Turbine rotor assembly and turbine

Abstract

One aspect of the invention relates to a turbine rotor assembly comprising a disk (2) having an axis X, the disk comprising a plurality of slots (20) including a longitudinal direction (x') for inserting blade roots (32), the longitudinal direction being inclined relative to a straight line d parallel to the axis X and passing through the slots (20). The component includes at least one plate (4) located in a groove (20), the plate including a main portion (40) located in the groove (20) and two anti-rotation portions (421, 431) located on opposite sides of the main portion (40), the two anti-rotation portions pressing against a second radial surface (23) of the disc (2) and intended to contact the blade root (32), characterized in that the two anti-rotation portions (421, 431) are traversed by a plane (P(d,x)) including a straight line d and a rotation axis X, and the width (L42, L43) of at least one of the anti-rotation portions (421, 431) measured perpendicular to the radial and axial directions is greater than the width (L1) of the main portion (40).

Description

Technical Field

[0001] The technical field of this invention is the field of turbines (e.g., turboprop engines or turbojet engines). More specifically, this invention relates to axial stop plates for turbine rotors and rotor assemblies equipped with such turbines. A primary objective of this invention is to provide axial locking for fan blades within the fan blade housing on a fan disk. Background Technology

[0002] A turbine rotor (e.g., a rotor implemented in a low-pressure turbine) extends about a longitudinal axis and typically includes one or more rotor disks with multiple movable vanes on their outer periphery.

[0003] The movable blades have a radially inward extension extending into the blade or into the blade root. Each of these movable blades is housed in one of a plurality of disk slots at its root, which open to the outer peripheral surface of the rotor disk. The blade root is positioned within the slot of the rotor disk by translation along the slot direction at an angle of 0° to 30° relative to the turbine axis.

[0004] To facilitate the mounting of the movable blades onto the rotor disc, sufficient clearance must be provided to allow the blade roots to easily slide into the slots. Therefore, once the blade roots are installed in the slots, a relatively large clearance exists, necessitating axial retaining devices to hold one or more blade roots in place. These axial retaining devices could be, for example, flanges mounted and wedged on both sides of the blades and the disc, or even axial wedges, each positioned in a corresponding slot to hold the blades axially within the slot.

[0005] The axial stop, with a narrow width of 1 mm to 50 mm and a thickness of 0.3 mm to 5 mm, is designed to allow as much air as possible to pass through the gap between the blade root and the bottom of the slot to cool the blade root. Indeed, as the rotor rotates, each blade root is subjected to high temperatures during turbine operation because the blades are positioned in the flow path of the high-temperature gas passing through the low-pressure turbine. Since the disk slots receiving the blade roots are directly exposed to these gases, it may be necessary to cool these slots to prevent any damage to the disks. For this purpose, it is particularly known to collect a portion of the air flowing outside the flow path of the low-pressure turbine and deliver it via a cooling circuit to the slots in the rotor disk—either through channels in the disk (as described in the applicant's French patent application FR3054855) or via a fresh air flow channel formed between the disk and a cylindrical flange axially mounted against the blade root—to supply air between the blade root and the bottom of the disk slots. The flange can further be used to hold the blade root in the opposite axial direction.

[0006] Figure 1A An axial view of the assembly with a low-width axial stop 1 is shown. This assembly includes a main portion 10 housed in a groove 20 of the disc 2, located between the bottom of the groove 20 and the blade root 32 of the blade 3. Figure 1A Two blades 3 are shown; each blade includes a blade 30, a platform 31 extending from the end of the blade 30, and a blade root 32 extending from the platform 31, the blade root 32 being accommodated in a groove 20 located between two teeth 21 of the disk 2. Figure 1B The image also shows an axial stop plate 1, which is shown in three dimensions.

