FR3162801A1 - Multi-channel fluid transfer device with a central part comprising two concentric bodies rotationally joined by respective teeth - Google Patents

Abstract

A device (10) for transferring multiple fluid paths comprises: a central portion (20); a peripheral portion (22) rotating around the central portion; and transfer chambers (24A-24C) between the central and peripheral portions. The central portion defines first fluid paths (FP1A-FP1C) connecting fluid inlets (14A, 14C) to the transfer chambers. The peripheral portion (22) defines second fluid paths (FP2A-FP2C) connecting fluid outlets (16A-16C) to the transfer chambers. The central portion includes an outer body (210) delimiting a housing (215), and an inner body (212) comprising a central portion (212A) extending into the housing (215) and a connecting flange (224) carrying the fluid inlets (14A to 14C). The external and internal bodies are prevented from rotating relative to each other by cooperation between radial teeth (226) of the internal body (212) and axial teeth (218) of the external body (210). Figure for the abbreviation: Figure 1

Description

Multi-channel fluid transfer device with a central part comprising two concentric bodies rotationally joined by respective teeth

The present invention relates to the field of fluid transfer devices designed to transfer multiple fluid paths from a fixed frame of reference to a rotating frame of reference, or more generally between two frames of reference rotating relative to each other. Such frames of reference are in practice defined by parts or assemblies of parts.

In specific applications within the field of turbomachinery for aircraft propulsion, the fixed reference frame can be defined by a stator of such a turbomachine, while the rotating reference frame can be defined by its rotor. In such applications, the fluid is, for example, oil or another fluid intended for the hydraulic control of actuators. In specific applications, the device under consideration is of the type commonly referred to as an OTB (Oil Transfer Bearing), and is thus designed to supply a cylinder controlling the pitch of one or more propeller blades, as well as a blade safety actuator.

Prior art

Multi-channel fluid transfer devices between two relatively rotating reference frames, such as those used to control actuators in turbomachinery for aircraft propulsion, are generally bulky and heavy, which penalizes the overall performance of turbomachinery and results in a negative impact on climate change.

• une partie centrale comprenant un corps externe définissant une surface externe de la partie centrale, à géométrie de révolution selon un axe ;
• une partie périphérique, présentant une surface interne à géométrie de révolution selon l’axe agencée autour de la surface externe de la partie centrale avec faculté de rotation par rapport à cette dernière selon l’axe ;
• au moins un palier interposé radialement entre le corps externe de la partie centrale et la partie périphérique pour guider ces dernières en rotation relative ;
• des chambres de transfert définies entre – et délimitées par – la surface externe de la partie centrale et la surface interne de la partie périphérique ;

In this context, research is focused on developing an improved multi-channel fluid transfer device, generally comprising:

• a central part comprising an external body defining an external surface of the central part, with a geometry of revolution about an axis;
• a peripheral part, presenting an internal surface with a geometry of revolution around the axis arranged around the external surface of the central part with the ability to rotate relative to the latter around the axis;
• at least one bearing interposed radially between the external body of the central part and the peripheral part to guide the latter in relative rotation;
• transfer chambers defined between – and delimited by – the external surface of the central part and the internal surface of the peripheral part;

• la partie centrale définit des premiers chemins fluidiques raccordant respectivement des entrées fluidiques du dispositif, définies à une extrémité axiale de la partie centrale située d’un premier côté axial, aux chambres de transfert au travers de la surface externe de la partie centrale ;
• la partie périphérique définit des seconds chemins fluidiques raccordant respectivement des sorties fluidiques du dispositif aux chambres de transfert au travers de la surface interne de la partie périphérique.

and in which:

• the central part defines first fluidic paths connecting respectively fluidic inlets of the device, defined at an axial end of the central part located on a first axial side, to the transfer chambers through the external surface of the central part;
• the peripheral part defines second fluidic paths connecting respectively fluidic outlets of the device to the transfer chambers through the internal surface of the peripheral part.

In the context of the development of such a device, a problem arises concerning the mounting of the device in a hard-to-reach environment, for example within a turbomachine, when such a mounting requires blindly connecting the fluidic inlets of the device to a fluid supply structure.

This problem is particularly marked in cases where the fluid supply structure is radially supported in cantilever within the turbomachine, by support means exhibiting a certain flexibility, so that this fluid supply structure exhibits a certain axial mobility which interferes with the connection operations, in the axial direction, of the fluidic inlets of the device to the fluid supply structure.

The present invention is the result of technological research conducted by the Applicant, aimed at significantly improving aircraft performance and, in this sense, contributing to the reduction of their environmental impact.

