportant lesdits moyens de calcul.  Preferably, the turbomachine comprises a computer comprising said calculating means.
La turbomachine est de préférence un turbopropulseur d'aéronef. The turbomachine is preferably an aircraft turboprop.
DESCRIPTION DES FIGURES DESCRIPTION OF THE FIGURES
L'invention sera mieux comprise et d'autres détails, caractéristiques et avantages de l'invention apparaîtront plus clairement à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :  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:
- la figure 1 est une vue schématique en perspective d'un réducteur de vitesse à deux lignes intermédiaires de transmission,  FIG. 1 is a schematic perspective view of a speed reducer with two intermediate transmission lines,
- la figure 2 est une vue schématique d'une ligne intermédiaire de transmission, selon la technique antérieure, - la figure 3 est une vue schématique d'une ligne intermédiaire de transmission, selon un mode de réalisation de l'invention, et FIG. 2 is a schematic view of an intermediate transmission line, according to the prior art, FIG. 3 is a schematic view of an intermediate transmission line, according to one embodiment of the invention, and
- la figure 4 est une vue schématique d'une ligne intermédiaire de transmission, selon une variante de réalisation de l'invention.  - Figure 4 is a schematic view of an intermediate transmission line, according to an alternative embodiment of the invention.
DESCRIPTION DETAILLEE  DETAILED DESCRIPTION
La figure 1 représente de manière schématique un réducteur 10 de vitesse à deux lignes intermédiaires de transmission, ce réducteur 10 comportant pour l'essentiel quatre parties : une ligne d'entrée 12, une ligne de sortie 14 et deux lignes intermédiaires de transmission 16 qui sont entraînées par la ligne d'entrée 12 et entraînent à leur tour la ligne de sortie 14.  FIG. 1 schematically represents 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 transmission lines 16 which are driven by the input line 12 and in turn drive the output line 14.
Les différentes parties 12, 14, 16 du réducteur forment des parties tournantes et sont en général montées dans un carter du réducteur qui n'est pas représenté ici, ce carter comportant un premier orifice pour le passage de la ligne d'entrée et son raccordement à un premier élément d'une turbomachine par exemple, et un second orifice pour le passage de la ligne de sortie et son raccordement à un second élément de la turbomachine. Le premier élément est par exemple un arbre de turbine de la turbomachine et le second élément est un arbre d'entraînement d'une hélice de cette turbomachine dans le cas où cette dernière est un turbopropulseur.  The different parts 12, 14, 16 of the gearbox form rotating parts and are generally mounted in a housing of the gearbox which is not shown here, this casing 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 orifice 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.
La ligne d'entrée 12 comprend un arbre 18 portant un pignon 20 à denture externe droite. Le pignon 20 et l'arbre 18 sont coaxiaux et tournent autour d'un même axe noté B.  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 around the same axis noted B.
La ligne de sortie 14 comprend un arbre 22 portant un pignon 24 à denture externe droite. Le pignon 24 et l'arbre 22 sont coaxiaux et tournent autour d'un même axe noté A. Ils tournent ici dans le même sens de rotation que le pignon 20 et l'arbre 18 de la ligne d'entrée.  The output line 14 comprises a shaft 22 carrying a pinion 24 with external external 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.
Les lignes d'entrée et de sortie 12, 14 sont parallèles. Leurs axes de rotation A, B sont donc parallèles. Les lignes intermédiaires de transmission 16 sont sensiblement parallèles et identiques. Chaque ligne 16 comporte un arbre 25 qui porte un pignon d'entrée 26 à une première extrémité et un pignon de sortie 28 à une seconde extrémité. Les pignons de sortie 28 sont engrenés avec le pignon 24 de la ligne de sortie 14. Les pignons d'entrée 26 sont engrenés avec le pignon 20 de la ligne d'entrée 12. Les pignons 26, 28 sont à dentures externes droites. Chaque arbre 25 et ses pignons 26, 28 sont coaxiaux et tournent autour d'un même axe noté C, parallèle aux axes A et B. 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 a first 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 gears 26, 28 are coaxial and rotate about the same axis noted C, parallel to the axes A and B.