[0007] Therefore, the axial stop 1 includes a main portion 10 housed within and along the groove 20, and a first longitudinal end 13 for axially retaining the blade 3. This first longitudinal end extends from a first end of the main portion 13 to the outside of the groove 20 and abuts against the radial surface of the blade root 32 to secure the blade root in the axial direction. Figure 1A The first radial surface 23 of the disk 2 is shown, and the longitudinal end 13 is visible. The stop plate 1 also includes a second longitudinal end 12 for axially holding the second (invisible) radial surface of the disk 2, the second longitudinal end extending from the end of the main portion 13 opposite to the first end.

[0008] However, the axial stop 1 may be misaligned relative to the direction x' of the groove 20. Figure 2A and Figure 2B The diagrams schematically illustrate an axial stop 1 housed within a groove 20 and aligned within the groove 20 along its inclination direction x' relative to the rotation axis x, and an axial stop 1 housed within the groove 20 but, in the most unfavorable case, not aligned with the inclination direction x' relative to the groove 20. Here, the direction x' of the groove 20 forms a 21° angle with respect to the rotation axis x. The direction x' and the rotation axis x each extend in two parallel planes. Figure 2A In this configuration, the axial stop 1 protrudes only from the disk 2 by its thickness e, representing the second longitudinal end 12 abutting against the radial surface of the disk 2. Of course, if the radial surface of the blade root 3 is flush with the radial surface of the disk 2 opposite to the abutting surface, the first longitudinal end 13 can also protrude from the disk 2. Figure 2BAs can be seen, each axial stop 1 has a width L1 obtained perpendicular to the insertion direction x'. On the one hand, since the width L1 is smaller than the width L2 of the bottom of the corresponding slot 20 (which accommodates the main portion 10 of the end surface facing the blade root 21), and on the other hand, since the insertion direction x' of each slot 20 is tilted by a few degrees (21° in this document) relative to the axis of rotation x, each axial stop 1 can pivot (an angle of 6° in this document), which is measured between the longitudinal direction x” of the axial stop 1 and the insertion direction x' of the slot 20. This pivoting results in the axial stop 1 having an axial protrusion L3, L4 on each side relative to the disk 2, which may cause a displacement of a distance L5 along the translational direction x' of the blade root 32. This displacement distance L5 of the blade root 32 and the axial stop 1 may cause turbulence, reduce turbine efficiency, and damage to the blade 3 and the axial stop 1.

[0009] Figure 1B An axis d is shown passing through the middle of the main part of the axial stop plate 1. This axis d is parallel to the axis of rotation X. The axis d passes through the middle of the axial stop plate 1 in the radial plane p(d, x), which also contains the axis of rotation x.

[0010] Figure 1C An axial view of the axial stop plate 1 along the rotation axis X is shown, where the plane p(d, x) includes the rotation axis x and the axis d and is represented by dashed lines.

[0011] Therefore, it is necessary to prevent the thin-thickness axial stop plate from pivoting. Summary of the Invention

[0012] The present invention provides a solution to the problems discussed above by providing an axial stop plate that is held at an angle by covering the longitudinal end of the rotor in an axial view.

[0013] One aspect of the present invention relates to a turbine rotor assembly comprising: - A disk having a rotation axis, the disk comprising: - The first and second radial surfaces that are axially opposite each other on the disk. - Multiple teeth located on the radial outer periphery of the disk, connecting the first radial surface to the second radial surface, and - Multiple slots, each slot defined by two circumferentially adjacent teeth, each slot extending from a first axial end edge connecting the slot to the first radial surface to a second axial end edge connecting the slot to the second radial surface, each slot having a longitudinal direction for insertion into the root of the impeller, the longitudinal direction preferably being inclined relative to the axis of rotation. - A plate for holding a blade in one of the plurality of slots in a single axial direction, the plate comprising: - A main portion installed within the groove, extending along the longitudinal direction between a first longitudinal end and an opposing second longitudinal end, the main portion having a width perpendicular to both the longitudinal and radial directions. - At the first and second longitudinal ends extending axially on both sides of the main part, each of the first and second longitudinal ends includes an anti-rotation portion. The anti-rotation portion of the first longitudinal end mates with a second radial surface of the disk located radially between the bottom of the groove and the axis of rotation. The anti-rotation portion of the second longitudinal end is designed to mate with the root of the impeller. - Characterized by the fact that at least one anti-rotation portion has a width obtained perpendicular to the radial and axial directions, the width being greater than the width obtained perpendicular to the radial and axial directions of the main portion.

