Device for cooling turbomachine annular casing having longitudinal axis, turbomachine assembly, turbomachine and turbomachine

Abstract

A device (40) for cooling a turbomachine annular casing (46) having a longitudinal axis X comprises a gas collection 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 comprises injection holes (57) which are open radially inward towards the cartridge receiver (46). The gas collection housing comprises a radially inner surface (42b) having an opening (50) intended to be arranged radially opposite the cartridge receiver (46). The opening allows fluid communication between the interior volume of the gas collection housing and the interior volume of the wire set. The cooling device also includes a joint (58) having a generally V-shaped radial cross-section, the apex of which is oriented radially outward.

Description

Technical Field

[0001] This document relates to a device for cooling the casing of an aerospace turbine (e.g., a dual-ducted turbine). Background Technology

[0002] Figure 1 A dual-duct, dual-rotor turbomachinery 1 is shown. The axis of this turbomachinery is called the X-axis, which corresponds to the axis of rotation of the rotating component. In the following text, the terms axial and radial are defined relative to the X-axis.

[0003] The turbomachinery 1 includes, from upstream to downstream along the airflow direction, the following components in sequence: fan 2, low-pressure compressor 3, high-pressure compressor 4, combustion chamber 5, high-pressure turbine 6, and low-pressure turbine 7.

[0004] The air from fan 2 is divided into a main airflow 8 that flows through the main annular channel 8 and a secondary airflow 10 that flows through the secondary annular channel 11 surrounding the main annular channel 9.

[0005] 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 located in the main annular flow channel 9.

[0006] The high-pressure turbine rotor 6 and the high-pressure compressor rotor 4 are rotatably coupled through the first shaft 12 to form the high-pressure main body.

[0007] The low-pressure turbine rotor 7 and the low-pressure compressor rotor 3 are rotatably coupled through the second shaft 13 to form a low-pressure main body; the fan 2 can be directly connected to the low-pressure compressor rotor 3, or connected, for example, through a planetary gear system.

[0008] like Figure 2 As shown more clearly, the low-pressure turbine 7 specifically includes multiple axially arranged stages, each stage comprising a moving blade row 14 and a guide vane 19 formed by a stationary blade ring. The moving blade row includes a disc 15 on which blades 16 are mounted. The ends of the blades 16 are surrounded by retaining rings 17 made of abrasive material, which are fixed to the turbine casing 18. The guide vane 19 is located downstream of the moving blade row 14. The guide vane 19 and the retaining ring 17 are mounted to the casing by flanges or hooks 20 extending from the radially inner surface of the casing 18.

[0009] To ensure high efficiency of the turbomachinery, it is necessary to limit the airflow that does not pass through the stage blade rows 14, i.e., to limit leakage between the radially outer ends of the blades 16 and the retaining rings 17 made of abrasive material. For this purpose, the clearance at this interface must be controlled, as it depends on the temperature of the casing 18, particularly the temperature of the area on the casing 18 containing the hooks or flanges 20 that support the retaining rings 17.

[0010] The main airflow from combustion chamber 5 is at high temperature, which heats downstream components such as the static and dynamic components of turbines 6 and 7.

[0011] To control the aforementioned clearances and prevent premature damage to the static and moving components of the turbine, a highly efficient cooling device that can be effectively integrated into the turbine mechanical environment is required.

[0012] The applicant's patent application FR 3 050 228 relates to a component of a cooling device D for a low-pressure turbine casing C, such as... Figure 3 As shown, the device includes an axially extending gas collection housing B.

[0013] The pressurized cooling air from the secondary flow path is delivered from a location downstream of the turbomachinery fan to the gas collection housing B via a longitudinally extending air supply pipeline, and connected to the air supply opening O of the gas collection housing B.

[0014] The device also includes pipes T, which extend circumferentially from both sides of the gas collecting housing B. The ramp R includes two of these pipes T, each consisting of a curved pipe with a circular cross-section, and each pipe T extends circumferentially around the casing, for example, extending 360°.