• le corps externe délimite en son sein un logement s’étendant selon l’axe et présentant une extrémité axiale ouverte, du premier côté axial, et le corps externe présente, autour de l’extrémité axiale ouverte du logement, des dents axiales s’étendant en saillie en direction du premier côté axial ;
• la partie centrale comprend un corps interne comprenant une portion centrale s’étendant dans le logement du corps externe ;
• le corps interne comprend une bride de raccordement s’étendant radialement en saillie de la portion centrale du corps interne, au-delà de l’extrémité axiale ouverte du logement en direction du premier côté axial, et portant, du premier côté axial, des connecteurs fluidiques définissant respectivement les entrées fluidiques du dispositif ;
• le corps interne présente des dents radiales s’étendant axialement en direction d’un second côté axial opposé au premier côté axial, à partir de la bride de raccordement, et radialement en saillie de la portion centrale du corps interne ;
• chacune des dents radiales est engagée dans une encoche correspondante définie entre deux dents axiales correspondantes consécutives parmi lesdites dents axiales du corps externe, de manière à empêcher une rotation relative entre le corps externe et le corps interne ;

The invention aims to remedy the problem described above and proposes, for this purpose, such a device for transferring fluid through multiple channels, in which:

• the external body delimits within itself a housing extending along the axis and having an open axial end, on the first axial side, and the external body has, around the open axial end of the housing, axial teeth extending in projection towards the first axial side;
• the central part comprises an internal body including a central portion extending into the housing of the external body;
• the internal body includes a connecting flange extending radially in projection from the central portion of the internal body, beyond the open axial end of the housing in the direction of the first axial side, and carrying, on the first axial side, fluidic connectors respectively defining the fluidic inlets of the device;
• the internal body has radial teeth extending axially in the direction of a second axial side opposite the first axial side, from the connecting flange, and radially projecting from the central portion of the internal body;
• Each of the radial teeth is engaged in a corresponding notch defined between two consecutive corresponding axial teeth among said axial teeth of the external body, so as to prevent relative rotation between the external body and the internal body;

the first fluidic paths being jointly defined by the external body and the internal body.

As will become clearer below, the configuration of the central part allows for a two-step assembly process. In this process, the internal body is first mounted alone onto a corresponding structure using its fluidic connectors, while the rest of the device, including the external body and the peripheral part, is then mounted around the internal body. This facilitates the mounting of the internal body onto the aforementioned structure, including connecting the internal body's fluidic connectors to corresponding fluidic connectors on the structure. Ultimately, the axial teeth of the external body and the radial teeth of the internal body ensure that these two bodies are rotationally locked together, preventing either body from rotating relative to the other.

In preferred embodiments, at least one of the radial teeth of the internal body incorporates a conduit connecting one of the corresponding fluidic channels to one of the corresponding fluidic inlets.

In preferred embodiments, the axial teeth of the external body each have two lateral surfaces respectively delimiting two of said notches, an axial end surface, a radially internal surface, and two beveled surfaces each connecting the axial end surface jointly to the radially internal surface and to one of the corresponding lateral surfaces.

In preferred embodiments, the respective radially internal surfaces of the axial teeth are inscribed in a virtual surface of cylindrical shape of revolution about the axis.

In preferred embodiments, the respective axial end surfaces of the axial teeth lie in a plane transverse to the axis.

In preferred embodiments, for each of the notches, the lateral surfaces of the axial teeth delimiting the notch extend parallel to a median axial plane of the notch.

In preferred embodiments, the chamfered surfaces of each of the axial teeth extend symmetrically with respect to a median axial plane of the axial tooth.

In preferred embodiments, the radial teeth of the internal body each have two opposing lateral surfaces, an axial end surface, a radially external surface, and two beveled surfaces connecting respectively the axial end surface to the two lateral surfaces of the radial tooth considered.

In preferred embodiments, the two lateral surfaces of each of the radial teeth of the internal body extend parallel to each other.

In preferred embodiments, the outer body of the central part includes a stop opposing axial displacement of the outer body relative to the peripheral part in the direction of the first axial side.

• des canaux fluidiques définis chacun par au moins l’un des corps interne et externe et raccordés, du premier côté axial, aux entrées fluidiques ; et
• pour chacun des canaux fluidiques, au moins un piquage fluidique formé dans le corps externe, raccordé au canal fluidique considéré du second côté axial, et débouchant, au travers de la surface externe de la partie centrale, dans la chambre de transfert correspondante.

In preferred embodiments, the central part comprises, for defining said first fluidic paths:

• fluidic channels, each defined by at least one of the internal and external bodies and connected, on the first axial side, to the fluidic inlets; and
• for each of the fluidic channels, at least one fluidic branch formed in the external body, connected to the fluidic channel considered on the second axial side, and opening, through the external surface of the central part, into the corresponding transfer chamber.

The invention also relates to an aircraft turbomachine, comprising at least one device of the type defined above, a stator attached to one of the central and peripheral parts of the device, and a rotor attached to the other of the central and peripheral parts of the device, in which the one, among the stator and the rotor, which is attached to the central part, comprises a fluid supply structure provided with fluid connectors cooperating by mutual engagement respectively with the fluid connectors defining the fluid inputs of the device.

• S-A) mettre à disposition le corps externe, le corps interne, la partie périphérique et ledit au moins un palier ; puis
• S-B) d’une part, monter le corps interne sur une structure d’alimentation en fluide portée par l’un parmi un stator et un rotor de la turbomachine, en engageant réciproquement les connecteurs fluidiques définissant les entrées fluidiques du dispositif, portés par la bride de raccordement du corps interne, avec des connecteurs fluidiques correspondants de la structure d’alimentation en fluide ; et
• S-C) d’autre part, pré-assembler la partie périphérique autour du corps externe en interposant ledit au moins un palier entre ceux-ci ; puis
• S-D) amener l’ensemble pré-assemblé à l’étape S-C en position autour de la portion centrale du corps interne en insérant cette dernière dans le logement délimité par le corps externe, jusqu’à ce que chacune des dents radiales du corps interne s’engage dans une encoche correspondante définie entre deux dents axiales correspondantes consécutives parmi les dents axiales du corps externe, de manière à empêcher une rotation relative entre le corps externe et le corps interne ; puis
• S-E) fixer la partie périphérique à l’autre parmi le stator et le rotor de la turbomachine.

