Injector for de-icing device of an air intake of an aircraft turbomachine nacelle and associated method

Abstract

An injector (3) for a de-icing device for an air inlet of an aircraft turbomachine nacelle, the injector (3) comprising a peripheral element (30) internally defining a through-flow channel (6) so as to circulate an internal flow of fresh air in the through-flow channel (6) from upstream to downstream along an injection axis (X3), the peripheral element (30) comprising an opening (31) configured to inject a flow of hot air into the through-flow channel (6), the injector (3) comprising a nozzle (4) mounted downstream of the peripheral element (30) to extend internally the through-flow channel (6), the nozzle (4) comprising a peripheral body (40) that converges from upstream to downstream along the injection axis (X3). Figure 5

Description

Title of the invention: Injector for a de-icing device for an air intake of an aircraft turbomachine nacelle and associated method technical field

[0001] The present invention relates to the field of aircraft turbomachinery and more particularly to an injector for a de-icing device for an air intake of a nacelle of an aircraft turbomachine.

[0002] In a known manner, an aircraft includes one or more turbomachines to enable its propulsion by accelerating an airflow which circulates from front to back in the turbomachine.

[0003] With reference to [Fig. 1], a turbomachine 100 is shown extending along a turbomachine axis X and comprising a fan 101 rotatably mounted about the turbomachine axis X in a nacelle comprising a shell 102. The terms front and rear are subsequently defined with respect to the airflow F. The turbomachine 100 includes at its front end an air inlet 200 comprising a cavity 204, extending annularly about the turbomachine axis X, which includes an inner wall 201 facing the turbomachine axis X and an outer wall 202 opposite the inner wall 201. The walls 201 and 202 are connected by a leading edge 203. Thus, the air inlet 200 allows the incoming airflow F to be separated into an internal airflow FINT guided by the inner wall 201. and an external airflow FEXT guided by the external wall 202.Subsequently, the terms inside and outside are defined radially with respect to the turbomachine X axis.

[0004] As is known, during the flight of an aircraft, due to temperature and pressure conditions, frost is likely to accumulate near the leading edge 203 and the inner wall 201 of the air inlet 200 and to form blocks of frost which are likely to be ingested by the turbomachine 100. Such ingestions must be avoided in order to improve the service life of the turbomachine 100 and reduce malfunctions.

[0005] To eliminate the accumulation of frost, again with reference to [Fig.1], it is known to circulate a flow of hot air FAC in the inner cavity 204 in order to heat the inner wall 201 by thermal convection and thus prevent the accumulation of frost which melts as it accumulates.

[0006] The introduction of the hot air flow FAC into the internal cavity 204 is achieved by an injector 300, traditionally in the form of a cylindrical tube oriented in a direction perpendicular to the axis of rotation. Bomachine X as illustrated in [Fig.2]. The hot air flow FAC moves circumferentially in the inner cavity 204 in order to heat the inner wall 201 and the outer wall 202.

[0007] In practice, the energy efficiency of such a heater is low since the hot air flow FAC does not mix homogeneously with the fresh air flow already present in the internal cavity 204. This can generate hot spots in the air inlet 200 which can reduce its lifespan.

[0008] It has been proposed to use an injector comprising a peripheral element internally defining a passage vein by patent application FR3136225. The peripheral element includes an opening configured to inject a flow of hot air so as to circulate a flow of fresh air in the passage vein.

[0009] One of the objectives of the present invention is to propose an injector comprising a peripheral element defining internally a passage vein further reducing the risk of hot spot formation in the air inlet while improving the mixing between the hot air flow and the fresh air flow. PRESENTATION OF THE INVENTION

[0010] The invention relates to an injector for a de-icing device for an air inlet of an aircraft turbomachine nacelle, the injector comprising a peripheral element defining internally a through-flow channel, so as to circulate an internal flow of fresh air in the through-flow channel from upstream to downstream along an injection axis, the peripheral element comprising an opening configured to inject a flow of hot air into the through-flow channel.

[0011] The injector is remarkable in that it includes a nozzle mounted downstream of the peripheral organ to extend internally the traversing passage vein, the nozzle comprising a peripheral body which is convergent from upstream to downstream along the injection axis.

