BE1024760A1 - DEFROSTING DEVICE FOR AXIAL TURBOMACHINE - Google Patents

Abstract

The invention relates to a de-icing device (32) for a turbomachine flow guide surface. The deicing surface includes a pressure surface, an extrados blade surface (26), a primary flow surface of a separation spout of a low pressure compressor. The defrosting device (32) comprises a defrosting module (38) movable between a retracted position and a deployed position where it projects a de-icing fluid (40) pressurized against the guiding surface, the defrosting module (38) being configured to be driven to the deployed position by the pressure of the deicing fluid (40). The module (38) is placed in a space between two successive blades (26) of an annular row of blades. Each deicing module (38) is a thermowell with an inflatable envelope, or a monobloc body (46) produced by additive manufacturing.

Description

(71) Applicant (s):

SAFRAN AERO BOOSTERS S.A.

4041, HERSTAL (MILMORT)

Belgium (72) Inventor (s):

DE VRIENDT Olivier 4690 BASSENGE Belgium

THOMAS Vincent 4342 HOGNOUL Belgium (54) DEFROSTING DEVICE FOR AXIAL TURBOMACHINE (57) The invention relates to a deicing device (32) of a turbomachine flow guide surface. The defrosting surface comprises a lower surface, a lower surface of the blade (26), a primary flow surface of a separation nozzle of a low pressure compressor. The defrosting device (32) comprises a defrosting module (38) movable between a retracted position and a deployed position where it projects a deicing fluid (40) pressurized against the guide surface, the defrosting module (38) being configured to be driven to the deployed position by the pressure of the deicing fluid (40). The module (38) is placed in a space between two successive blades (26) of an annular row of blades. Each de-icing module (38) is a thermowell with an inflatable envelope, or a one-piece body (46) produced by additive manufacturing.

FtG. 3

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Description

DEFROST DEVICE FOR AXIAL TURBOMACHINE

Technical area

The invention relates to the defrosting of a turbomachine separation nozzle. More specifically, the invention relates to a device for defrosting a turbomachine via the circulation of a deicing fluid. The invention also relates to an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.

Prior art

In flight, crossing a humid air zone can cause an ice layer to form in an aircraft turbojet engine. This layer of ice tends to disrupt the flow as it thickens, and becomes a danger when it breaks up into blocks ingested by the turbojet engine. In order to guard against this risk, the separation nozzle at the compressor inlet is commonly equipped with a de-icing and anti-icing system.

Document EP 2 821 597 A1 discloses a double-flow turbojet engine with a low-pressure compressor, the main inlet of which is equipped with a defrosting separation nozzle. The defrosting function is provided by a hot gas taken from the high pressure compressor and circulating in the separation nozzle. For this purpose, axial channels are provided in the separation spout and are covered by a sheet metal forming the separation surface including the circular upstream edge of the spout. This circulation of hot air against the sheet brings calories to those closest to surfaces subject to icing. However, the scope of action remains limited.

Summary of the invention

Technical problem

The object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to optimize the defrosted surface and the reliability of defrosting of a turbomachine. The invention has

BE2016 / 5890 also aims to offer a simple, resistant, light, economical, easy to produce, convenient to maintain, easy to inspect, and performance-enhancing solution.

Technical solution

The subject of the invention is a device for defrosting a turbomachine flow guide surface, in particular a turbomachine compressor; remarkable in that it comprises a mobile defrost module between a retracted position and a deployed position where it projects a pressurized deicing fluid against the guide surface, said deicing module being configured to be driven towards the deployed position by the pressure of the de-icing fluid.

According to particular embodiments, the deicing device can include one or more of the following characteristics, taken in isolation or according to all the possible technical combinations:

- The device comprises at least one blade with a leading edge, in the deployed position the device is at the level of said blade.

- The module is arranged axially half upstream of the blade, or upstream of the leading edge of the blade.

