DEVICE FOR DRAINING LIQUIDS FOR AN AIRCRAFT ENGINE

Abstract

Device (10) for draining liquids for an aircraft engine (1), comprising a collector (11) designed to collect liquids drained from the engine, characterised in that said device comprises means (13, 19) for pumping the liquids held in the collector and for discharging said liquids, and monitoring means (14) designed to indicate when the liquids have been collected by the collector in an anomalous manner, said monitoring means being designed to be activated when the flow rate of collected liquids is greater than the delivery of the pumping means.

Description

TECHNICAL FIELD

The present invention relates to a device for draining liquids for an aircraft engine, to an aircraft engine comprising such a device, and to a method for inspecting said engine.

PRIOR ART

In engines for aircraft such as helicopters, it is often necessary to discharge different types of liquids, for example fuel or oil, to prevent said liquids from building up and disrupting the functioning of said engines. For example, some engines require purging operations, which cause losses of liquids (fuel, oil, etc.) that have to be recovered and treated.

In the current state of the art, a return tank is provided for recovering said liquids, i.e. at least one duct is provided to convey the liquids to the aircraft fuel tank. However, this technology has several drawbacks. Indeed, the aircraft manufacturer is forced to provide said return tank used for recovering the different liquids drained from the engine. This technical constraint is exacerbated by the fact that the flow rates and temperatures of said liquids may be high. Leaks can also result from “latent” faults. Moreover, the recovered oil contaminates the fuel stored in the tank. Having to deal with these potential leaks thus places great restrictions on the aircraft manufacturer and does not help the incorporation of the engine on aircrafts that do not have a return tank.

In addition, oil or fuel leaks can occur in the engine as a result of some parts having a faulty seal, yet this may not actually affect the functioning of said parts. In the current state of the art, a maintenance operation is carried out immediately after detection of leaks of this type, which have no adverse effect on the engine, and this increases the frequency of these operations and the overall maintenance costs for an aircraft engine. This is the case in particular in HMU hydromechanical systems, the dynamic seal of which can produce external leaks. The fuel leaks in the region of the drain of the drive are the main reason for pump units/HMUs being removed, even though said leaks do not have a significant impact on the functioning of the engine. It would thus be desirable to be able to keep an HMU hydromechanical system in operation, even if the dynamic seal thereof is not perfect.

Several solutions are known for discharging the liquids drained from an aircraft engine, yet none of these effectively and fully addresses the problem and requirements set out above. For example, one solution is to discharge the drained liquids to a scupper of the engine deck. This solution is unsatisfactory because it leads to liquids being dumped into the atmosphere or onto the runway, which is tolerated less and less. Another solution is to provide the engine with a treatment device for the drain of the liquids, said device comprising a collector designed to collect the liquids drained from the engine. This collector can be connected to the exhaust nozzle of the engine by means of a duct in such a way that the drained liquids are conveyed and pumped from the collector to the jet nozzle where they are combusted. In this case, flames and smoke may appear at the outlet of the jet nozzle, and this is not pleasant to see, in particular when the engine is started up.

The object of the present invention is to find a solution to the problem and requirements set out above.

DISCLOSURE OF THE INVENTION

The present invention relates to a device for draining liquids for an aircraft engine, comprising a collector designed to collect liquids drained from the engine.

According to the invention, said draining device is characterised in that it comprises means for pumping the liquids held in the collector and for discharging said liquids, and monitoring means designed to indicate when the liquids have been collected by the collector in an anomalous manner, said monitoring means being designed to be activated when the flow rate of collected liquids is greater than the delivery of the pumping means.

As in the prior art, the collector recovers the various drained liquids (oil, fuel, etc.) from the engine. The pumping and discharging means allow the liquids to be pumped from the collector in order to discharge them. Lastly, the monitoring means allow the flow rate of the collected liquids to be monitored and make it possible to detect when this flow rate is anomalous. Said flow rate is anomalous when it is greater than the delivery of the pumping means. Therefore, the pumping delivery is preferably set at a threshold value (of approximately several litres per hour, for example) corresponding to normal functioning of the engine, i.e. to functioning for which the liquid losses and leaks that may occur do not affect the functioning of the engine (i.e. except when there is an engine fault). In other words, during normal operation, the pumping means discharge all the liquids collected in the collector when said pumping means are active. On the other hand, in the event of a malfunction and large liquid leaks, i.e. when there is an engine fault, the delivery of the pumping means is no longer sufficient for discharging the liquids collected in the collector. The monitoring means are thus designed to be activated and thus detect this anomalous situation. A maintenance operation can then be carried out on the engine. The monitoring means of the device according to the invention thus make it possible to limit the maintenance operations to those cases when large leaks of drained liquids are detected, and this is particularly advantageous especially in terms of the engine maintenance costs. The monitoring means thus prevent engine parts being removed prematurely and minimise the periodic inspections of the prior art.

