CA2908979A1

CA2908979A1 - Splitter nose with plasma de-icing for axial turbomachine compressor

Info

Publication number: CA2908979A1
Application number: CA2908979A
Authority: CA
Inventors: Ghislain Herbaut; David Bouillon
Original assignee: Techspace Aero SA
Current assignee: Safran Aero Boosters SA
Priority date: 2014-10-21
Filing date: 2015-10-19
Publication date: 2016-04-21
Also published as: RU2015144650A; US20160108754A1; US10309250B2; CN105525954A; EP3012416A1; BE1022482B1; CN105525954B; EP3012416B1

Abstract

A splitter nose delimiting the inlet of a low-pressure compressor of an axial turbomachine has a separation surface with an upstream circular edge suitable for separating a flow entering into the turbomachine into a primary flow and a secondary flow, and a plasma de-icing device. The device has two annular layers of dielectric material partially forming the separation surface, an electrode forming the upstream edge, an electrode forming an outer wall of the splitter nose, an electrode forming an outer shell which supports blades, an electrode delimiting the primary flow. The device generates plasmas opposing the presence of ice on the partitions of the splitter nose. A turbomachine with a splitter nose is provided with a de-icing system downstream of the fan.

Description

Description SPLITTER NOSE WITH PLASMA DE-ICING FOR AXIAL TURBOMACHINE
COMPRESSOR
Technical field [0001] The present disclosure relates to a splitter nose of an axial turbomachine with a de-icing system. More particularly, the disclosure is related to a splitter nose for a primary flow and a secondary flow of a turbomachine, the splitter nose being provided with a de-icing system. The disclosure also is related a turbomachine comprising a splitter nose with a de-icing system.
Background

[0002] In order to optimize their thrust and their efficiency while reducing noise nuisance, jet engines work with a plurality of annular air flows. Generally, a turbomachine separates an incoming flow into a primary flow and a secondary flow; the latter two have the forms of annular sleeves. The primary flow goes through the compressors, a combustion chamber, then is expanded in turbines. The secondary flow outwardly circumvents the compressor, the combustion chamber, the turbine; and then rejoins the primary flow at the outlet of the jet engine. The flows are separated by a circular splitter nose placed upstream of the compressor, its geometry limits the entry of air into the compressor.

[0003] The air entering into the turbomachine remains at atmospheric temperature at the splitter nose. Since these temperatures can drop to -50 C at altitude, ice can form on the nose with the moisture. During a flight, this ice can extend and build up to form blocks at the head of stator blades of the compressor. These blocks can thus modify the geometry of the nose and affect the air flow entering into the compressor, which can reduce its efficiency. Unchecked, the blocks can become particularly massive. Consequently there is a risk of them becoming detached and being ingested by the compressor, with the risk of damaging the rotor and stator blades in passing. To the extent that it does not first undergo a passage through the fan, this ingestion is particularly detrimental. To limit this formation of ice, the splitter noses are provided with a de-icing device.

[0004] The document US2004065092 A1 discloses an axial turbomachine including a low-pressure compressor whose inlet is delimited by an annular splitter nose. The nose is used to separate a flow entering into the turbomachine into a primary flow entering into the compressor, and a secondary flow circumventing the compressor. The splitter nose is linked to the upstream row of blades of the compressor and comprises an electric de-icing system with an epoxy resin covering the body of the splitter nose, and a heating resistor embedded in the resin. The resistor takes the form of a winding to increase the heat imparted to the splitter nose, but this coil form requires the thickness of the layer of resin to be increased. This increase in thickness adds a geometrical constraint. With the splitter nose becoming less sharp, more disturbances appear in the separated flows, which reduces the efficiency of the turbomachine.
Summary Technical issue

[0005] An embodiment of the disclosure aims to resolve at least one of the problems raised by the prior art. More specifically, an embodiment of the disclosure aims to increase the efficiency of a turbomachine provided with a splitter nose with a de-icing system. The disclosure also aims to improve the de-icing of a splitter nose between a primary flow and a secondary flow of an axial turbomachine.
Technical solution

[0006] It will have been well understood that the subject of the disclosure is a splitter nose with a system for forming plasma on an annular flow guiding surface of a turbomachine, the plasma being adapted to heat up the surface, preferably adapted to de-ice it. The disclosure helps avoid both the formation of ice and possibly liquefy the ice.