- The device comprises two neighboring blades, in particular successive and / or of the same annular row, said two adjacent blades define between them a trajectory for a flow of the turbomachine, the mobile deicing module which being disposed in said trajectory in order to defrost Said two blades.

- The device / That it comprises an annular row of vanes with two neighboring vanes defining a space between them, the de-icing module being arranged in said space.

- The or each blade has a radial height HR, the travel C of the module between the retracted position and the deployed position represents at least 5% of the radial height HR, or at least 10%.

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- The defrosting module comprises one or more orifices for spraying defrosting fluid towards the guide surface, the orifices being arranged in one or more rows of orifices.

- At least one, or, or each orifice is turned radially inward and / or downstream.

- The defrosting module includes an envelope adapted to be inflated by the pressure of the deicing fluid so as to be maintained in the deployed position.

- In the deployed position, the envelope is generally tubular.

- The defrosting module comprises a body, the body possibly having a main elongation arranged in the direction of movement between the deployed position and the retracted position.

- The body is generally in the shape of a cylinder and is crossed by a main passage coaxial with the axis of the cylinder, preferably each orifice communicates with said main passage.

- The device comprises a separation spout with an annular separation surface in which the defrost module is disposed, the separation surface showing a reduction in diameter at the axial level of said defrost module.

- The defrosting module includes a radial retention portion, possibly in the form of a platinum.

- The defrosting module is configured to project the deicing fluid in at least one or more directions transverse to the axial direction of the turbomachine.

- The device / That it includes means for returning the module to the retracted position.

- The defrosting module is in one piece and / or made of one piece.

- The device / That it comprises a surface delimiting the outside of an annular flow of the turbomachine, in the retracted position the module is radially outside of said surface and / or touches said surface, and in the deployed position the module projects inwards relative to said surface.

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- The deicing fluid is a hot gas, possibly taken from a compressor, possibly high pressure; or heated by a turbomachine heating system.

- Each of the two neighboring blades comprises a cord, the mobile defrost module being disposed between the strings of the two blades in order to defrost them.

- The defrost module is mainly radially movable.

- In the retracted position, the envelope is folded back on itself.

- The holes are arranged laterally on the module. The lateral direction being understood in the circumferential direction of the turbomachine.

- The internal wall includes a pocket at least partially housing the module in the retracted position.

- The device comprises a module guide surface, the body possibly sliding against said guide surface.

- The holes are distributed over the radial height of the defrost module.

- The module is configured to be driven towards, and / or up to, the position deployed by the static pressure and / or the dynamic pressure of the deicing fluid, said pressure possibly keeping the module in the deployed pressure.

- The trajectory is generally parallel to the strings of said two blades.

- The space is delimited by the leading edges and the trailing edges of the two blades.

- Stroke C is a radial stroke, and / or greater than the width of the module, and possibly of the body or the envelope.

- The envelope includes a free end and an end secured to the defrosting surface and / or its support.

- The envelope is made of a polymer, in particular an elastomer.

The device comprises an annular row of mobile defrost modules according to any possible technical combination of the characteristics defined ciBE2016 / 5890 above, optionally each of the modules is associated with a blade or a pair of blades.

The training of the defrosting module by the pressure of the pressurized deicing fluid is not an essential aspect of the invention. The invention also relates to a turbomachine compressor, the compressor comprising a deicing device and two adjacent blades defining between them a trajectory for a flow of the turbomachine, remarkable in that the deicing device comprises a mobile deicing module which is arranged in said trajectory in order to defrost said two neighboring blades.

The invention also relates to a turbomachine, in particular a turbojet engine, comprising a de-icing device, remarkable in that the device is in accordance with the invention, preferably the de-icing device comprises an annular row of mobile de-icing modules; said mobile defrost modules being identical.

In general, the advantageous modes of each object of the invention are also applicable to the other objects of the invention. As far as possible, each object of the invention can be combined with the other objects. The objects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another.