The draining device according to the invention minimises the contact with the aircraft manufacturer and makes it unnecessary to have a return tank. Advantageously, the draining device thus does not have a return tank.

According to a particular embodiment of the invention, the pumping means comprise an electric, mechanical or pneumatic pump.

In a variant, the pumping means can comprise a jet pump ejector. This ejector can comprise a first line for the flow of drained liquids, one end of which forms an inlet for the liquids held in the collector and the other end of which forms an outlet for discharging the liquids, and a second line for atomising pressurised gas, which line extends around or inside the first line and is designed so that the atomised gas leaving said second line forces the liquids to be discharged through the outlet of the first line.

The first line can be connected to a valve, for example a flap valve. In one embodiment, this valve is controlled electrically or mechanically. In a variant, said valve can be controlled by a pressurised fluid, the valve being closed when the fluid pressure is lower than a particular threshold and open when said pressure is above this threshold. The valve thus makes it possible to control the flow of the drained liquids in the first line. This can make it possible to precisely control the time at which the drained liquids are discharged so that they are not discharged as the engine is ignited, for example.

The second line of the ejector can comprise a gas inlet connected to means for bleeding pressurised gas, for example from a compressor of the engine. The gas inlet of the second line of the ejector can be connected to the bleeding means by means of a valve, for example a flap valve, or by means of a flow cross-section constriction. This valve can be electric, mechanical or pneumatic (controlled by a pressurised fluid). The valve can be controlled by the bled pressurised gas. In this case, as explained above, said valve can be closed when the gas pressure is lower than a particular threshold and open when said pressure is greater than this threshold. This is particularly advantageous since the flap valve then functions autonomously, the pressurised gases feeding the second line of the ejector when their pressure is sufficient to open the flap valve. The flap valve can be designed to open when the aircraft is in flight and when the engine is in cruising mode, for example.

According to one embodiment, the pumping means are incorporated in the collector. In other words, the pumping means are fitted in or on the collector, thereby reducing the size of the device. If the pumping means comprise an ejector of the aforementioned type, the second line of said ejector can be fitted in the collector in the region of an outlet for liquids drained from said collector, which outlet thus forms the first line of the ejector. In a variant, the pumping means are located at a distance from the collector and connected to a liquid outlet thereof by means of a conduit.

Preferably, the monitoring means comprise a visual and/or electrical alarm designed either to be visible to an operator inspecting the collector, or to emit a signal intended for the cockpit of the aircraft. The alarm is triggered when the flow rate filling the collector is greater than the delivery of the pumping means. Said alarm allows any anomalous leak in the engine to be indicated, as explained above. In a variant, the monitoring means can comprise an inspection hole or window provided in the collector. An operator can thus check the level or volume of liquids in the collector and decide whether or not to carry out a maintenance operation. It is also possible to monitor several flow rate thresholds to observe the progression of a fault and schedule a check.

Advantageously, the monitoring means of the collector comprise an overflow designed to let liquids escape from the collector when the flow rate of collected liquids is greater than the delivery of the pumping means. Flows of oil or fuel to the outside are thus prevented apart from in the case of faults. If such a flow were to occur, an operator could easily confirm, for example by means of the drip marks at the overflow, that the collector has received too great a flow rate of liquids. Said operator could then decide whether to carry out a maintenance operation.

The invention also relates to an aircraft engine comprising an exhaust nozzle for combustion gases. The engine is characterised in that it comprises at least one draining device according to the invention, the outlet of the pumping means leading into the jet nozzle directly or by means of a conduit.

The drained liquids discharged from the collector are thus conveyed to the exhaust nozzle of the engine where they are combusted. As explained above, the time at which the drained liquids are discharged can be determined in advance, for example by means of a flap valve connected to the first or second line of a jet pump ejector forming the pumping means. It is thus conceivable to discharge the drained liquids into the jet nozzle only when the aircraft is in flight, so as to minimise external pollution.

