阅读说明：本技术 飞行器涡轮发动机密封模块 (Aircraft turbine engine seal module ) 是由 西蒙·尼古拉斯·莫利埃尔 尼古拉斯·让-马克·马塞尔·博奎因 雷诺·詹姆斯·马尔泰 文森特·弗 于 2019-07-03 设计创作，主要内容包括：涡轮发动机涡轮密封模块,其绕轴线延伸并包括固定到壳体的分配器,分配器包括连接到外平台的至少一个叶片,外平台包括固定到壳体的扰流板,密封模块包括叶轮,叶轮安装成在壳体内旋转并由紧固到壳体的密封环环绕,密封环被分成扇区并包括一环排的环扇区,环扇区布置成使两个相邻扇区的周向端部边缘彼此面对,每个环扇区包括承载耐磨涂层的本体和钩,耐磨涂层构造成与由叶轮承载的至少一个密封唇部接合,钩周向延伸并构造成与壳体的轨道接合,钩有C形截面,钩的开口朝上游轴向定向并接纳轨道,每个环扇区包括偏转器,偏转器布置在涂层上游并相对于轴线径向向内和向上游延伸,使偏转器的径向向内端部绕分配器的外平台的下游端部延伸。(A turbine engine turbine seal module extending about an axis and including a distributor secured to the casing, the distributor including at least one blade connected to an outer platform, the outer platform including a spoiler secured to the casing, the seal module including an impeller mounted for rotation within the casing and surrounded by a seal ring secured to the casing, the seal ring being divided into sectors and including a ring row of ring sectors arranged with circumferential end edges of two adjacent sectors facing each other, each ring sector including a body carrying a wear-resistant coating configured to engage at least one seal lip carried by the impeller, and a hook extending circumferentially and configured to engage a track of the casing, the hook having a C-shaped cross-section, an opening of the hook being oriented axially upstream and receiving the track, each ring sector including a deflector arranged upstream of the coating and extending radially inwardly and upstream relative to the axis, with the radially inward end of the deflector extending around the downstream end of the outer platform of the distributor.)

1. A turbine seal module of a turbine engine, in particular for an aircraft, the seal module extending around an axis and comprising a distributor (12) fixed to a casing (14), the distributor (12) having at least one blade connected to an outer platform (12a), the outer platform (12a) comprising a spoiler (34) for fixing to the casing (14), the seal module further comprising an impeller (16) mounted for rotation within the casing (14) and surrounded by a sealing ring (18) fastened to the casing (14), the sealing ring (18) being divided into sectors and comprising a row of ring sectors arranged so that the circumferential end edges of two adjacent sectors face each other, each ring sector comprising a body (20) carrying a wear-resistant coating (22) and a hook (32), the abradable coating being configured to engage with at least one sealing lip (24) carried by the impeller (16), the hooks extending circumferentially by being located upstream of the abradable coating (22) and being configured to engage with a fastening track (36) of the casing (14), the hooks (32) having a substantially C-shaped cross-section, the openings of the hooks being oriented axially upstream and intended to receive the track (36), characterized in that each ring sector further comprises a deflector (60) arranged upstream of the abradable coating and extending radially inward with respect to the axis and extending upstream such that the radially inward end of the deflector extends around the downstream end of the outer platform (12a) of the distributor (12), and wherein the circumferential extent of each hook (32) is the same as the circumferential extent of the deflector (60), and a circumferential end of the hook (32) is deflected in a circumferential direction of a circumferential end of the deflector (60).

2. The sealing module according to claim 1, wherein the deflector (60) comprises an annular foil sector axially interposed between the hook (32) and the wear-resistant coating (22) and/or axially interposed between the hook and the body (20).

3. The sealing module of claim 2, wherein the foil has a generally V-shaped cross-section, a radially outer portion (60a) of the foil extending radially, and a radially inner portion (60b) of the foil being truncated and extending radially inwardly from upstream to downstream.

4. The sealing module according to claim 3, wherein the hook (32) comprises an intermediate bottom wall (42) connecting two walls, respectively an inner wall (40) and an outer wall (38), extending circumferentially, the radially outer portion of the foil sector being axially interposed between the bottom wall of the hook (32) and the wear-resistant coating (22) and/or between the bottom wall of the hook and the body (20).

