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CN-116568909-B - Turbine blade for an aircraft turbine provided with a channel for injecting a main flow into an interlabial cavity

CN116568909BCN 116568909 BCN116568909 BCN 116568909BCN-116568909-B

Abstract

The invention relates to a vane (60) and a sealing element (59) forming an assembly for a turbine of a turbine. The vane (60) comprises a blade (61) and a platform (62) connected to the sealing element (59). An internal passage (80) passes through the platform (62) to draw fluid circulating in a main conduit (21A) defined by the platform and to inject the fluid so drawn into an inter-lip cavity (50 a, 51A) defined by the sealing element (59). The invention enables the formation and strength of secondary flows to be reduced while improving the tightness.

Inventors

  • Jean Charles Marie Coucero
  • THOMAS LANGEVIN
  • Bernoit guylaum sylette

Assignees

  • 赛峰飞机发动机公司

Dates

Publication Date
20260512
Application Date
20211201
Priority Date
20201210

Claims (11)

  1. 1. An assembly for a turbine (17, 18) of a turbine (11) extending about a longitudinal axis (A1), the assembly comprising at least one vane (60) and a sealing element (59), the sealing element (59) forming a wear part (41) or lip (47) of a dynamic sealing joint (40, 45), the vane (60) comprising a platform (62) and a vane (61) extending from the platform (62), the platform (62) forming a first surface (71) from which the vane (61) extends and which is intended to define a main duct (21A) in which the vane (61) extends for receiving fluid flowing in a direction (S1) from a leading edge (63) of the vane towards a trailing edge (64) of the vane and from an upstream portion (P1) of the platform (62) towards a downstream portion (P2) of the platform, the sealing element (59) being connected to the platform (62) and forming a first surface (71) from which the vane (61) extends, and which is intended to define at least one internal channel (51A) and at least one opening (82) through which the inner part (51A) is intended to be opened, the assembly comprising at least one internal channel (51A) opening (81), the at least one suction opening into a first surface (71) of an upstream portion (P1) of the platform (62), the at least one injection opening into the second surface (59A), the vane (60) including a root (62A) between the platform (62) and the sealing element (59), the internal passage (80) passing through the platform (62), the root (62A) and the sealing element (59), and The at least one suction opening (81) is positioned upstream of the leading edge (63) of the blade (61) with respect to the flow direction (S1) of the fluid in the main conduit (21A).
  2. 2. The assembly of claim 1, wherein the sealing element (59) is annular.
  3. 3. Assembly according to claim 1 or 2, wherein the upstream portion (P1) of the platform (62) is delimited by an imaginary line (LL 1) equidistant from the leading edge (63) of the blade (61) and the trailing edge (64) of the blade.
  4. 4. The assembly of claim 1 or 2, wherein, -The at least one suction opening (81) is positioned downstream of the leading edge (63) of the blade (61) and upstream of the trailing edge (64) of the blade (61) with respect to the flow direction (S1) of the fluid in the main conduit (21A).
  5. 5. The assembly of claim 1 or 2, wherein the at least one internal channel (80) comprises a plurality of internal channels that are fluidly independent of each other and/or a plurality of internal channels that are fluidly connected to each other.
  6. 6. Assembly according to claim 1 or 2, wherein the at least one suction opening (81) is provided at the lower surface side of the blade (61).
  7. 7. Assembly according to claim 1 or 2, wherein the assembly comprises the wear part (41, 46) and a rotor element (44,39) carrying the lips (42, 47) of the dynamic sealing joint (40, 45), the inter-lip cavity (50 a,51 a) extending longitudinally between two of the lips (42, 47) and extending radially between the wear part (41, 46) and a rotor element (44,39) carrying the lips (42, 47).
  8. 8. Assembly according to claim 1 or 2, wherein the blade (60) is intended to be fastened to the casing of the turbine (11), the sealing element (59) forming a wear part (41) and being carried by the root of the blade (60), the wear part (41) being intended to cooperate with a lip (47) carried by the rotor of the turbine (11).
  9. 9. Turbine (17, 18) for a turbine (11), the turbine comprising an assembly according to any one of claims 1 to 8.
  10. 10. Turbine (11) comprising a turbine (17, 18) according to claim 9.
  11. 11. Method for manufacturing an assembly according to any one of claims 1 to 8, comprising the step of additive manufacturing of at least one vane (60) of the assembly.