[0007] The subject of the disclosure is a splitter nose of an axial turbomachine, the nose comprising: a separation surface with an upstream circular edge, intended to separate a flow entering into the turbomachine into a primary annular flow and a secondary annular flow; a layer of dielectric material partially forming the separation surface; noteworthy in that it further comprises at least one de-icing plasma-generating electrode, which partially forms the separation surface and which is adapted to be able to form a plasma in combination with the dielectric layer in order to de-ice the separation surface.

[0008] According to an embodiment of the disclosure, the or at least one plasma-generating electrode forms the upstream edge of the separation surface, possibly the electrode runs along the upstream edge over most of its perimeter.

[0009] According to an embodiment of the disclosure, the or at least one plasma-generating electrode is arranged so as to delimit the primary flow of the turbomachine.

[0010] According to an embodiment of the disclosure, the electrode has at least one face, possibly a main face, totally covered by the dielectric layer, possibly the electrode is a profiled member of rectangular section, the electrode having three faces totally covered by the dielectric layer.

[0011] According to an embodiment of the disclosure, the separation surface comprises an inner annular portion intended to delimit the primary flow, an outer annular portion intended to delimit the secondary flow, and a joining annular portion linking the inner annular portion to the outer annular portion, possibly the electrode is arranged on the joining portion.

[0012] According to an embodiment of the disclosure, the dielectric layer occupies substantially all of the joining portion.

[0013] According to an embodiment of the disclosure, the separation surface has a profile of revolution about the axis of rotation of the turbomachine, the profile of the outer portion is generally more inclined relative to the axis of rotation than the profile of the inner portion, preferentially said profiles are generally inclined relative to one another by an angle less than 45 , preferentially less than 30 , more preferentially less than 20 .

[0014] According to an embodiment of the disclosure, the separation surface has a profile of revolution about the axis of rotation of the turbomachine, the profiles of the inner and outer annular portions being generally straight, and the profile of the joining portion is curved with a radius of curvature R
less than 50.00 mm, preferentially less than 10.00 mm, more preferentially less than 5.00 mm.

[0015] According to an embodiment of the disclosure, the electrode is a first electrode, the splitter nose comprising a second electrode separated from the first electrode by the dielectric layer, the electrodes being configured to be able to form a plasma on the separation surface in combination with the layer of dielectric material.

[0016] According to an embodiment of the disclosure, the splitter nose comprises an outer annular wall, possibly the outer wall is the second electrode.

[0017] According to an embodiment of the disclosure, the outer wall comprises an upstream annular hook with an upstream surface and a downstream surface possibly open axially in the downstream direction, the dielectric layer covering the upstream surface of the hook.

[0018] According to an embodiment of the disclosure, the splitter nose comprises an outer shell and an annular row of stator blades extending radially inwards from the outer shell, possibly the outer shell is the second electrode.

[0019] According to an embodiment of the disclosure, the splitter nose comprises at least one body made of composite material with an organic matrix and fibres, notably glass fibres; possibly, the composite body is the outer shell and/or the outer annular wall.

[0020] According to an embodiment of the disclosure, the dielectric layer is formed by the matrix of the composite material.

[0021] According to an embodiment of the disclosure, the dielectric layer is a first dielectric layer, the splitter nose further comprising a second circular dielectric layer with a tubular portion, possibly the dielectric layers are separated axially by a circular gap.

[0022] According to an embodiment of the disclosure, the dielectric layers each have a form of revolution with a profile of revolution about the axis of rotation, the dielectric layer furthest upstream has a profile of revolution radially higher than the other dielectric layer.

[0023] According to an embodiment of the disclosure, the electrode is a first electrode, the nose comprising at least four electrodes distributed in two sets of electrodes configured to be able to generate at least two, preferentially at least three, circular plasmas to de-ice the separation surface.

[0024] According to an embodiment of the disclosure, the splitter nose is configured to delimit and/or form the inlet of a compressor of the axial turbomachine.