Benefits

The invention offers a solution improving the operational safety of a deicing device. Indeed, each module exploits the pressure of its deicing fluid to deploy, to reach its deployed position, and to stay there. This simplifies the control chain of the de-icing device, and makes it possible to move the control means away from the separation edge since a source of pressure downstream is sufficient to ensure actuation.

In addition, the invention radially increases the surface reached by the deicing fluid with the same module since its radial height brings it radially closer to the critical surfaces. The circumferential coverage increases thanks to the width of the module. The homogeneity of defrosting improves, possibly via the distribution of the orifices.

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Also, the retractable nature of the modules promotes their integration into a narrow separation spout like that of the compressor. The simplicity of their actuation tends towards the same advantage. From then on, it becomes possible to install the modules as close as possible to the separation edge, also when the blades of the upstream rectifier come very close to each other.

Brief description of the drawings

FIG. 1 represents an axial turbomachine according to the invention.

FIG. 2 is a diagram of a turbomachine compressor according to the invention.

FIG. 3 illustrates a deicing device according to the invention.

îo Figure 4 shows a defrosting module according to a first embodiment of the invention.

FIG. 5 outlines an installation of a defrosting module according to the first embodiment of the invention.

FIG. 6 shows a defrost module in a deployed position according to a second embodiment of the invention.

Figure 7 shows the defrost module according to the second embodiment in the retracted position according to the invention.

FIG. 8 outlines an installation of a defrosting module according to the second embodiment of the invention.

Description of the embodiments

In the following description, the terms internal and external refer to a positioning relative to the axis of rotation of an axial turbomachine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The radial direction is perpendicular to the axis of rotation.

Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.

Figure 1 shows in a simplified manner an axial turbomachine. In this specific case, it is a double-flow turbojet engine. It may be an open blower turbojet, outside of the nacelle. The turbojet engine 2 comprises a first level of compression, called a low-pressure compressor 4, a second level of compression, called a high-pressure compressor 6, a

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BE2016 / 5890 7 combustion chamber 8 and one or more turbine levels 10. In operation, the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6. The latter have several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until the inlet of the combustion chamber 8.

An inlet fan commonly designated as a fan or blower 16 is coupled to the rotor 12 and generates an air flow which is divided into an annular primary flow 18 passing through the various aforementioned levels of the turbomachine, and an annular secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet. The secondary flow can be accelerated so as to generate a thrust reaction useful for the flight of an aircraft.

FIG. 2 is a view in section along the axis 14 of a compressor of a turbomachine such as that of FIG. 1. The compressor can be a low-pressure compressor 4. A part of the fan 16 can be observed there and the separation nozzle 22 of the primary flow 18 and the secondary flow 20. The nozzle 22 is upstream of the external casing 27 of the compressor. The rotor 12 comprises several rows of rotor blades 24, in this case three.

The low pressure compressor 4 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26.

The rectifiers are associated with the fan 16 or a row of rotor blades to straighten the air flow, so as to convert the speed of the flow into static pressure.

The separation nozzle 22 comprises an internal annular wall 28 which optionally forms an external ring upstream of the compressor and from which the stator vanes 26 extend essentially radially, as well as an external annular wall 30 in contact with the secondary flow 20. In order to defrost the turbomachine, a defrosting device 32 is added. It can be axially enclosed in the internal annular wall 28.

Figure 3 sketches the defrosting device 32 associated with the separation spout

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BE2016 / 5890 whose internal wall 28 and external wall 30 are visible. They materialize an annular separation surface 34 with a circular separation edge 36 upstream, which gives rise to the primary flow 18 and the secondary flow 20 from a flow entering the turbomachine.

The defrosting device 32 comprises at least one defrosting module 38.

Although only one module 38 and only one stator blade 26 are shown, it is conceivable to provide an annular row of modules 38, each associated with a blade 26 or with an inter-blade space, or with two blades 26 The modules 38 in the row are identical.

îo The defrost module 38 is mobile. It can move mainly radially, possibly substantially axially, for example between a retracted position (shown in dotted lines) and a deployed position (drawn in solid lines) in which it penetrates the primary flow 18 and in which it projects relative to the internal wall 28. It can slide radially against a guide surface of the internal wall 28.