[0015] Each tube T has an air inlet leading into the flow channel of the gas collecting housing B and a closed distal end. Each tube T also has a cylindrical wall with air injection holes facing the casing C, allowing cooling air to enter the gas collecting housing B, then into the tube T, and finally exit through the injection holes facing the casing C, thereby cooling the casing. This is called impingement cooling because the air impinges on the casing C.

[0016] It has been found that the area on the casing directly opposite housing B is cooled more thoroughly than the rest of the casing circumferentially.

[0017] This is because the cooling air flowing out from the radial inner surface of the casing impacts the gearbox, and its discharge efficiency is not as good as the impacting air flowing out of the pipe. Therefore, the casing forms a local obstruction, preventing the impacted cooling air from flowing radially outward, that is, preventing it from flowing out of the cooling device.

[0018] This localized stagnation leads to uneven circumferential cooling of the casing and causes premature wear of the casing, which in turn shortens the service life of the static and dynamic components of the low-pressure turbine due to the difficulty in controlling the blade tip clearance. Summary of the Invention

[0019] Therefore, this document relates to a cooling device for a turbomachinery annular casing having a longitudinal axis X, the cooling device comprising an air intake housing and a cooling ramp extending circumferentially around the longitudinal axis, the ramp being connected to the housing such that an internal volume of the housing is in fluid communication with an internal volume of the ramp, the ramp including a jet orifice opening radially inward toward the casing, characterized in that the housing includes a radially inner surface having an opening intended to be arranged radially toward the casing, the opening allowing fluid communication between the internal volume of the housing and the internal volume of the ramp.

[0020] The terms axial, radial, annular, and circumferential are all defined relative to the longitudinal axis of the turbomachinery.

[0021] In this document, the term "shell" refers to "gas collection shell".

[0022] During operation, the cooling device allows cooling air from the internal volume of the gas collecting housing to flow through the opening into the internal volume of the ramp.

[0023] The cooling air is then ejected from the internal volume of the ramp through jet holes that open radially inward toward the casing.

[0024] Cooling air impacts the casing in a circumferentially uniform manner, thus better controlling its temperature. This allows for better control of thermal stress on the casing, extending its service life. Uneven air circulation around the casing is avoided by placing the openings in one of its radially inner surfaces.

[0025] The ramp may be arranged radially between the opening of the casing and the housing.

[0026] In other words, the entire ramp can be arranged radially inside a circle tangent to the radial inner surface of the housing. In this configuration, the opening of the gas collecting housing is radially located outside the ramp that establishes fluid communication with it.

[0027] The air gap between the housing opening and the casing can be larger than the air gap between the corresponding ramp and the casing.

[0028] The air gap between the first element and the second element should be understood as the radial distance from the longitudinal axis that separates the two elements radially.

[0029] The air gap between the ramp and the casing should be understood as the air gap between the injection hole of the ramp and the radial outer surface of the casing.

[0030] The air gap between the gas collecting housing opening and the casing can be 2 mm to 10 mm.

[0031] The air gap between the ramp and the casing can be 2 mm to 10 mm.

[0032] The cooling device is configured such that cooling air is first ejected from the jet opening radially toward the casing, and then, after impacting the casing, is discharged radially outward away from the cooling device.

[0033] More specifically, this configuration allows cooling air located in the radial space between the housing and the casing to be discharged after impact.

[0034] The ramp may include two branches extending circumferentially in opposite directions from both sides of the housing.

[0035] The branch can be a cylindrical tube.

[0036] The branch can extend circumferentially around the longitudinal axis at an angle of 45° to 360°, or 90° to 180°.

[0037] Two branches of the same ramp can extend to cover the entire circumference of the casing together.

[0038] In other words, the ramp can be a circular ramp extending around a longitudinal axis.

