DEVICE FOR DE-ICING A TURBOMACHINE NOZZLE

Abstract

The invention relates to a de-icing device designed to supply de-icing air to a turbomachine separation nozzle extending along a longitudinal axis, the turbomachine comprising:—the separation nozzle which is designed to be positioned downstream from a turbomachine fan and comprises an internal casing and an external casing which form a separation between a primary flow vein for a primary stream and a secondary flow vein for a secondary stream, said streams issuing from the fan, the internal casing and the external casing defining an inter-vein space;—turbomachine guide vanes designed to be secured by screws to the internal casing such that the screws extend into the inter-vein space, the de-icing device being intended to be positioned in the inter-vein space and comprising—an air inlet;—an air outlet;—a plurality of channels extending from the air inlet toward the air outlet; the channels being arranged in relation to one another such that they are designed to extend from the air inlet toward the air outlets, passing between the screws for securing the guide vanes.

Claims

1-9. (canceled)

10. A de-icing device configured for supplying de-icing air for a turbomachine splitter nose, said turbomachine splitter nose extending along a longitudinal axis, the de-icing device comprising: the splitter nose which is intended to be positioned downstream of a fan of the turbomachine, the splitter nose comprising an inner casing and an outer casing to form a separation between a primary flow path for a primary stream and a secondary flow path for a secondary stream, the primary flow path and the secondary flow path being derived from the fan, the inner casing and the outer casing defining an inter-flow path space; guide blades of the turbomachine intended to be fixed by screws to the inner casing, so that the screws extend into the inter-flow path space, the de-icing device being intended to be positioned in the inter-flow path space and comprises: an air inlet; an air outlet; a plurality of channels extending from the air inlet to the air outlet; the channels being arranged relative to each other so that the channels are intended to extend from the air inlet to the air outlet by passing between the screws for fixing the guide blades.

11. The device according to claim 10, wherein the channels extending from the air inlet to the air outlet are cylindrical.

12. The device according to claim 10, wherein the air inlet and/or the air outlet has/have a cylindrical section.

13. The device according to claim 10, wherein one of the channels extends longitudinally between the air inlet and the air outlet.

14. The device according to claim 10, comprising five channels.

15. A method for manufacturing a device for de-icing a turbomachine splitter nose according to claim 10, wherein the nose is obtained by means of additive manufacturing, preferably of the powder laser fusion type.

16. A de-icing assembly comprising a plurality of de-icing devices according to claim 10, the de-icing devices being intended to be disposed in the inter-flow path space around the inner casing, the air inlets of each of the de-icing devices being connected together by a hot air supply duct configured to bring hot air to each air inlet.

17. A splitter nose of a turbomachine comprising an inner casing and an outer casing delimiting an inter-flow path space, the splitter nose comprising a de-icing assembly according to claim 10, disposed in the inter-flow path space.

Description

PRESENTATION OF THE FIGURES

[0031] Other characteristics, aims and advantages of the invention will emerge from the following description, which is purely illustrative and not limiting, and which should be read with reference to the appended drawings in which, in addition to the already discussed FIG. 1:

[0032] FIG. 1 illustrates a splitter nose of a turbofan engine comprising a de-icing device according to the invention;

[0033] FIG. 2 illustrates a de-icing device according to the invention;

[0034] FIGS. 3a and 3b each illustrate a de-icing assembly according to two variants of the invention.

[0035] In all of the figures, similar elements bear identical references.

DETAILED DESCRIPTION OF THE INVENTION

[0036] FIG. 1 illustrates a splitter nose 1 of a turbofan engine comprising a de-icing device 30 according to the invention.

[0037] As already mentioned, the nose 1 comprises an inner casing 11 and an outer casing 12. In addition, within the primary flow path I, at the inlet of the low-pressure compressor 2 and then downstream, there are sets of stator 22, 22a then rotor 21 blades for the progressive compression of the primary air stream FI.

[0038] An upstream row of stator blades 22a comprises guide blades which are the first blades impacted by the primary stream FI at the primary flow path air inlet I.

