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CN-121986208-A - Device for cooling a turbomachine annular casing having a longitudinal axis, turbomachine component, turbomachine and turbomachine

CN121986208ACN 121986208 ACN121986208 ACN 121986208ACN-121986208-A

Abstract

An apparatus (40) for cooling a turbomachine annular casing (46) having a longitudinal axis X includes a gas collecting housing (42) and a cooling wire set (52) extending circumferentially about the longitudinal axis. The wire set is connected to the gas collection housing such that an interior volume of the gas collection housing is in fluid communication with an interior volume of the wire set. The wire set includes injection holes (57) that open radially inward toward the casing (46). The gas collecting housing comprises a radially inner surface (42 b) having an opening (50) intended to be arranged radially opposite the casing (46). The opening allows fluid communication between the internal volume of the gas collection housing and the internal volume of the wire set. The cooling device further includes a joint (58) having a generally V-shaped radial cross-section with the apex of the V oriented radially outward.

Inventors

  • Sherman Kanagalatnam
  • Nikulas Daniel Drapotai
  • Xieri Pierre Mary Lai Kuitai

Assignees

  • 赛峰飞机发动机公司

Dates

Publication Date
20260505
Application Date
20241004
Priority Date
20231004

Claims (10)

  1. 1. A cooling device (40) for a turbomachine annular casing (46) having a longitudinal axis X, comprising a gas collecting housing (42) and a cooling ramp (52) extending circumferentially around the longitudinal axis X, the ramp (52) being connected to the gas collecting housing (42) such that the internal volume of the gas collecting housing (42) is in fluid communication with the internal volume of the ramp (52), the ramp (52) comprising injection holes (57) opening radially inwards towards the radially outer surface of the casing (46), characterized in that the gas collecting housing (42) comprises a radially inner surface (42 b) having an opening (50) intended to be arranged radially opposite to the radially outer surface of the casing (46), the opening (50) allowing fluid communication between the internal volume of the gas collecting housing (42) and the internal volume of the ramp (52), wherein the cooling device (40) further comprises a joint (58) having a substantially V-shaped radially outwards oriented apex.
  2. 2. The cooling device (40) according to the preceding claim, wherein the ramp (52) is intended to be arranged radially between a radially outer surface of the casing (46) and an opening (50) of the gas-collecting housing (42).
  3. 3. The cooling device (40) of any of the preceding claims, wherein the ramp (52) comprises first and second branches (52 a,52 b) extending circumferentially opposite from both sides of the gas-collecting housing (42).
  4. 4. The cooling device (40) according to the preceding claim, wherein the joint (58) is a three-way joint (58 a,58b,58 c) with a first tube (58 a) connected to the first branch (52 a) of the ramp (52), a second tube (58 b) connected to the second branch (52 b) of the ramp (52), and a third tube (58 c) connected to the opening (50).
  5. 5. The cooling device (40) of claim 1, wherein the joint (58) is symmetrical about a plane P that contains a longitudinal axis X of the turbomachine and a direction through an axis Y of an opening (50) of the gas collecting housing (42).
  6. 6. The cooling device (40) of claim 4, comprising a plurality of cooling ramps (52), the radially inner surface (42 b) of the gas-collecting housing (42) having a plurality of openings (50), each opening being intended to be arranged radially opposite the radially outer surface of the casing (46), the device (40) comprising a plurality of tee joints (58 a,58b,58 c) joints (58), each ramp (52) being associated with a respective opening (50) and joint (58).
  7. 7. The cooling device (40) according to the preceding claim, wherein the plurality of openings (50) are arranged along a longitudinal axis X.
  8. 8. A turbomachine assembly comprising an annular turbomachine casing (46) and a cooling device (40) according to any of the preceding claims, said cooling device being mounted on said casing (46) and surrounding said casing.
  9. 9. Turbomachine, for example a low pressure turbomachine (7), comprising a turbomachine assembly according to the preceding claim.
  10. 10. Turbomachine comprising at least one turbomachine (7) according to the preceding claim.