[0025] According to an embodiment of the disclosure, the or each plasma has an annular form, possibly the plasma is segmented and forms a plurality of arcs.

[0026] According to an embodiment of the disclosure, the splitter nose comprises two first electrodes surrounded by at least one dielectric layer, the first electrodes being more than 1.00 mm apart; preferentially more than 3.00 mm apart.

[0027] According to an embodiment of the disclosure, the splitter nose comprises two second electrodes separated from one another by a dielectric layer, said layer being possibly in annular contact with each of the second electrodes.

[0028] According to an embodiment of the disclosure, at least one or each dielectric layer has a constant thickness.

[0029] According to an embodiment of the disclosure, the electrode is at least partially, preferentially totally, incorporated in the thickness of the dielectric layer.

[0030] According to an embodiment of the disclosure, the profiles of revolution about the axis of rotation of the turbomachine of the inner and outer annular portions are generally straight and inclined relative to one another by an angle greater than 5 , preferentially greater than 10 , more preferentially greater than 15 .

[0031] According to an embodiment of the disclosure, the splitter nose is a splitter nose formed on an upstream end of a compressor, notably low-pressure, of an axial turbomachine; or the splitter nose is formed on an upstream casing of an axial turbomachine, the upstream casing comprising a primary annular seam for the primary flow and a secondary annular seam for the secondary flow.

[0032] According to an embodiment of the disclosure, the splitter nose comprises two dielectric layers and two sets of electrodes, each set having a first electrode intended to be in contact with a flow of the turbomachine, a second electrode, a dielectric layer being inserted between each second electrode and a flow of the turbomachine.

[0033] According to an embodiment of the disclosure, the separation surface has a profile of revolution about the axis of rotation of the turbomachine, the profile of revolution of the outer portion forms the radial majority of the profile of revolution of the separation surface.

[0034] According to an embodiment of the disclosure, the splitter nose has a generally circular blade form with a circular blade cord, or circular edge, oriented axially in the upstream direction, preferentially the circular blade comprises a sharpening oriented axially in the upstream direction.
"Sharpening" should be understood to mean the part of the blade which is thinned, possibly gradually, to form the cutting edge with the cord of the blade.

[0035] An axial turbomachine comprising a splitter nose, noteworthy in that the splitter nose conforms to the disclosure, is also a subject of the disclosure.

[0036] According to an embodiment of the disclosure, the turbomachine comprises a fan, the splitter nose being arranged downstream of the fan.

[0037] According to an embodiment of the disclosure, the turbomachine comprises a power supply connected to at least one, possibly to each, electrode, and which is configured to form at least one de-icing plasma with the at least one electrode and at least one dielectric layer.

[0038] An embodiment of the disclosure aims to offer an energy-efficient system, which makes it possible to de-ice the splitter nose with a minimum of primary energy. The overall efficiency of the turbomachine can be thereby improved. The distribution of the electrodes; and the thickness and the configuration of the dielectric layers make it possible to distribute plasma zones to combat the build-up of ice. The presence of a plurality of sets of electrodes limits the level of energy required.

[0039] The use of the plasma is light by virtue of the thinness of its electrodes.
The temperature can be set so as not to degrade the dielectric layer, which facilitates the adoption of a wall and a shell that are composites with organic matrices. The chosen configuration is robust and makes it possible to withstand the ingestions of foreign bodies. In the event of a loss of a blade, the splitter nose withstands strong accelerations, for example of 100 g.
Brief description of the drawings

[0040] Figure 1 outlines an axial turbomachine according to the disclosure.

[0041] Figure 2 delineates a turbomachine compressor according to the disclosure.

[0042] Figure 3 represents a splitter nose according to the disclosure.
Description of the embodiments

[0043] In the following description, the terms internal or inner and external or outer refer to a positioning relative to the axis of rotation of an axial turbomachine.

[0044] Figure 1 is a simplified representation of an axial turbomachine. In this precise case, it is a double-flow jet engine. The jet engine 2 comprises a first level of compression, called low-pressure compressor 4, a second level of compression, called high-pressure compressor 6, a 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 the two compressors 4 and 6 in motion. The latter comprise a number of rows of rotor blades associated with rows of stator blades. The rotation of the rotor about its axis of rotation 14 thus makes it possible to generate a flow of air and progressively compress the latter to the inlet of the combustion chamber 8. Gear reduction means make it possible to increase the speed of rotation transmitted to the compressors.

