阅读说明：本技术 用于涡轮机的周转或行星减速齿轮的圈形齿轮 (Ring gear for an epicyclic or planetary reduction gear of a turbomachine ) 是由 让-查尔斯·米歇尔·皮埃尔·迪乔凡尼 弗洛里安·拉普帕波特 马克·多米尼克·塞弗里德 于 2018-07-02 设计创作，主要内容包括：用于涡轮机、特别是飞行器的涡轮机的周转或行星减速齿轮(10)的圈形齿轮(114),所述圈形齿轮围绕轴线X延伸并且包括第一和第二同轴环形元件(114a,114b),并且该第一和第二同轴环形元件分别包括取向不同的两个内环形齿组(150),所述齿组中的每一个具有节圆直径和基本上垂直于所述轴线的中间平面,其中节圆直径与中间平面在圈形齿轮的轴向横截面中具有表示为Y的交点,所述第一和第二环形元件进一步分别包括用于使所述第一和第二元件彼此附接的第一和第二径向外环形凸缘(114ab,114bb),其特征在于,所述第一和第二凸缘中的每一个包括周边部分(114ab1,114bb1),周边部分在相对于所述轴线X成角度并且基本上穿过所述交点Y的平面中延伸。(A ring gear (114) for an epicyclic or epicyclic reduction gear (10) of a turbomachine, in particular of an aircraft, said ring gear extending about an axis X and comprising a th and a second coaxial annular element (114a, 114b), and this th and second coaxial annular elements respectively comprising two inner annular sets of teeth (150) of different orientation, each of said sets of teeth having a pitch circle diameter and a median plane substantially perpendicular to said axis, wherein the pitch circle diameter and the median plane have, in an axial cross section of the ring gear, an intersection point denoted Y, said th and second annular elements respectively comprising, at a stage , a th and a second radial outer annular flange (114ab, 114bb) for attaching said th and second elements to each other, characterized in that each of said th and second flanges comprises a peripheral portion (114ab1, 114bb1) extending in a plane angled with respect to said axis X and substantially passing through said intersection point Y.)

1. A ring gear (114) for an epicyclic or planetary reduction gear (110) of a turbine engine, in particular of an aircraft, which extends about an axis X and comprises a th and a second coaxial annular element (114a, 114b), and which and second coaxial annular element each comprise two inner annular sets of teeth (150) of different orientation, each of said sets of teeth having a pitch diameter (D) and a median plane (P) substantially perpendicular to said axis, and which pitch diameter and median plane have, in an axial cross-section of the ring gear, an intersection point denoted Y, said and second annular element step respectively comprising and second radial outer annular flanges (114ab, 114bb) for attaching said and second elements to each other, characterized in that each of said and second flanges comprises a peripheral portion (114ab1, 114bb1) extending in a plane which is angled with respect to said axis X and substantially passes through said intersection point Y.

2. The ring gear (114) of the preceding claim, wherein the peripheral portion is an inner peripheral portion (114ab1, 114bb1) of each of the and second flanges (114ab, 114 bb).

3. Ring gear (114) according to the preceding , wherein the inner peripheral portion (114ab1, 114bb1) connects the substantially radially outer peripheral portion (114ab2, 114bb2) of the respective flange to a longitudinal end of the body (114aa, 114ba) of the respective element.

4. The ring gear (114) according to the preceding wherein the main body (114aa, 114ba) is substantially cylindrical and includes the set of teeth (150) at its inner periphery.

5. The ring gear (114) according to the preceding claim, wherein the main bodies (114aa, 114ba) are at an axial distance of from each other.

6. The ring gear (114) according to of claims 3 to 5, wherein the angled peripheral portions (114ab1, 114bb1) each have an inner peripheral surface (115a) that extends radially outward in extension of an end radial surface (115b) of the respective body (114aa, 114 ba).

7. Ring gear (114) according to of the preceding claim, wherein the peripheral portions (114ab1, 114bb1) each form an angle between 0 ° and 90 ° with respect to the axis X.

8. The ring gear (114) of of the preceding claim, wherein the angled peripheral portions (114ab1, 114bb1) define between them an inter-element annular cavity (166) for oil to pass through.

9. The ring gear (114) according to of the preceding claim, wherein the angled peripheral portion (114ab1, 114bb1) has a substantially constant thickness.

10. Epicyclic or planetary reduction gear (110) for a turbine engine, in particular of an aircraft, characterized in that it comprises a ring gear (114) according to in the preceding claim.

Technical Field

The present invention relates to the field of turbine engines, and more particularly to the field of differential transmission systems in these turbine engines, in particular planetary or epicyclic reduction gears.