The radial stroke C of the module 38 from the retracted position to the deployed position can represent at least: 5%, 10%, 15%, 20%, or 25%, of the radial height HR of the blade 26. The radial height HR can be the average height of the blade 26, for example measured perpendicular to the axis of rotation 14.

In the deployed position, the module 38 allows a pressurized deicing fluid 40 to be projected against a guide surface of the turbomachine. This guide surface may include the lower surface 42 of the blade, and / or the upper surface of the blade placed opposite; Or vice versa. The defrosting surface can also comprise a part of the separation surface 34, and in particular at the level of the blade 26 axially.

The pressurized deicing fluid 40 may be a hot gas or a liquid. The gas can come from the high pressure compressor; which simplifies the device 32.

In addition or as an alternative, the device 32 may include a system for heating and / or pressurizing the deicing fluid 40 in order to limit the impact on the high pressure compressor, and possibly defrosting before the start of the turbomachine.

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Return means 44, such as a spring, allow the module 38 to be brought into the retracted position, for example towards or against the external wall 30. These return means 44 favor passive actuation, and therefore safer. The risk that a module 38 remains blocked in the primary flow 18 after a defrosting or preventive anti-icing phase is reduced.

In the retracted position, the module 38 can be enclosed in an annular plenum 39 of the spout, the plenum 39 being able to serve as a collector or reservoir temporarily receiving the deicing fluid 40 before it treats the guide surface. Still in this position, the radially internal face of the module 38 can be flush with the separation surface 34 at the level of the internal wall 28.

FIG. 4 represents the defrosting device 32 in which the defrosting module 38 appears in section between two adjacent stator vanes 26, optionally of the same annular row.

The defrost module 38 essentially comprises a body 46. This body

46 may essentially be rigid, for example made of polymer or metal. The body 46, and possibly the module 38, may have come from material, for example produced by additive manufacturing. It becomes one piece. It can be hollowed out, for example so as to provide a main passage 50 there. This passage 50 can generally pass through the body 38, for example radially, and / or according to the direction of deployment. In the option where the body 46 is generally cylindrical, the axis of symmetry of this cylinder can correspond with the elongation of the passage 50; and / or to the direction of movement of the module 38.

In addition, the body 46 may show a series of holes 52, for example arranged in one or more rows, in particular radial. These orifices 52 make it possible to guide and orient the jet of deicing fluid 40 when it is projected against the guide surface to be treated. The passage 50 connects the plenum 39 to each orifice 52, and therefore to the primary flow 18. When the deicing fluid 40 circulates through the module 38, its pressure acts so as to maintain the latter in its deployed position, overcoming the effort return means, and possibly overcoming the thrust of the primary flow 18. Consequently, the module is able to move, in particular to deploy, autonomously as soon as a

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BE2016 / 5890 supply of 40 pressurized deicing fluid is ensured. This makes the module energetically passive.

The module 38 can include a retention portion 47 from which the body 46 extends.

This portion 47 radially stops the module 38, and freezes its orientation. It is in radial contact with the internal wall 28 in the deployed position.

FIG. 5 shows a plan view of the internal annular wall 28, the internal portion of the separation surface 34 being delimited by the separation edge 36, which appears perpendicular to the axis of rotation 14.

The de-icing module 38, in particular the body 46, is disposed between two adjacent stator vanes 26, that is to say two consecutive vanes of the same annular row. In plan, the module 46 is located in a space 54 delimited by the leading edges 56 and the trailing edges 58 of the blades 26.

The space 54 can be delimited by the lower surface 60 of one of the blades 26, and by the upper surface 62 of the other blade 26. Each space 54 between two blades 26 can be provided with a deicing module 38 When it is deployed, the module 38, in particular its body 46, remains in said space 54.