[0045] An inlet fan, commonly called fan or blower 16, is coupled to the rotor and generates a flow of air which is divided into a primary flow 18 passing through the various abovementioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct (partially represented) along the machine to then rejoin the primary flow at the turbine outlet. The secondary flow can be accelerated so as to generate a thrust reaction.
The primary 18 and secondary 20 flows are annular flows, they are channelled by the casing of the turbomachine.

[0046] Figure 2 is a cross-sectional view of a compressor of an axial turbomachine such as that of figure 1. The compressor can be a low-pressure compressor 4. The figure shows a part of the fan 16 and the splitter nose 22 for the primary flow 18 and the secondary flow 20. The rotor 12 comprises a number of rows of rotor blades 24, in this case three.

[0047] The low-pressure compressor 4 comprises a number of synchronization rings, in this case four, which each contain a row of stator blades 26. The synchronization rings are associated with the fan 16 or with a row of rotor blades to straighten the flow of air, so as to convert the velocity of the flow into static pressure.

[0048] The splitter nose 22 circumferentially and/or axially delimits the inlet of the compressor 4. It can comprise an outer shell 28 and an outer annular wall 30 which can be linked using an annular hook 32 formed on the outer wall 30. The stator blades 26 extend essentially radially from the outer shell 28 to which they are welded. In order to avoid the presence or the formation of frost, of ice on the splitter nose, the latter is provided or associated with a plasma de-icing system or plasma generator. The latter makes it possible to heat up the splitter nose, in particular the air situated upstream, in order to avoid having frost form thereon and build up thereon; and/or in order to melt a layer of frost which might have appeared thereon.

[0049] The splitter nose 22 corresponds to an upstream part of the casing of the compressor and is mounted overhanging thereon. According to the disclosure, the splitter nose can also be an upstream axial turbomachine casing, for example a fan mounting casing. The upstream casing can include a primary annular seam for the primary flow and a secondary annular seam for the secondary flow, the annular seams being coaxial and one inside the other. It can comprise a row of casing arms passing through the secondary seam.

[0050] Figure 3 represents a splitter nose 22 with electrodes (28; 30; 34; 36) and dielectric layers (42; 44) configured to create de-icing plasmas (46; 48;
50). The axis of rotation 14, the primary flow 18 and the secondary flow 20 are represented.

[0051] The splitter nose 22 has a separation surface 52 which makes it possible to split the flow from the fan by dividing it up between the primary flow 18 and the secondary flow 20. The separation surface 52 has a form of revolution about the axis of rotation 14, its profile of revolution is in the form of a wedge; of acute angle. It forms a protruding and essentially thin circular blade, which has the effect of preserving the passage section remaining to the primary and secondary flows for a given incoming flow.
The efficiency of the turbomachine may thus be optimized.

[0052] The separation surface 52 forms the skin, the jacket of the splitter nose 22;
it faces more in the upstream direction than in the downstream direction. It comprises an outer annular portion 54 formed by the outer annular wall 30 which guides the secondary flow 20; an inner annular portion 56 formed by the outer shell 28, in contact with the primary flow 18; and a joining annular portion 58 where the upstream circular edge 60 which forms a protruding leading edge can be arranged. The profile of revolution of the outer portion 54 is generally straight and inclined relative to the axis of rotation 14. The profile of revolution of the inner portion 56 is substantially straight and substantially parallel to the axis of rotation 14. The profiles of revolution of the inner 56 and outer 54 annular portions are generally inclined relative to one another by an angle of between 5 and 45 , possibly between 20 and 25 . They can converge in the upstream direction. The joining portion 58 can have a curved or bent profile, with an average and/or constant radius of curvature R less than 100 mm, preferentially less than or equal to 5 mm. The joining portion 58 is distinguished from at least one or from each inner or outer annular portion in that the profile there becomes straight. Alternatively, the joining portion can essentially be a circular line, such as the upstream circular edge; it can essentially be a rectilinear extension of a profile of the annular portions.