Background

Disclosure of Invention

To this end, the invention relates to an annular gear for epicyclic or planetary reduction gears of turbine engines, in particular of aircraft, said annular gear extending about an axis X and comprising a th and a second coaxial annular element, and the th and second coaxial annular elements respectively comprising two inner annular sets of teeth of different orientation, each of said sets of teeth having a pitch circle diameter and an intermediate plane substantially perpendicular to said axis, and with which the pitch circle diameter has, in axial section of the annular gear, an intersection point denoted Y, said th and second annular elements further steps respectively comprising a th and a second radially outer annular flange for attaching said th and second elements to each other and more preferably to an annular rack intended to extend around at least part of the annular gear, characterized in that each of said th and second flanges comprises a portion which is angled with respect to the axis of intersection point in said circumferential plane.

In the present application, the term "intersection point" refers to the intersection point between the pitch circle diameter of a set of teeth and the mid-plane of the set of teeth, wherein the intersection point is located in the axial cross-section of the ring gear.

Furthermore, in the present application, the expressions "inner", "outer", "inner", "outer" and the like are expressions referring to the axis of the turbine engine, in particular to the X axis of the ring gear of the reduction gear in the framework of the invention.

The flange of the element is thus adapted to optimize the path of the force from the set of teeth to the fastening area of the element. The angled planes can be better understood in two dimensions. In three dimensions, the angled plane is a relatively conical surface, wherein the angle of the cone may vary with respect to the X-axis. In this case, it can be considered that the peripheral portion extending on the neutral fiber (fiber layer) is angled with respect to the plane X and passes through the point Y.

The ring gear according to the present invention may comprise or more of the following features taken independently of each other or in combination with each other:

-the peripheral portion is an inner peripheral portion of each of the th and second flanges,

said inner peripheral portion connecting the substantially radial outer peripheral portion of the respective flange to the longitudinal end of the main body of the respective element,

-the body is substantially cylindrical and comprises at its inner periphery the set of teeth,

-the bodies are at an axial distance from each other, which enables correction of misaligned sets of teeth by passing a correction tool into the inter-body space;

said angled peripheral portions each have an inner peripheral surface which extends radially outwards in extension of the end radial surface of the respective body; the end radial surface extending to the body enables an assembly to be obtained which is easy to machine, as it has no grooves, and indirectly more robust, which reduces the instances of misalignment;

-the angled peripheral portions each form an angle between 0 ° and 90 ° with respect to the axis, which allows a more direct force path and better distribution of stresses;

-said angled peripheral portions delimiting between them an inter-element annular chamber for the passage of oil; this allows oil to not be trapped between the angled peripheral portions;

the angled peripheral portion has a substantially constant thickness, which allows better distribution of the stresses;

the axial position of the angled peripheral portion with respect to the support plane of the two annular elements is predetermined; this position and angle enables a reduction in misalignment of the sets of teeth.

The invention also relates to an epicyclic or planetary reduction gear for a turbine engine, in particular of an aircraft, characterized in that it comprises a ring gear as described hereinbefore.

Drawings

The invention will be better understood and other details, features and advantages of the invention will become more apparent when the following description is read with reference to the accompanying drawings, in which:

FIG. 1 schematically illustrates an axial cross-section of a turbine engine using the present invention.

Figure 2 shows a detailed cross-sectional view of the epicyclic reduction gear.

Fig. 3 is a cut-away perspective view of the reduction gear of fig. 2.

Fig. 4 is a partial axial sectional view of a reduction gear provided with a ring gear according to the present invention.

Fig. 5 is a partial perspective view of the ring gear of fig. 4.

Fig. 6 is a partial axial cross-section of the ring gear of fig. 4.

Detailed Description

Fig. 1 shows a turbine engine 1 which generally comprises a fan propeller S, a low-pressure compressor 1a, a high-pressure compressor 1b, an annular combustion chamber 1c, a high-pressure turbine 1d, a low-pressure turbine 1e and an exhaust pipe 1 h. The high-pressure compressor 1b and the high-pressure turbine 1d are connected by a high-pressure shaft 2 and form a high-pressure body (HP) therewith. The low-pressure compressor 1a and the low-pressure turbine 1e are connected by a low-pressure shaft 3 and form a low-pressure Body (BP) therewith.

The fan propeller S is driven by a fan shaft 4 which is coupled to the BP shaft 3 by means of an epicyclic reduction gear 10, shown schematically here.

The reduction gear 10 is positioned in the front of the turbine engine. The fixed structure, here schematically comprising an upstream portion 5a and a downstream portion 5b, is arranged to form an enclosure E1 surrounding the reduction gear 10. The enclosure E1 is closed upstream by a seal on the bearing, allowing the fan shaft 4 to pass through, and downstream by a seal at the sleeve of the BP shaft 3.