[0039] In this particular example, the ramp can extend 360°, so that the cooling applied to the casing is uniform throughout the casing (i.e., in its entire circumference): this prevents premature wear of the entire casing and extends its service life.

[0040] The device may include at least one tee connector, a first pipe connected to a first branch of the ramp, a second pipe connected to a second branch of the ramp, and a third pipe connected to the opening.

[0041] In this embodiment, a single opening in the housing is in fluid communication with the ramp, and the fluid communication between the housing and the ramp is provided by the tee joint.

[0042] Furthermore, this limits the size of the device: only one opening is needed to ensure fluid communication between the two branches of the ramp.

[0043] Obviously, a first opening associated with the first branch of the corresponding ramp and a second opening, distinct from the first opening, associated with the second branch of the corresponding ramp can still be provided. In this case, the two openings provide fluid communication between the two branches of the same ramp.

[0044] The connector may be an additional component, allowing the first ramp and the second ramp to be interchangeably assembled to the first pipe or the second pipe.

[0045] The joint may have a generally T-shaped radial cross section.

[0046] The joint may have a generally V-shaped radial cross section with its apex pointing radially outward.

[0047] The connector allows the gas collection housing to supply cooling air to the ramp branch with minimal pressure loss.

[0048] This reduces pressure loss caused by cooling air flowing through the joint geometry: the roughly V-shaped radial cross section ensures a smooth transition of cooling air flow direction from radial to circumferential (tangential).

[0049] The joint may be symmetrical about a plane containing the longitudinal axis X of the turbomachinery and the axis of the housing opening.

[0050] This symmetry allows the cooling air to be evenly distributed in each branch.

[0051] In fact, the cooling airflow flowing through the housing opening enters the first pipe of the connector and is divided into first and second streams that flow into the first and second branches respectively, so that the first and second streams have the same flow rate.

[0052] Distributing cooling air evenly in each branch improves the uniformity of casing cooling.

[0053] The cooling device may include multiple cooling ramps. The radial inner surface may have multiple openings, each intended to be radially aligned with the casing. The device may include multiple tee fittings, with each ramp associated with a corresponding opening and fitting.

[0054] The plurality of openings can be arranged along the longitudinal axis X.

[0055] In this way, the casing is cooled at the spray nozzles on its outer surface, directly opposite the multiple cooling ramps. The cooling effect is improved because the circumferential cooling of a single cooling ramp is repeated along the longitudinal axis through multiple cooling ramps.

[0056] This document also relates to a turbomachinery assembly comprising an annular turbomachinery casing and a cooling device of the aforementioned type, the cooling device being mounted on and surrounding the casing.

[0057] This document also relates to a turbine, such as a low-pressure turbine, which includes turbomachinery components of the aforementioned type.

[0058] In this way, during operation, the uniform cooling of the annular casing by the cooling device reduces the radial clearance between the turbine blades and the radial inner surface of the casing, and improves engine performance.

[0059] This document also relates to a turbomachinery comprising at least one turbine of the aforementioned type.

[0060] The turbomachinery may be an aircraft turbomachinery.

[0061] The aircraft may be a fixed-wing aircraft or a rotary-wing aircraft.

[0062] The turbomachinery can be a turbojet engine or a turboprop engine for an aircraft. Attached Figure Description

[0063] Other features, details, and advantages will become apparent from reading the following detailed description and analyzing the accompanying drawings, in which: -[ Figure 1 [This is an axial sectional view of a conventional twin-ducted turbojet engine;] -[ Figure 2 This is a partial axial cross-sectional view of a prior art turbojet engine, with particular emphasis on the low-pressure turbine; -[ Figure 3 This is a partial perspective view of a prior art cooling device; -[ Figure 4A This is a partial perspective view of a cooling device according to an embodiment of this document; -[ Figure 4B ] for Figure 4A Axial sectional view of the implementation method; -[ Figure 4C ] for Figure 4A Perspective view of the implementation method; and -[ Figure 5 This is a detailed partial view of a cooling device according to one embodiment of this document. Detailed Implementation

[0064] Figure 4A , 4B Figures 4C and 4C show a portion of a cooling device for a turbomachinery casing according to an embodiment of this document.

