Ventilation air distributor for turbine of aircraft turbine engine

Abstract

The invention relates to a ventilation air distributor (50) for a turbine (10) of an aircraft turbine engine, the distributor (50) comprising:-an annular air manifold (52) extending about an axis (X), and-at least one axial extension (54) extending from the manifold (52) along the axis (X), the axial extension (54) comprising at least two ducts (64) fluidly connected to the manifold (52), and at least two ducts (64) each comprising radially outwardly oriented air outlets (66), the air outlets (66) of the ducts (64) being at an axial distance from each other or from each other and from the manifold (52).

Description

Technical Field

[0001] The present invention relates to a ventilation air distributor for a turbine of an aircraft turbine engine, and a turbine and an aircraft turbine engine including such a distributor. Background Technology

[0002] Technical background includes, in particular, documents US-A1-2015 / 047359, US-A1-2015 / 285147, US-B2-10,655,475, US-A1-2018 / 187550 and US-A-5,497,613.

[0003] Aircraft turbine engines typically include at least one compressor, an annular combustion chamber, and at least one turbine. Air entering the compressor is compressed, mixed with fuel, and burned in the combustion chamber. The combustion gases then expand in the turbine, allowing the turbine rotor to rotate, which in turn drives the compressor rotor.

[0004] Several turbine engine technologies exist, such as turboprop engines or turbojet engines, which include a propeller located upstream of the turbine engine, which is also driven by the turbine's rotor. The propeller may or may not be ducted.

[0005] There are also various turbine engine configurations, such as single-body or multi-body. For example, in a twin-body turbine engine, the turbine engine includes a low-pressure body and a high-pressure body. The low-pressure body includes a low-pressure compressor rotor connected to the low-pressure turbine rotor via a low-pressure shaft. The high-pressure body includes a high-pressure compressor rotor connected to the high-pressure turbine rotor via a high-pressure shaft. In the gas flow direction within the turbine engine, from upstream to downstream, the twin-body turbine engine then includes a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine.

[0006] A turbocharged engine compressor comprises one or more compression stages that surround and extend along the same axis, each compression stage comprising a rotor wheel and a stator blade ring (also known as stator blades).

[0007] Similarly, the turbine of a turbine engine includes one or more expansion stages that surround and extend along the same axis, each expansion stage including a rotor wheel and a stator blade ring (also known as a distributor blade assembly).

[0008] The turbine of a turbocharged engine carries the combustion gases that flow through it and is exposed to relatively high temperatures during operation, which affects the characteristics of its components and assemblies. Therefore, optimal turbine cooling is a crucial factor in ensuring the optimal service life of the turbine and the turbocharged engine.

[0009] In a turbine, each rotor wheel includes an annular disk that carries blades on its periphery. Each rotor wheel disk includes an annular flange, which is attached, for example, to the annular flange of the disk of the adjacent rotor wheel via a screw-nut type device. The flanges of the disks of two adjacent rotor wheels, together with the disks, define an annular pocket in which high temperatures exist during operation, which can be severe for surrounding components.

[0010] This invention provides a simple, effective, and economical solution to this problem. Summary of the Invention

[0011] This invention relates to a ventilation air distributor for a turbine of an aircraft turbine engine, the distributor comprising: - An annular air manifold, the annular air manifold extending about an axis, and - At least one axial extension extending from the manifold along the axis, the axial extension including at least two pipes fluidly connected to the manifold, and each of the at least two pipes including radially outwardly oriented air outlets, the air outlets of the pipes being axially distanced from each other or from the manifold.

[0012] The distributor is particularly well-suited for integration into the turbine of a turbofan engine. A manifold can be attached to the turbine's stator. An air outlet is configured to direct towards an attachment flange for attaching the turbine's rotor wheel, allowing air collected by the manifold to be ducted through and projected or sprayed onto the flange at its level. The rotor wheel can rotate about the distributor's axis and will drive the air supplied by the distributor to rotate, specifically through the air outlet in the duct, which will allow the air to be specifically distributed within the aforementioned bag to reduce its temperature. Screws or bolts attaching the flanges together aid in the air rotation. Therefore, the invention allows the airflow to burst at the level of the attachment flange to generate dynamic cold air movement, circulating the airflow and cooling the bag.

