EP3847339A1

EP3847339A1 - Rotor disc with axial retention of the blades, assembly of a disc and a ring, and turbomachine

Info

Publication number: EP3847339A1
Application number: EP19774140.8A
Authority: EP
Inventors: Patrick Jean Laurent SULTANA; Arnaud Lasantha GENILIER
Original assignee: Safran Aircraft Engines SAS
Current assignee: Safran Aircraft Engines SAS
Priority date: 2018-09-04
Filing date: 2019-08-26
Publication date: 2021-07-14
Anticipated expiration: 2039-08-26
Also published as: EP3847339B1; CN112585334A; US20210355830A1; FR3085420A1; FR3085420B1; WO2020049238A1; US11486252B2; CN112585334B

Abstract

The invention relates to a rotor disc (36) for a turbomachine (10), the disc (36) extending circumferentially about an axis (A) and having a plurality of cells (60) configured to receive the roots of blades (58), each cell (60) having a downstream radial wall (64) configured to axially lock the blade root (58) in the cell (60), each downstream radial wall (64) comprising a ventilation channel (66) for the cell (60) having an inlet orifice (68), which opens into the cell (60), and an outlet orifice (70), which opens onto a downstream surface of the disc (36). The invention also relates to an assembly for a turbomachine, comprising such a disc (36) and an upstream retaining ring, and to a turbomachine comprising such an assembly.

Description

ROTOR DISC WITH AXIAL STOP OF THE BLADES. DON DISC AND RING AND TURBOMACHINE ASSEMBLY

Technological area

The present disclosure relates to a rotor disc for a turbomachine, for example a low pressure turbine rotor disc of a turbojet engine.

Technological background

In known manner, a turbomachine comprises an aerodynamic stream in which succeed mobile wheels (part of the rotor) which recover the energy of the gases from the combustion chamber and the distributors (part of the stator) which straighten the gas flow in the aerodynamic stream. The movable wheels generally comprise a movable disc rotating around an axis of rotation, the disc being provided with blades. The blades can be manufactured separately and assembled on the disk by fitting the blade roots into the cells of the disk. The shape of the cells is generally obtained by pinning each cell. The cells are therefore through. As a result, the blades are generally blocked axially on their upstream and downstream faces by retaining rings.

In particular in a low pressure turbine of a turbomachine, the axial retaining rings of the blades generally located upstream and downstream of the blade roots are subjected to stresses which can cause gas leaks, in particular the retaining ring downstream which is subjected to more stresses than the upstream retaining ring, since it is subjected to mechanical and thermal stresses which are greater, in particular because of the aerodynamic axial force which tends to push the dawn downstream. In addition, the blade is also blocked axially by a movable ring bearing against the downstream retaining ring. This movable ring rotates around the axis of rotation with the rotor and generally bears against two successive stages of the turbine rotor, the movable ring being clamped axially between the two stages in order to guarantee the axial locking of the blades in the disc. . Also, the lifetime of the retaining rings, in particular of the downstream retaining ring, and of the movable ring is dependent on the mechanical and thermal stresses that these parts undergo in operation. Replacing these parts can prove to be a very complex and costly operation, particularly in terms of time.

It will be noted that the terms “upstream” and “downstream” are defined with respect to the direction of air circulation in the turbomachine.

Presentation

The present description aims to remedy these drawbacks at least in part.

To this end, the present disclosure relates to a rotor disk for a turbomachine, the disk extending circumferentially around an axis and comprising a plurality of cells configured to receive blade roots, each cell comprising a downstream radial wall configured to axially block the root of the blade in the cell, each downstream radial wall comprising a ventilation channel for the cell, comprising an inlet orifice which opens into the cell and an outlet orifice which opens on a downstream surface of the disc.

The axis of rotation of the disc defines an axial direction which corresponds to the direction of the axis of symmetry (or quasi-symmetry) of the disc. The radial direction is a direction perpendicular to the axis around which the disc extends circumferentially and intersecting this axis. Likewise, an axial plane is a plane containing the axis of the disc and a radial plane is a plane perpendicular to this axis.