Description

Turbine blade for an aircraft turbine provided with a channel for injecting a main flow into an interlabial cavity Technical Field The present invention relates to the field of turbines for aircraft turbines. Background Conventional turbines for aircraft turbines include one or more stages, each stage including a stator and a rotor wheel. The stator includes stationary vanes connected by their radially outer ends to the casing and distributed circumferentially about the longitudinal center axis of the turbine to form a stator ring. The rotor wheel comprises a disc and vanes connected to the disc by their radially inner ends while being circumferentially distributed around the disc. The stator of a stage is configured such that fluid flow (typically including gas from the combustion chamber) penetrating into the stage is accelerated and deflected by the stator vanes in the direction of the vanes of the rotor wheel of the stage, thereby driving the vanes of the rotor wheel of the stage to rotate about the longitudinal central axis. Typically, each stator and rotor vane of a turbine includes a blade and two platforms radially defining therebetween a circumferential portion of an annular main duct in which the blade extends. The fluid passing through the turbine flows mainly in this main pipe. During conventional turbine operation, the interaction of the fluid with the stator and rotor wheels creates vortices on the platform of the buckets, forming a "secondary" flow. To illustrate this phenomenon, fig. 1 shows a part of two vanes 1A and 1B of a turbine stator 1, these vanes 1A and 1B being adjacent to each other in the circumferential direction. Fig. 1 shows more specifically the radially inner part of the blade 2 of each of the vanes 1A and 1B and the platform 3. The blade 2 of each vane 1A and 1B includes a leading edge 4, a trailing edge 5, a lower surface 6 and an upper surface 7. The platform 3 of each vane 1A and 1B defines, radially internally, a circumferential portion of an annular main duct in which the fluid flows in a direction S1 from the leading edge 4 of the blade 2 towards the trailing edge 5 of the blade 2. Given the typical viscosity of the fluid circulating in the main conduit of the turbine, the flow of this fluid along the surface of the platform 3 has a velocity gradient GV1 such that in the vicinity of this surface, the velocity of the fluid layer is lower as it approaches this surface. Furthermore, the fluid flowing in the main conduit is subjected to a pressure gradient GP1, in this example the pressure gradient GP1 being oriented from the lower surface 6 of the blade 2 of the vane 1B towards the upper surface 7 of the blade 2 of the vane 1A. The pressure gradient GP1 is typically sufficient to deflect a fluid layer flowing near the surface of the platform 3. This results in the occurrence of various types of eddy currents. The first type of vortex T1, called "horseshoe-shaped, has the shape of two counter-rotating branches distributed on both sides of the blade 2. A second type of vortex T2, called "channel vortex", is formed between two adjacent blades 2. A third type of vortex T3, called "angular vortices", travels along the connecting line between the blade 2 and the platform 3 of each vane. Such secondary flows T1, T2 and T3, which typically occur at the root and tip of the blade 2, are not directed along the main flow direction S1 of the fluid flowing through the main duct, resulting in a reduced efficiency of the turbine and an increased kerosene consumption. Disclosure of Invention It is an object of the invention to limit the formation of such secondary streams or to reduce the intensity of such secondary streams. More generally, the present invention is directed to improving the performance of a turbine of a turbomachine. To this end, the invention is directed to an assembly for a turbine of a turbomachine according to the features of claim 1. The internal channel enables suction of a portion of the fluid flowing along the first surface of the platform and avoids that portion of the fluid facilitating the formation of the secondary flow. Thus, the present invention makes it possible to limit the formation of secondary streams and to reduce the intensity of secondary streams that can still be produced, thereby increasing the efficiency of the turbine and reducing the kerosene consumption of the turbine. Given the static pressure difference between the area of the main conduit surrounding the at least one suction opening and the area surrounding the at least one injection opening, fluid circulating in the main conduit and reaching the at least one suction opening is indeed sucked into the at least one internal channel. Given the general structure of a turbine that can be equipped with such an assembly, the area surrounding the at least one injection opening is located outside the main duct and has a lower static pressure than the area to which the at least one suction opening o