[0065] The cooling device 40 includes an air collection housing 42 extending along the longitudinal axis X of the turbomachinery 1. The housing is a hollow structure and defines an internal volume 44.

[0066] Axis X-point Figure 1 The longitudinal axis of the medium-sized turbomachinery.

[0067] The figure shows axis X', which is parallel to the turbine axis X. Axis X and X' lie in the same radial plane.

[0068] The gas collection housing 42 includes an upper surface 42a (radially outward relative to the longitudinal axis X), a lower surface 42b (also referred to as a radially inward radial surface 42b relative to the longitudinal axis X), the shape of which matches the casing 46, and two sides 42c, 42d, which connect the circumferential ends of the upper surface 42a and the lower surface (radially inward surface) 42b.

[0069] The upstream and downstream ends of the housing 42 are connected to lugs 43a and 43b for fixing the housing 42 to the turbine stator.

[0070] The upper surface 42a includes a first portion 42a-1 that is inclined relative to the longitudinal axis, and its downstream end is connected to a second portion 42a-2 that is parallel to the longitudinal axis X, with the two portions forming an included angle α.

[0071] The first part 42a-1 of the upper surface 42a of the gas collecting housing 42 has an air supply port 48 (also called an air supply opening 48) for receiving pressurized cooling air from upstream of the turbomachinery 1.

[0072] As described in the background art, the cooling air supply can be achieved, for example, through a pipe (not shown) extending longitudinally from the air supply port 48 of the air collection housing 42 and leading to a portion downstream of the turbomachined fan 2, for example, leading to a secondary airflow 10 flowing in the downstream portion of the turbomachined fan 2.

[0073] The gas collection housing 42 also includes a plurality of openings 50 distributed on the longitudinal axis X of the radial inner surface of the housing 42, so that the radial inner surface is radially aligned with the casing 46.

[0074] The plurality of openings 50 are connected to the plurality of ramps 52 via a plurality of connectors, such that each opening 50 is associated with a ramp 52 and a connector 58 to form a triplet.

[0075] Multiple ramps 52 are radially arranged between the opening 50 of the gas collecting housing 42 and the casing 46, such that the air gap E1 between the opening 50 of the gas collecting housing 42 and the casing 46 is greater than the air gap E2 between the associated ramp 52 and the casing 46 in the ternary group.

[0076] Each ramp 52 includes first and second branches 52a, 52b extending circumferentially around the casing 46 from both sides of the gas collection housing 42, and injection holes 57 distributed along the branches 52a, 52b and arranged radially opposite to the casing 46.

[0077] Each connector 58 includes three tubes, such as Figure 5 As specifically shown.

[0078] The first tube 58a and the second tube 58b are connected to the first and second branches 52a and 52b respectively, and to the third tube 58c of the connector 58.

[0079] The third tube 58c is connected to the opening of the gas collecting housing 42 via its radial outer end 58c-1, and is connected to the first and second tubes 58a and 58b via its radial inner end 58c-2.

[0080] During operation, the cooling airflow enters the internal volume of the air collection housing 42 through the air supply port 48 (arrow 61a), and then flows through multiple openings 50 and their associated connectors 58 (arrow 61b).

[0081] When the cooling airflow reaches the radial inner end 58a-1 of the first pipe 58a of the connector 58, it splits into two streams. The first stream (arrow 61c) flows into the internal volume of the first branch 52a, and the second stream (arrow 61d) flows into the internal volume of the second branch 52b.

[0082] The first and second streams then flow circumferentially in branches 52a and 52b and are ejected through injection holes 57, whereupon the cooling air then impacts the casing 46.

[0083] The cooling air after the impact is then discharged radially outward (arrow 61e) through the gap 62 between the circumferentially adjacent ramps 52.