The invention also relates to a method for mounting a device of the type defined above within an aircraft turbomachine, comprising at least steps consisting of:

• SA) to make available the external body, the internal body, the peripheral part and said at least one level; then
• SB) on the one hand, mount the internal body on a fluid supply structure supported by one of the stator and rotor of the turbomachine, by reciprocally engaging the fluid connectors defining the fluid inlets of the device, carried by the connection flange of the internal body, with corresponding fluid connectors of the fluid supply structure; and
• SC) on the other hand, pre-assemble the peripheral part around the external body by interposing said at least one bearing between them; then
• SD) bring the pre-assembled unit from step SC into position around the central portion of the inner body by inserting the latter into the housing defined by the outer body, until each of the radial teeth of the inner body engages in a corresponding notch defined between two consecutive corresponding axial teeth among the axial teeth of the outer body, so as to prevent relative rotation between the outer body and the inner body; then
• SE) fix the peripheral part to the other between the stator and the rotor of the turbomachine.

The invention will be better understood, and other details, advantages, and features thereof will become apparent from the following description, given by way of non-limiting example and with reference to the accompanying drawings, in which:

FIG. 1 is a schematic axial cross-sectional view of a device for transferring multiple fluid paths according to a preferred embodiment of the invention, whose fluid inlets are connected to a fluid supply structure within a turbomachine;

FIG. 2 is a view similar to the FIG. 1 , according to another cutting plan;

FIG. 3 is a schematic perspective view of an external part intended to be part of a central part of the device;

FIG. 4 is a schematic perspective view of an internal part also intended to be part of the central part of the device;

FIG. 5 is a schematic perspective view of the central part of the device, formed by the internal and external parts;

FIG. 6 is a schematic axial cross-sectional view of the turbomachine including the fluid supply device and structure;

FIG. 7 is a flowchart of a process for assembling the device within the turbomachine;

FIG. 8 is a schematic axial cross-sectional view of the internal part, whose fluidic inlets are connected to the fluid supply structure, at the end of an SB step of the process;

FIG. 9 is a schematic axial cross-sectional view of the pre-assembled external part to the peripheral part, following an SC step of the process;

FIG. 10 is a schematic axial cross-sectional view of the device during an SD step of the process.

Throughout these figures, identical references may designate identical or analogous elements.

Detailed presentation of preferred embodiments I. General Information

Figures 1 and 2 illustrate a device 10 for transferring several fluid paths between two frames rotating relative to each other, for example between a turbomachine stator, defining a fixed frame, and a turbomachine rotor, defining a frame rotating about an axis 8. In the example described, there are three fluid paths, but the principles described below are of course applicable regardless of the number of fluid paths.

In this description, the axial direction X is the direction of axis 8. The radial direction R is at every point a direction orthogonal to and passing through axis 8, and the orthoradial or circumferential direction C is at every point a direction orthogonal to both the radial direction R and axis 8. A transverse plane is a plane orthogonal to axis 8. Unless otherwise specified, the terms "internal" and "external" refer respectively to the relative proximity and relative distance of an element from axis 8. Furthermore, the term "axial" is used with reference to axis 8.

The stator includes, for example, a fluid supply structure 12 having several fluid outlets 12A-12C, in this case three in number, which are connected respectively to fluid inlets 14A-14C of the device, while the rotor includes fluid receiving means (not shown) connected to fluid outlets 16A-16C of the device. Although the present description provides, for convenience, a direction of fluid flow from the fluid inlets to the fluid outlets through the device 10, a reverse direction of flow is possible without departing from the scope of the invention. In this respect, the terms "inlet" and "outlet" should be considered, throughout this application, as synonymous with passageways or "fluid ports."

With further reference to figures 1 and 2, the device 10 generally comprises a central part 20, and a peripheral part 22 arranged around the central part 20 with the ability to rotate relative to the latter along the axis 8.

The central part 20, for example, is designed to be integral with the stator, in this case the fluid supply structure 12, while the peripheral part 22, for example, is designed to be integral with the rotor. In other application examples, the roles of the central part 20 and the peripheral part 22 can be reversed, with the central part then being integral with a rotor and the peripheral part being integral with a stator.

The central portion 20 has an external surface 20A with a geometry of revolution about axis 8, and preferably cylindrical in shape. The peripheral portion 22 has an internal surface 22A with a geometry of revolution about axis 8, arranged around the external surface 20A of the central portion 20, and preferably with a shape broadly similar to that of the external surface 20A up to a homothetic transformation, the two surfaces possibly differing further by the presence of different annular orifices and grooves. In the illustrated embodiment, the internal surface 22A of the peripheral portion 22 is defined by a single part. Alternatively, the internal surface 22A of the peripheral portion 22 can be defined jointly by several parts belonging to the peripheral portion 22.