[0039] To prevent the formation of ice on the splitter nose 1, a de-icing assembly allows supplying de-icing air initially taken at the level of the compressor via at least one tube 3 so that air can be injected into an upstream end cavity 13 inside the splitter nose 1. The hot air injected into the splitter nose 1 can then travel through this cavity of the nose 1 up to bores or grooves 131 allowing injecting the hot air into the primary flow path I so as to be able to de-ice the blades, particularly by spraying with hot air the first inlet guide row comprising stator blades 22a.

[0040] Each stator blade 22, 22a has a radial fastening system 4 at the level of the inner casing 11. In the represented embodiment, the first input guide row comprising stator blades 22a is for example mechanically welded to the casing 11. The other stator rows of guide blades 22 have a screwing-fastening system whose screws 4 are bulky. Also, the inter-flow path space 10 is constrained by the fastening system and by the space requirement of devices for de-icing 30 the splitter nose 1. As can be seen in FIG. 1, the fastening systems 4 require providing enough space to be able to place the de-icing devices 30 by hot air.

[0041] Referring to FIG. 1, the de-icing assembly comprising several de-icing devices 30 as illustrated on the one hand in FIG. 2 and on the other hand in FIGS. 3a and 3b. These devices are arranged in the inter-flow path space as illustrated in FIGS. 3a and 3b for example.

[0042] Each de-icing device 30 intended to be positioned in the inter-flow path space comprises an air inlet 31 and an air outlet 32. The air stream is represented by an arrow in FIG. 2. The air inlet 31 and the air outlet 32 are located facing each other and are preferably each constituted by a cylinder. Each de-icing device 30 is for example made of a material such as a nickel-based alloy such as inconel 625 or, where appropriate, such as steel capable of withstanding the temperatures of the hot de-icing air.

[0043] Channels 33 extend from the air inlet 31 to the air outlet 32.

[0044] The channels 33 are configured to bring hot air entering through the air inlet 31 to the air outlet 32 by extending from the air inlet 31 to the air outlet 32 by passing between the screws 4 of systems for fixing the stator blades 22 fixed to the inner casing 11.

[0045] The channels 33 are preferably cylindrical but can take other shapes. For example, between manifolds associated with the inlets and outlets, the channels may be at least partially straight while extending substantially longitudinally, considering a parallel to the general axis of rotation in the turbomachine and the overall direction of flow of the air stream in the turbomachine (see FIG. 3a).

[0046] As can be seen in FIG. 2, curved channels are on either side of a central channel which is straight between the air inlet 31 and the air outlet 32. The further the channels are from the central channel, the more the radius of curvature is accentuated. This is due to the fact that all the channels must leave from the air inlet 31 to arrive to the air outlet 32. This air outlet 32 opens out in the case of FIG. 2 directly into the cavity 13, for example passing through a corresponding orifice made in a radial shroud 111 of the inner casing 11.

[0047] In this figure, the de-icing device 30 comprises five channels, of course a different number can be provided. The number of channels will depend on a compromise particularly between the maximum flow rate for each de-icing device, the circumferential spacing between the fastening system screws, the height radially available in the inter-flow path space, the pressure drop resulting from the connections of the channels and for example the allocated mass of material so that the device is sufficiently resistant.

[0048] Such a de-icing device is advantageously obtained by means of an additive manufacturing method, preferably of the laser fusion type of a nickel-based alloy powder or of the steel type. Such a method allows obtaining complex shapes like the shape of FIG. 2.

[0049] In relation to FIGS. 3a and 3b, a de-icing assembly disposed in the splitter nose comprises several de-icing devices as described above. Each of these devices includes an outlet 32 as a manifold extending circumferentially in correspondence with its corresponding sector in the circumferential cavity 13. In one embodiment, each manifold outlet 32 includes at least one air outlet orifice towards the cavity 13.

[0050] As can be seen in these figures, the de-icing devices 30 are intended to be disposed around the inner casing 11 of the de-icing nose of the turbomachine in the inter-flow path space 10, the air inlets 31 of each of the de-icing devices being connected together by a hot air supply duct 34 configured to bring hot air to each air inlet. The hot air supply duct 34 is itself supplied by at least one general hot air supply tube 3.

[0051] The supply duct 34 is circumferential and conforms in its shape to the shape of the inner casing and preferably extends between two rows of stator blade fixing screws.