5. The sealing module according to any one of the preceding claims, wherein the circumferential extent of each deflector (60) is the same as the circumferential extent of the abradable coating (22) and the circumferential extent of the body (20), and the circumferential ends of the deflectors (60) are substantially axially aligned with the circumferential ends of the body (20) and the abradable coating (22).

6. The sealing module of claim 5, wherein the body (20) includes slots at circumferential ends thereof for receiving sealing strips (58) between sectors, and the deflector (60) includes notches (62) at circumferential ends thereof, the notches being axially aligned with the slots such that upstream axial ends of at least some of the sealing strips enter the notches (62).

7. The sealing module according to any one of the preceding claims, wherein each ring sector comprises at least one sealing strip (58) at one of its circumferential ends, the axial end of which passes through the notch (62) of the deflector (60) and bears axially on its hook (32), and at the other circumferential end of which comprises at least one sealing strip, the upstream axial end of which passes through the notch (62) of the deflector and bears axially on the hook of the adjacent ring sector.

8. A turbine engine comprising at least one sealing module according to any one of the preceding claims.

Technical Field

The present invention relates to a turbine engine module, which may be, for example, a turbine or a forming part of a turbine.

Background

Disclosure of Invention

The invention therefore proposes a turbine engine seal module, in particular for an aircraft, which extends around an axis and comprises a distributor fixed to a casing and which comprises at least one blade connected to an outer platform comprising a spoiler fixed to the casing, the turbine casing further comprising an impeller mounted for rotation within the casing and surrounded by a sealing ring fastened to the casing, the sealing ring being divided into sectors and comprising a row of ring sectors arranged so that the circumferential end edges of two adjacent sectors face each other, each ring sector comprising a body carrying a wear-resistant coating configured to engage with at least one sealing lip carried by the impeller and a hook extending circumferentially by being located upstream of said wear-resistant coating and configured to engage with a fastening track of the casing, the hook has a substantially C-shaped cross section, the opening of which is oriented axially upstream and is intended to receive the rail. The invention is characterized in that each ring sector further comprises a deflector which is arranged upstream of said coating and which extends radially inwards and upstream with respect to the axis, so that a radially inwards end of the deflector extends around a downstream end of the outer platform of the distributor. The invention is also characterized in that the circumferential extent of each hook is the same as the circumferential extent of the deflector, and the circumferential ends of the hooks are deflected in the circumferential direction of the circumferential ends of the deflector.

The deflector is therefore intended to be located within the above-mentioned annular space between the outer periphery of the impeller and the outer periphery of the distributor located upstream, and to enable the passage of gas in this space to be limited. In particular, the deflector makes it possible to limit the passage of leakage gases upstream of each ring sector at the level of the hooks, reducing the risk of these gases passing into the gaps between the sectors at the level of the hooks of each ring sector. The housing is thus best protected and has an optimum service life.

End deflection is also advantageous because gas that may pass radially inward and outward through the circumferential gaps between the circumferential ends of the deflector is blocked by the hooks extending toward these gaps, and gas that may pass radially inward and outward through the circumferential gaps between the circumferential ends of the hooks is blocked by the deflector sectors extending toward these gaps.

The module according to the invention may comprise one or more of the following features taken alone or in combination with each other:

-said deflector comprises an annular foil sector axially interposed between the hook on the one hand and the coating on the other hand, and/or between the hook and the body;

-the foil has a substantially V-shaped cross-section, the radially outer portion of the foil extending radially and the radially inner portion of the foil being truncated and extending radially inwards from upstream to downstream;

the hook comprises an intermediate bottom wall connecting two circumferential walls, respectively a radially inner wall and a radially outer wall, the radially outer portion of the foil sector being axially interposed between the bottom wall of the hook and the coating and/or between the bottom wall of the hook and the body;

