Turbomachine bladed wheel
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2020-09-08
- Publication Date
- 2026-07-31
AI Technical Summary
The existing bladed wheels in turbomachines suffer from significant leakage through the clearances between the circumferential ends of the flange sectors, leading to reduced efficiency due to higher pressure differentials across the wheel.
Implementing a labyrinth-type seal formed by protruding and recessed parts at the circumferential ends of the flange sectors, which interlock to minimize leakage through these clearances.
The labyrinth seal significantly reduces leakage rates, enhancing the efficiency of the turbomachine by maintaining pressure integrity and compensating for thermal expansion of the flange sectors.
Smart Images
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Abstract
Description
Description Title of the invention: Bladed turbine wheel for turbomachinery. Technical field of the invention. The invention includes a bladed turbomachine wheel, in particular a rotor wheel of a turbomachine compressor. Prior art A bladed wheel from the earlier art, known from document FR 2913 064 in the name of the Plaintiff, is illustrated in figures 1 and 2. The bladed wheel 1 is intended for a high-pressure compressor of a turbomachine and includes a rotor disc 2 having an axle. In the following description, the terms axial, radial, and circumferential are defined with respect to the axis of disk 2, which is also the axis of bladed wheel 1 and of the turbomachine. Furthermore, the terms upstream and downstream are defined with respect to the direction of gas flow within the turbomachine. The disc 2 comprises a central hub 3 and teeth 4 extending radially outward from the hub 3. The teeth 4 delimit between themselves dovetail-shaped recesses 5 extending axially. The bladed wheel 1 also includes blades 6 regularly distributed around its circumference and mounted on the outer periphery of the disc 2. More specifically, each blade 6 has a radially internal foot, engaged in a recess 5 of the disc 2, and a blade 7 extending radially outwards from the foot. A platform 8 extends between the foot and the blade 8. The bladed wheel 1 further comprises an annular flange 9 extending radially opposite the alveoli 5 of the disk 2 and bearing on an axially downstream end of the disk 2 and the feet of the blades 6. The flange 9 is made up of a plurality of angular sectors 10 arranged circumferentially end to end so as to form said annular flange 9. The downstream ends of the teeth 4 of the disc 2 have downward-facing hooks 11, which cooperate with complementary upward-facing hooks 12 of the flange 9. The hooks 11 and 12 maintain each sector 10 of the flange 9 in axial and radial position. The bladed wheel | also includes an annular ring 13 mounted between a radially internal area of the flange 9 and a downstream radial face 14 of the hub 3 of the disc 2. The ring 13 is housed in a groove 15 of the flange 9. The radially external periphery 9a of the flange 9 rests on the downstream ends of the teeth 4 and / or the feet of the blades 6. The radially internal periphery 9b of the flange 9 is supported, via the annular ring 13, on the downstream radial face 14 of the hub 3 of the disc 2. As illustrated in [fig.3], the adjacent sectors 10 of the flange 9 are mounted with a circumferential clearance j between the corresponding circumferential ends 16 of the sectors 10. Such a clearance j results in radial air slots or passages 17 located circumferentially and radially opposite the alveoli 5 of the disk 2. In operation, in the case of a compressor, the pressure downstream of the bladed wheel 1 is greater than the pressure upstream of said bladed wheel 1. The air located downstream of the bladed wheel 1 then tends to pass through the aforementioned gaps j and then the assembly gaps between the feet of the blades 6 and the teeth 4 of the disc 2 delimiting the cells 5, before emerging upstream of the bladed wheel 1. Such a leakage rate penalizes the efficiency of the turbomachine. Presentation of the invention The invention aims to remedy this drawback in a simple, inexpensive and reliable way. To this end, the invention relates to a bladed turbomachine wheel, comprising a disk extending around an axis, the disk comprising a hub and teeth on the radially external periphery of the hub, the teeth delimiting between themselves recesses, the wheel comprising blades regularly distributed around the circumference, each blade comprising a radially internal foot mounted in a recess of the disk and a blade extending from the foot, the wheel comprising an annular flange extending radially opposite the recesses of the disk and adapted to bear against an axially downstream or upstream end of the disk and / or the feet of the blades, the flange comprising a plurality of angular sectors arranged circumferentially end to end so as to form said annular flange, characterized in that each sector comprises at least one circumferential end having a projecting part,engaged by interlocking into a recessed portion of an adjacent circumferential end of an adjacent sector, said protruding and recessed portions extending circumferentially and radially. In this way, the protruding and recessed sections form a labyrinth-type seal capable of