[0014] By virtue of the present invention, the fact that the width of the anti-rotation portion obtained perpendicular to the radial and axial directions is greater than the width of the main portion measured perpendicular to the radial and axial directions can reduce or even prevent the plate from pivoting within the groove along the width of the anti-rotation portion and half the width of the groove. Furthermore, the anti-rotation portion at the first longitudinal end (which engages with a second radial surface of the disc located radially between the groove and the axis of rotation) is positioned to prevent the plate from covering the blade root on either axial side.

[0015] In addition to the features just discussed in the preceding paragraph, a plate according to one aspect of the invention may have one or more of the following additional features, which are considered individually or in any technically possible combination: - According to one embodiment, a first longitudinal end extends radially from one end of the main portion toward the axis of rotation, and a second longitudinal end extends radially outward from the other end of the main portion.

[0016] - According to one embodiment, the first radial surface of the disk is an upstream radial surface, and the second radial surface of the disk is a downstream radial surface.

[0017] - According to one embodiment, each anti-rotation portion extends only on one side relative to the remaining portion of the corresponding first longitudinal end and second longitudinal end, the first longitudinal end and the second longitudinal end including edges that lie in the same plane as the edge of the main portion.

[0018] According to one embodiment, the widths of each of the two anti-rotation portions, obtained perpendicular to both the radial and axial directions, extend in a plane orthogonal to the axis of rotation. Therefore, the anti-rotation portions extend circumferentially to prevent the plate from rotating. This helps to balance the weight at the longitudinal ends. In other words, in an axial view, the plane orthogonal to the axis of rotation passing through the two longitudinal ends creates a cover over these two longitudinal ends. In other words, by radially positioning axis d at the anti-rotation portion within the groove, this axis d (in the same direction) parallel to the axis of rotation X passes through the anti-rotation portion, thereby preventing the plate from pivoting within the groove.

[0019] - According to one example of this embodiment, the plane passes through the axial and circumferential center of the groove.

[0020] - According to one embodiment, the first longitudinal end and the second longitudinal end of the plate have the same shape.

[0021] According to one embodiment, the first longitudinal end and the second longitudinal end have the same dimensions. This achieves symmetrical longitudinal ends, making it easier and more cost-effective to manufacture the longitudinal ends by cutting metal sheets, while also reducing waste.

[0022] According to one embodiment, the maximum width of the main portion perpendicular to both the radial and axial directions is at most half the width of the groove perpendicular to both the radial and longitudinal directions. This allows for the formation of cooling channels and reduces the weight of the plate.

[0023] - According to one embodiment, the maximum width of the main portion perpendicular to the radial and axial directions is at most half the width of the groove perpendicular to the radial and axial directions.

[0024] - According to one embodiment: - The first longitudinal end includes a first curved portion extending from the main portion to the first longitudinal end as an anti-rotation portion. - The second longitudinal end includes a second curved portion extending from the main portion to the anti-rotation portion of the second longitudinal end. - Wherein, the first and second curved portions each have a maximum width obtained perpendicular to the radial and axial directions, respectively, which is smaller than the maximum width obtained perpendicular to the radial and axial directions of the corresponding anti-rotation portions. This makes the plate easy to manufacture while providing an axial spring effect through the curved folds. According to one example, the first longitudinal end includes a first intermediate portion, and the second longitudinal end includes a second intermediate portion, with the first and second intermediate portions each extending between the corresponding folds and rotating portions.

[0025] According to one embodiment, the first longitudinal end includes a first intermediate portion, and the second longitudinal end includes a second intermediate portion. The first intermediate portion and the second intermediate portion each extend between a corresponding bend and an anti-rotation portion. The first intermediate portion and the second intermediate portion each have a width perpendicular to the radial direction and the axial direction, which gradually widens from the bend corresponding to the anti-rotation portion.