[0013] The dispenser according to the invention may include one or more of the following features, which may be independent of or combined with each other: - Each of the pipes includes a first section and a second section, with the first section of each pipe extending along the axis from the manifold to the curved second section; - Pipelines share the same first section and have independent second sections; - The pipes are connected to each other by at least one material web extending in a plane passing through the axis, or even connected to the manifold; - At least one of the material webs is perforated, which allows air to flow into the housing; - The manifold has an axial cross-section that is generally C-shaped, and the manifold includes an annular opening that is axially oriented away from the at least one axial extension; - The manifold includes an internal annular attachment flange and / or an external annular attachment flange; - At least some of the air outlets are located at different radial distances from the axis, and in particular at radial distances that increase with the distance from the manifold; - Each of the air outlets has an elongated or circular shape along a circumference centered on the axis; - At least one of the air outlets is equipped with one or more air jet nozzles; - The at least one axial extension is fluidly connected to the manifold through an axial through-hole formed in the manifold; - The distributor includes two or more axial extensions distributed around the axis; - The distributor includes two or more axial extensions distributed around the axis; - The at least one axial extension is non-circular.

[0014] The present invention also relates to a turbine for an aircraft turbine engine, the turbine comprising a plurality of expansion stages surrounding and extending along a common axis, each expansion stage comprising a rotor wheel and a stator blade ring, each rotor wheel comprising an annular disk carrying blades at its periphery, each rotor wheel disk comprising an annular flange attached to an annular flange of an adjacent rotor wheel disk, the flanges of two adjacent rotor wheel disks being located between the disks of these wheels and comprising a minimum inner diameter greater than the minimum inner diameter of the disks, the turbine further comprising a distributor as described above, the distributor being attached to the stator of the turbine, the axis of the distributor coinciding with the axis of the turbine, and the manifold of the distributor being located upstream of the expansion stage relative to the airflow from the manifold to the duct in the distributor, the air outlet of the distributor being located in the connecting plane of the flange, the connecting plane being perpendicular to the axis.

[0015] Advantageously, the number of pipes and air outlets is n, and the number of turbine stages or rotor wheels is n+1.

[0016] Preferably, the air outlet is located at a radial distance from the axis, the radial distance increasing with the distance from the manifold, and the rotor wheel disc has an inner radius increasing with the distance from the manifold, and the inner radius is smaller than the aforementioned distance relative to the air flow from the manifold to the duct in the distributor, which is directly located downstream of these wheels for the air outlet.

[0017] The distributor can be installed radially in an annular space between the rotor wheel and the journal, which is used to connect these wheels to the turbine shaft.

[0018] The present invention also relates to a turbine engine, particularly an aircraft turbine engine, comprising at least one distributor as described above or at least one turbine as described above. Attached Figure Description

[0019] Further features and advantages will become apparent from the following description of non-limiting embodiments of the invention with reference to the accompanying drawings, in which: [ Figure 1 ] Figure 1 This is a semi-schematic axial cross-sectional view of the turbine of an aircraft turbine engine. [ Figure 2 ] Figure 2 This is a semi-schematic axial cross-sectional view of a turbine of an aircraft turbine engine, which is equipped with a ventilation air distributor according to an embodiment of the present invention. [ Figure 3 ] Figure 3 This is a schematic perspective view of the axial extension of the ventilation air distributor according to the present invention. [ Figure 4 ] Figure 4 This is a schematic perspective view of the annular manifold of the ventilation air distributor according to the present invention, and [ Figure 5 ] Figure 5 This is a schematic perspective view of the axial extension of a ventilation air distributor according to a variant embodiment of the present invention. Detailed Implementation

[0020] Figure 1 The image shows a turbine 10, for example, of a twin-plane type aircraft turbine engine. Turbine 10 could be, for example, a low-pressure turbine.

[0021] Turbine 10 includes multiple expansion stages, four in the example shown.

[0022] These expansion stages surround and extend along the same axis X. Each stage includes a rotor wheel 12 and a stator blade ring 14 (also called a distributor blade assembly or turbine distributor). In the example shown, the stator blades 14 are located downstream of the rotor wheel 12 relative to the gas flow in the turbine, but the reverse is also possible.