Each blade 26 has a rope 64, for example a medium rope. The neighboring blades 26 define between them a path 66, for example in the form of a corridor passing between them. The trajectory 66 can be a general trajectory. It can be generally parallel to the strings 64.

FIG. 6 represents a deicing device 132 according to a second embodiment of the invention. This figure 6 shows the numbering of the previous figures for identical or similar elements, the number being however incremented by 100. Specific numbers are used for the elements specific to this embodiment.

The device 132 is substantially identical to the first embodiment, it differs from it in that the body of the module 138 is replaced by an envelope 168, possibly of tubular shape. In this figure, the module 138 is in its deployed position, which means that its envelope is deployed inward. Envelope 168 may have come in one piece. At its radially external end it can be fixed to the internal wall 128 via its retention portion 147, while its internal end

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BE2016 / 5890 remains free. It can form an inflatable envelope, possibly both flexible and inextensible. The area of the envelope 168 can remain identical from the deployed position to the retracted position. It is essentially hollowed out so as to form an internal passage 150 over its entire radial height. This passage 150 communicates with the orifices 152, which pass through the envelope 168 according to its thickness. The orifices 152 form two rows, each of them facing one of the stator vanes 126.

FIG. 7 represents the deicing device 132 according to the second embodiment where the module 138 is retracted in the separation spout, and in particular in the internal wall 128. Its retention portion 147 remains in place despite the change in position of envelope 168.

The supply of pressurized deicing fluid is stopped, so that the effect of pressure on the casing 168 no longer pushes it into the primary flow 118. Thanks to the return means 144, it returns to its retracted position. Its radial height decreases.

Thus, the envelope 168 is folded back on itself thanks to its flexibility. It can be stored in an accordion, it can fold between the holes 152, and / or at the level of the holes 152 which provide more flexibility for folding. In this configuration, the envelope 168 remains at least partially in the internal wall 128, for example in a housing 170. Optionally, a part is housed outside this internal wall 128, for example in the plenum 139.

FIG. 8 shows a plan view of the internal annular wall 128 according to the second embodiment of the invention. This FIG. 8 is essentially identical to FIG. 5, it differs from it in that the de-icing module

138, and in particular its body 146 is disposed both upstream of the leading edges 156 of the blades 126 and downstream of the separation edge 136.

Thus, the de-icing module 138 projects de-icing fluid 140 downstream. It remains in trajectory 166.

According to the invention, the teaching of the first embodiment can be applied to the second embodiment, and vice versa.

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Claims (15)