Unless otherwise specified, the adjectives inside / inside and outside / outside are used with reference to a radial direction so that the inside of an element is, in a radial direction, closer to the axis of rotation of the disc as the outer part of the same element.

Each cell having a downstream radial wall, it is possible to axially block the blade in the cell and to dispense with the use of a downstream retaining ring. It is understood that the downstream radial wall may have come integrally with the disc. In addition, due to the absence of the downstream retaining ring, it is also possible to remove the retaining hook of the downstream retaining ring of the blade. Thus, the blade, in particular the blade root and the internal platform, can have a simpler geometric shape. The manufacture of dawn is therefore less complex.

In addition, due to the absence of the downstream retaining ring, it is also possible to overcome the upstream part of the movable ring, that is to say the part of the movable ring upstream of the sealing wipers. Indeed, the movable disc may no longer be in compression between two rotor stages to maintain the downstream retaining ring.

The assembly of the rotor stages, and in particular of the blades on the discs of the different rotor stages is less complex and involves the use of a reduced number of elements. A reduction in rotor weight is thus obtained.

Thanks to the presence of a ventilation channel whose inlet orifice is present in each downstream radial wall, it is possible to ventilate each cell and thus to ensure efficient and homogeneous cooling of all the cells of the disk.

In addition, the cooling of the disc is controlled by the size of the outlet of the ventilation channel.

With this arrangement, it is possible to reduce the leakage of the air flow in the cooling flow. The flow of the cooling flow can therefore be better controlled and therefore reduced, which makes it possible to increase the purge flow upstream of the first movable wheel at constant total flow (purge flow and cooling flow). Thus, this arrangement improves the efficiency of the turbomachine.

The turbomachine can for example be a turbojet.

The rotor can for example be a turbine rotor.

The turbine can for example be a low pressure turbine.

In some embodiments, the outlet orifice opens onto a downstream surface of the downstream radial wall.

In certain embodiments, each downstream radial wall comprises an outlet orifice.

In some embodiments, the ventilation channel connects at least two inlet ports and an outlet port. The ventilation channel is present in the downstream radial wall and also in parts of the disc delimiting the cells, for example disc teeth which delimit the cell, in the circumferential direction.

In some embodiments, the ventilation channel connects all the inlet ports.

The ventilation channel can be a circumferential channel connecting all the inlet ports with each other.

The circumferential direction is a direction along a circle which is in a radial plane and whose center is the axis of rotation.

It is understood that the ventilation channel may have another shape than a circumferential shape.

In some embodiments, the inlet ports have an inlet diameter and the outlet ports have an outlet diameter, the number of inlet ports being greater than or equal to the number of outlet ports and the inlet diameter being greater than or equal to the outlet diameter.

In some embodiments, the inlet orifices have a frustoconical shape widening from downstream to upstream.

The flaring of the frustoconical shape makes it possible to limit the pressure drop in the ventilation channel.

In some embodiments, the inlet ports have an inlet diameter and the outlet ports have an outlet diameter, the number of inlet ports being greater than or equal to the number of outlet ports and the inlet diameter being less than or equal to the outlet diameter.

When the number of inlet ports is greater than the number of outlet ports, the manufacture of the disc is facilitated because the number of outlet ports is limited.

Furthermore, when the outlet diameter is greater than the inlet diameter, the evacuation of dust which may be present in the air flow is facilitated.

In some embodiments, at least one of the inlet ports is axially aligned with at least one of the outlet ports. The orifices being of generally circular shape, it is understood that the center of the circle forming the inlet orifice and the center of the circle forming the outlet orifice are aligned in a direction parallel to the axis of rotation when a straight line connecting the center of the inlet orifice to the center of the outlet orifice is parallel to the axis of rotation.

In some embodiments, at least one of the inlet orifices is offset circumferentially and / or radially with respect to at least one of the outlet orifices.

Thus, the center of the circle forming the inlet orifice and the center of the circle forming the outlet orifice can be offset from one another in a circumferential and / or radial direction.