[0026] - According to one embodiment, each of these anti-rotation portions has a width obtained perpendicular to the radial and axial directions, which is greater than the width obtained perpendicular to the radial and axial directions of the main portion.

[0027] According to one embodiment, each of these anti-rotation portions has a width obtained perpendicular to both the radial and longitudinal directions, which is greater than the width obtained perpendicular to both the radial and axial directions of the main portion. This simplifies the manufacturing of the plate and allows for the formation of two symmetrical longitudinal ends.

[0028] - According to one example of the latter two embodiments of the component, the plate is formed from a metal sheet that is cut and folded to form a first longitudinal end and a second longitudinal end from the main portion. This simplifies the manufacturing of the plate.

[0029] - According to one embodiment, the assembly further includes blades, each blade including a blade root received in a corresponding slot that opens radially outward from the disk, each plate including: - The main part between the bottom of the corresponding groove and the root of the corresponding impeller. - An anti-rotation portion that mates with the radial surface of the impeller root. Therefore, in this embodiment, this component is the movable impeller of the turbine rotor.

[0030] - According to one embodiment, the component includes multiple air circuits leading to each slot, which allows the presence of the plate while allowing airflow.

[0031] - According to one embodiment, the component includes an air circuit leading to at least one slot.

[0032] - In particular, according to one example of these two embodiments, the disk includes the air circuit.

[0033] - Another aspect of the invention relates to a turbine comprising a turbine rotor assembly according to different aspects, having or not having a combination of features of various embodiments.

[0034] A better understanding of the invention and its various applications can be achieved by reading the following description and reviewing the accompanying drawings. Attached Figure Description

[0035] These accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention.

[0036] [ Figure 1A The diagram schematically shows an axial view of an assembly including a disc, blade root, and plate according to the prior art.

[0037] [ Figure 1B [Illustrative illustration of prior art] Figure 1A A three-dimensional view of the component board.

[0038] [ Figure 1C [Illustrative illustration of prior art] Figure 1A An axial view of the component's plate.

[0039] [ Figure 2A The diagram schematically shows a top view of a prior art plate within a slot.

[0040] [ Figure 2B [Illustrative illustration of prior art] Figure 2A A top view of the plate, which is misaligned within the slot.

[0041] [ Figure 3A The diagram schematically illustrates an axial view of a first example component according to a first embodiment of the present invention, the component including a disk, a blade root, and a plate.

[0042] [ Figure 3B The schematic illustration shows an example of the components according to a first embodiment of the present invention. Figure 3A The axial view is the opposite of the axial view.

[0043] [ Figure 4 The image shows the results based on... Figure 3A A perspective view of an axial retaining plate, representing an example of the component.

[0044] [ Figure 5A [Showing according to] Figure 3A A schematic diagram of the top view of the plate inside the groove.

[0045] [ Figure 5B It shows Figure 3A A schematic diagram of the axial view of the component plate.

[0046] [ Figure 6 A perspective view of an axial retaining plate according to a second example of the component is shown. Detailed Implementation

[0047] These figures are for illustrative purposes only and not for limiting the scope of the invention.

[0048] [ Figure 3AThe diagram shows a schematic axial view of a portion of a component according to an example of a first embodiment of the present invention.

[0049] This component includes at least one disk 2 of a turbine rotor, such as at least one disk of a turbine, more precisely, at least one disk of a low-pressure turbine stage. Disk 2 in... Figure 1A As described in the text, the disk includes a first radial surface 23 (in...) Figure 3A (The middle part is visible) and the second radial surface 22 opposite to the axial direction of disk 2 (as shown in the image). Figure 3B (as shown) Figure 3B Partially schematically showing the view from the other side of disk 2. Figure 3A Components.