La figure 2 représente une ligne intermédiaire de transmission 16 selon la technique antérieure, dont les pignons 26, 28 sont à dentures droites. Les références 30 et 32 désignent des paliers de guidage de la ligne de transmission, qui sont montés entre l'arbre 25 de la ligne et le carter du réducteur (non représenté). Les paliers 30, 32 sont ici des paliers à roulement, le palier 30 étant un palier à billes situé à une extrémité de l'arbre 25 et le palier 32 étant un palier à rouleaux situé à l'extrémité opposée de l'arbre.  Figure 2 shows an intermediate transmission line 16 according to the prior art, the gears 26, 28 are 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 gear (not shown). The bearings 30, 32 are here 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.
La figure 3 représente un mode de réalisation de l'invention qui est ici appliqué à une ligne intermédiaire de transmission 16' mais qui peut s'appliquer à toute partie tournante de réducteur.  FIG. 3 represents 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.
La ligne intermédiaire 16' diffère de celle 16 de la figure 2 essentiellement en ce qu'au moins l'une de ses dentures est hélicoïdale et en ce qu'elle est en outre associée à des moyens de mesure des efforts axiaux lors de la transmission d'un couple de rotation.  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.
Dans l'exemple représenté, c'est la denture du pignon 26' qui coopère avec la ligne d'entrée 12, qui est hélicoïdale. La denture du pignon 20 de la ligne d'entrée 12 doit avoir une forme complémentaire de celle du pignon 26' de la ligne intermédiaire 16' et a donc une forme hélicoïdale. En variante ou en caractéristique additionnelle, l'autre pignon 28 de la ligne 16' peut avoir une denture hélicoïdale. Lors de la transmission d'un couple de rotation de la ligne d'entrée 12 à la ligne intermédiaire 16, le pignon 20 de la ligne d'entrée applique des efforts axiaux à la denture du pignon 26' de la ligne intermédiaire, par l'intermédiaire des dentures hélicoïdales. Ces efforts axiaux sont directement proportionnels au couple transmis. 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 '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.
Selon l'invention, le couple transmis est calculé à partir d'une valeur mesuré des efforts axiaux appliqués à la ligne intermédiaire 16'. Pour cela, la ligne intermédiaire 16' est équipée de moyens de mesure des efforts axiaux précités.  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.
Dans l'exemple de réalisation de la figure 3, les moyens de mesure In the embodiment of FIG. 3, the measurement means
34 sont intégrés dans le palier de guidage 30 qui est ainsi du type instrumenté. Ces moyens de mesure 34 sont par exemple configurés pour mesurer les efforts axiaux appliqués à la ligne 16' à partir des déplacements axiaux relatifs entre les bagues externe et interne du palier34 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. 30.
Dans la variante de réalisation de la figure 4, les moyens de mesure 34 sont montés entre la bague externe du palier de guidage 30 et le carter 36 du réducteur. Les moyens de mesure 34 comprennent par exemple un capteur d'effort du type à jauge de déformation (extensométrique ou piézorésistive), du type à mesure de déplacement, du type à fibre optique, etc. Ils sont par exemple configurés pour mesurer les efforts axiaux appliqués à la ligne 16' à partir des déplacements axiaux relatifs entre la bague externe du palier 30 et le carter 36.  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.
Les moyens de mesure 34 sont configurés pour émettre un signal de sortie qui est transmis à des moyens de calcul 38, tels qu'un calculateur de la turbomachine, pour calculer le couple de rotation appliqué à la ligne 16'.  The measuring means 34 are configured to emit an output signal which is transmitted to calculation means 38, such as a calculator of the turbomachine, for calculating the torque applied to the line 16 '.
Pour cela, les moyens de calcul 38 utilisent la relation mathématique suivante : r * Fa  For this, the calculation means 38 use the following mathematical relationship: r * F
C = C =
Figure imgf000008_0001
avec C : le couple transmis par la denture (en N.m), rp : le rayon primitif du pignon (en m), β : l'angle d'hélice de la denture (en rad), et Fa : l'effort axial induit par la denture (en N).
Figure imgf000008_0001
with C: the torque transmitted by the toothing (in Nm), r p : the pitch radius of the pinion (in m), β: the helix angle of the toothing (in rad), and Fa: the axial force induced by the toothing (in N).
Bien que l'invention ait été décrite ci-dessus en relation avec une ligne intermédiaire du réducteur, elle pourrait s'appliquer de la même façon à la ligne d'entrée ou à la ligne de sortie du réducteur.  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.