With reference to fig. 2 and 3, the reduction gear 10 comprises a ring gear 14 fixed to a fixed structure 5a, 5b with flexible means arranged to allow it to follow any movement of the fan shaft 4, for example in the case of degraded operation, by means of a support 20, in a planetary architecture the support comprises a more or less flexible part driving the ring gear and a shaft-carrying part held by roller bearings or bearings and fitted with a fan.

The reduction gear 10 is engaged on the one hand on the BP shaft 3 by means of splines 7 driving the planet pinions 11 and on the other hand is engaged on the fan shaft 4 attached to a planet carrier 13, in general, the planet pinions 11 drive series of planet pinions or planet gears 12 regularly distributed over the circumference of the reduction gear 10, the axis of rotation X of which coincides with the axis of rotation of the turbine engine, the number of planet gears 12 being generally defined between three and six, in addition to the case where the sun gear rotates only around its axis of rotation, the planet gears 12 also rotate around the axis X of the turbine engine by engaging on an internal set of teeth of a ring gear 14, which is fixed to the stator of the turbine engine by means of a flange 20 in the case of an epicyclic gear, or to the rotor of the turbine engine in the case of a sun gear, every of the planet gears 12 use bearings (ball bearings or roller bearings) that can be smooth bearings (as shown in fig. 2) or with rolling elements, connected to the planet shaft 16 of the planet carrier 13, to rotate freely.

The rotation of the planet gears 12 about their planet shafts 16, due to their pinions in cooperation with the set of teeth of the ring gear 14, drives the planet carrier 13 in rotation about the axis X and therefore the fan shaft 4 connected to it in rotation at a rotation speed less than that of the BP shaft 3.

The oil movement to the reduction gear 10 and inside it is shown in figures 2 and 3, the arrows in figure 2 showing the path followed by the oil from the buffer tank connected to the fixed structure of the turbine engine to the pinion and then to the bearing to be lubricated the lubrication device generally comprises three parts, part , part , connected to the fixed structure and carrying the oil to the rotating part of the reduction gear 10, a wheel, rotating with a planet carrier 13 , which receives the oil in the case of an epicyclic gear, and a distributor mounted on the planet carrier (which is fixed to the planetary architecture) and to which the oil distribution circuit is supplied by an impeller in order to deliver the oil to the location to be lubricated.

Fig. 4-6 illustrate an embodiment of a ring gear 114 according to the present invention.

The ring gear 114 extends around an axis which is the axis X of the reduction gear 110 and the turbine engine and comprises two coaxial annular elements, called -th annular element 114a or upstream element and a second annular element 114b or downstream element.

Each element 114a, 114b includes an annular body 114aa, 114ba having a generally cylindrical shape and connected to a radially outwardly extending annular flange 114ab, 114 bb.

Each body 114aa, 114ba includes an inner annular set of teeth 150 at its inner periphery. Although not visible in the drawings, the set of teeth 150 of the two bodies or members is complementary to the set of teeth of a planetary gear of the type shown in fig. 3. The sets of teeth 150 of elements 114a, 114b are chevron-shaped.

Each tooth set 150 includes an outer diameter through its outer periphery, an inner diameter through its inner periphery, and a pitch diameter D measured substantially at the mid-height or radial mid-dimension of the tooth set. Furthermore, P denotes a median plane of each tooth set, wherein this plane is substantially perpendicular to the aforementioned axis and passes through the middle of the tooth set substantially in the axial direction.

The main bodies 114aa, 114ba of each element are connected by longitudinal end portions to respective flanges 114ab, 114bb the main body 114aa is connected at its downstream end (on the side of the other main bodies 114ba) to the flange 114ab and the main body 114ba is connected at its upstream end (on the side of the other main bodies 114 aa) to the flange 114 bb.

Each flange 114ab, 114bb has a generally dihedral shape and comprises two peripheral portions, an inner peripheral portion 114ab1, 114bb1 and an outer peripheral portion 114ab2, 114bb2, respectively.

The outer peripheral portions 114ab2, 114bb2 extend substantially perpendicular to the axis and thus have a substantially radial orientation. These peripheral portions are intended to be axially pressed against each other and thus each comprise an annular radial support surface 152.

In the example shown, the portions 114ab2, 114bb2 are used to secure the elements 114a, 114b from and to secure these elements to the ring carrier 154.

To this end, the portions 114ab2, 114bb2 each include an annular row of axial through holes 156, the annular row of axial through holes for passing a nut-type or similar type of fastening device 158 therethrough the apertures 156 of the portions 114ab2, 114bb2 are aligned and receive the fastening devices 158.

The ring carrier 154 also comprises an annular flange 160 for fastening to the flanges 114ab, 114bb, and in particular to the portions 114ab2, 114bb 2. the flange 160 is applied axially on of the portions 114ab2, 114bb2, i.e. here on the portion 114ab2 of the upstream element 114 a. consequently, the portion 114ab2 is axially interposed between the flange 160 and the portion 114bb 2. the opposite is also possible.