[0050] The disk 2 includes a plurality of teeth 21 and a plurality of slots 20, each slot being defined by two circumferentially adjacent teeth 21 located on the radial outer periphery of the disk 2. Therefore, the disk includes a plurality of teeth and a plurality of slots arranged in an alternating circumferential pattern along its outer periphery. Each slot 20 lies in a plane parallel to the axis of rotation X (this plane is in...). Figure 3A and Figure 3B (Not shown in the diagram) The groove 20 extends from the first axial end edge 202 connecting the groove 20 to the first radial surface 23 to the second axial end edge 203 connecting the groove 20 to the second radial surface 22. The groove 20 is inclined relative to the axis of rotation X, but each groove lies in a plane tangent to a circle having the axis of rotation X. A coordinate system xrt is shown, where axis x represents the axial direction parallel to the axis of rotation X, axis r represents the radial direction, and axis t represents the tangential direction. Therefore, each groove 20 has Figure 5A The longitudinal direction x' shown is Figure 5A A schematic top view (i.e., radial view) of the slot 20 is shown, as explained below; these directions are different from each other with respect to the axis of rotation X, but are parallel to each other. Therefore, the longitudinal direction x' (each longitudinal direction is also referred to as an inclined longitudinal direction) lies within a cylinder whose axis intersects the axis of rotation X. Thus, each slot 20 allows the blade root 32 to be inserted along this longitudinal direction x', which is inclined relative to a straight line d (for each slot 20) parallel to the axis x and passing through the corresponding slot 20. The first radial surface 23 and the second radial surface 22 are each perpendicular to the axis of rotation X and the straight line d.

[0051] The assembly includes at least one plate 4 located in the slot 20, but preferably includes as many plates 4 as slots 20. The assembly may also include one blade 3 for each slot 20, each blade including a blade root 32 located in the corresponding slot 20. Figure 3A The image shows only two blades 3, two slots 20, two plates 4, one tooth 21, and two partial teeth 21. This assembly could be, for example, a turbine rotor stage of a low-pressure turbine.

[0052] In the direction from the second radial surface 22 to the first radial surface 23, each plate 4 is used to hold the blade 3 axially in the longitudinal direction x'.

[0053] Each plate 4 includes a main portion 40 mounted in a groove 20, the main portion extending along a longitudinal direction x' between a first longitudinal end 402 and an opposing second longitudinal end 403. Figure 4 The plate 4 is further shown in the three-dimensional view. The first longitudinal end 402 and the second longitudinal end 403 are located in the same radial plane as the first axial edge 202 and the second axial edge 203, respectively.

[0054] In this paper, each main section 40 has a maximum width L1 measured perpendicular to the longitudinal direction x'. In this paper, the main section 40 is plate-shaped and has: a constant width, i.e., a maximum width L1 obtained perpendicular to the longitudinal direction x' and along its entire length in the radial direction; and a constant thickness e4. Figure 4 As can be seen in the image, this thickness is measured radially. In this document, the maximum width L1 is at most half the width L2 of the groove 20 measured in the same direction in the same plane. This allows for the formation of two channels extending along the main portion 40 on both sides when the main portion 40 is radially located between the bottom of the groove 20 and the blade root 32 inserted into the groove. Therefore, each channel can be used to cool the blade root, for example, by connecting to a fresh air duct (not shown).

[0055] The plate 4 also includes a first longitudinal end 42 extending from the first longitudinal end 402 of the main portion 40. The first longitudinal end 42 includes at least one first anti-rotation portion 421, which abuts against a second radial surface 22 of the disk 2 located between the bottom of the groove and the axis x.

[0056] The first anti-rotation portion 421 includes an axial stop surface 422 that contacts the second radial surface 22 of the disk 2 (the second radial surface is referred to herein as the downstream radial surface), and... Figure 3B As shown in the figure, the blade root 32 includes a platform 31 on the upstream side.