Description

Device for cooling a turbomachine annular casing having a longitudinal axis, turbomachine component, turbomachine and turbomachine Technical Field This document relates to a device for cooling a casing of an aero-turbomachine (for example a double-duct turbomachine). Background Fig. 1 shows a double-duct double-rotor turbomachine 1. The axis of the turbomachine, called the X-axis, corresponds to the axis of rotation of the rotating member. Hereinafter, the terms axial and radial are defined with respect to the X-axis. The turbomachine 1 comprises, in order from upstream to downstream in the direction of airflow, a fan 2, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6 and a low-pressure turbine 7. The air from the fan 2 is split into a primary air flow 8 flowing through a primary annular flow passage 8 and a secondary air flow 10 flowing through a secondary annular flow passage 11 surrounding the primary annular flow passage 9. The low pressure compressor 3, the high pressure compressor 4, the combustion chamber 5, the high pressure turbine 6 and the low pressure turbine 7 are all arranged in a main annular flow passage 9. The high pressure turbine rotor 6 is rotationally coupled with the high pressure compressor rotor 4 by a first shaft 12 forming a high pressure body. The low pressure turbine rotor 7 and the low pressure compressor rotor 3 are rotationally coupled by a second shaft 13 forming a low pressure body, the fan 2 may be connected directly to the low pressure compressor rotor 3 or, for example, by a planetary gear train. As is more clearly shown in fig. 2, the low-pressure turbine 7 comprises in particular a plurality of axially successive stages, each stage comprising a row of blades 14 and a guide 19 constituted by a ring of vanes. The blade row comprises a disk 15 on which blades 16 are mounted. The ends of the blades 16 are surrounded by a fixing ring 17, which fixing ring 17 is made of an abradable material, said fixing ring 17 being fixed to a turbine casing 18. The guide 19 is located downstream of the bucket row 14. The guide 19 and retaining ring 17 are mounted to the casing by means of a flange or hook 20 extending from the radially inner surface of the casing 18. To ensure high efficiency of the turbomachine, it is necessary to limit the amount of air flow that does not flow through each stage bucket row 14, i.e. to limit leakage between the radially outer ends of the buckets 16 and the retaining ring 17 made of abradable material. For this purpose, the gap at this interface must be controlled, since it depends on the temperature of the casing 18, in particular of the region of the casing 18 containing the hooks or flanges 20 supporting the fixing ring 17. The main gas flow from the combustion chamber 5 has a high temperature and will heat downstream components, such as the stationary and moving components of the turbines 6, 7. In order to control the clearances and prevent premature failure of the various stationary and moving parts of the turbine, it is desirable to provide an efficient cooling device that can be effectively integrated into the turbomachinery environment. Patent application FR 3 050 228 in the name of the applicant relates to a component of a cooling device D for a low-pressure turbine casing C, which device comprises an axially extending gas-collecting housing B, as shown in fig. 3. The charge cooling air from the secondary flow path is delivered from a portion downstream of the turbo-machinery fan to the air-collecting housing B through a longitudinally extending air-supply duct, and is connected to the air-supply opening O of the air-collecting housing B. The device further comprises a tube T extending circumferentially from both sides of the gas collecting housing B to both sides of the gas collecting housing B. The ramp R comprises two said tubes T, which are constituted by bends of circular section, each tube T extending circumferentially around the casing, for example 360 °. Each tube T has an air inlet opening into the flow channel of the collector housing B and a closed distal end. Each tube T also has a cylindrical wall provided with air injection holes directed towards the casing C, so that cooling air can enter the gas-collecting housing B and then the tube T, finally cooling the casing by being injected through the injection holes directed towards the casing C. This is called impingement cooling because the air impinges on the casing C. It has been found that the region of the casing facing the housing B is cooled more sufficiently than the rest of the casing C in the circumferential direction. This is because the cooling air flowing out of the radially inner surface of the housing, after striking the casing, is less efficient in discharging than the striking air flowing out of the tube. The housing thus forms a local barrier, preventing the cooling air after impingement from flowing radially o