Flange 160 includes an aperture aligned with aperture 156 and also receiving a fastening device 158, the head of which may be applied axially on the downstream face of portion 114bb2, the nut of which may be applied axially on the upstream face of flange 160, or vice versa. In the example shown, the flange 162 of the annular oil collector is axially supported on the portion 114bb2 and receives the head of the nut on the downstream face of that portion.

Portions 114ab2, 114bb2 further include a group of axially threaded through holes 163 that allow disassembly of ring carrier 154 from ring gear 114. the second group of axially threaded through holes 163 enables disassembly of element 114a from element 114 b. portions 114ab2, 114bb2 also include at least pins 165 for angularly fixing elements 114a, 114 b. each portion 114ab2, 114bb2 may include or more of these holes 163, which are intended to align with or more similar holes 163 of the other portion and receive fixing pins 165. pins 165 have a generally cylindrical shape and are axially oriented here.

The portion 114bb2 comprises at its outer periphery a cylindrical centering rim 164. this rim 164 carried by the element 114b is configured to cooperate with the outer periphery of the other elements 114a by means of axial sliding and radial support, so as to ensure centering of the other elements 114a during installation and operation alternatively, the elements 114a may comprise such a rim intended to cooperate with the elements 114b to center the elements 114 b.

The rim 164 is intended to cooperate with the outer periphery of the flange 114ab of the element 114a and in particular with the radially outer free annular edge of the portion 114ab2 of this element. Thus, during installation, rim 164 extends around portion 114ab 2.

In the example shown, the rim 164 also ensures centering of the ring carrier 154. The rim 164 may be fitted with the outer periphery of the flange 160 as noted above.

The rim 164 extends continuously over 360 ° here. Thus, the rim is neither split nor sectorized. Thus, the reference surface for centering is uninterrupted.

The inner peripheral portions 114ab1, 114bb1 are angled relative to the axis X of the ring gear 114. Portion 114ab1 extends radially in an outward direction from upstream to downstream, and portion 114bb1 extends in an inward direction from upstream to downstream. In the example shown, the portions 114ab1, 114bb1 are at an angle of 0 ° to 90 °, more preferably between 30 ° and 60 °, relative to the axis X, and delimit an annular cavity 166 having a substantially triangular-shaped cross-section, the apex of which is oriented radially outwards. The axial location of the portions 114ab1, 114bb1 is such that the centerline passes through the intersection of the mid-plane of the set of teeth and the pitch circle diameter of the set of teeth.

Portions 114ab1, 114bb1 can connect portions 114ab2, 114bb2 to the bodies of elements 114aa, 114bb because of the orientation of portions 114ab1, 114bb1 and their connection to the longitudinal ends of bodies 114a, 114b (downstream and upstream longitudinal ends, respectively), the bodies are axially spaced a predetermined distance from each other.

During operation, lubrication oil is intended to flow through the interbody space and infiltrate the cavity 166. A substantially radial passage is provided between the flanges 114ab, 114bb to allow oil to drain radially toward the outside of the ring gear.

Here, , the oil passages are formed by substantially radial notches or grooves 168 formed in the surface 152 of the flange, each flange includes annular rows of notches 168, which annular rows of notches are axially aligned with the notches 168 of the other of the flanges, the notches are formed at a distance of from the apertures 156, 165 and 163 through which the fastening devices 158 pass, as in the illustrated example (FIG. 5), each notch has a cross-section that is, for example, semi-circular (semi-elliptical) or rectangular in shape.

The notch is in fluid communication at its radially inner end with the cavity 166 and at its axially outer end with an oval shaped oil outlet through bore 170 formed in the centering rim 164. In other words, the oil passages open at their radially outer ends to the outer cylindrical surface of the rim 164 to form the oil outlet orifices 170 of these oil passages.

Fig. 6 shows a partial axial cross section of the reduction gear 110, wherein Y denotes an intersection point between the plane P of each tooth group 150 and the pitch circle diameter D. As can be seen in the figures, the inner peripheral portion 114ab1, 114bb1 of each flange extends in a plane substantially passing through the intersection point Y. In this embodiment, this position and the above-mentioned inclination are two important features.

Each inner peripheral portion 114ab1, 114bb1 has an inner peripheral surface 115a that extends radially outwardly in extension of the end radial surface 115b of the respective body. The axial distance between the surfaces 115b corresponds to the inter-element distance and to the maximum axial dimension of the cavity 166.

The inner peripheral portions 114ab1, 114bb1 have a substantially constant thickness.

In addition to the rim 164, the ring gear elements 114a, 114b are symmetrical with respect to a mid-plane that is perpendicular to the axis and passes substantially between the elements.

The ring gear 114 according to the present invention is easier to produce, install and control than the prior art.