[0012] The injector advantageously allows the internal fresh airflow to be drawn in by the hot airflow in the through-flow channel, thus improving the mixing. Thanks to the nozzle, the internal fresh airflow and the hot airflow circulating in the through-flow channel are guided and concentrated at the center of the inner cavity of the air inlet, thereby reducing their dispersion on the walls of the air inlet at the injector outlet. This results in a reduced risk of hot spots. In addition, the convergence of the nozzle increases the ejection velocity.

[0013] According to one aspect, the nozzle comprises shear openings that are through-body and are configured to allow a circulation culation of fresh outside airflow from outside the nozzle to inside the nozzle so as to promote mixing between the internal fresh airflow and the hot airflow in the through passage.

[0014] The shear openings allow for forced turbulent mixing between the fresh air passing through the shear openings and the hot air flow injected into the through passage vein, which reduces the risk of hot spot formation in the air inlet.

[0015] According to one aspect, the shear openings are in the form of longitudinal slots. Such slots maximize the supply of fresh air. In particular, the longitudinal slots have a main extension axis that runs along the injection axis.

[0016] According to one aspect, the peripheral element comprises an inner guiding wall including a downstream portion that flares downstream. Such an inner guiding wall promotes the development of an upstream low pressure, which accelerates the internal flow of fresh air.

[0017] According to one aspect, the opening is formed at a downstream end of the inner guide wall. Such an opening is simple to manufacture and allows for precise calibration of the ejection section.

[0018] According to one aspect, the mouth is formed upstream of the downstream portion, which flares downstream of the inner guide wall. The advantage of this configuration is to use the acceleration of the hot air flow injected into the mouth to draw a greater quantity of fresh air into the through passage, thereby increasing the mixing between the fresh air flow and the hot air flow.

[0019] According to one aspect, the peripheral organ has a smallest radial dimension at a longitudinal position along the injection axis. The mouth is located at the longitudinal position or upstream of said longitudinal position.

[0020] According to one aspect, the peripheral element comprises an outer wall opposite the inner guiding wall, and the nozzle is mounted on the outer guiding wall. This advantageously allows the nozzle to encompass the entire through stream of air to guide and accelerate it as it exits the peripheral element.

[0021] According to one aspect, the opening is peripheral. Such an opening allows for optimal suction of the internal fresh airflow. The fresh airflow and the hot airflow circulate concentrically, which allows the fresh airflow to be accelerated by the hot airflow while promoting their mixing.

[0022] According to one aspect, the mouthpiece is discontinuous and comprises a plurality of independent openings.

[0023] According to another aspect, the mouthpiece is continuous and includes a slit.

[0024] According to another aspect, the injector comprises at least one rotating element of the hot air flow during its injection so as to promote the mixing between the internal fresh air flow and the hot air flow in the through passage vein.

[0025] The invention also relates to a de-icing device for an air inlet of an aircraft turbomachine nacelle extending along a turbomachine axis, the air inlet comprising an inner cavity extending annularly around the turbomachine axis and comprising an inner wall facing the turbomachine axis and an outer wall opposite the inner wall, the walls being connected by a leading edge, the de-icing device comprising at least one injector as previously described.

[0026] The invention also relates to an air inlet of an aircraft turbomachine nacelle extending along a turbomachine axis, the air inlet comprising an inner cavity, extending annularly around the turbomachine axis, which includes an inner wall facing the turbomachine axis and an outer wall which is opposite the inner wall, the walls being connected by a leading edge, the air inlet comprising a de-icing device as previously described.

[0027] The invention also relates to an air inlet of an aircraft turbomachine nacelle extending along a turbomachine axis, the air inlet comprising an inner cavity, extending annularly around the turbomachine axis, which includes an inner wall facing the turbomachine axis and an outer wall which is opposite the inner wall, the walls being connected by a leading edge, the air inlet comprising at least one injector as previously described.

[0028] The invention also relates to a method of using a de-icing injector as previously described for de-icing an air inlet of an aircraft turbomachine nacelle extending along a turbomachine axis, the air inlet comprising an inner cavity, extending annularly around the turbomachine axis and comprising an inner wall facing the turbomachine axis and an outer wall opposite the inner wall, the walls being connected by a leading edge, the method comprising a step of injecting a hot air stream so as to circulate an internal fresh air stream in the through passage, the internal fresh air stream and the hot air stream circulating from upstream to downstream with respect to an injection axis in the nozzle.