-the circumferential extent of each deflector is the same as the circumferential extent of the body and the circumferential extent of the coating, and the circumferential ends of the deflectors are substantially axially aligned with the circumferential ends of the body and the circumferential ends of the coating;

the body comprises, at the circumferential ends of the body, grooves for housing sealing lips between the sectors, and the deflector comprises, at the circumferential ends of the deflector, notches axially aligned with these grooves, so that the upstream axial ends of at least some of the sealing lips enter these notches, and therefore the sealing lips extend as far as possible to the hooks, which optimizes the seal between the sectors;

each ring sector comprises, at one of its circumferential ends, at least one sealing lip, the upstream axial end of which passes through the notch of the deflector and bears axially on the hook of that ring sector, and at the other circumferential end of its circumferential ends, at least one sealing lip, the upstream axial end of which passes through the notch of the deflector and bears on the hook of the adjacent ring sector.

The invention also relates to a turbine engine comprising at least one sealing module as described above.

Drawings

The invention will be better understood and other details, features and advantages thereof will appear, by reading the following description, given as a non-limiting example, with reference to the accompanying drawings, in which:

FIG. 1 is a partial schematic half-view of an axial cross-section of a turbine engine;

FIG. 2 is a partial schematic half-view in axial cross-section of another turbine engine turbine;

FIG. 3 is a perspective partial schematic view, on a larger scale, of a sealing ring of the turbine of FIG. 2;

FIG. 4 is a partial schematic half-view in axial cross-section of a turbine engine module according to the invention;

FIG. 5 is a perspective schematic view of a sealing ring sector of the module of FIG. 4; and

figures 6 and 7 are perspective schematic views on a larger scale of the gaps between sectors of the sealing ring of the module of figure 4.

Detailed Description

Referring initially to fig. 1, fig. 1 shows a turbine 10 (here at low pressure) of a turbine engine, such as a turbine engine or an aircraft turboprop, comprising a plurality of stages (only one of which is shown here) each comprising a distributor 12 formed by a ring of rows of fixed blades carried by a casing 14 of the turbine, and an impeller 16 mounted downstream of the distributor 12 and rotating about an axis (not visible) in a ring 18 secured to the casing 14.

The ring 18 is divided into sectors and formed by a plurality of sectors carried end to end in the circumferential direction by the casing 14 of the turbine.

Each ring sector 18 comprises a circumferentially extending body 20 and a coating 22 of wear resistant material fixed by brazing and/or welding on a radially inner surface of the body 20, the coating 22 being honeycomb-type and intended for minimizing the radial clearance between the impeller and the ring sector 18 by friction on the outer sealing lips 24 of the vanes of the impeller 16. The sealing lip 24 is formed to project above an outer platform 16a of the impeller 16, the outer platform 16a being connected to the blades of the impeller.

Each ring sector 18 comprises, at the upstream end of each ring sector, a hook 32 with a C-or U-shaped cross section, which extends circumferentially and the opening of which opens upstream, the hook 32 engaging axially from downstream on a fastening spoiler 34, which is oriented downstream of the distributor 12, which distributor 12 extends circumferentially upstream of the ring sector 18 on the one hand, and on a cylindrical rail 36 of the housing 14 to which the distributor is fastened on the other hand. The spoiler 34 has a substantially L-shape and protrudes from a platform 12a of the distributor 12, to which at least one blade of the distributor is connected.

The hook 32 of each ring sector 18 comprises two walls 38 and 40 extending circumferentially and upstream, each wall respectively radially outward and radially inward being connected together at the downstream end of each wall by a substantially radial intermediate bottom wall 42 and each wall respectively extending radially outside and inside the track 36, the inner wall 40 retaining the spoiler 34 of the distributor radially on the track 36.

As shown in fig. 1, axial retention of the distributor 12 is ensured by an anti-rotation pin 44 carried by the housing 14 and engaged in a recess of the distributor 12. Axial retention of the distributor downstream is ensured by an annular split ring 46 which is mounted in an annular groove 48 of the track 36, which opens radially inwards. In this case, the spoiler 34 of the distributor 12 is axially supported downstream on a ring 46 which is radially held in a groove of the housing track by an inner wall 40, which inner wall 40 extends radially inside the ring 46. In one variant, the axial stop function of the ring 46 may be directly ensured by the housing track 36.

