The disclosed embodiments relate to an anti-icing and deicing system for an aircraft engine pod, using a resistive mat.
The disclosed embodiments also relate to an aircraft engine pod with an improved deicing device and optimized acoustic attenuation based on a resistive mat.
Finally, the disclosed embodiments relate to a deicing system with arrays of resistive elements consisting of segregated resistive mats which is particularly applicable to the deicing of aircraft engine pods.
It is known practice to produce aircraft pods, the internal passage of which surrounds a fan, comprising a tubular air intake provided with a lip and a fan casing provided with a first internal tubular acoustic attenuation piece in which a tubular transition part connects the air intake to the fan casing.
The air intake and the lip have traditionally been deiced by conveying hot air from the jet engine along pipes or passages positioned in the thickness of the pod to the air intake.
One technical problem stems from the fact that the hot air carried is, under certain flight conditions, at a very high temperature (up to 600° C.) and from the fact that the tubular acoustic attenuation piece or pieces made of composite are incompatible with such temperatures.
Deicing is particularly necessary when the airplane is in a descent phase and particularly during the long final descents during which the engines are running at idling speeds for prolonged periods. In such cases, the temperature of the air in the hot air ducts is low and a high air flow is needed.
This implies that, conversely, when the outside temperature is high and the engine is providing thrust, if the deicing airflow regulating valve is open, the air reaches the aforementioned high temperatures. This is especially the case when the valve is locked in the open position to allow flight to proceed if the valve control system has failed.
Reducing the air temperature in the phases during which excessive heat is to be avoided is a very complicated matter because, in the prior art, the hot air deicing systems need to be engineered to allow the engine to be deiced during the phases at which it is running at idling speeds and to produce a device capable of cooling the air under special circumstances would entail complicated equipment (a heat exchanger, valve, regulator and other components) which would prove bulky and heavy.
Hence, in the prior art, it has been found preferable to keep the heat-sensitive acoustic attenuation part away from the part that is deiced and in order to do this, the tubular transition part comprises a junction region where the air intake and the fan casing meet, which region has no deicing means in order to keep the tubular part equipped with the acoustic attenuation means away from the part which is heated.
This construction presents two problems in particular: the first is that an annular section of the air intake has no acoustic attenuation material, thus reducing the effectiveness of these noise-reduction means, and the second of which is that this same annular section has no deicing means and therefore remains potentially exposed to the build-up of ice.
The deicing system of the disclosed embodiments are intended to allow the acoustic attenuation regions and the regions that are deiced to be brought closer together and even overlapped, and also affords a reduction in engine pressure drops given that, for a civilian aircraft engine of the customary power, the hot air anti-icing system of the prior art taps of the order of 60 to 80 kW of power off the engine without any true regulating or limiting means.
The deicing device of the disclosed embodiments are also intended to appreciably reduce, if not even to eliminate, the annular transition section and bring the part that is deiced and the part that is provided with the acoustic attenuation means closer together, or even overlap them, so as to increase both the area that is deiced and the area that is equipped with acoustic attenuation means.
In addition, the deicing device according to the disclosed embodiments which are laid out on the surface does not require any complex pipe and valve systems.
Furthermore, the pneumatic system of the prior art is able to perform the anti-icing function but not the deicing function in a simple and readily implementable way, whereas the system of the disclosed embodiments allows specific regions to be deiced by temporarily delivering to them the power needed for this deicing function, the power drawn being tailored to suit the anti-icing and deicing modes chosen.
The disclosed embodiments propose to produce a deicing and anti-icing system that does not occupy any space inside the pod, does not consume very much power, and offers great flexibility as to use by adapting the deicing powers to suit the flight conditions and the conditions on the ground.
In this context, the disclosed embodiments provide a system for deicing and preventing icing of an aircraft engine pod, comprising an air intake provided with a lip followed by a tubular air intake piece equipped with a first acoustic attenuation panel, characterized in that it comprises deicing means consisting of at least one array of resistive heating elements embedded in an electrically insulating material, the deicing means being in the form of a mat incorporating the resistive elements within the thickness of the air intake lip.
According to one particular embodiment, the disclosed embodiments provide an aircraft engine pod comprising an air intake provided with a lip followed by a tubular air intake piece equipped with a first acoustic attenuation panel, characterized in that the lip is equipped with a deicing system provided with a deicing device which comprises deicing means consisting of at least one array of resistive heating elements embedded in an electrically insulating material, the deicing means being in the form of a mat incorporating the resistive elements within the thickness of the air intake lip, the array forming part of the wall of the lip, covering part of the lip, internal to the air intake, and extending, on the one hand, over at least part of the lip external to the air intake and, on the other hand, over at least one junction region where the lip and the first acoustic attenuation panel of the tubular air intake piece meet.