[0029] According to one aspect, the method includes a step of injecting fresh outside air from outside the nozzle into the inside of the nozzle so as to mix the internal fresh air flow and the hot air flow in the through passage. PRESENTATION OF THE FIGURES

[0030] The invention will be better understood upon reading the following description, given solely by way of example, and referring to the accompanying drawings given by way of non-limiting examples, in which identical references are given to similar objects and on which:

[0031] Fig. 1 is a schematic representation of an air inlet of a nacelle according to the prior art.

[0032] Fig. 2 is a schematic cross-sectional representation of the circulation of a flow of hot air in the air inlet according to the prior art.

[0033] Fig. 3 is a schematic representation of an air inlet of a nacelle according to the invention.

[0034] The [Fig.4] is a schematic representation from downstream of an injector according to one embodiment of the invention.

[0035] The [Fig.5] is a schematic perspective representation of the injector according to one embodiment.

[0036] Fig. 6 is a schematic side-sectional representation of the injector of Fig. 5.

[0037] Fig. 7 is a schematic front view representation of the injector of Fig. 5.

[0038] Figure 8 is a schematic side-sectional representation of the injector of the [Fig.5] during its use.

[0039] Fig. 9 is a representation of an injector according to another embodiment with an injection slot.

[0040] Fig. 10 is a schematic side-section representation of an injector with an injection slot in use.

[0041] The [Fig. 11] is a schematic cross-sectional representation of the circulation of a flow of hot air in the air inlet according to the invention.

[0042] It should be noted that the figures set out the invention in detail to implement the invention, said figures being of course able to serve to better define the invention where appropriate. DETAILED DESCRIPTION OF THE INVENTION

[0043] With reference to [Fig. 3], a turbomachine 1 is shown extending along a turbomachine axis X and comprising a fan 10 rotatably mounted about the turbomachine axis X in a nacelle comprising a shell 12. Hereafter, the terms front and rear are defined with respect to the airflow F. The turbomachine 1 includes at its front end an air inlet 2 comprising an inner cavity 20, extending annularly about the turbomachine axis X, which includes an inner wall 21 facing the turbomachine axis X and a The outer wall 22 is opposite the inner wall 21. The walls 21 and 22 are connected by a leading edge 23. Thus, the air inlet 2 separates the incoming airflow F into an inner airflow FINT guided by the inner wall 21 and an outer airflow FEXT guided by the outer wall 22. The terms inner and outer are subsequently defined radially with respect to the turbomachine axis X. The inner cavity 20 is bounded anteriorly by the inner wall 21 and the outer wall 22 connected by the leading edge 23. In this example, the inner cavity 20 is bounded aft by a partition 24.

[0044] The inner cavity 20 is filled with a flow of fresh air FAF, for example, a stagnant air flow or a hot air flow that has been injected previously and has cooled down.

[0045] The turbomachine 1 includes a de-icing device to eliminate frost accumulation on the air inlet 2. In a known manner, the de-icing device includes an injector 3 of a hot air flow FAC into the internal cavity 20. The circulation of a hot air flow FAC prevents, by thermal convection, the accumulation of frost, which melts as it forms. Preferably, the hot air flow FAC is drawn from the turbomachine 1.

[0046] As illustrated in [Fig. 5], the injector 3 comprises a peripheral element 30 internally defining a through-flow channel 6 and a nozzle 4 mounted downstream of the peripheral element 30 to extend the through-flow channel 6 internally. In this example, the peripheral element 30 has a circular shape, but it is understood that it could have another peripheral shape, for example, an elongated shape, in particular, an oblong one. With reference to [Fig. 4], the through-flow channel 6 has a disc-shaped cross-section and the peripheral element 30 has a circumferential shape, but it is understood that other shapes could be suitable.

[0047] As illustrated in [Fig. 5], the injector 3 is oriented along an injection axis X3 along which the through-flow channel 6 extends. The injection axis X3 is oriented from upstream to downstream in [Fig. 6]. In this example, with reference to [Fig. 11], the injection axis X3 extends substantially tangentially / perpendicularly with respect to the turbomachine axis X.