[0053] The plasma generator comprises a number of sets of electrodes (28; 30;
34; 36), in this case two sets, and two layers of dielectric materials (42;
44). Possibly, a same dielectric layer (42; 44) is common to several sets of electrodes. At least one dielectric layer (42; 44) can comprise epoxy. Each dielectric layer (42; 44) can have a form of revolution about the axis of rotation 14, with a profile of revolution in the form of a hook which envelops an upstream portion of the shell or of the wall. The profile of revolution of the dielectric layer furthest upstream 42 can overlap the profile of the other dielectric layer 44 over substantially all of its height.
A
dielectric layer 44 or a portion of dielectric layer can be at the interface between the wall 30 and the shell 28, by forming a tubular seal. At least one or each layer has a thickness E, possibly constant, of between 0.10 and 1.00 mm, preferentially between 0.40 mm and 0.60 mm, possibly equal to 0.50 mm. The dielectric layers (42; 44) are separated axially by an annular groove 62 forming an axial circular gap 62, which can allow for a relative movement between the shell and the wall at the level of the hook 32. This particular feature allows for a differential expansion.

[0054] One of the sets of electrodes, or upstream set, comprises a first electrode 34 which can form the upstream circular edge 60 by running along it. The first electrode 34 has an upstream face facing the incoming flow; from the fan. It is arranged radially; at mid-height of the joining portion 58. The upstream set comprises a second electrode 30, which can be formed by the outer wall 30 of the splitter nose. This second electrode 30 can also equally be another added electrode. The upstream dielectric layer 42, which is the furthest upstream, is inserted between the electrodes (30; 34) of the upstream set and forms the joining portion. It covers the wall 30 over its portion forming the hook 32. The upstream set of electrodes makes it possible to create a number of annular plasmas (46; 48), here two, inside and outside the upstream edge 60. The outer plasma 46 extends downstream on the separation surface.

[0055] Another set of electrodes (36; 44), or downstream set, or even inner set; in as much as this set is surrounded by the upstream set and/or begins downstream of the upstream set; comprises a delimiting first electrode 36, encircling the primary flow. Its second electrode 28 can be the outer shell 28, or another added electrode. The inner dielectric layer 44 extends from the associated first electrode 36 towards the blade 26; possibly over most of the space between the associated first electrode 36 and the outer radial end of the leading edge 64 of the blade. This set makes it possible to generate a plasma 50 inside the splitter nose.

[0056] At least one or each first electrode (34; 36) is at least partially housed in the thickness of the associated dielectric layer 44. At least one or each first electrode (34; 36) can be circular and coaxial with the nose, and/or can have a profiled form, with a rectangular section. One of the main sides of the rectangle is in contact with a flow (18; 20), the main aspect corresponds to the size of the side and therefore to the surface of the corresponding electrode. Three other sides, including a main side, are mostly or totally covered by a dielectric layer (42; 44).

[0057] Each set makes it possible to form a circular plasma (46; 48; 50). At least one or more plasmas can be formed in one or more toric portions. A
plasma can be segmented, and be formed by a number of angular plasma portions.

[0058] The plasma generator comprises a power supply (not represented) which provides, for example, a voltage of 2 kV to 10 kV, a sinusoidal or square alternating signal with a period of a few nanoseconds. At least one or more electrodes are linked to the ground. The plasma generator is configured so as to ionize a portion of the gas, and to drive the ions formed using an electrical field. In addition, the plasma generator is configured to heat up the air.

[0059] Possibly, the outer wall of the de-icing nose and/or the outer shell is made of a composite material with organic matrix such as epoxy. The composite can also comprise glass fibres. According to this alternative, the composite can form a dielectric layer; possibly the shell and/or the wall is merged with its dielectric layer. In this case, additional electrodes can be added to form different sets and generate a number of plasmas.

Claims

1. Splitter nose of an axial turbomachine, the nose comprising:
- a separation surface with an upstream circular edge, intended to split a flow entering into the turbomachine into a primary annular flow and a secondary annular flow;
- a layer of dielectric material partially forming the separation surface;
wherein it further comprises at least one de-icing plasma-generating electrode, which partially forms the separation surface and which is adapted to be able to form a plasma in combination with the dielectric layer in order to de-ice the separation surface.