More specifically, the air intake is divided into a succession of deicing sectors which form a succession of subarrays controlled by at least one control circuit designed either to heat the sectors in sequence or to deliver power to certain sectors simultaneously.
According to one aspect of the preferred embodiments, the deicing system comprises deicing means consisting of at least two arrays of resistive heating elements embedded in an insulating material, at least two series of resistive elements of said arrays being segregated in such a way as to form two segregated arrays incorporated into the thickness of a panel that is to be deiced.
The deicing system according to the disclosed embodiments advantageously comprises array control circuits comprising two independent channels for controlling the supply of electrical power to the two resistive arrays.
The disclosed embodiments also relate to a method of controlling a deicing and anti-icing system for an aircraft engine pod air intake, characterized in that the air intake is divided into a succession of deicing sectors, a succession of resistive arrays positioned in the deicing sectors are controlled by at least one control circuit designed to deliver power to said sectors simultaneously or in sequence.
Aside from the improvement in operational flexibility afforded by the system according to the disclosed embodiments, a system such as this is particularly well suited to increasing the acoustic insulation of the air intake made of composite, because a system such as this does not subject its environment to high temperatures even when running in downgraded mode.
Other features and advantages of the disclosed embodiments will be better understood from reading the description which will follow of one nonlimiting exemplary aspect of the disclosed embodiments given with reference to the drawings which depict:
The disclosed embodiments are concerned chiefly with the deicing and prevention of icing of parts of aircraft and, in particular, of the engine pods of these aircraft.
An aircraft engine pod 1 is depicted schematically in general in
A pod 1 such as this comprises an air intake 2 provided with a lip 3 followed by a tubular air intake piece 4.
The front part of such a pod according to the prior art is depicted in
According to the exemplary embodiments shown in
The deicing means according to the disclosed embodiments cover part 3b of the lip, internal to the air intake, and extend, on the one hand, over part 3a of the lip external to the air intake and, on the other hand, over a junction region 7a, 7b, 7c where the lip and the tubular air intake piece meet.
More specifically and particularly according to the exemplary embodiment of
The composite tubular piece 4 comprises an outer skin 4a and an inner skin 4b sandwiching an acoustic attenuation material to form said first acoustic attenuation panel 5 and the projection 8 consists of a pinched-together edge of the outer and inner skins 4a, 4b, these pinched-together edges being joined together by bonding or curing under the action of heat the resin with which the skins 4a, 4b are impregnated, as is known in the methods for producing composite acoustic panels, for example described in document EP 0 897 174 A1.
According to the example of
A construction such as this has the advantage of producing an acoustic attenuation region that is continuous from the inside of the engine as far as the leading edge of the lip, and this is particularly of advantage in combating noise.
According to the example of
According to the example of
The deicing means 6a cover the external region 3a of the lip, the means 6b cover the internal region 3b of the lip which in this instance has a first acoustic region 9, the means 6c cover a junction region 7c where the lip and the air intake meet, and the means 6d cover part of a second acoustic region 5.
The deicing means 6, 6a, 6b, 6c, 6d depicted are electrical means and in particular consist of a mat incorporating heating resistors.
To protect this mat, it is preferable to position it on the internal surface of the lip at least in the exposed tip or leading edge part of the lip. When the deicing means have to cover an acoustic panel, the mat may, on the other hand, be positioned on the external surface of the panel and be pierced with holes to allow the acoustic attenuation panel to work by leaving a proportion of open surfaces compatible with the desired acoustic attenuation.
The disclosed embodiments are particularly applicable to aircraft pods that comprise parts made of composite and particularly pods in which the tubular air intake piece 4 and the acoustic attenuation panels 5, 9 are made of composite.
When electrical deicing means are produced, the device is designed to operate as an anti-icing device preventing ice from forming on those surfaces that are to be protected or as a deicing device so that it can remove a deposit of ice that has built up on the surface.
A device and system such as this and the way in which they operate are described in
As explained above, and particularly in the case of engines of the turbofan type, an earlier technique employed in deicing systems was to tap pneumatic power off the engine to route hot air through pipework to the regions that are to be deiced.
A technique such as this relies on there being enough pneumatic power that can be taken from the engine propulsion power, on there being control valve devices and electrical control systems for operating these valves and on there being enough space to lead the pipework into the pods.
By comparison with this complex prior art, the system comprises electrical heating elements embedded in the thickness of the panels that form the air intake lip 3 and the tubular air intake piece to produce a system for deicing the pod 1 of an aircraft engine comprising an air intake 2 provided with a lip 3.
As depicted in
The arrays of resistive elements 102 comprise heating electrical resistors that dissipate electrical power through the Joule effect and which are embedded in the insulating material 101.
The deicing means are either metal resistive elements, for example made of copper, or composite resistive elements, for example elements made of carbon.