[0048] With reference to [Fig. 6], the peripheral element 30 comprises a heating cavity 33 and a supply element 32 configured to supply the heating cavity 33 with a flow of hot air FAC. The supply element 32 is preferably in the form of a hollow casing. In this example, with reference to [Fig. 4], the supply element 32 comprises a mounting foot 39 configured to be fixed to the air inlet 2, in particular, to the partition wall 24.

[0049] As illustrated in Figures 5 and 6, the peripheral organ 30 comprises an em The nozzle 31 is configured to inject a hot air flow FAC from upstream to downstream along the injection axis X3. Preferably, the nozzle 31 is peripheral and has a shape analogous to the peripheral organ 30. In this example, with reference to [Fig. 5], the peripheral nozzle 31 is circular and oriented downstream. With reference to [Fig. 5], the peripheral nozzle 31 is formed from a plurality of independent openings 310 (orifices, slots, etc.) so as to form a discontinuous peripheral nozzle. It is understood that a continuous nozzle, in particular in the form of a continuous slot, could also be suitable as illustrated in [Fig. 9].

[0050] With reference to [Fig. 8], the peripheral inlet 31 is configured to inject, from the heating cavity 33, a peripherally shaped hot air flow FAC so as to circulate an internal fresh air flow FAFi in the through-flow channel 6. The internal fresh air flow FAFi flows from upstream to downstream relative to the injection axis X3, the internal fresh air flow FAFi circulating internally within the peripherally shaped hot air flow FAC to allow mixing between the hot air flow FAC and the internal fresh air flow FAFi. As illustrated in Figures 5 and 8, the hot air flow FAC has a peripheral shape, here an annular cross-section, and the internal fresh air flow FAFi is guided axially along the injection axis X3 internally within the hot air flow FAC. In other words, the hot air flow FAC and the internal fresh air flow FAFi are concentric.As will be shown later, the peripheral organ 30 is configured to accelerate the internal fresh air flow FAFi by the Coanda effect in the passage vein 6 as illustrated in [Fig.8].

[0051] With reference to [Fig. 6], the peripheral element 30 is generally shown in longitudinal section along the injection axis X3. The peripheral element 30 comprises a section including an inner guide wall 301 and an outer wall 302 relative to the injection axis X3. The inner guide wall 301 and the outer wall 302 internally delimit the heating cavity 33. Preferably, the walls 301 and 302 of the peripheral element 30 are made of material. The flow channel 6 extends internally to the inner guide wall 301.

[0052] The inner guide wall 301 comprises an upstream converging portion 301a along the injection axis X3 and a downstream diverging portion 301b along the injection axis X3. In this example, the downstream diverging portion 301b is radially flared from upstream to downstream. In other words, the radial dimension of the inner guide wall 301 increases from upstream to downstream.

[0053] With reference to [Fig. 6], the inner guide wall 301 is inclined relative to the injection axis X3 at an angle of inclination between 5° and 45° in order to obtain an optimal Coanda effect. Preferably, the angle of inclination 0 is between 10° and 15°, preferably equal to 12°.

[0054] With reference to [Fig. 6], the peripheral element 30 has a convex, streamlined upstream portion to allow the flow of fresh air to circulate with minimal pressure loss. With reference to [Fig. 8], this guides internal fresh air flows FAFi into the through passage 6 to accelerate them and external fresh air flows FAFe outward from the peripheral element 30 to generate turbulence T and maximize downstream mixing. The outer wall 302 guides the external fresh air flows FAFe axially as they bypass the through passage 6.

[0055] The nozzle 4 which is mounted downstream of the peripheral organ 30 to extend internally the traversing passage vein 6 will henceforth be presented.

[0056] The nozzle 4 has a peripheral body 40 which is convergent from upstream to downstream along the injection axis X3. In this example, the peripheral body 40 has a circular cross-section.

[0057] According to one aspect, as illustrated in [Fig. 6], the upstream nozzle diameter Dd is greater than the downstream organ diameter De so as to fully guide the airflows circulating in the through passage vein 6 at the level of the peripheral organ 3. According to one aspect, the downstream nozzle diameter De is greater than the intermediate organ diameter Db so as not to block the external fresh airflow FAFe entering the through passage vein 6.