[0084] In the volume 64 arranged radially between the radial inner surface 42b of the gas collecting housing 42 and the casing 46, the cooling air after impact can be discharged without being trapped by the solid structure of the gas collecting housing 42.

[0085] For reference Figure 5 The figure illustrates one embodiment of the connector area.

[0086] In this particular example, the joint 58 is symmetrical about a plane P, which contains the longitudinal axis X of the turbomachinery and the axis Y of the associated opening 50, the axis Y of which is a radial axis (perpendicular to the longitudinal axis X).

[0087] Therefore, the second and third tubes 58b and 58c are symmetrical about the plane P and form radially outward-opening grooves 66. The grooves 66 are contained within the plane of symmetry P.

[0088] Therefore, the connector 58 has a roughly V-shaped radial cross section, with its apex 68 pointing radially outward toward the opening 50 of the gas collecting housing 42.

[0089] During operation, the cooling airflow 60 flows radially inward through the opening 50 and the radially outer end 58a-1 of the first pipe 58a of the connector 58.

[0090] The cooling airflow 60 then flows through the first pipe 58a and splits into first and second streams 60a and 60b, which flow into the internal volumes of the first and second branches 52a and 52b, respectively.

[0091] This diversion is achieved by the tip 67 of the internal volume of the connector 58, which is the reverse profile of the groove 66.

[0092] The symmetry of connector 58 about plane P allows cooling air to be evenly distributed in the first and second branches 52a and 52b of the associated ramp 52 (arrows 61c and 61d, respectively).

Claims

1. A cooling device (40) for a turbomachinery annular casing (46), the annular casing having a longitudinal axis X, the cooling device 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) including a jet orifice (57) opening radially inward toward the radially outer surface of the casing (46), characterized in that, The gas collection housing (42) includes a radially inner surface (42b) having an opening (50) 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 collection housing (42) and the internal volume of the ramp (52), wherein the cooling device (40) also includes a connector (58) having a generally V-shaped radial cross section with its apex radially outwardly oriented.

2. The cooling device (40) according to the preceding claim, characterized in that, The ramp (52) is intended to be arranged radially between the radial outer surface of the casing (46) and the opening (50) of the gas collection housing (42).

3. The cooling device (40) according to any one of the preceding claims, characterized in that, The ramp (52) includes first and second branches (52a, 52b) extending circumferentially in opposite directions from both sides of the gas collection housing (42).

4. The cooling device (40) according to the preceding claim, characterized in that, The connector (58) is a tee connector (58a, 58b, 58c), with its first pipe (58a) connected to the first branch (52a) of the ramp (52), its second pipe (58b) connected to the second branch (52b) of the ramp (52), and its third pipe (58c) connected to the opening (50).

5. The cooling device (40) according to claim 1, characterized in that, The joint (58) is symmetrical about plane P, which includes the longitudinal axis X of the turbomachinery and the direction Y through the axis of the opening (50) of the gas collecting housing (42).

6. The cooling device (40) according to claim 4, comprising a plurality of cooling ramps (52), wherein the radially inner surface (42b) of the gas collecting housing (42) has a plurality of openings (50), each opening being arranged radially opposite to the radially outer surface of the casing (46), the device (40) comprising a plurality of tee joints (58a, 58b, 58c), each ramp (52) being associated with a corresponding opening (50) and joint (58).

7. The cooling device (40) according to the preceding claim, characterized in that, The plurality of openings (50) are arranged along the longitudinal axis X.

8. A turbomachinery assembly comprising an annular turbomachinery casing (46) and a cooling device (40) according to any one of the preceding claims, the cooling device being mounted on the casing (46) and surrounding the casing.

9. A turbine, such as a low-pressure turbine (7), comprising the turbomachinery components according to the preceding claim.

10. A turbomachinery comprising at least one turbine (7) according to the preceding claim.

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