[0057] Plate 4 also includes a second longitudinal end portion 43 extending from the second longitudinal end 403 of the main portion 40. The second longitudinal end portion 43 includes at least one second anti-rotation portion 431 abutting against a radial surface 324 of the blade root 32, which is a downstream radial surface on the side of the first radial surface 23 of the disk 2 herein. Thus, the anti-rotation portion 431 includes an axially abutting surface 432 contacting the radial surface 324 of the blade root 32. The second anti-rotation portion 431 extends radially outward (relative to the axis X) from the second longitudinal end 403, i.e., in the opposite direction to the first anti-rotation portion 421, which extends radially inward (towards the axis X) from the first longitudinal end 402.

[0058] At least one of the two anti-rotation portions 421, 431 has a width L42, L43 greater than the maximum width L1 of the main portion. In this example, each of the two longitudinal ends 42, 43 has an anti-rotation portion 421, 431 that is wider than the maximum width L1 of the main portion. The width L42, L43 of each of the two anti-rotation portions 421, 431 is measured perpendicular to both the radial and axial directions.

[0059] The anti-rotation parts 421 and 431 are oriented toward each other in the circumferential direction so that a plane (P(d, x)) passes through them. This plane includes the straight line d and the axis of rotation X, as shown below. Figure 5B As shown, Figure 5B for Figure 5A A schematic diagram of the axial view of plate 4 of the component shown. Figure 5A A schematic top view of the plate 4 in the groove 20 without the blade root 32 is shown, wherein the straight line d passes above the anti-rotation portion 421 of the first longitudinal end 42, and, depending on the radial distance of the straight line d relative to the axis X, passes above or even below the anti-rotation portion 431 of the second longitudinal end 43. Unlike the combination... Figure 2B The existing technology board described Figure 5A The plate 4 shown is prevented from rotating by its anti-rotation portions 421 and 431, which abut against the disc and teeth.

[0060] In this example, the straight line d passes through the middle of the width of the groove 20 measured perpendicular to the axis X, and between the first radial surface 22 and the second radial surface 23 of the disk 2, but can be offset toward one of the two teeth (while remaining parallel to the axis of rotation X). With the straight line d offset toward one of these teeth, one of the two anti-rotation portions 421, 431 advantageously has a larger width than the other anti-rotation portion 431, 421.

[0061] Advantageously, the two anti-rotation portions 421, 431 include sides flush with the plane (P(d, x)). This helps to avoid redundant, non-functional material.

[0062] exist Figure 4 In the example shown, the two longitudinal ends 42 and 43 have the same shape, but can each have different shapes. These longitudinal ends 42 and 43 also have the same dimensions. Therefore, the same machine tool can form these two longitudinal ends 42 and 43 without changing the settings or program.

[0063] In this example, the first longitudinal end 42 includes a first intermediate portion 423 extending from the first anti-rotation portion 421 and a first folded portion 420 extending from the main portion 40 to the first intermediate portion 423; the second longitudinal end 43 includes a second intermediate portion 433 extending from the second anti-rotation portion 431 and a second folded portion 430 extending from the main portion 40 to the second intermediate portion 433. More precisely, the first folded portion 420 extends from the first longitudinal end 402. Furthermore, the second folded portion 430 extends from the second longitudinal end 403 of the main portion 40.

[0064] The first fold 420 and the second fold 430 are each bent to form a spring effect, thereby applying force to the first anti-rotation portions 421 and 431 respectively so that they abut against the disc 2 and the blade root 32 respectively.

[0065] In this example, the first fold 420 and the second fold 430, as well as the first intermediate portion 420 and the second intermediate portion 430, each have a constant width equal to the width L1 of the main portion 40. A fold is formed between each intermediate portion 420, 430 and each anti-rotation portion 421, 421 of each longitudinal end 42, 43.

[0066] Figure 5A The thickness e4 of the first longitudinal end 42 and the second longitudinal end 43 shown is the same as the thickness of the main portion 40. In particular, the plate 4 is formed of a cut and folded metal sheet, which forms two different longitudinal ends 42, 43 from the main portion 40.

[0067] Preferably, the rotor assembly includes a flange (not shown) mounted on one side of the first radial surface 22 of the disk 2 to retain the blade root 32 in a direction opposite to the axial insertion direction.