An annular space 23 is defined between the external surface 20A of the central part 20 and the internal surface 22A of the peripheral part 22.

In general, the annular space 23 comprises, arranged axially in alternation, first annular regions defining transfer chambers 24A-24C, and second annular regions 26A-26D, with a smaller cross-section compared to the transfer chambers 24A-24C, to separate the latter, on the one hand, from each other, and, on the other hand, from the outside of the annular space 23. Thus, a second annular region 26B, 26C is arranged between any pair of consecutive transfer chambers 24A-24B and 24B-24C, and second annular regions 26A, 26D are arranged respectively at two opposite axial extremities of the annular space 23. Due to their relatively small cross-section, the second annular regions 26A-26D serve to limit and control fluid leakage between the central part 20 and the peripheral part 22 from the transfer chambers 24A-24C.

For each of the fluid paths to be transferred, the central section 20 comprises a fluidic path in fluidic communication with a corresponding fluidic path within the peripheral section 22, in order to allow the fluid of the considered path to flow from a corresponding fluidic inlet 14A-14C integral with the central section 20, to a corresponding fluidic outlet 16A-16C integral with the peripheral section 22. Furthermore, the pairwise communication between the fluidic paths of the central section 20, referred to as the first fluidic paths hereafter and referenced FP1A-FP1C, and the fluidic paths of the peripheral section 22, referred to as the second fluidic paths hereafter and referenced FP2A-FP2C, is implemented via the transfer chambers 24A-24C, defined between the external surface 20A of the central section 20 and the internal surface 22A of the peripheral section. 22, as will become clearer in what follows. Each first fluidic path FP1A-FP1C therefore connects a corresponding fluidic inlet 14A-14C to a corresponding transfer chamber 24A-24C, the latter being further connected to a corresponding fluidic outlet 16A-16C by a corresponding second fluidic path FP2A-FP2C.

The fluidic inlets 14A-14C are arranged at a longitudinal end of the central part 20 located on a first axial side S1. The fluidic outlets 16A-16C can be arranged at a longitudinal end of the peripheral part 22 located on a second axial side S2 opposite the first axial side S1 and/or in an external surface 28 of the peripheral part 22. In the illustrated example, a fluidic outlet 16A is arranged at the longitudinal end of the peripheral part 22 on the second axial side S2, while two other fluidic outlets 16B and 16C are defined in the external surface 28 of the peripheral part 22.

As mentioned above, the peripheral part 22 is configured to connect the fluidic outlets of system 16A-16C to the transfer chambers 24A-24C, respectively, through the internal surface 22A of the peripheral part 22. The means for achieving this result will not be described here and are outside the scope of the invention. An example of a configuration for the peripheral part is given, for instance, in the patent application filed in France on October 20, 2023, under number FR2311395.

Furthermore, the peripheral part 22 includes, for example, an annular flange 29 extending radially outwards to allow the peripheral part 22 to be fixed to the aforementioned rotor of the turbomachine.

To connect the central part 20 and peripheral part 22 by allowing rotational guidance of one relative to the other, the system 10 includes at least one radially interposed bearing between the central part 20 and the peripheral part 22, for example two bearings 110A, 110B with rollers arranged axially on either side of the set of transfer chambers 24A to 24C.

II. Central Part

With constant reference to Figures 1 and 2, the central part 20 comprises a main portion 30 defining the aforementioned external surface 20A. The central part 20 further comprises, at one end of it located on the first axial side S1, a connecting portion 32, and at the other end of it located on the second axial side S2, a trunnion 34. The trunnion 34 is, for example, separated from the external surface 20A by a shoulder 35A, while the external surface 20A is separated from the connecting portion 32 by a shoulder 35B.

Within the assembled device (Figures 1 and 2), one of the bearings 110B, located on the first axial side S1, is, for example, arranged against the shoulder 35B in the direction of the first axial side S1, while the other bearing 110A, located on the second axial side S2, is, for example, arranged against the shoulder 35A in the direction of the first axial side S1. The peripheral part 22 is, for example, axially sandwiched between the two bearings 110A and 110B. The assembly thus formed is, for example, axially tightened by means of a nut 122 mounted on the axial end of the trunnion 34.

To define the first fluidic paths FP1A-FP1C, the main portion 30 generally comprises corresponding fluidic channels 36A-36C, respectively connected, on the first axial side S1, to the fluidic inlets 14A-14C, and for each of the fluidic channels 36A-36C, at least one fluidic branch 38A-38C connected to the fluidic channel 36A-36C considered on the second axial side S2, and opening through the external surface 20A, into a corresponding transfer chamber 24A-24C.

In the preferred example shown, the fluidic channels 36A-36C are concentric channels extending along axis 8. The aforementioned external surface 20A surrounds all of these fluidic channels 36A-36C.

Thus, the main portion 30 comprises, for example, a first tubular channel 36A centered with respect to the axis 8, a second annular channel 36B extending around the first channel 36A, and a third annular channel 36C extending around the second channel 36B.

On the trunnion side 34, i.e. the second axial side S2, the channels 36A-36C have staggered ends along the axis 8 so that the further a channel is implanted from the axis 8, the less it extends towards the second axial side S2.