2. Splitter nose according to Claim 1, wherein the or at least one plasma-generating electrode forms the upstream edge of the separation surface, possibly the electrode runs along the upstream edge over most of its perimeter.

3. Splitter nose according to any one of Claims 1 and 2, wherein the or at least one plasma-generating electrode is arranged so as to delimit the primary flow of the turbomachine.

4. Splitter nose according to any one of Claims 1 to 3, wherein the electrode has at least one face, possibly a main face, totally covered by the dielectric layer, possibly the electrode is a profiled member of rectangular section, the electrode having three faces totally covered by the dielectric layer.

5. Splitter nose according to any one of Claims 1 to 4, wherein the separation surface comprises an inner annular portion intended to delimit the primary flow, an outer annular portion intended to delimit the secondary flow and a joining annular portion linking the inner annular portion to the outer annular portion, possibly the electrode is arranged on the joining portion.

6. Splitter nose according to Claim 5, wherein the dielectric layer occupies substantially all the joining portion.

7. Splitter nose according to any one of Claims 5 and 6, wherein the separation surface has a profile of revolution about the axis of rotation of the turbomachine, the profile of the outer portion is generally more inclined relative to the axis of rotation than the profile of the inner portion, preferentially said profiles are generally inclined relative to one another by an angle less than 45°, preferentially less than 30°, more preferentially less than 20°.

8. Splitter nose according to any one of Claims 5 to 7, wherein the separation surface has a profile of revolution about the axis of rotation of the turbomachine, the profiles of the inner and outer annular portions being generally straight, and the profile of the joining portion is curved with a radius of curvature R less than 50.00 mm, preferentially less than 10.00 mm, more preferentially less than 5.00 mm.

9. Splitter nose according to any one of Claims 1 to 8, wherein the electrode is a first electrode, the splitter nose comprising a second electrode separated from the first electrode by the dielectric layer, the electrodes being configured to be able to form a plasma on the separation surface in combination with the layer of dielectric material.

10. Splitter nose according to any one of Claims 1 to 9, wherein it comprises an outer annular wall, possibly the outer wall is the second electrode.

11. Splitter nose according to Claim 10, wherein the outer wall comprises an upstream annular hook with an upstream surface and a downstream surface possibly open axially in the downstream direction, the dielectric layer covering the upstream surface of the hook.

12. Splitter nose according to any one of Claims 1 and 2, wherein it comprises an outer shell and an annular row of stator blades extending radially inwards from the outer shell, possibly the outer shell is the second electrode.

13. Splitter nose according to any one of Claims 1 to 12, wherein it comprises at least one body made of composite material with an organic matrix and fibres, notably glass fibres; possibly the composite body is the outer shell and/or the outer annular wall.

14. Splitter nose according to Claim 13, wherein the dielectric layer is formed by the matrix of the composite material.

15. Splitter nose according to any one of Claims 1 to 14, wherein the dielectric layer is a first dielectric layer, the splitter nose further comprising a second circular dielectric layer with a tubular portion, possibly the dielectric layers are separated axially by a circular gap.

16. Splitter nose according to any one of Claims 1 to 15, wherein the dielectric layers each have a form of revolution with a profile of revolution about the axis of rotation, the dielectric layer furthest upstream has a profile of revolution radially higher than the other dielectric layer.

17. Splitter nose according to any one of Claims 1 to 16, wherein the electrode is a first electrode, the nose comprising at least four electrodes distributed in two sets of electrodes configured to be able to generate at least two, preferentially at least three, circular plasmas to de-ice the separation surface.

18. Axial turbomachine comprising a splitter nose, wherein the splitter nose conforms to any one of Claims 1 to 17.

19. Turbomachine according to Claim 18, wherein it comprises a fan, the splitter nose being arranged downstream of the fan.

20. Turbomachine according to any one of Claims 18 and 19, wherein it comprises a power supply connected to at least one, possibly each, electrode, and which is configured to form at least one de-icing plasma with the at least one electrode and at least one dielectric layer.