ensuring watertightness between the circumferential ends of the flange sectors. This seal generates a significant pressure drop, thus limiting the leakage flow through the interface zones between the circumferential ends of the flange sectors. This also limits leakage flow between the upstream and downstream sides of the bladed wheel, at the level of the clearances between the feet and the disc teeth. This helps to improve the efficiency of the turbomachine. The bladed wheel can be a rotor wheel, suitable for being driven in rotation around of the axis of the disc. The bladed wheel can be a compressor wheel, for example, a high-pressure compressor wheel, or a turbomachine wheel. The bladed wheel can also be a turbine wheel. Each circumferential end of each sector may have a shoulder delimiting the protruding part and the recessed part. In other words, each sector can have a substantially constant thickness in the circumferential direction, the protruding part and the recessed part of each circumferential end being formed by the creation of a shoulder which locally reduces the thickness of material in order to form the recessed part, the area of material defining the protruding part. The protruding and recessed parts can be fitted together with play in the circumferential direction. The circumferential clearance can be between 0.1 and 0.3 mm. The circumferential clearance makes it possible in particular to compensate for any expansion effects of the sectors, especially when the flange is subjected to high temperatures during operation. The circumferential interlocking distance between the protruding part and the recessed part is, for example, between 3 and 5 mm. The bladed wheel may include an annular sealing ring mounted between an upstream or downstream face of the disc hub and the flange. The circlip may be engaged in at least one recessed area of the flange to ensure its centering and retention in position. The circlip may be located opposite an area on the radially inner periphery of the flange. The circlip may have a conical surface, flaring out towards the disc, cooperating with a complementary conical surface of the flange. The downstream or upstream end of the disc may include hooks cooperating with complementary hooks of the flange sectors, said hooks ensuring the retention of the flange sectors in position. The hooks can be adapted to retain the flange sectors radially and axially. In particular, the hooks can prevent the sectors from moving radially outwards when subjected to centrifuge forces during the rotation of the bladed wheel. The circumferential ends of the sectors can be located circumferentially opposite the alveoli of the disc and the feet of the blades. The turbomachine compressor may include a bladed wheel of the aforementioned type. The invention also relates to a turbomachine, characterized in that it comprises a compressor of the aforementioned type or a bladed wheel of the aforementioned type. A turbomachine is, for example, a turbojet or a turboprop aircraft engine. The invention also relates to an aircraft, characterized in that it comprises a turbomachine of the aforementioned type. The aircraft is, for example, an airplane. Brief description of the figures [fig.1] is a perspective view of part of a bladed wheel according to the prior art, [fig.2] is a detailed cross-sectional view of part of the bladed wheel of the earlier art, [fig.3] is a schematic top view of part of the bladed wheel of the earlier art, [fig.4] is a perspective view of part of a bladed wheel according to one embodiment of the invention, [fig.5] is a view corresponding to [fig.3], of a bladed wheel according to the invention, [fig.6] is a perspective and detail view of a part of the bladed wheel according to the invention, [fig.7] is a perspective view of one end of a flask sector, [Fig. 8] is a perspective view of a second end of a flange sector. Detailed description of the invention Figures 4 to 8 illustrate a bladed wheel 1 according to one embodiment of the invention. The bladed wheel 1 is intended for a high-pressure compressor and comprises a rotor disc 2 having a shaft. The disc 2 includes a central hub 3 and teeth 4 extending radially outward around the periphery of the hub 3. The teeth 4 define dovetail-shaped recesses 5 extending axially. The bladed wheel 1 also includes blades 6 regularly distributed around the circumference and mounted on the outer periphery of the disc 2. More particularly, each blade 6 has a radially internal foot, engaged in a cavity 5 of the disc 2, and a blade 7 extending radially outwards from the foot. The bladed wheel 1 further comprises an annular flange 9 extending radially opposite the alveoli 5 of the disk 2 and bearing on an axially downstream end of the disk 2 and the feet of the blades 6. The flange 9 consists of a plurality of angular sectors 10 arranged circumferentially end to end so as to form said annular flange 9. The downstream ends of the teeth 4 of the disc 2 have downward-facing hooks 11, which cooperate with complementary upward-facing hooks 12 of the flange 9. The hooks 11 and 12 help to maintain each tooth in an axial and radial position. sector 10 of flask 9. The bladed wheel 1 also includes an annular ring 13, similar to that illustrated in Figures 1 and 2, mounted between a