In the illustrated preferred example, the main portion 30 comprises, for each fluidic channel 36A-36C, a corresponding series of fluidic ports 38A-38C, each having an internal end connected to the channel 36A-36C in question and an external end opening through the external surface 20A into the corresponding transfer chamber 24A-24C. The fluidic ports of each series 38A-38C thus extend from a corresponding channel 36A-36C. The ports 38A-38C of each series are, for example, arranged in the form of an annular row of ports regularly distributed around the axis 8. Preferably, each of the fluidic ports 38A-38C extends in the radial direction R.

In the context of the present invention, the central part comprises an external body 210 and an internal body 212 (distinct from one another), which together define the first fluidic paths FP1A-FP1C, as will become clearer below. Each of these bodies can be made in one piece or be composed of several parts. In the illustrated example, the external body 210 is thus made in one piece, while the internal body 212 is formed of three concentric parts joined together.

With reference to the FIG. 3 The external body 210, which is represented therein in isolation, comprises a first end portion 210A which defines the trunnion 34, a second end portion 210B forming part of the connecting portion 32 of the central part 20, and between these two end portions, an intermediate portion 210C forming an external part of the main portion 30 of the central part 20. The intermediate portion 210C defines in particular the external surface 20A of the central part 20.

Furthermore, the intermediate portion 210C delimits within itself a housing 215 extending along the axis 8 and having an open axial end 216, on the first axial side S1. The housing 215 is preferably of axisymmetric shape along the axis 8.

Furthermore, the external body 210 has, around the open axial end 216 of the housing, axial teeth 218 extending in projection towards the first axial side S1, from a flange 220 which extends radially outwards from the corresponding axial end of the intermediate portion 210C. The flange 220 and the axial teeth 218 thus constitute the second end portion 210B of the external body 210.

The axial teeth 218, for example three in number, define notches 222 between them ( FIG. 3 ). These are open in both the axial X and radial R directions.

The axial teeth 218 are regularly distributed around the axis 8 and are of similar shape so that the notches 222 are also regularly distributed around the axis 8 and of similar shape.

The flange 220 also forms the aforementioned shoulder 35B (figures 1 and 2).

With reference to the FIG. 4 , the internal body 212, which is represented there in isolation, has a central portion 212A, extending along the axis 8 and preferably having an axisymmetric shape along the axis 8. Within the assembled device (figures 1 and 2), the central portion 212A extends within the housing 215 of the external body 210 and is surrounded by the latter.

As can be seen more clearly in Figures 1 and 2, the outer body 210 and the inner body 212 jointly define the various fluidic channels 36A-36C. In the illustrated example, the tubular channel 36A is essentially formed in the center of the inner body 212, with the exception of a terminal portion of this channel 36A which is directly defined by the outer body 210 and into which the corresponding fluidic ports 38A open. Similarly, the annular channel 36B is essentially formed within the inner body 212, with the exception of a terminal portion of this channel 36B which is internally delimited by the inner body 212 and externally delimited by the outer body 210, and into which the corresponding fluidic ports 38B open. Finally, the annular canal 36C comprises a proximal portion defined within the internal body 212 and a distal portion that is internally delimited by the internal body 212 and externally delimited by the external body 210, and into which the corresponding fluid ports 38C open. The fluid ports 38A-38C, on the other hand, are entirely defined within the external body 210.

The inner body 212 further includes a connecting flange 224 extending to an axial end of the inner body 212 located on the first axial side S1 (figures 1, 2 and 4).

The central portion 212A thus forms an internal part of the main portion 30 of the central portion 20, while the connecting flange 224 forms a part of the connecting portion 32 of the central portion 20.

In particular, the connecting flange 224 extends radially outwards from the central portion 212A. Within the assembled device (figures 1 and 2), the connecting flange 224 is located axially beyond the open axial end 216 of the housing 215 in the direction of the first axial side S1.

In addition, the connecting flange 224 carries, on the first axial side S1, fluidic connectors which respectively define the fluidic inlets 14A-14C of the device.

The connecting flange 224 further includes mounting holes 223 for centering pins 225 integral with the fluid supply structure 12 (Figures 1 and 2, and FIG. 5 ).

The internal body 212 further has radial teeth 226 which extend axially in the direction of the second axial side S2, from the connecting flange 224, and which extend radially outwards projecting from the central portion 212A ( FIG. 4 ). These radial teeth 226 are arranged and shaped to be able to engage respectively in all or part of the notches 222.

Thus, within the assembled device (Figures 1 and 2), each of the radial teeth 226 is engaged in a corresponding notch 222 (defined between two consecutive corresponding axial teeth 218 of the external body 210). This engagement occurs with little or no play. The radial teeth 226 thus cooperate with the axial teeth 218 in such a way as to prevent relative rotation between the external body 210 and the internal body 212. FIG. 5 illustrates the external body 210 and internal body 212 in their reciprocal engagement configuration as within the assembled device.

In the illustrated example, there are two radial teeth 226, so one of the notches 222 remains free within the assembled device. Generally, the number of radial teeth 226 is less than or equal to the number of notches 222, and therefore to the number of axial teeth 218.