The downstream end of the ring sector 18 is radially clamped on a cylindrical track 30 of the housing by a distributor located downstream of the ring sector. The ring sectors 18 bear radially outwardly on a radially inwardly cylindrical surface of the housing's track 30 and radially inwardly on a radially outwardly cylindrical surface of the downstream distributor's cylindrical rim 28. Furthermore, the downstream end of the ring sector 18 is clamped axially on the cylindrical track 30 via lugs.

It is also known to thermally protect and resist wear of the track 36 using an annular foil 50, the annular foil 50 being divided into sectors and comprising a circumferential row of foil sectors arranged end-to-end in the circumferential direction. The ring foil has a generally C-shaped or U-shaped cross-section and comprises coaxial ring walls of inner and outer walls 52 and 54, respectively, which are connected together by an intermediate bottom wall 56.

The foil 50 is mounted on the housing track 36 and on the spoiler 34 of the dispenser 12 such that the inner wall 52 of the foil sector 50 is interposed between the inner wall 40 of the hook 32 of the ring sector 18 on the one hand and the spoiler 34 of the dispenser 12 on the other hand, and between the inner wall 40 of the hook 32 of the ring sector 18 and the annular ring 46 on the other hand, such that the outer wall 54 of the foil sector is interposed between the outer wall 38 of the hook 32 of the ring sector and the housing track 36, and such that the bottom wall 56 of the foil sector is interposed between the bottom wall 42 of the hook of the ring sector and the housing track 36.

The foil sectors 50 are made of sheet metal and make it possible to avoid direct contact between the hooks 32 of the ring sectors 18 and the casing rails 36, which makes it possible on the one hand to protect the casing rails from wear caused by friction and on the other hand to thermally protect the casing rails from the ring, which may be very hot in operation due to the proximity to the combustion gases flowing into the turbine duct.

To avoid gas leakage towards the casing 14, it is also known to mount the sealing lip 58 at the level of the circumferential gap between the sectors. The longitudinal edges of the circumferential ends of the ring sectors comprise mounting grooves for the sealing lips 58. The sealing lips 58 each have a generally elongate and flat shape and each comprise a longitudinal edge engaged in a groove in the edge of a ring sector and an opposite longitudinal edge engaged in a groove facing the edge of an adjacent ring sector.

Fig. 1 illustrates a first sealing technique 18 in which the body 20 and hook 32 are formed from a single piece.

Fig. 2 illustrates a second sealing ring technique 18, in which the body 20 and hook 32 are formed from assembled components. The reference numerals used in fig. 2 are the same as those of fig. 1 in the case of representing the same elements.

The second technique consists in the case where the hooks 32 are fixed under the body, just upstream of the coating 22 (as in patent application FR-a 1-3914350), and in the case where the hooks 32 are fixed upstream of the body (as in the case illustrated by way of example).

In operation, combustion gases flow from upstream to downstream in the turbine duct through the blades of the distributor 12 and the modular blades of the impeller 16. The outer periphery of each distributor 12 is spaced apart by an axial gap J adjacent the outer periphery of the impeller 16 through which leakage gas may pass. The engagement of the sealing lip 24 with the abradable coating 22 restricts the upstream to downstream passage of these leakage gases between the wheel 16 and the ring 18. Thus, the leakage gas circulates in an annular space E extending radially between the outer platform 12a of the distributor 12 and the outer platform 16a of the impeller 16, and axially between the downstream spoiler 34 of the distributor 12 and the upstream sealing lip 24a of the impeller 16.

The strips 58 limit the passage of the gas radially outwards from the space E at the level of the circumferential gap between the bodies 20 of the ring sectors. However, as can be seen most clearly in fig. 3, there is always a circumferential gap between the hooks 32, and gas can pass radially outwards from the space E, in particular between the intermediate bottom walls 42 (arrows F) of the hooks 32.

Fig. 4 and the following illustrate an embodiment of the invention that makes it possible to solve at least some of these problems. The reference numerals used in fig. 3 are the same as those of the previous drawings in the case of representing the same elements.