[0058] The nozzle 4 comprises a mounting end 4a, located upstream, connected to the peripheral member 30 and a free end 4b, located downstream. As illustrated in [Fig. 6], the mounting end 4a of the nozzle 4 is connected to the outer wall 302 of the peripheral member 30.

[0059] The nozzle 4 includes shear openings 5 ​​which are through the peripheral body 40 and configured to permit a flow of fresh air FAFe from outside the nozzle 4 to inside the nozzle 4 so as to mix the internal fresh air flow FAFi with the hot air flow FAC in the through passage 6.

[0060] As illustrated in figures 5 to 7, the shear openings 5 ​​are preferably distributed around the periphery of the nozzle 4.

[0061] In this embodiment example, with reference to [Fig.6], the mouth 31 is formed at the upstream end of the inner guide wall 301 so that the hot air flow FAC is introduced directly into the nozzle 4.

[0062] According to one aspect, the injector comprises at least one element for rotating the hot air flow FAC during its injection so as to promote mixing between the internal fresh air flow FAFi and the hot air flow FAC in the through passage 6. The rotating element may, for example, be in the form of a hot air flow rotation element FAC by providing openings of ci a projection 5 having a tangential component or a peripheral opening 31 having a tangential component. The rotation element may also be in the form of a deflection piece mounted in the peripheral opening 31 as described in patent application FR2210126 filed on 04 / 10 / 2022.

[0063] An example of implementing a method for using a defrosting device according to the invention will now be presented. The method includes a step of injecting a peripherally shaped hot air flow FAC into the internal cavity 20 so as to circulate an internal fresh air flow FAFi in the passage channel 6. The internal fresh air flow FAFi flows from upstream to downstream relative to the injection axis X3 internally to the peripherally shaped hot air flow FAC as illustrated in [Fig.8].

[0064] The hot air flow FAC is injected at very high speed into the heating cavity 33. As a result, the internal fresh air flow FAFi is accelerated during the injection of the hot air flow FAC, which increases the air flow in the internal cavity 20 of the air inlet 2.

[0065] As illustrated in [Fig. 8], when the internal fresh air flow FAFi circulates internally with the peripherally shaped hot air flow FAC, the two mix in the through air channel 6, particularly at the nozzle 4, to form a mixed airflow FAM at the optimal temperature. Advantageously, the convergent shape of the nozzle 4 guides the mixed airflow FAM, thus limiting the risk of a hot spot forming with the walls of the air inlet 2.

[0066] Furthermore, thanks to the shear openings 5, external fresh air flows FAFe are allowed to enter the through air stream 6 via the nozzle 4, generating turbulence T downstream of the peripheral element 30 which homogenizes the mixture between the internal fresh air flow FAFi and the hot air flow FAC. The mixed air flow FAM thus provides homogeneous heating of the walls 21, 22, 23 of the air inlet 2. In other words, the risk of forming a hot spot in the air inlet 2 is reduced. The service life of the air inlet 2 is increased.

[0067] Such an injector 3 can be mounted in an existing air inlet 2, which is advantageous. Thanks to the invention, a mixed airflow FAM of optimal temperature and high flow rate circulates in the internal cavity 20 to defrost the walls 21, 22, 23 of the air inlet 2 and prevent any accumulation of frost.

[0068] In another embodiment, with reference to Figures 9 and 10, the mouth 31 is formed at the level of the inner guide wall 301 so that the hot air flow FAC is guided by the inner guide wall 301 before being introduced into the nozzle 4.

[0069] In this example, the peripheral opening 31 is in the form of a A continuous circular slot 312 is oriented downstream. To allow very high-speed injection via the mouthpiece 31, the heating cavity 33 includes an injection channel 34 located directly adjacent to the mouthpiece 31. Preferably, the injection channel 34 is convergent so as to accelerate the hot air flow FAC during its injection through the mouthpiece 31. Preferably, as illustrated in [Fig. 9], the peripheral member 30 includes a peripheral lip 35 extending projecting into the heating cavity 33 and partially delimiting the injection channel 34. Such a peripheral lip 35 allows the shape of the injection channel 34 to be precisely defined and, consequently, the desired compression or acceleration.