As shown in Figures 1 and 2, each of the radial teeth 226 of the internal body 212 incorporates a conduit 230, 232 connecting one of the fluidic channels 36B, 36C corresponding to one of the corresponding fluidic inlets 14B, 14C.

By integrating such conduits 230, 232, the radial teeth 226 are thus used for the fluidic connection of the fluidic inlets 14B, 14C, which are tubular in shape, to the fluidic channels 36B and 36C, which are annular in shape.

In the illustrated example, the fluidic channel 36A being tubular in shape, the corresponding fluidic inlet 14A is arranged directly at an axial end of this fluidic channel 36A.

To facilitate the reciprocal engagement of the axial teeth 218 and the radial teeth 226 during assembly operations of the external body 210 on the internal body 212, the teeth 218 and 226 advantageously adopt shapes optimized for this purpose.

Thus, with reference to the FIG. 3 , the axial teeth 218 each have two opposing lateral surfaces 240A, 240B which respectively contribute to defining two of the corresponding notches 222 located on either side of the axial tooth in question, an axial end surface 242, a radially internal surface 244, and two beveled surfaces 246A, 246B. Each of the beveled surfaces 246A, 246B connects the axial end surface 242 jointly to the radially internal surface 244 and to one of the corresponding lateral surfaces 240A, 240B.

Furthermore, the respective radially internal surfaces 244 of the axial teeth 218 are inscribed in a virtual cylindrical surface of revolution about the axis 8. The set of axial teeth 218 can thus rotate freely around the central portion 212A about the axis 8 during assembly operations of the external body 210 on the internal body 212, as will become clearer in what follows.

Furthermore, the respective axial end surfaces 242 of the axial teeth 218 are inscribed in a plane P transverse to the axis 8.

In addition, for each of the notches 222, the respective lateral surfaces 240A, 240B of the axial teeth delimiting the notch extend parallel to a median axial plane M of the notch.

In addition, the chamfered surfaces 246A, 246B of each of the axial teeth 218 extend symmetrically with respect to a median axial plane N of the axial tooth.

The chamfered surfaces 246A, 246B of each of the axial teeth 218 meet along a segment 248 connecting an axial end of the radially internal surface 244 of the axial tooth in question to a radially internal end of its axial end surface 242. Each of the chamfered surfaces 246A, 246B thus has five sides. The axial end surface 242 of each of the axial teeth 218 is substantially in the shape of an angular sector, the apex of which constitutes the aforementioned radially internal end of the axial end surface 242 in question.

Furthermore, with reference to the FIG. 4 , the radial teeth 226 of the internal body 212 each have two opposing lateral surfaces 250A, 250B, an axial end surface 252, a radially external surface 254, and two beveled surfaces 256A, 256B connecting respectively the axial end surface 252 to the two lateral surfaces 250A, 250B of the radial tooth considered.

In addition, the two lateral surfaces 250A, 250B of each of the radial teeth 226 extend parallel to each other.

III. Turbomachine

There FIG. 6 illustrates a turbomachine 310, for example a twin-spool turbofan engine for aircraft, generally comprising a fan 312 for the intake of an airflow F1 which divides downstream of the fan into a primary flow F2 flowing in a primary flow channel, hereinafter referred to as the primary flow PV, and a secondary flow F3 flowing in a secondary flow channel, hereinafter referred to as the secondary flow SV, arranged around the primary flow PV.

The turbomachine includes, for example, a low-pressure compressor 314, a high-pressure compressor 316, a combustion chamber 318, a high-pressure turbine 320, and a low-pressure turbine 322, which together define the primary flow PV. The respective rotors of the high-pressure compressor and the high-pressure turbine are connected by a shaft called the "high-pressure shaft," while the respective rotors of the low-pressure compressor and the low-pressure turbine are connected by a shaft called the "low-pressure shaft," in a well-known manner. These rotors are mounted to rotate about a shaft 328 of the turbomachine.

The turbomachine includes a device 10 of the type described above, with axis 8 for example coinciding with axis 328 of the turbomachine 310.

A stator 330 of the turbomachine is attached to one of the central 20 and peripheral 22 parts of the device, in this case the central part 20. A rotor 340 of the turbomachine is attached to the other part, in this case the peripheral part 22, of the device.

Device 10, illustrated very schematically on the FIG. 6 For example, it is arranged so that its fluidic outlets 16A-16C are connected to fluidic chambers of actuators mounted on the aforementioned rotor 340 to enable the control of such actuators. In particular, the device is, for example, of the type commonly known as an OTB (Oil Transfer Bearing) and is designed to supply a cylinder controlling the blade pitch of one or more propellers, as well as a blade safety actuator.

With further reference to Figures 1 and 2, the stator includes the fluid supply structure 12. The latter is provided with fluid connectors 12A-12C cooperating by mutual engagement respectively with the fluid connectors defining the fluid inlets 14A-14C of the device 10. The fluid connectors 12A-12C are for example female connectors in which the male type fluid connectors defining the fluid inlets 14A-14C are engaged by push-fit.

The fluid supply structure 12 is further provided with centering pins 225. These are, for example, fitted into orifices 260 provided for this purpose within the structure 12.