[0023] The stator blades 14 are supported by an annular housing 16 extending around axis X and all stages. Each stator blade 14 includes an annular row of blades 18 extending radially between an inner annular platform 20 and an outer annular platform 22. Each stator blade 14 is fan-shaped, meaning that the inner platform 20 and the outer platform 22 are themselves fan-shaped. The outer platform 22 includes hooks 23 for attaching the blade assembly 14 to the housing 16. The inner platform 20 carries an annular cylinder 24 made of a wear-resistant material.

[0024] The rotor wheels 12 are attached together and form an integral component assembly attached to the turbine shaft (not shown) by a journal 26 or similar.

[0025] Each rotor wheel 12 includes an annular disk 28, on which blades 30 are carried at their periphery. The disk 28 of each rotor wheel 12 includes annular flanges 32, 34, which are attached to the annular flanges of the disk 28 of the adjacent rotor wheel 12.

[0026] The disk 28 of the most upstream rotor wheel 12 includes a single downstream attachment flange 32 for attachment to the disk 28 of the rotor wheel 12 located just downstream. The disks 28 of the other rotor wheels 12 each include an upstream attachment flange 34 and a downstream attachment flange 32 for attachment to the disks 28 of the rotor wheel 12 located just upstream and the disks of the rotor wheel 12 located just downstream, respectively, except that the disk 28 of the most downstream rotor wheel 12 has its downstream attachment flange 32 attached to the aforementioned journal 26.

[0027] Flanges 32, 34 of discs 28 of two adjacent rotor wheels 12 are located between the discs 28 of these wheels and include a minimum inner diameter marked as D1 between the first and second stages, D1' between the second and third stages, and D1” between the third and fourth stages.

[0028] D2, D3, D4, and D5 are the minimum inner diameters of the rotor wheels 12 (especially their discs 28) of the expansion stages from upstream to downstream.

[0029] The diagram shows the diameter D2-D5 increasing from upstream to downstream, i.e., D2 <D3<D4<D5。

[0030] We can also see that the diameter D1-D1' increases from upstream to downstream, that is, D1 <D1’<D1”。

[0031] Finally, we can see that D1 is greater than D2 and D3, D1' is greater than D3 and D4, and D1" is greater than D4 and D5.

[0032] Therefore, the flanges 32, 34 of the discs 28 of two adjacent rotor wheels 12 located between these discs 12 include a minimum inner diameter D1-D1'', which is greater than the minimum inner diameters D2-D5 of these discs.

[0033] The radii corresponding to diameters D1-D1'' and D2-D5 are represented as D1 / 2, D1' / 2, D1'' / 2, D2 / 2, D3 / 2, D4 / 2, and D5 / 2, respectively.

[0034] In the example shown, the flange 36 of the annular shield 38 is inserted between the flanges 32 and 34 of the disk 28. These shields 38 support an annular lip 40, which extends radially outward and mates with the aforementioned cylinder 24.

[0035] Reference numeral 41 refers to the annular bag of hot air located between flanges 32, 34 and disc 28 during operation, and which may reach high and excessively high temperatures for surrounding components during operation.

[0036] U defines the connecting plane of flanges 32 and 34, which is perpendicular to axis X and passes between flanges 32 and 34 and, for example, at the level of flange 36 of shroud 38. U1 is the connecting plane of flanges 32 and 34 between the first and second stage disks 28, U2 is the connecting plane of flanges 32 and 34 between the second and third stage disks 28, and U3 is the connecting plane of flanges 32 and 34 between the third and fourth stage disks 28.

[0037] The turbine 10 may include an annular stator 42 centered on the axis X upstream. In the example shown, the outer periphery of the stator 42 is connected to the inner periphery of another turbine distributor 44, which is located upstream of the expansion stage and may, for example, form part of a high-pressure turbine. The inner periphery of the stator 42 is connected to an annular wear-resistant sleeve 46, which surrounds the lip 48 of another shroud 49, which is rotatably fixed together with the journal 26.