In some embodiments, the downstream radial wall has a thickness greater than or equal to 0.5 mm (millimeter) and less than or equal to 10 mm.

The thickness of the walls makes it possible to limit the mass of the disc.

In some embodiments, the inlet orifices have a diameter greater than or equal to 0.5 mm and less than or equal to 10 mm.

The inlet orifice having a diameter greater than or equal to 0.5 mm makes it possible to limit the risk of fouling of the ventilation duct.

In some embodiments, the outlet tubes have a diameter greater than or equal to 0.5 mm and less than or equal to 10 mm.

The outlet orifice having a diameter greater than or equal to 0.5 mm makes it possible to limit the risk of fouling of the ventilation duct.

The present disclosure also relates to an assembly for a turbomachine comprising a disc as defined above and an upstream retaining ring.

The assembly may include vanes assembled on the disc.

The present description also relates to a turbomachine comprising an assembly as defined above.

It is understood that the turbomachine may include one or more stages comprising an assembly as defined above. For example, the turbomachine can be a turbojet. For example, the assembly as defined above can be arranged in the low pressure turbine of the turbojet engine.

Brief description of the drawings

Other characteristics and advantages of the subject of this presentation will emerge from the following description of embodiments, given by way of nonlimiting examples, with reference to the appended figures, in which:

- Figure 1 is a schematic view in longitudinal section of a turbojet;

- Figure 2 is an enlarged view of part of Figure 1;

- Figure 3 is a partial perspective view of a turbine disk according to a first embodiment;

- Figure 4 is a partial perspective view of the disc of Figure 3;

- Figure 5 is a partial perspective view of a turbine disk according to a second embodiment;

- Figure 6 is a sectional view along the plane VI-VI of Figure 5;

- Figure 7 is a view similar to the view of Figure 5 with a partial section showing a ventilation channel.

In all of the figures, the elements in common are identified by identical reference numbers.

detailed description

Figure 1 shows in section along a vertical plane passing through its main axis A, a turbofan engine 10 which is an example of a turbomachine. The turbofan 10 has, from upstream to downstream according to the circulation of the air flow F, a blower 12, a low pressure compressor 14, a high pressure compressor 16, a combustion chamber 18, a high pressure turbine 20 , and a low pressure turbine 22. The terms “upstream” and “downstream” are defined with respect to the direction of air circulation in the turbomachine, in this case, according to the circulation of the air flow F in the turbojet engine 10.

The turbojet engine 10 includes a fan casing 24 extended rearward, that is to say downstream, by an intermediate casing 26, comprising an external ferrule 28 and an internal ferrule 30 parallel and arranged in a radial direction R, internally with respect to the outer shell 28. The radial direction R is perpendicular to the main axis A.

The terms "external" and "internal" are defined with respect to the radial direction R so that the internal part of an element is, in the radial direction, closer to the main axis A than the external part of the same item.

The intermediate casing 26 further comprises structural arms 32 distributed circumferentially and extending radially between the internal ferrule 30 to the external ferrule 28. For example, the structural arms 32 are bolted to the external ferrule 28 and on the internal ferrule 30. The structural arms 32 make it possible to stiffen the structure of the intermediate casing 26.

The main axis A is the axis of rotation of the turbojet engine 10 and the low pressure turbine 22. This main axis A is therefore parallel to the axial direction.

The low pressure turbine 22 comprises a plurality of impellers which form the rotor of the low pressure turbine 22.

FIG. 2 represents a first and a second stage of the low pressure turbine 22. The first stage comprises a first impeller 34 formed of a first disc 36 on the periphery of which the blades 38 are assembled. Similarly, the second stage comprises a second impeller 40 formed of a second disc 42 on the periphery of which are assembled vanes 38. The first and second impeller 34, 40 are separated from each other by a distributor 44 .

The first and second discs 36, 42 of the rotor each comprise at least one connecting ferrule 46.