Advantageously, the pumping means are connected to means for bleeding gas from either a compressor or a system for removing gas from the engine.

The invention also relates to an aircraft having a draining device according to the invention.

The invention also relates to a method for inspecting an engine, the method comprising a step of maintaining the engine after the monitoring means of the device have been activated.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention will be better understood and further details, features and advantages of the invention will become apparent upon reading the following description, given by way of non-limiting example and with reference to the accompanying drawings, in which:

FIG. 1 is a schematic side view of an aircraft engine comprising a draining device according to the invention.

FIG. 2 is a schematic side view of a first embodiment of a draining device according to the invention.

FIGS. 3 to 10 are schematic side views of alternative embodiments of the draining device according to the invention.

DETAILED DESCRIPTION

With reference to the side view in FIG. 1, an aircraft engine 1 (in this case an engine of a helicopter) comprises (seen in a cutaway view) a gas generator 2 formed by a compressor 3, by a combustion chamber 4 and by a turbine 5, which is connected to a free turbine 6. The free turbine 6 drives the main rotor (not shown) by means of a power shaft 7 via a gearbox (not shown). The gases from the combustion are ejected into an exhaust nozzle 9.

In order to make the engine clean, the engine 1 is provided with a drainage device 10 intended for collecting the residual liquids (fuel, oil, water condensates, impurities, etc.) coming from the engine.

Typically, a draining device 10 comprises a collector 11 and lines 12 for draining liquids originating from various parts of the engine, the outlets of which lines lead into the collector 11.

A device according to the invention for draining liquids further comprises means for pumping liquids held in the collector 11 and for discharging said liquids, and monitoring means designed to indicate when the liquids have been collected by the collector 11 in an anomalous manner.

FIG. 2 shows a first embodiment of the draining device 10 according to the invention, the pumping and discharging means and the monitoring means being denoted by the reference numerals 13 and 14, respectively.

In the example shown, the pumping and discharging means 13 comprise an inlet 15 connected to a liquid outlet 17 of the collector 11 by means of a conduit 16, and an outlet 18 leading into the exhaust nozzle 9 of the engine 1. The collector 11 receives the drained liquids from the lines 12 (shown schematically by arrows) and is preferably provided with a vent 12′ for venting the internal cavity of the collector, in which the liquids are received.

In this case, the pumping and discharging means 13 comprise a jet pump ejector 19 provided with a first line 20 for the flow of drained liquids, one (upstream) end of which forms the aforementioned inlet 15 and the other (downstream) end of which forms the aforementioned outlet 18. As shown schematically in FIG. 1, said outlet 18 can comprise a constriction in its flow cross-section so as to define a diffuser downstream.

The pumping and discharging means 13 also comprise a second line 21 for atomising pressurised gas, which in this case extends inside the first line 20 and is designed so that the atomised gas leaving said second line 21 forces the liquids flowing in the line 20 to be discharged towards the outlet thereof 18 and into the jet nozzle 9. This pressurised gas is intended to expand in the aforementioned diffuser, and this creates negative pressure and forces the drained liquids to flow as far as into the jet nozzle 9.

The second line 21 thus comprises a pressurised-gas outlet 22 located in the region of the outlet 18 of the first line 20. The inlet 23 of the second line is connected, by means of a conduit 24, to means (not shown in the drawing) for bleeding pressurised gas from the engine 1. The pressurised gas can be bled from the compressor 3 of the engine, for example in the region of the plane P25 or P3 (the plane P25 being located between two impellers and the plane P3 being located downstream of these impellers).

To control both the activation of the pumping and the time at which the liquids are discharged into the jet nozzle 9, the conduit 24 is provided with a flap valve 25 that is intended to open and let the bled pressurised gas pass into the conduit as far as to the ejector 19 when the pressure of this gas is greater than or equal to a predetermined threshold value. In this case, the flap valve 25 is shown by means of a movable ball biased, by a compression spring, against a seat surrounding a gas outlet of the bleeding means. Thus, the flap valve 25 is actuated by the pressurised gas. The aforementioned gas pressure threshold value, which depends in particular on the spring rate of the spring in the above example, is preferably determined in order to precisely control the time at which the drained liquids are discharged, in particular so that said discharge does not occur as soon as the engine is ignited.