[0070] The inlet 31 is positioned upstream of the diverging downstream portion 301b of the inner guide wall 301 so as to guide the hot air flow FAC and enhance the Coanda effect. With reference to [Fig. 10], the hot air flow FAC is guided by the surface of the peripheral element 30 to allow for high-speed injection. This generates, downstream of the inlet 31, a low-pressure zone that draws in the internal cool air flow FAFi located upstream of the peripheral inlet 31. In other words, due to the injection of the hot air flow FAC, the internal cool air flow FAFi is drawn downstream along the injection axis X3, thereby increasing its speed in the manner of a bladeless fan. Advantageously, the mouth 31 is oriented to allow injection along the inner wall of the guide 301. The hot air flow FAC is thus pressed against the inner wall of the guide 31.As will be shown later, the hot air flow FAC circulates in contact with the inner wall of guide 301, which allows the internal fresh air flow FAFi to be drawn in optimally and accelerated. This improves the formation of T turbulence and enhances mixing.

Claims

Demands

1. Injector (3) for de-icing an air inlet (2) of an aircraft turbomachine nacelle (1), the injector (3) comprising a peripheral member (30) internally defining a through-flow channel (6), so as to circulate an internal fresh air flow (FAFi) in the through-flow channel (6) from upstream to downstream along an injection axis (X3), the peripheral member (30) comprising an inlet (31) configured to inject a hot air flow (FAC) into the through-flow channel (6), injector characterized in that it comprises a nozzle (4) mounted downstream of the peripheral member (30) to internally extend the through-flow channel (6), the nozzle (4) comprising a peripheral body (40) which is convergent from upstream to downstream along the injection axis (X3).

2. Injector (3) according to claim 1, wherein the nozzle (4) includes shear openings (5) which are through-body (40) and which are configured to permit circulation of fresh outside airflow (FAFe) from outside the nozzle (4) into the inside of the nozzle (4) so ​​as to promote mixing between the internal fresh airflow (FAFi) and the hot airflow (FAC) in the through-body passage (6).

3. Injector (3) according to claim 2, wherein the shear openings (5) are in the form of longitudinal slots.

4. Injector (3) according to any one of claims 1 to 3, wherein the peripheral member (30) comprises an inner guide wall (301) having a downstream portion (301b) flared downstream.

5. Injector (3) according to claim 4, in which the mouth (31) is formed at a downstream end of the inner guide wall (301).

6. Injector (3) according to claim 4, wherein the mouth (31) is formed upstream of the downstream portion flared downstream (301b) of the inner guide wall (301).

7. Injector (3) according to any one of claims 4 to 6, wherein the peripheral member (30) comprising an outer wall (302) opposed to the inner guide wall (301), the nozzle (4) is mounted to the outer guide wall (302).

8. Injector (3) according to any one of claims 1 to 7, comprising at least a device for rotating the hot air flow (FAC) during its injection so as to promote mixing between the internal fresh air flow (FAFi) and the hot air flow (FAC) in the through passage vein (6).

9. Air inlet (2) of an aircraft turbomachine nacelle (1) extending along a turbomachine axis (X), the air inlet (2) comprising an inner cavity (20), extending annularly around the turbomachine axis (X), comprising an inner wall (21) facing the turbomachine axis (X) and an outer wall (22) opposite the inner wall (21), the walls (21, 22) being connected by a leading edge (23), the air inlet (2) comprising at least one injector (3) according to any one of claims 1 to 8.

10. A method of using an injector according to any one of claims 1 to 8 for de-icing an air inlet (2) of an aircraft turbomachine nacelle (1) extending along a turbomachine axis (X), the air inlet (2) comprising an inner cavity (20) extending annularly around the turbomachine axis (X) and comprising an inner wall (21) facing the turbomachine axis (X) and an outer wall (22) opposite the inner wall (21), the walls (21, 22) being connected by a leading edge (23), the method comprising a step of injecting a hot air stream (FAC) so as to circulate an internal fresh air stream (FAFi) in the through-flow channel (6), the internal fresh air stream (FAFi) and the hot air stream (FAC) circulating upstream to downstream relative to an injection axis (X3) in the nozzle (4).

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