In the embodiment of Figure 2, the first disc 36 has a connecting ring 46, in this case a connecting ring 46 downstream and the second disc 42 has two connecting ferrules 46, a connecting ferrule 46 upstream and a connecting ferrule 46 downstream. The first and second discs 36, 42 are assembled with each other by means of a plurality of bolts 48 arranged in a circumferential direction C in orifices carried by the connecting ferrule 46 downstream of the first disc 36 and by the connecting ferrule 46 upstream of the second disc 42. The bolts 48 also make it possible to assemble a movable ring 50 to the first impeller 34 and to the second impeller 40.

In Figure 2, the movable ring 50 comprises an assembly web 52 extending in the radial direction R.

The movable ring 50 carries sealing wipers 54 which cooperate in sealing with a ring of abradable material 56 carried by the dispenser 44.

As shown in Figure 2, the blade 38 is assembled on the first disc 36 by insertion of a blade root 58 in a cell 60 for receiving the blade root.

As can be seen in FIG. 3, the cell 60 is delimited in the circumferential direction C by teeth 62 forming parts of the first disc 36 delimiting the cells 60 in the circumferential direction C. Each cell 60 has a wall downstream radial 64. The downstream radial wall 64 is integrally formed with the teeth 62 of the disc 36 and therefore the disc 36 and makes it possible to axially block the blade root 58 in the cavity 60. In particular, the axial blocking is achieved by abutment of a downstream face 58A of the blade root 58 against an upstream face 64A of the downstream radial wall 64.

In the embodiment of Figures 2 to 4, each downstream radial wall 64 comprising a ventilation channel 66 of the cell. The ventilation channel 66 of the cell 60 comprises an inlet orifice 68 and an outlet orifice 70. The ventilation channel 66 opens, via the inlet orifice 68, onto the upstream face 64A of the downstream radial wall 64 and, through the outlet orifice 70, on a downstream face 34A of the disc 34. In the embodiment of FIGS. 2 to 4, the outlet orifice 70 opens onto the downstream face of the radial wall 64, c ' that is to say that each downstream radial wall 64 has an inlet port 68 and an outlet port 70. In an embodiment not shown, the outlet orifice 70 could lead to a part of the downstream face 34A of the disc 34 which is not the downstream face of the downstream radial wall 64.

In the embodiment of Figures 2 to 4, the inlet port 68 of each ventilation channel 66 is aligned with the outlet port 70 in a direction parallel to the main axis A, it is ie a direction parallel to the axis of rotation of the first disc 36. In addition, the inlet port 68 and the outlet port 70 are circular, the inlet port 68 has a diameter inlet D68 and the outlet orifice 70 has an outlet diameter D70, the inlet diameter D68 of the inlet orifice 68 being equal to the outlet diameter D70 of the outlet orifice 70. The channel of ventilation 66 therefore has the form of a right cylinder with a circular base, the axis of which is parallel to the main axis A of the turbojet engine 10.

The vanes 38 of the first impeller 34 have a retaining hook 72 of an upstream retaining ring 74 for the axial locking of the vanes 38 in the cells 60.

In the embodiment of Figure 2, only the first disc 36 comprises cells each having a downstream radial wall. It will be noted that the blade 38 of the second impeller 40 has hooks 72 for holding an upstream and downstream retaining ring. It is understood that the second disc 42 could also include cells each having a downstream radial wall to allow the axial locking of the blade roots. The same applies to the other stages of the low pressure turbine 22. The blades 38 of these discs could then have only one groove 72 for receiving an upstream retaining ring. It will be noted that in the embodiment of FIG. 2, the movable ring 50 includes a portion playing the role of upstream retaining ring 74 for the blades 38 of the second impeller 40.

For example, the first disc 36 can be produced by additive manufacturing, in particular by an additive manufacturing process on a powder bed.

In what follows, the elements common to the various embodiments are identified by the same reference numerals.

Figures 5 to 7 show a second embodiment. In the embodiment of FIGS. 5 to 7, the channel of ventilation 66 of the first disc 36 extends in the circumferential direction C and goes around the first disc 36.

In the embodiment of FIGS. 5 to 7, the ventilation channel 66 connects all the inlet ports 68 to one another and connects at least two inlet ports 68 to an outlet port 70.