The fluid supply structure 12 is radially cantilevered within the turbomachine by support means having a certain flexibility, so that this fluid supply structure 12 has a certain mobility about the axis 8. Such mobility hinders the connection operations, by fitting in the axial direction, of the fluid inlets 14A-14C of the device to the corresponding connectors of the fluid supply structure 12, and makes the assembly method which will now be described particularly advantageous.

IV. Assembly Procedure

With reference to the FIG. 7 , the method of mounting the device 10 within a turbomachine, such as the turbomachine 310 of the FIG. 6 , generally includes the following steps SA to SE.

The S-A step initially consists of making available the external body 210, the internal body 212, the peripheral part 22 and the – or, in this case, the – bearings 110A, 110B.

With reference to the FIG. 8 , step SB consists, on the one hand, of mounting the internal body 212 on the fluid supply structure 12 carried for example by the stator 330 of the turbomachine, by reciprocally engaging the fluid connectors carried by the connecting flange 224, defining the fluid inlets 14A-14C, with the fluid connectors 12A-12C of the fluid supply structure, and, where applicable, by engaging the centering pins 225 in the mounting holes 223 of the connecting flange 224 and in the corresponding holes 260 of the fluid supply structure 12. The reciprocal engagement of the fluid connectors 12A-12C and 14A-14C, and the engagement of the centering pins 225 in the holes 223 and 260, is for example achieved by press fitting.

With reference to the FIG. 9 , the SC step consists, on the other hand, of pre-assembling the peripheral part 22 around the external body 210 by interposing each bearing 110A, 110B between them, so as to allow a relative rotation between the peripheral part 22 and the external body 210.

For example, this involves mounting the bearing 110B around the intermediate portion 210C of the external body 210 until this bearing is axially abutted against the shoulder 35B, then moving the peripheral portion 22 around the intermediate portion 210C of the external body 210 until the peripheral portion is axially abutted against the bearing 110B, then mounting the bearing 110A around the trunnion 34 until this bearing 110A is abutted against the shoulder 35A, and finally mounting the nut 122 on the axial end of the trunnion 34 so as to axially tighten the assembly thus formed. In particular, the nut 122 constitutes an example of a stop opposing axial displacement of the external body 210 relative to the peripheral portion 22 in the direction of the first axial side S1.

Steps S-B and S-C are independent of each other and can therefore be implemented in any order, or simultaneously.

The SD step then consists of bringing the pre-assembled assembly to the SC step in position around the central portion 212A of the internal body 212 by inserting the latter into the housing 215 delimited by the external body 210 ( FIG. 10 ), until each of the radial teeth 226 engages in a corresponding notch 222 defined between two consecutive corresponding axial teeth 218, so as to prevent relative rotation between the external body 210 and the internal body 212.

During this step, the optimized shape of the teeth 218 and 226 – in particular the arrangement of the beveled surfaces 246A, 246B and/or 256A, 256B – allows for self-adjustment of the angular position of the external body 210 relative to that of the internal body 212. Indeed, if the notches 222 do not coincide with the radial teeth 226, the reciprocal support of the axial teeth 218 on the radial teeth 226 causes, thanks to the beveled surfaces, an appropriate angular displacement of the external body 210 relative to the internal body 212, until the notches 222 actually coincide with the radial teeth 226.

It is therefore possible to carry out this operation blindly, that is to say without being able to see or directly manipulate the external body 210, and nevertheless without risk of compromising the assembly of the device 10.

The SE step of the process consists, finally, of attaching the peripheral part 22 to the rotor 340 of the turbomachine ( FIG. 6 ), for example by means of the annular flange 29.

It should be noted that at the end of the assembly process, the external body 210 is not directly fixed to the internal body 212, and that a relative displacement of these two bodies along the axis 8 is prevented only by the fixing of the peripheral part 22, with respect to which the external body is axially abutted, to the rotor 340 which, in practice, is not axially movable with respect to the stator 330.

Claims (13)