radially internal area 9b of the flange 9 and a downstream radial face 14 of the hub 3 of the disc 2. The ring 13 is housed in a groove 15 of the flange 9, so as to ensure its centering and retention in position. The ring 13 has a conical surface, flaring out towards the disc 2, cooperating with a complementary conical surface 15a of the flange 9, widening out towards the disc 9. The radially external periphery 9a of the flange 9 is supported on the downstream ends of the teeth 4 and / or the feet of the blades 6. The radially internal periphery 9b of the flange 9 is supported, via the annular ring 13, on the downstream radial face 14 of the hub 3 of the disc 2. As illustrated in figures 5 to 8, each circumferential end 16 of each sector 10 has a projecting part 18, engaged by interlocking into a recessed part 19 of an adjacent circumferential end 16 of an adjacent sector 10, said projecting parts 18 and recessed parts 19 extending circumferentially and radially. In particular, each circumferential end 16 of each sector 10 has a shoulder delimiting the projecting part 18 and the recessed part 19. Each sector 10 has a substantially constant thickness in the circumferential direction, the protruding part 18 and the recessed part 19 of each circumferential end 16 being formed by the making of a shoulder which locally reduces the thickness of material so as to form the recessed part 19, the area of material defining the protruding part 18. The protruding part 18 and the recessed part 19 can be fitted together with a clearance j' in the circumferential direction. The circumferential clearance j' can be between 0.1 and 0.3 mm. The circumferential fitting distance d between the protruding part 18 and the recessed part 19 is, for example, between 3 and 5 mm. In this way, the protruding parts 18 and the recessed parts 19 form a labyrinth-type joint capable of ensuring the seal between the circumferential ends of the sectors 10 of the flange 9, such a joint generating a significant pressure loss allowing to limit the leakage flow through the interface zones between the circumferential ends 16 of the sectors 10 of the flange 9. The leakage flows between the downstream and upstream sides of the bladed wheel 1 are thus limited, at the level of the clearances between the feet and the teeth 4 of the disc 2. This helps to improve the efficiency of the turbomachine. Furthermore, the circumferential play j' allows, in particular, for compensation of any potential expansion effects of sectors 10, especially when the flange 9 is subjected to high temperatures during operation.
Claims
Demands
1. Rouc aubagéc (1) of turbomachinc, comprising a disk (2) extending around an axis, the disc (2) comprising a hub (3) and teeth (4) on the radially external periphery of the hub (3), the teeth (4) delimiting between them are the alveoli (5), the wheel (1) comprising regular blades (6) loosely distributed around the circumference, each blade (6) comprising a radially internal foot mounted in a socket (5) of the disc (2) and a blade (7) extending from the foot, the wheel (1) comprising a flange annular (9) extending radially opposite the alveoli (5) of the disc (2) and capable of bearing against an axially downstream or upstream end of the disc (2) and / or the feet of the blades (6), the flange (9) comprising a plurality of angular sectors (10) arranged circumferentially joined end to end so as to form said annular flange (9), characterized in that each sector (10) has at least one circumferential extremity differential (16) having a projecting part (18), engaged by em- limping in a hollow part (19) of a circumferential end adjacent rent (16) of an adjacent sector (10), said parties in projection (18) and recess (19) extending circumferentially and ra- dialement.
2. Bladed wheel (1) according to claim 1, characterized in that each circumferential end (16) of each sector (10) includes a shoulder delimiting the projecting part (18) and the recessed part (19).
3. Bladed wheel (1) according to claim 1 or 2, characterized in that the protruding parts (18) and recessed parts (19) are fitted together with a clearance (j') in the circumferential direction.
4. Bladed wheel (1) according to any one of claims 1 to 3, characterized in which includes an annular sealing ring (13) mounted between a upstream or downstream face (14) of the hub (3) of the disc (2) and the flange (9).
5. Bladed wheel (1) according to any one of claims 1 to 4, characterized in that the downstream or upstream end of the disk (2) has hooks (11) cooperating with complementary hooks (12) of sectors (10) of the flange (9), said hooks (10, 11) ensuring that it is held in position sectors (10) of the flask (9).
6. Bladed wheel (1) according to any one of claims 1 to 5, characterized in what the circumferential extremities (16) of the sectors (10) are located circumferentially opposite the alveoli (5) of the disc (2) and feet of the dawns (6).
7. Turbomachine compressor, characterized in that it comprises a bladed wheel (1) according to one of the claims | to 6.
8. Turbomachine, characterized in that it comprises a compressor according to claim 7 or a bladed wheel (1) according to one of the claims instructions 1 to 6.
9. Aircraft, characterized in that it comprises a turbomachine according to the re- demand 8.