[0038] Figures 2 to 4 An embodiment of a ventilation air distributor 50 is shown. Basically, the distributor 50 includes two components: an annular manifold 52 and at least one axial extension 54.

[0039] In the example shown, the distributor 50 is installed in an annular space located radially between the rotor wheel 12 and the journal 26.

[0040] Figure 2 A device equipped with a dispenser 50 is shown. Figure 1 The turbo 10, and Figure 3 and Figure 4The axial extension 54 and manifold 52 of the distributor 50 are shown respectively.

[0041] The manifold 52 has an annular shape around an axis, which is axis X when the distributor 50 is installed in the turbine 10.

[0042] The distributor 50 is configured to be attached to the stator of the turbine 10 via its manifold 52. The distributor 50 is preferably attached to the stator via a flexible connection to allow for different expansion of these components during operation. This flexibility can be provided by the geometry of the manifold. The curved shape of the manifold allows it to deform within the elastic resistance limits of the manifold material without breaking.

[0043] By definition, manifold 52 has an air collection function, but also has the function of supplying air to an axial extension 54 that is fluidly connected to manifold 52.

[0044] In the example shown, the manifold 52 has an axial cross-section that is generally C-shaped, and the manifold includes an annular opening 56 that is axially opposite to the axial extension 54 or the plurality of extensions.

[0045] The opening 56 is configured to face upstream to collect air upstream, and the axial extension 54 or each axial extension 54 is configured to face downstream to distribute the air downstream.

[0046] In the example shown, manifold 52 is attached to stator 42. Manifold 52 may include one or more annular attachment flanges. In the example shown, the manifold includes an inner annular attachment flange 58 and an outer annular attachment flange 60, the inner annular attachment flange 58 being specifically designed for attachment to a carrier. Figure 1 The wear-resistant cylinder 46 is an element, and the outer annular attachment flange 60 is used to attach to the distributor 44 or to the intermediate annular portion located between the manifold 52 and the distributor 44.

[0047] Flanges 58 and 60 can be continuous at 360° or include radial notches, or they can be toothed, such as... Figure 4 As shown. These flanges 58, 60 include axial orifices through which attachment devices such as screws or bolts can pass.

[0048] Manifold 52 can be fan-shaped or formed as a single component.

[0049] The manifold 52 may include at least one axially oriented orifice 62 for fluid connection to the axial extension 54 or each of the axial extensions 54. The orifice 62 may be formed in a sector of the manifold 52 that is fixed to the axial extension 54 or, as... Figure 3 The axial extension 54 shown or an integral part thereof.

[0050] The following description refers to one axial extension 54, but if the dispenser 50 includes multiple axial extensions, it applies to each axial extension of the dispenser 50.

[0051] The axial extension 54 extends from the manifold 52 along the axis X.

[0052] The axial extension 54 includes at least two conduits 64 fluidly connected to the manifold 52, and each conduit 64 includes a radially outwardly oriented air outlet 66.

[0053] In the example shown, the axial extension 54 includes three pipes 64. With the number of stages of the turbine 10 denoted as N, it should be understood that the number of pipes 64 in the distributor 50 is N-1. In other words, the number of pipes 64 and air outlets 66 is n, and the number of stages or rotor wheels 12 of the turbine 10 is n+1.

[0054] The air outlets 66 of the duct 64 are located at an axial distance from each other or from the manifold 52, that is, the air outlets 66 are distributed uniformly or non-uniformly along the axis X.

[0055] The distributor 50 therefore has the general shape of a multi-branch comb.

[0056] Each pipe 64 includes a first section 64a and a second section 64b. The first section 64a of each pipe 64 extends along axis X from manifold 52 to the curved second section 64b.

[0057] Pipeline 64 can share the same first section 64a and have an independent second section 64b.

[0058] The ducts 64 can be connected to each other, or even connected to the manifold 52, by at least one material web 68 extending in a plane P1 passing through the axis X. This web, or each web 68, can be used to reinforce the axial extensions 54 and the manifold 52. The ducts 54 can have different internal cross-sections to accommodate potential aerodynamic pressure drops.

