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CN-122029344-A - Flow guide assembly for a turbomachine

CN122029344ACN 122029344 ACN122029344 ACN 122029344ACN-122029344-A

Abstract

The invention relates to a flow guiding assembly (6) comprising-two outer annular shell portions (62) and an inner annular shell portion (64) defining a first flow channel (V2) therebetween for a flow (F2), wherein the shell portions are each divided into an outer shell portion and an inner shell portion (620,640) arranged circumferentially about an axis (a), and-a discharge duct (66) located within the inner shell portion (62) and opening into an opening (65) formed in the inner shell portion (62), wherein the ducts (66) define an inner discharge flow path (F3) intended to be ejected into the first flow channel (V2) through the openings (65), and wherein each of the ducts (66) is formed integrally with one of the inner shell portion portions (640) by a composite material, the inner shell portion comprising the opening (65) into which the duct (66) opens.

Inventors

  • Julian Ventrella
  • Jerome Paul Marceau MACE
  • Philip Didier Edmund Andre Liberal Nabias
  • FLORIAN BENJAMIN KEVIN LACROIX

Assignees

  • 赛峰飞机发动机公司

Dates

Publication Date
20260512
Application Date
20241007
Priority Date
20231016

Claims (15)

  1. 1. A flow guiding assembly (6) for a turbine (10), in particular for an aircraft, the assembly (6) comprising: Two annular shell parts, respectively an outer annular shell part (62) and an inner annular shell part (64), which extend in such a way that one annular shell part surrounds the other annular shell part and about the same axis (A), which outer and inner shell parts (62, 64) delimit between them a first flow channel (V2) for a flow (F2), which outer and inner shell parts (62, 64) consist of a plurality of sections and each comprise an outer and an inner shell section (620,640) arranged circumferentially end to end about said axis (A), -Discharge ducts (66) located inside the inner housing part (62) and opening into openings (65) formed on the inner housing part (62), the discharge ducts (66) defining an internal passage (660) of a discharge flow (F3) configured to be injected into the first channel (V2) through the openings (65), Characterized in that each of the discharge ducts (66) is formed integrally of composite material with one of the sections of the inner housing part (640), which inner housing part section (640) comprises an opening (65), which discharge duct (66) opens into.
  2. 2. The flow directing assembly of claim 1 wherein each inner housing section (640) extends axially between upstream and downstream rims (642, 644) extending at least partially radially inward of the section (640), an opening (65) to which the discharge conduit (66) opens being located between these upstream and downstream rims (642, 644).
  3. 3. The flow guiding assembly according to claim 2, characterized in that at least one of the upstream and downstream rims (642, 644) is L-shaped in axial cross-section and comprises a radial wall (640 a ) connected to a cylindrical wall (640 b ) forming a free end of the inner shell section (640).
  4. 4. A flow directing assembly according to claim 2 or 3, wherein the flow directing assembly further comprises: -at least one gasket (8) arranged against an upstream edge (642) of the inner housing section and in particular against a cylindrical wall (642 b) of the inner housing section (640), and/or -A heat exchanger (9) arranged against a downstream edge (644) of the inner housing section (640), in particular against a cylindrical wall (644 b) of the inner housing section (640).
  5. 5. The flow guiding assembly according to any one of claims 2 to 4, wherein each inner housing section (640) comprises a radially inwardly protruding rib (646) at its downstream rim (644), e.g. at its radial wall (644 a), and the rib is located between the opening (65) and the downstream rim (644).
  6. 6. The flow directing assembly of any one of claims 2 to 5 wherein each inner housing section (640) has an additional thickness (E 642 ,E 644 ) at least one of the upstream and downstream rims (642, 644).
  7. 7. The flow directing assembly of any one of the preceding claims wherein each discharge conduit (66) is tubular and includes an elongate axis (B) along an interior passage (660) of the discharge conduit that is inclined relative to a section of the inner housing portion (640).
  8. 8. The flow guiding assembly according to any of the preceding claims, wherein each discharge conduit (66) is connected to the shell portion by a curved or bent connection (665) each having the same thickness (E 665 ) as the minimum thickness (E 66 ) of the discharge conduit (66) and/or the minimum thickness (E 640 ) of the region of the inner shell portion (640).
  9. 9. The flow guiding assembly according to any of the preceding claims, further comprising a drain fin (666) fitted or formed in each of the openings (65) of the inner housing section (640).
  10. 10. The flow guiding assembly according to any of the preceding claims, characterized in that the assembly (6) comprises connecting arms (68) for connecting the outer housing part (62) and the inner housing part (64) together, which connecting arms extend radially between the outer housing part (62) and the inner housing part (64) and are connected to the outer housing part (62) and the inner housing part (64), which arms (68) are tubular and can be penetrated by an auxiliary device, which auxiliary device is configured to penetrate the first channel (V2).
  11. 11. A flow directing assembly according to any preceding claim, wherein the composite material has an organic or ceramic matrix.
  12. 12. The flow directing assembly of any one of the preceding claims, wherein the composite material comprises fibers selected from carbon fibers, glass fibers, aramid fibers and polyamide fibers, or a mixture of at least two of these fibers.
  13. 13. The flow directing assembly according to any one of claims, wherein each discharge conduit (66) is inclined at an angle (a) with respect to a section of the inner housing portion (640), such as between 20 ° and 70 °.
  14. 14. Turbine (10), in particular for an aircraft, comprising a flow guiding assembly (6) according to any of the preceding claims.
  15. 15. Method for manufacturing a flow guiding assembly (6) according to any of claims 1 to 13, characterized in that the method comprises the steps of: (a) A female mould is provided comprising a cavity and, (B) A fiber preform is formed in a cavity of the mold, (C) The fiber preform is compacted and the fiber preform is consolidated, (D) Consolidating the fibrous preform with a cured resin to integrally form each discharge duct (66) with one of the inner shell section (640), (E) Removing the part obtained in step (d) from the mould, and (F) The housing portion (64) is provided.