[0068] Specifically, the rotor assembly may include one or more fresh air circuits (each fresh air circuit leading to each slot 20), and a tooth-to-slot sandwich duct formed between each tooth 21 forming the slot 20 and the main portion 51 of each wedge 5. The flange may also abut against the disc to form part of a cooling channel and provide an outlet or inlet for fresh air to circulate through the tooth-to-slot sandwich duct into the slot 20.

[0069] For example, the component is a turbine rotor, such as a low-pressure turbine rotor extending along a longitudinal axis, which typically includes one or more rotor disks 2, the outer periphery of which has a plurality of movable blades 3. Each movable blade 3 has a radially inward extension extending to the blade 30 or the blade root. These movable blades 3 are received at their roots 32 within slots 20 that open to the outer peripheral surface of the rotor disk.

[0070] By translating along a longitudinal insertion direction x' inclined relative to the turbine axis x, the blade root 32 is positioned within the slot 20 of the rotor disk 2. Each stage of the rotor can therefore include a rotor assembly.

[0071] Therefore, the component may include movable blades 3, each movable blade including a blade root 32 that is received in a corresponding slot 20, thereby forming a turbine rotor stage of a turbine, such as a low-pressure turbine or even a fan rotor.

[0072] Therefore, each main part 51 is located between the bottom of the corresponding groove 20 and the corresponding blade root 32, and each longitudinal axial retaining end 53 is pressed against the radial surface of the corresponding blade root 32.

[0073] Figure 6 A three-dimensional view of plate 4 of an assembly according to an exemplary embodiment is shown. Plate 4 is identical to the plate of the first exemplary embodiment except that the first longitudinal end 42 and the second longitudinal end 43 are different from each other, and the widths of the intermediate portions 430, 420 between the anti-rotation portions 421, 431 and the corresponding first folds 420, 430 gradually increase as they extend until they reach the maximum widths L42, L43 of the anti-rotation portions 431, 422. In this example, the radial lengths of each of the first longitudinal ends 42, 43 are different; in particular, the first longitudinal end 42 is shorter radially (i.e., in height) than the second longitudinal end 43 because the “height” of the anti-rotation portion 421 is limited by the axial stop flange integrated at the disc. Therefore, it is not possible to extend it in height. Furthermore, the anti-rotation portion 431 includes a side edge on the protruding side relative to the bend 430, which is beveled so that it does not protrude from the spherical radial surface 324 of the impeller root 32.

[0074] The present invention also relates to a turbine including such a turbine rotor assembly.

[0075] Unless otherwise specified, the same element appearing in different figures shall have a single reference numeral.

Claims

1. A turbine rotor assembly, the turbine rotor assembly comprising: - A disk (2) having a rotation axis (x), the disk comprising: ○ The first radial surface (23) and the second radial surface (22) are axially opposite to the disk (2). ○ A plurality of teeth (21) located on the radial outer periphery of the disk (2), the plurality of teeth connecting the first radial surface (23) to the second radial surface (22), and ○ A plurality of slots (20), each slot being defined by two circumferentially adjacent teeth (21), each slot (20) extending from a first axial end edge (202) connecting the slot (20) to the first radial surface (23) to a second axial end edge (203) connecting the slot (20) to the second radial surface (23), each slot (20) including a longitudinal direction (x') for inserting a blade root (32), said longitudinal direction preferably being inclined relative to the axis of rotation (x). - A plate (4) for holding the blade (3) in one of the plurality of slots (20) in a single axial direction, the plate comprising: ○ A main portion (40) installed in the groove (20), the main portion (40) extending along the longitudinal direction (x') between a first longitudinal end (402) and an opposite second longitudinal end (403), the main portion having a width (L1) measured perpendicular to the longitudinal direction (x') and the radial direction. ○ A first longitudinal end (42) and a second longitudinal end (43) extending axially on both sides of the main part (40), each of the first longitudinal end (42) and the second longitudinal end (43) includes an anti-rotation portion (421, 431). The anti-rotation portion (421) of the first longitudinal end (42) engages with the second radial surface (22) of the disk (2). The anti-rotation portion (421) extending from the first longitudinal end (42) engages with the second radial surface of the disk located radially between the bottom of the groove and the axis of rotation. The anti-rotation portion (431) of the second longitudinal end (43) is designed to engage with the root (32) of the impeller. ○ Characterized by at least one anti-rotation portion (421, 431) having a width (L41, L42) perpendicular to the radial and axial directions, which is greater than the width (L1) of the main portion (40) perpendicular to the radial and axial directions.