Claims 1. Defrosting device (32; 132) of a turbomachine flow guide surface ( 2), in particular of a turbomachine compressor (2); characterized in that it includes 3. Device (32; 132) according to claim 2, characterized in that the 15 module (38; 138) is arranged axially in the upstream half of the blade (26; 126), or upstream of the leading edge (56; 156) of dawn. 4. Device (32; 132) according to one of claims 1 to 3, characterized in that it comprises two neighboring blades (26; 126) define between them a path (66; 166) for a flow of the turbomachine, the module of Defrosting (38; 138) being arranged in said trajectory in order to defrost said two blades. 5 lower surfaces, an upper surface of the blade (26), a primary flow surface of a separation nozzle of a low pressure compressor. The defrosting device (32) comprises a defrosting module (38) movable between a retracted position and a deployed position where it projects a deicing fluid (40) pressurized against the guide surface, the defrosting module (38) being configured to be driven to the deployed position by the pressure of the deicing fluid (40). The module (38) is placed in a space between two successive blades (26) of an annular row of blades. Each de-icing module (38) is a thermowell with an inflatable envelope, or a one-piece body (46) produced by additive manufacturing. 5 radial (47; 147), possibly in the form of a platinum. 15. Device (32; 132) according to one of claims 1 to 14, characterized in that the defrosting module (38; 138) is configured to project the deicing fluid (40; 140) in at least one or more directions transverse to the axial direction of the turbomachine (2). îo 16. Device (32; 132) according to one of claims 1 to 15, characterized in that it comprises return means (44; 144) of the module (38; 138) in the retracted position. 17. Device (32) according to one of claims 1 to 16, characterized in that the defrost module (38; 138) is in one piece and / or made of one piece. 15 18. Device (32; 132) according to one of claims 1 to 17, characterized in that it comprises a surface delimiting the outside of an annular flow (18) of the turbomachine, in the retracted position the module ( 38; 138) is radially outside said surface and / or touches said surface, and in the deployed position the module projects inwardly relative to 20 said surface. 19. Device (32; 132) according to one of claims 1 to 18, characterized in that the deicing fluid (40; 140) is a hot gas, optionally taken from a compressor (6) or heated by a heating system of the turbomachine (2). 25. Turbomachine (2), in particular a turbojet, comprising a deicing device (32; 132), characterized in that the device (32; 132) conforms to one of claims 1 to 19, preferably the device defrost (32; 132) comprises an annular row of modules for 2016/5890 BE2016 / 5890 15 mobile defrost (38; 138); said defrost modules being identical. BE2016 / 5890 BE2016 / 5890 BE2016 / 5890 B E2016 / 5890 BE2016 / 5890 140 BE2016 / 5890 2016/5890 BE2016 / 5890 Abridged DEFROST DEVICE FOR AXIAL TURBOMACHINE The invention relates to a deicing device (32) of a turbomachine flow guide surface. The defrost surface includes a surface 5 (52; 152) spraying deicing fluid (40; 140) towards the guide surface, the orifices being arranged in one or more rows of orifices (52; 152). 5. Device (32; 132) according to one of claims 1 to 4, characterized in that it comprises an annular row of blades (26; 126) with two neighboring blades defining a space (54) between them, the defrost module (38; 25 138) being arranged in said space. 5 a deicing module (38; 138) movable between a retracted position and a deployed position where it projects a deicing fluid (40; 140) pressurized against the guide surface, said deicing module (38; 138) being configured to be driven to the deployed position by the pressure of the deicing fluid (40; 140). îo 2. Device (32; 132) according to claim 1, characterized in that it comprises at least one blade (26; 126) with a leading edge (56; 156), in the deployed position the device is at radially level of said blade. 6. Device (32; 132) according to one of claims 2 to 5, characterized in that the or each blade (26; 126) has a radial height HR, the stroke C of the module (38; 138) between the position retracted and position 2016/5890 BE2016 / 5890 13 deployed represents at least 5% of the radial height HR, or at least 10%. 7. Device (32; 132) according to one of claims 1 to 6, characterized in that the defrost module (38; 138) comprises one or more orifices 8. Device (32; 132) according to claim 7, characterized in that at least one, or the, or each orifice (52; 152) is turned radially inward and / or downstream. 9. Device (132) according to one of claims 1 to 8, characterized in that the defrosting module (138) comprises an envelope (168) adapted to be inflated by the pressure of the deicing fluid (40; 140) in order to '' be maintained in the deployed position. 15 10. Device (132) according to claim 9, characterized in that in the deployed position, the envelope (168) is generally tubular. 11. Device (32) according to one of claims 1 to 8, characterized in that the defrosting module (38) comprises a body (46), the body possibly having a main elongation arranged in the direction of 20 movement between the deployed position and the retracted position. 12. Device (32) according to claim 11, characterized in that the body (46) is generally in the form of a cylinder and is traversed by a main passage (50) coaxial with the axis of the cylinder, preferably each orifice (52) communicates with said main passage. 25 13. Device (32; 132) according to one of claims 1 to 12, characterized in that it comprises a separation spout (22) with an annular separation surface (34) in which the defrost module is disposed ( 38; 138), 2016/5890 BE2016 / 5890 14 the separation surface showing a reduction in diameter at the axial level of said defrosting module. 14. Device (32; 132) according to one of claims 1 to 13, characterized in that the defrosting module (38; 138) comprises a retention portion 15 (Figure 3) National application number