Description

Flow guide assembly for a turbomachine Technical Field The present invention relates to the field of turbines, and in particular to the field of double flow turbines for aircraft. In particular, the present invention relates to a flow directing assembly for a turbine, for example to enable one or more flows to be directed in a passage of the turbine. The invention also relates to a turbine comprising such a flow guiding assembly. Background The prior art includes, inter alia, documents US-A1-2018/291841 and FR-A1-3119199. Dual flow turbines, particularly for aircraft, typically include a fan and a gas generator (or engine). The gas generator includes, from upstream to downstream, according to the flow of gas in the turbine, at least one compressor, a combustion chamber and at least one turbine. The gas generator may be mounted in an inner housing, also referred to as an inter-channel housing (or intermediate housing). The fan is located upstream of the gas generator and in the outer housing. The air passing through the turbine is split into a main stream (or hot air stream) flowing in the gas generator and a secondary stream (or cold air stream) from the fan flowing around the inter-channel housing. The dual flow turbine includes a main duct through which the main flow passes, and a secondary duct extending around the main duct and through which the secondary flow passes. The primary and secondary channels are separated by an inter-channel housing. The turbine is also equipped with a flow directing system or assembly, also known as a "kit engine (KIT ENGINE)". The guide assembly is used for guiding a secondary flow, in particular originating from the compressor, and/or a so-called discharge flow, into a secondary duct of the turbine. To achieve this, the pilot assembly includes a drain conduit (or valve) known as a variable drain valve (Variable Bleed Valve, VBV) or process drain valve (Handling Bleed Valve, HBV). The discharge duct is located in the inter-channel housing and causes a portion of the main flow compressed by the compressor to be sucked into and injected into the secondary flow of the secondary duct (in particular for discharging the high pressure compressor), which portion is mixed with the secondary flow. The purpose of this discharge is to stabilize the compressor operation by limiting turbulence, rotational flow separation or floating phenomena. Fig. 1 and 2 illustrate examples of such flow directing assemblies 6, which may include: Two annular shell portions (outer annular shell portion 62 and inner annular shell portion 64) extending one around the other and around the same axis a, the two shell portions 62, 64 defining a first flow channel V2 therebetween for a first flow F2 (e.g. a secondary flow in a turbine), the shell portions 62, 64 being constituted by a plurality of segments and each comprising shell segment portions 620, 640 arranged circumferentially end to end around the axis a, -Connecting arms 68 for connecting the shells 62, 64 together, the connecting arms extending radially between the shells 62, 64 and being connected to these shells 62, 64, these arms 68 being tubular and being able to be traversed by auxiliary means configured to pass through the first flow channel V2, and Discharge ducts 66 located inside the inner shell portion 64 and opening into openings 65 formed on the inner shell portion 64, these discharge ducts 66 defining internal passages for the discharge flow F3, which is configured to be injected into the first flow channel V2 through these openings 65. The guide assembly 6 performs the following functions: directing a tertiary flow (e.g. exhaust flow) formed by a primary flow entering the exhaust duct to a secondary duct (e.g. a first flow channel of a directing assembly), Ensuring the aerodynamic continuity of the tertiary flow, Guiding and ensuring continuity of the main flow entering the guiding assembly and exiting in the discharge duct, Ensuring the passage and maintenance of auxiliary devices (such as electrical, mechanical, hydraulic, gas/oil exchangers) between the gas generator and the outer casing (or nacelle) surrounding the gas generator, Providing a mechanical coupling between the gas generator and the nacelle, Ensuring fire protection between the different compartments of the gas generator and the secondary duct, and -Enabling access to the equipment and auxiliary devices for maintenance purposes. The guide assembly 6 includes a drain fin (or grid) 666 attached into each of the openings 65 of the inner housing section 640. The drain fins 666 rectify the drain flow in the secondary conduit and prevent any foreign objects from entering the main conduit via the drain conduit 66. The inner housing section 640, the drain pipe 66 and the drain fin 666 are connected to each other by a bolt type attachment. The guide assembly 6 further comprises a sealing element 7 attached between the inner housing section 640 and the discharge conduit 66 to provi