[0059] In the example shown, the first web 68a extends in plane P1 between manifold 52 and first pipe 64, with the outlet 66 of the first pipe 64 located upstream. The second web 68b extends in plane P1 between the first pipe 64 and the second pipe 64, with the outlet 66 of the second pipe located downstream of the outlet of the first pipe 64. The third web 68c extends in plane P1 between the second pipe 64 and the third pipe 64, with the outlet 66 of the third pipe 64 located downstream.

[0060] In the example shown, the material web or each material web 68 may be perforated. The perforations 70 reduce the mass of the axial extension 54 and thus the mass of the dispenser 50. The perforations also allow air circulation during rotation (the air applied to the flange will be driven by non-aerodynamic elements such as screws and the rotation of the rotor). To avoid overheating, it is preferable to enable this rotational air circulation.

[0061] As can be seen from the drawings, at least some, and preferably all, of the outlets 66 are located at different radial distances H1, H2, H3 from the axis X. Advantageously, the radial distances H1 - H3 increase with the increasing distance from the manifold 52, i.e., the distance H1 of the most upstream air outlet 66 is less than the distance of the intermediate air outlet 66, and the distance of the intermediate air outlet 66 itself is less than the distance of the most downstream air outlet 66. Thus, H1 < H2 < H3.

[0062] Figure 1 and Figure 2 Show: - H1 < D1 / 2; H2 < D1’ / 2; H3 < D1'' / 2; - H1 > D2 / 2; H2 < D3 / 2; H3 < D4 / 2; - H1 can be less than or equal to D3 / 2; - H2 can be less than or equal to D4; - H3 can be greater than D5.

[0063] These dimensions are particularly advantageous for optimizing ventilation without affecting the assembly of the rotor of the turbine 10, i.e., the attachment of the rotor wheel 12 and the flange mounting, as described below.

[0064] Each air outlet 66 can have an elongated shape or a circular shape along the circumference centered on the axis X. The elongated shape can be obtained by extruding the outlet 66 or the end of the duct 64 including the outlet 66, and can allow better distribution of the air leaving the duct 64.

[0065] The drawings also show that the outlets 68 are respectively located in (or intersect) the aforementioned planes U1 to U3. This means that the outlets 68 are oriented such that the air leaving the duct 64 is projected onto the flanges 32, 34.

[0066] In the case where the dispenser 50 includes two or more axial extensions 54, these extensions are distributed evenly or unevenly around the axis X.

[0067] Figure 5A variation of the distributor 50 is shown, wherein one or more of the distributor's air outlets 66 are equipped with one or more air jet nozzles 72. In the example shown, one of the outlets 68 is equipped with an element 74 comprising three air jet nozzles 72 for jetting air in different directions. The element 74 is directly fitted into the outlet 66 of the conduit 64 via a male-female fit. In another embodiment, the connection may be threaded.

[0068] During operation, air is collected by distributor 50 at the level of manifold 52 and delivered to their outlets 68 via pipes 64. The air can be compressed in section 64a and expanded in section 64b. The air is then discharged to the level of flanges 32, 34 and driven to rotate by screws or bolts attached to these flanges. This creates a cooling zone between 10° and 20°, which has an angle rather than a single cooling point. This propagation makes cooling more efficient. Distributor 50 is fixed, while flanges 32, 34, along with the rotor of turbine 10, are movable. The air is driven to rotate about axis X and ventilates the aforementioned air bag 41 of turbine 10, thereby preventing excessive temperature rise in this area.

[0069] When assembling the rotor of turbine 10, the following steps can be performed in sequence: -The downstream rotor wheel 14 or the disk 28 of the downstream wheel 14 is placed horizontally, so that its axis X is vertically oriented. - The dispenser 50 is axially pre-positioned above the wheel 14 or the disc at its desired final position and is held in place by, for example, a frame. Other rotor wheels 14 or other discs 28 are stacked and attached at the level of their flanges 32, 34, which is made possible by the aforementioned dimensions.

[0070] During the clamping step of disc 28, dispenser 50 can be rotated about axis X so as not to obstruct the passage and handling of the tool used to perform clamping, and then dispenser is repositioned to its desired final position.