For example, in the embodiment of Figures 5 to 7, each downstream radial wall 64 does not have an outlet port 70, each downstream radial wall 64 having an inlet port 68, that is to say say that an inlet port 68 opens onto the upstream face 64A of each downstream radial wall 64. For example, the downstream radial wall 64 of a cell 60 in two has an outlet port 70. This example is not limiting. Thus, the downstream radial wall 64 of a cell 60 out of three, or even more, may include an outlet orifice 70.

In the embodiment of Figures 5 to 7, in a first cell 60 whose downstream radial wall 64 has an inlet port 68 and an outlet port 70, the inlet port 68 is aligned with the outlet of the ventilation channel 66 of the first cell 60.

In a second cell 60, adjacent to the first cell 60, the downstream radial wall 64 has an inlet port 68 communicating with the outlet port 70 of the first cell 60 through the ventilation channel 66 and the orifice inlet 68 of the second cell 60 is not aligned with the outlet orifice 70, the inlet orifice 68 is offset in the circumferential direction C relative to the outlet orifice 70 of the ventilation channel 66 of the second cell 60. It is understood that the ventilation channel 66 of the second cell 60 connects the inlet port 68 of the downstream radial wall 64 of the second cell 60 to the outlet port 70 of the downstream radial wall 64 of the first cell 60.

In the embodiment of Figures 5 to 7, the inlet diameter D68 of the inlet orifices 68 is less than the outlet diameter D70 of the outlet orifices 70.

Although the present description has been described with reference to a specific embodiment, it is obvious that various modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. For example, the inlet may not be aligned in a direction parallel to the main axis A with the outlet. In addition, individual characteristics of the various embodiments mentioned can be combined in additional embodiments. Therefore, the description and the drawings should be considered in an illustrative rather than restrictive sense.

Claims

1. rotor disc (36, 42) for a turbomachine (10), the disc (36, 42) extending circumferentially around an axis (A) and comprising a plurality of cells (60) configured to receive blade roots (58), each cell (60) having a downstream radial wall (64) configured to axially lock the blade root (58) in the cell (60), each downstream radial wall (64) comprising a ventilation channel (66) of the cell (60) comprising an inlet orifice (68) which opens into the cell (60) and an outlet orifice (70) which opens onto a downstream surface of the disc (36, 42).

2. Disc (36, 42) according to claim 1, wherein the outlet orifice (70) opens onto a downstream surface of the downstream radial wall (64).

3. Disc (36, 42) according to claim 1 or 2, wherein the ventilation channel (66) connects at least two inlet ports (68) and an outlet port (70).

4. Disc (36, 42) according to any one of claims 1 to

3, in which the ventilation channel (66) connects all the inlet openings

(68).

5. Disc (36, 42) according to any one of claims 1 to

4, in which the inlet ports (68) have an inlet diameter (D68) and the outlet ports (70) have an outlet diameter (D70), the number of inlet ports being greater than or equal the number of outlet orifices and the inlet diameter (D68) being less than or equal to the outlet diameter (D70).

6. Disc (36, 42) according to any one of claims 1 to

5, wherein at least one of the inlet ports (68) is axially aligned with at least one of the outlet ports (70).

7. Disc (36, 42) according to any one of claims 1 to 6, in which at least one of the inlet orifices (68) is circumferentially and / or radially offset with respect to at least one of the orifices of outlet (70).

8. Disc (36, 42) according to any one of claims 1 to 7, wherein the downstream radial wall (64) has a thickness greater than or equal to 0.5 mm and less than or equal to 10 mm.

9. Disc (36, 42) according to any one of claims 1 to 8, in which the inlet orifices (68) and / or the outlet orifices (70) have a diameter greater than or equal to 0.5 mm and less than or equal to 10 mm.

10. An assembly for a turbomachine comprising a disc (36, 42) according to any one of claims 1 to 9 and an upstream retaining ring (74).

11. Tubomachine (10) comprising an assembly according to claim 10.