The ring 18 differs from the above-described rings in that in particular each ring sector further comprises a deflector 60 which is arranged upstream of the coating 22 and which extends radially inwards with respect to the above-described axis, so that its radially inward end extends around the downstream end of the outer platform 12a of the distributor 12. In the example shown, the deflector 60 is formed by a separate component from the hooks 32 and the body 20, and is axially interposed between the upstream hooks 32 and the downstream body 20, and between the upstream hooks and the coating 22. The deflector 60 may be formed from an annular foil sector.

The deflector 60 here has a substantially curved orientation and a substantially V-shape. Thus, the deflector comprises a radially outer portion 60a extending into a plane substantially perpendicular to the above-mentioned axis and a truncated radially inner portion 60 b.

The portion 60a is interposed between the intermediate bottom wall 42 of the hook 32 and the upstream end of the body 20 and between the bottom wall of the hook and the upstream end of the coating 22.

The portion 60b extends radially inward from downstream to upstream. The inner periphery of portion 60b defines a diameter D that is less than the minimum inner diameter D1 of hook 32 and the minimum inner diameter D2 of coating 22. The inner periphery here surrounds the end of the outer platform 12a of the distributor 12 with a small radial clearance (fig. 4).

The deflector 60 has a circumferential extent about the same axis as the body 20 and the coating 22. The circumferential ends of the deflector 60 are substantially axially aligned with the circumferential ends of the body 20 and the coating 22, as can be seen in fig. 5.

Thus, fig. 5 also makes it possible to see that the deflector 60 comprises, at its circumferential end, a notch 62 axially aligned with the groove 64 for housing the sealing strip 58 between the sectors. These notches 62 are designed to be penetrated by the strap 58. The height (or radial dimension) of each notch 62 is at least equal to the height of the bottoms of the two grooves 64 facing the housing for the strap (or radial dimension of the grooves 64 for housing the strap), and the width (or circumferential dimension) of each notch 62 is at least equal to the circumferential dimension between the bottoms of the two grooves 64 facing the housing for the strap.

It will be noted in the figures that the longitudinal edge of each circumferential end of the ring sector may comprise two slots 64 for accommodating two strips 58 having different lengths and extending in radial direction on top of each other. The upstream ends of the slots 64 are joined at the upstream end of each edge, and the upstream ends of the slots 64 are in communication with the notches 62, although it is possible for the two strips 58 of each edge to pass through the notches 62 (fig. 4 and 5). In one variation, the edge of each circumferential end of the ring sector may carry a single strip 58.

The circumferential extent of each hook 32 is the same as the circumferential extent of the deflector 60, and the circumferential ends of the hooks 32 are deflected in the circumferential direction of the circumferential ends of the deflector (fig. 5). Thus, each hook 32 comprises a circumferential end portion 32a protruding with respect to the circumferential end of the other part of the ring sector, and another circumferential end portion 32b (fig. 5) removed with respect to the circumferential end of the other part of the ring sector.

It will therefore be appreciated that during installation of the ring 18 on the housing, the ring sectors will interlock circumferentially together (fig. 6).

At the level of the circumferential end of each ring sector, including the projecting end portion 32a, the strip 58 bears axially on this end portion (the support zone Z can be seen in fig. 6 and 7). At the level of the circumferential end of each ring sector, including the removed end portion 32b, the strip 58 does not bear axially on this end portion 32b, but on the end portion 32a of the adjacent ring sector.

As can be seen in fig. 4, the deflector 60 extends into the space E between the hook 32 and the end 12 of the outer platform 12a of the dispenser and divides this space E into two parts, respectively an upstream part and a downstream part. The shape of the space E is imposed on the leakage gas flowing downstream through the gap J in the direction of the labyrinth seal defined by the seal lip 24. Thus, there is less risk of leakage gas circulating at the level of the hooks 32 of the ring sector. Furthermore, due to the circumferential deflection between the hooks 32 and the deflector 60, the gaps between the sectors at the level of these hooks are sealed. Thus, the present invention enables the casing 14 to be effectively protected and the life of the casing 14 to be increased, and also enables losses from the duct to the casing to be avoided, which increases the efficiency of the turbine engine.