Claims

1. A ventilation air distributor (50) for a turbine (10) of an aircraft turbine engine, said distributor (50) comprising: -A ring-shaped air manifold (52) extending around the axis (X), and - At least one axial extension (54) extending from the manifold (52) along the axis (X), the axial extension (54) including at least two pipes (64) fluidly connected to the manifold (52), and each of the at least two pipes including a radially outwardly oriented air outlet (66) located at an axial distance from each other or from the manifold (52).

2. The dispenser (50) according to claim 1, wherein, Each of the pipes (64) includes a first section and a second section (64a, 64b), with the first section (64a) of each pipe (64) extending along the axis (X) from the manifold (52) to the curved second section (64b).

3. The dispenser (50) according to claim 2, wherein, The pipes (64) share the same first section (64a) and have second sections (64b) that are independent of each other.

4. The dispenser (50) according to any one of the preceding claims, wherein, The pipes (64) are connected to each other or even to the manifold (62) by at least one material web (68) extending in a plane (P1) passing through the axis (X).

5. The dispenser (50) according to claim 4, wherein, The at least one material web (68) is perforated.

6. The dispenser (50) according to any one of the preceding claims, wherein, The manifold (62) has an axial cross-section that is generally C-shaped, and the manifold includes an annular opening (56) that is axially oriented away from the at least one axial extension (54).

7. The dispenser (50) according to any one of the preceding claims, wherein, The manifold (52) includes an inner annular attachment flange (58) and / or an outer annular attachment flange (60).

8. The dispenser (50) according to any one of the preceding claims, wherein, At least some of the air outlets (66) are located at different radial distances (H1, H2, H3) from the axis (X), and in particular at radial distances (H1, H2, H3) that increase with the distance from the manifold (52).

9. The dispenser (50) according to any one of the preceding claims, wherein, Each of the air outlets (66) has an elongated or circular shape along a circumference centered on the axis (X).

10. The dispenser (50) according to any one of the preceding claims, wherein, At least one of the air outlets (66) is equipped with one or more air jet nozzles (72).

11. The dispenser (50) according to any one of the preceding claims, wherein, The at least one axial extension (54) is fluidly connected to the manifold (52) through an axial through-hole (62) formed in the manifold (52).

12. The dispenser (50) according to any one of the preceding claims, wherein, The distributor includes two or more axial extensions (54) distributed around the axis (X).

13. A turbine (10) for an aircraft turbine engine, comprising a plurality of expansion stages surrounding and extending along a common axis (X), and each expansion stage comprising a rotor wheel (12) and a stator blade ring (14), each rotor wheel (12) comprising an annular disk (28) carrying blades (30) at its periphery, each rotor wheel (12) disk (28) comprising an annular flange (32) attached to an annular flange (34) of an adjacent rotor wheel (12) disk (28), the flanges (32, 34) of two adjacent rotor wheels (12) disks (28) located between the disks (28) of these wheels (12) and comprising a minimum inner diameter greater than that of the disks (28). The turbine (10) further includes a distributor (50) according to any one of the preceding claims, the distributor being attached to the stator (42) of the turbine (10), the axis of the distributor (50) being coincident with the axis (X) of the turbine (10), and the manifold (52) of the distributor being located upstream of the expansion stage relative to the air flow from the manifold (52) to the duct (64) in the distributor (50), the air outlet (66) of the distributor (50) being located in the connecting plane (U1, U2, U3) of the flanges (32, 34), the connecting plane being perpendicular to the axis (X).

14. The turbine (10) according to claim 13, wherein, The number of pipes (64) and air outlets (66) is n, and the number of stages or rotor wheels (12) of the turbine (10) is n+1.

15. The turbine (10) according to claim 13 or 14, wherein, The air outlet (66) is located at a radial distance (H1, H2, H3) from the axis (X), the radial distance increasing with the distance from the manifold (52), and the disc (28) of the rotor wheel (12) has an inner radius (D2 / 2, D3 / 2, D4 / 2), the inner radius increasing with the distance from the manifold (52), the inner radius being smaller than the distance (H1, H2, H3) of the air outlet (66) directly downstream of these wheels (12) relative to the air flow from the manifold (52) to the duct (64) in the distributor (50).

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