Claims

REVENDICATIONS
1. Réducteur de vitesse (10) pour une turbomachine, telle qu'un turbopropulseur, comprenant des parties tournantes (12, 14, 16') engrenées les unes avec les autres, caractérisé en ce qu'une première partie tournante (16') comprend un pignon (26') à denture hélicoïdale engrenée avec un pignon à denture hélicoïdale d'une seconde partie tournante (12), ladite première partie tournante étant équipée de moyens (34) de mesure des efforts axiaux auxquels elle est soumise du fait de la transmission d'un couple de rotation par ladite seconde partie tournante, lesdits moyens de mesure étant montés sur un palier à roulement (30) de guidage de ladite première partie tournante (16') et étant configurés pour être reliés à des moyens (38) de calcul dudit couple de rotation à partir d'un signal de sortie desdits moyens de mesure, par la relation mathématique suivante :
Figure imgf000010_0001
A speed reducer (10) for a turbomachine, such as a turboprop, comprising rotating parts (12, 14, 16 ') meshing with each other, characterized in that a first rotating part (16') comprises a pinion (26 ') with helical gear meshing with a helical gear pinion of a second rotating part (12), said first rotating part being equipped with means (34) for measuring the axial forces to which it is subjected as a result of the transmission of a rotational torque by said second rotating part, said measuring means being mounted on a rolling bearing (30) for guiding said first rotating part (16 ') and being configured to be connected to means (38); ) calculating said rotational torque from an output signal of said measuring means, by the following mathematical relationship:
Figure imgf000010_0001
avec C : le couple de rotation (en N.m), rp : le rayon primitif de la denture du palier de la première partie tournante (en m), β : l'angle d'hélice de cette denture (en rad), et Fa : l'effort axial induit par cette denture (en N).with C: the rotation torque (in Nm), r p : the pitch radius of the bearing toothing of the first rotating part (in m), β: the helix angle of this toothing (in rad), and Fa: the axial force induced by this toothing (in N).
2. Réducteur (10) selon la revendication 1 , caractérisé en ce que ledit palier à roulement (30) est un palier à billes. 2. Gearbox (10) according to claim 1, characterized in that said rolling bearing (30) is a ball bearing.
3. Réducteur (10) selon la revendication 2, caractérisé en ce que lesdits moyens de mesure (34) sont montés sur une bague externe dudit palier à roulement.  3. Gearbox (10) according to claim 2, characterized in that said measuring means (34) are mounted on an outer ring of said rolling bearing.
4. Réducteur (10) selon la revendication 3, caractérisé en ce que lesdits moyens de mesure (34) sont montés entre la bague externe du palier à roulement et un carter (36) du réducteur.  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.
5. Réducteur (10) selon la revendication 2 ou 3, caractérisé en ce que lesdits moyens de mesure (34) sont intégrés audit palier de guidage (30). 5. Gearbox (10) according to claim 2 or 3, characterized in that said measuring means (34) are integrated with said guide bearing (30).
6. Réducteur (10) selon l'une des revendications précédentes, caractérisé en ce que ladite première partie tournante est une ligne d'entrée (12), intermédiaire (16') ou de sortie (14) du réducteur. 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.
7. Turbomachine, caractérisée en ce qu'elle comporte au moins un réducteur (10) selon l'une des revendications précédentes.  7. Turbomachine, characterized in that it comprises at least one gear (10) according to one of the preceding claims.
8. Turbomachine selon la revendication 7, caractérisée en ce que le réducteur (10) comprend une ligne de sortie (14) configurée pour entraîner une hélice non carénée du turbopropulseur.  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.
9. Turbomachine selon la revendication 7 ou 8, caractérisée en ce qu'elle comprend un calculateur comportant lesdits moyens de calcul (38). 9. The turbomachine according to claim 7 or 8, characterized in that it comprises a computer comprising said calculating means (38).
10. Turbomachine selon l'une des revendications 7 à 9, caractérisée en ce qu'elle est un turbopropulseur. 10. Turbomachine according to one of claims 7 to 9, characterized in that it is a turboprop.
PCT/FR2015/052178 2014-08-19 2015-08-07 Speed reducer for a turbomachine WO2016027024A1 (en)

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FR1457872A FR3025010B1 (en) 2014-08-19 2014-08-19 SPEED REDUCER FOR A TURBOMACHINE
FR1457872 2014-08-19

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CN106774482A (en) * 2016-11-17 2017-05-31 陈翔斌 A kind of axis of rotation state-detection and control device
EP3315818A1 (en) * 2016-10-28 2018-05-02 Deere & Company Gear transmission
US20180156138A1 (en) * 2016-12-02 2018-06-07 Rolls-Royce Deutschland Ltd & Co. Kg Control system and method for a gas turbine engine
CN111089676A (en) * 2020-01-08 2020-05-01 北京仙进机器人有限公司 Rotating shaft force measuring device and manipulator with same

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FR3106155B1 (en) 2020-01-09 2022-07-15 Safran Aircraft Engines GEAR LUBRICATION SYSTEM FOR AN AIRCRAFT TURBOMACHINE

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EP3315818A1 (en) * 2016-10-28 2018-05-02 Deere & Company Gear transmission
CN106774482A (en) * 2016-11-17 2017-05-31 陈翔斌 A kind of axis of rotation state-detection and control device
CN106774482B (en) * 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
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CN111089676A (en) * 2020-01-08 2020-05-01 北京仙进机器人有限公司 Rotating shaft force measuring device and manipulator with same

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