The electrical insulator covering the resistive elements is a flexible material particularly of the silicone or neoprene type.
As depicted in
Each resistive element 102 is spaced away from the adjacent elements by enough of a distance to ensure appropriate electrical insulation (typically of the order of 2 mm for the customary supply voltages of 0 to 400 V DC or AC).
Furthermore, as depicted in
This duplication of the arrays is performed in such a way that should one of the arrays fail, the ice protection function will be afforded in a downgraded mode by the other of the arrays.
To control these arrays, the system depicted comprises array control circuits 106, 106a, 106b comprising two independent channels which independently control the delivery of electrical power to the two resistive arrays 103a, 103b. A schematic depiction of these control circuits is given in
Indeed, again with a mind to safety, and also to optimize the electrical power consumption of the system, the disclosed embodiments envision dividing the air intake into a succession of deicing sectors, 121 according to
The wiring 108a, 108b, 108c, 108d groups together the current inputs and outputs for the sectors it covers.
The power that has to be dissipated in order for the anti-icing system to work correctly depends on the position of the heating element within the air intake, the most critical region of the profile being the internal part of the air intake starting from the leading edge of the lip.
In order to prevent icing in a region such as this, the power to be dissipated is a power of the order of 1.5 W/cm2 applied continuously.
For the less critical regions, operation in deicing mode based on a cycle of periodic heating of the surfaces will make it possible to limit the power consumption of the system even though the instantaneous power dissipated is greater being of the order of 2 to 3 W/cm2.
In operation such as this in deicing mode, the control circuit or circuits are designed to deliver and cut off power to the arrays 103a, 103b or subarrays 201, 212 according to defined time cycles 109 depicted in
The time cycle depicted in
Operation in this deicing mode will, in respect of the air intake regions, make it possible to mitigate against deficiency of one of the circuits while at the same time maintaining sufficient deicing capability.
The system control circuit depicted in
These bundles constitute independent channels connected to the units 107a, 107b which are separated or connected to a single control unit itself connected by a bus 115 to a unit 113 that provides monitoring and communication with the instrument panel 114 to display system control and operating parameters.
As seen earlier, the supply of power to the heating arrays of a pod is performed using two independent sets of power supply wiring 108, 108a, 108b, 108c and dedicated sets of electrical connectors.
The wiring in each set is installed in such a way as to be completely separate from that of the other set, so as to minimize the risks of common failures in the circuits.
The system described optimizes the power consumption because the control circuits are designed to deliver and cut off power to the heaters in accordance with time cycles that are defined according to the phase of flight or conditions of use of the system.
The unit or units 107a, 107b monitor the sets of wiring and of resistive-array heaters, make sure that the electrical voltages and currents supplied are appropriate and monitor the system by measuring the absence of unintended short circuits or unintended open circuits.
Likewise, the unit power supply circuits, which for example supply power through busbars connected to DC voltage sources 116a, 116b and AC voltage sources 117a, 117b, are independent. Furthermore, to increase the level of redundancy, each unit is powered by two independent busbars.
At any given moment, each channel or unit uses the same electrical busbar so that, if there is a problem with electrical insulation between the two arrays of heaters, only one of the busbars will be affected.
In particular, in the event of loss of one of the busbars on one of the units or channels, the two units or channels will use the other busbar.
To control the system according to the disclosed embodiments, the air intake is divided into a succession of deicing sectors and a succession of resistive arrays 201, . . . , 212 positioned in the deicing sectors are controlled by at least one control circuit 106, 106a, 106b designed to deliver power to said sectors simultaneously or in sequence.
Deicing or anti-icing operation may be preferred according to the location of the subarrays.
An anti-icing phase 110 is carried out by operating at least one deicing sector continuously, whereas a deicing phase 111 is carried out by means of a cycle involving periodic heating of at least one sector.
The disclosed embodiments are not restricted to the exemplary embodiments depicted and, in particular, the methods of operation can be altered to favor anti-icing operation or deicing operation according to the flight conditions, the status of the system or the power available, it being possible for the segregated arrays to be separated laterally to cover consecutive regions as in
Number | Date | Country | Kind |
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05 51711 | Jun 2005 | FR | national |
05 51712 | Jun 2005 | FR | national |
05 51713 | Jun 2005 | FR | national |
This application is National Stage of International Application No. PCT/FR2006/050608 filed 19 Jun. 2006, which claims priority to, and the benefit of, French Application Nos. 05 51712, filed on 22 Jun. 2005, 05 51711, filed 22 Jun. 2005 and 05 51713 filed 22 Jun. 2005, the disclosures of which are incorporated herein by reference in their entireties.
Filing Document | Filing Date | Country | Kind | 371c Date |
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PCT/FR06/50608 | 6/19/2006 | WO | 00 | 3/22/2010 |