2. The turbine rotor assembly according to the preceding claim, wherein, The first radial surface (23) of the disk (2) is the upstream radial surface, and the second radial surface (22) of the disk (2) is the downstream radial surface.

3. The turbine rotor assembly according to claim 1 or 2, wherein, The widths (L41, L42) of each of the two anti-rotation portions (421, 431) perpendicular to the radial and axial directions extend in a plane orthogonal to the axis of rotation.

4. The turbine rotor assembly according to any one of the preceding claims, wherein, The first longitudinal end (42) and the second longitudinal end (43) of the disk (4) have the same shape.

5. The turbine rotor assembly according to the preceding claim, wherein, The first longitudinal end (42) and the second longitudinal end (43) have the same dimensions.

6. The turbine rotor assembly according to any one of the preceding claims, wherein, The maximum width (L1) of the main part (40) perpendicular to the radial and axial directions is at most half the width (L2) of the groove (20) perpendicular to the radial and longitudinal directions.

7. The turbine rotor assembly according to any one of the preceding claims, wherein: - The first longitudinal end (42) includes a first bend (420) of an anti-rotation portion (421) extending from the main portion (40) to the first longitudinal end (42). - The second longitudinal end (43) includes a second bend (430) of an anti-rotation portion (431) extending from the main portion (40) to the second longitudinal end (43). - Wherein, the first curved portion (420) and the second curved portion (430) each have a maximum width obtained perpendicular to the radial direction and the axial direction, and the maximum width of the first curved portion and the maximum width of the second curved portion are respectively smaller than the maximum width (L42, L43) of the corresponding anti-rotation portion (421, 431) obtained perpendicular to the radial direction and the axial direction.

8. The turbine rotor assembly according to any one of the preceding claims, wherein, The first longitudinal end (42) includes a first intermediate portion (423), and the second longitudinal end (43) includes a second intermediate portion (433). The first intermediate portion and the second intermediate portion each extend between the corresponding bend (420, 430) and the anti-rotation portion (421, 431). The first intermediate portion (423) and the second intermediate portion (433) each have a width perpendicular to the radial direction and the axial direction, which gradually widens from the corresponding bend (420, 430) toward the anti-rotation portion (421, 431).

9. The turbine rotor assembly according to any one of the preceding claims, wherein, Each of the anti-rotation portions (421, 431) has a width obtained perpendicular to the radial direction and the longitudinal direction of the main portion, which is greater than the width (L1) obtained perpendicular to the radial direction and the longitudinal direction of the main portion (40).

10. The turbine rotor assembly according to any one of the preceding claims, wherein, The plate (4) is formed of a metal sheet that has been cut and folded to form the first longitudinal end (42) and the second longitudinal end (43) from the main part (40).

11. The turbine rotor assembly according to any one of the preceding claims, the turbine rotor assembly further comprising a plurality of blades, each blade including a blade root (30) received in a corresponding slot (20) opening at the radial outer periphery of the disk (2), each plate (4) comprising: - The main part (40) located between the bottom of the corresponding groove (20) and the root of the corresponding blade (30). - An anti-rotation portion (431) that mates with the radial surface of the blade root (32).

12. The turbine rotor assembly according to any one of the preceding claims, the turbine rotor assembly comprising an air circuit leading to at least one slot (20).

13. A turbine comprising a turbine rotor assembly according to any one of the preceding claims.

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