Device (10) for transferring fluid through multiple channels, comprising:
- a central part (20) comprising an external body (210) defining an external surface (20A) of the central part (20), with a geometry of revolution about an axis (8);
- a peripheral part (22), having an internal surface (22A) with a geometry of revolution about the axis (8) arranged around the external surface (20A) of the central part with the ability to rotate relative to the latter about the axis (8);
- at least one bearing (110A, 110B) interposed radially between the external body (210) of the central part and the peripheral part (22) to guide the latter in relative rotation;
- transfer chambers (24A to 24C) defined between – and delimited by – the external surface (20A) of the central part and the internal surface (22A) of the peripheral part;
in which:
- the central part (20) defines first fluidic paths (FP1A to FP1C) connecting respectively fluidic inlets (14A to 14C) of the device, defined from a first axial side (S1), to the transfer chambers (24A to 24C), through said external surface (20A);
- the peripheral part (22) defines second fluidic paths (FP2A to FP2C) connecting respectively fluidic outlets (16A to 16C) of the device to the transfer chambers (24A to 24C) through said internal surface (22A);
in which:
- the external body (210) delimits within itself a housing (215) extending along the axis (8) and having an open axial end (216), on the first axial side (S1), and the external body (210) has, around the open axial end (216) of the housing, axial teeth (218) extending in projection towards the first axial side (S1);
- the central part (20) includes an internal body (212) comprising a central portion (212A) extending into the housing (215) of the external body (210);
- the internal body (212) includes a connecting flange (224) extending radially outward from the central portion (212A) of the internal body, beyond the open axial end (216) of the housing (215) in the direction of the first axial side (S1), and carrying, on the first axial side (S1), fluidic connectors defining respectively the fluidic inlets (14A to 14C) of the device;
- the internal body (212) has radial teeth (226) extending axially in the direction of a second axial side (S2) opposite the first axial side (S1), from the connecting flange (224), and radially projecting from the central portion (212A) of the internal body (212);
- each of the radial teeth (226) is engaged in a corresponding notch (222) defined between two consecutive corresponding axial teeth (218) among said axial teeth of the external body (210), so as to prevent a relative rotation between the external body (210) and the internal body (212);
the first fluidic paths (FP1A to FP1C) being jointly defined by the external body (210) and the internal body (212). Device according to claim 1, wherein at least one of the radial teeth (226) of the internal body (212) incorporates a conduit (230, 232) connecting one of the corresponding fluidic channels (36B, 36C) to one of the corresponding fluidic inlets (14B, 14C). Device according to claim 1 or 2, wherein the axial teeth (218) of the external body (210) each have two lateral surfaces (240A, 240B) respectively delimiting two of said notches (222), an axial end surface (242), a radially internal surface (244), and two chamfered surfaces (246A, 246B) each connecting the axial end surface (242) jointly to the radially internal surface (244) and to one of the corresponding lateral surfaces (240A, 240B). Device according to claim 3, wherein the respective radially internal surfaces (244) of the axial teeth (218) are inscribed in a virtual surface of cylindrical shape of revolution about the axis (8). Device according to claim 3 or 4, wherein the respective axial end surfaces (242) of the axial teeth (218) are inscribed in a plane (P) transverse to the axis (8). Device according to any one of claims 3 to 5, wherein, for each of the notches (222), the lateral surfaces (240A, 240B) of the axial teeth (218) delimiting the notch (222) extend parallel to a median axial plane (M) of the notch. Device according to any one of claims 3 to 6, wherein the chamfered surfaces (246A, 246B) of each of the axial teeth (218) extend symmetrically with respect to a median axial plane (N) of the axial tooth. Device according to any one of claims 3 to 7, wherein the radial teeth (226) of the internal body (212) each have two opposing lateral surfaces (250A, 250B), an axial end surface (252), a radially external surface (254), and two chamfered surfaces (256A, 256B) connecting respectively the axial end surface (252) to the two lateral surfaces (250A, 250B) of the radial tooth considered. Device according to claim 8, wherein the two lateral surfaces (250A, 250B) of each of the radial teeth (226) of the internal body (212) extend parallel to each other. Device according to any one of claims 1 to 9, wherein the outer body (210) of the central part (20) has a stop (122) opposing axial displacement of the outer body (210) relative to the peripheral part (22) in the direction of the first axial side (S1). Device according to any one of claims 1 to 10, wherein the central part (20) comprises, for defining said first fluidic paths (FP1A to FP1C):
- fluidic channels (36A to 36C), each defined by at least one of the internal (212) and external (210) bodies and connected, on the first axial side (S1), to the fluidic inlets (14A to 14C); and
- for each of the fluidic channels (36A to 36C), at least one fluidic branch (38) formed in the external body (210), connected to the fluidic channel considered on the second axial side (S2), and opening, through the external surface (20A) of the central part, into the corresponding transfer chamber (24A to 24C). Aircraft turbomachine (310), comprising at least one device (10) according to any one of claims 1 to 11, a stator (330) integral with one of the central (20) and peripheral (22) parts of the device, and a rotor (340) integral with the other of the central (20) and peripheral (22) parts of the device,
in which the one, among the stator and the rotor, which is integral with the central part (20), comprises a fluid supply structure (12) provided with fluid connectors (12A to 12C) cooperating by mutual engagement respectively with the fluid connectors defining the fluid inputs (14A to 14C) of the device. A method for mounting a device (10) according to any one of claims 1 to 11 within an aircraft turbomachine (310), comprising at least steps consisting of:
- SA) make available the external body (210), the internal body (212), the peripheral part (22) and said at least one bearing (110A, 110B); then
- SB) on the one hand, mounting the internal body (212) on a fluid supply structure (12) carried by one of a stator (330) and a rotor (340) of the turbomachine, by reciprocally engaging the fluid connectors defining the fluid inlets (14A to 14C) of the device, carried by the connection flange (224) of the internal body (212), with corresponding fluid connectors (12A to 12C) of the fluid supply structure (12); and
- SC) on the other hand, pre-assemble the peripheral part (22) around the external body (210) by interposing said at least one bearing (110A, 110B) between them; then
- SD) bring the pre-assembled assembly from step SC into position around the central portion (212A) of the inner body (212) by inserting the latter into the housing (215) delimited by the outer body (210), until each of the radial teeth (226) of the inner body (212) engages in a corresponding notch (222) defined between two consecutive corresponding axial teeth (218) among the axial teeth (218) of the outer body (210), so as to prevent relative rotation between the outer body (210) and the inner body (212); then
- SE) fix the peripheral part (22) to the other between the stator (330) and the rotor (340) of the turbomachine.