In this case, the means 14 for monitoring the collector 11 are shown by a single overflow 34. According to the invention, said monitoring means 14 are designed to be activated when the liquid flow rate received by the collector 11 is greater than the delivery of the pumping means 13 (ejector 19). The monitoring means 14 thus make it possible to indicate when the liquids have been collected by the collector 11 in an anomalous manner, in particular indicating a volume of drained liquid that is too high compared with the usual volume during normal operation of the engine.

When the flow rate of the collected liquids is greater than the delivery of the pumping means 13, the monitoring means 14 can be designed to emit a signal, which may be a visual and/or electrical alarm.

By setting the pumping delivery at a threshold value corresponding to normal functioning of the engine, i.e. to functioning for which the liquid losses and leaks that may appear do not affect the functioning of the engine, the pumping means 13 no longer have to discharge the collected liquids as soon as the flow rate of the collected liquids is greater than the pumping delivery. Where allowed by the collector, the level of liquids in the collector 11 will thus increase if there is an engine fault.

Where the collector 11 comprises a window through which an operator can see the level of liquids in the collector, this window, which is thus intended for alerting the operator (visual alarm), is comprised by the monitoring means 14.

In a variant or as an additional feature, the collector 11 can comprise an overflow 34 intended for letting the liquids escape from the collector 11, in particular when the volume of liquid collected is greater than the storage volume for the liquids in the collector 11. Instead of or in addition to the alarm means, an operator can see drip marks produced when the liquid passes the level of the overflow 34 if there is an engine fault, the overflow 34 thus forming another type of visual alarm. The overflow 34 can be connected, by means of a pipe, to the scupper of the engine deck or to an auxiliary recovery container.

As an electrical and visual alarm, the monitoring means 14 can comprise a sensor intended for detecting the level of liquids in the collector 11 and to emit a signal intended for the cockpit of the aircraft, which signal can be seen by the pilot by means of a warning light, for example.

The monitoring means 14 thus make it possible to detect a large, anomalous liquid leak sufficiently quickly to alert an operator or the aircraft pilot. The activation of the alarm indicates that an engine fault has occurred and that a maintenance operation should be carried out.

While not forming part of the invention, the engine, which is shown in a partial view in FIG. 2, comprises other draining means 26 which are used in this case to collect fuel that has not been combusted in the combustion chamber 4 and to discharge said fuel towards the jet nozzle 9 by means of a conduit 27, the outlet of which leads into the jet nozzle. The draining device 10 according to the invention is separate from these draining means 26, which are not provided with pumping means or monitoring means.

FIGS. 3 to 10 show alternative embodiments of the invention, in which the elements described above are denoted by the same reference numerals.

In the variant in FIG. 3, the pumping means 13 (ejector 19) are incorporated in the collector 11. The first line 20 is fitted directly at the liquid outlet 17 of the collector 11 and is connected to one end of a conduit 16, the other end of which leads into the jet nozzle 9. The second line 21 of the ejector 19 extends inside the first line 20 and its inlet 23 is connected, by means of a conduit 24 that can be provided with a flap valve 25, to the means for bleeding pressurised gas from the engine 1.

The draining device in FIG. 3 likewise comprises monitoring means 14 of the above type.

This device functions similarly to that in FIG. 2.

In the embodiment in FIG. 4, the pumping means 13 comprise an ejector 19, the first line 20 of which is fitted inside the second line 21 so as to form a nozzle. The inlet of the first line 20 is connected to the liquid outlet 17 of the collector 11 by means of the conduit 16. The inlet of the second line 21 is connected to air bleeding means by means of a conduit 24 and the outlet thereof extends around the outlet of the first line 20 and leads into the jet nozzle 9.

In this case, the ejector 19 functions like an exhaust nozzle in the manner of a paint spray gun, which operates by expelling the pressurised gas around the outlet 18 of the first line 20 in order to spray the liquids from the collector 11 towards the jet nozzle 9.

In addition, the conduit 24 connecting the second line 21 of the ejector to the bleeding means is provided with a constriction 28 in its flow cross-section (instead of the flap valve 25 in FIG. 2). This constriction 28 makes it possible to delay the discharge of the liquids so that it does not take place as the engine is started up. The pressure thus increases slightly in the second line 21 of the ejector during start-up, the liquids being discharged into the jet nozzle 9 when a predetermined pressure threshold is exceeded.

The draining device likewise comprises monitoring means 14 of the above type.

The alternative embodiment in FIG. 5 differs from the embodiment in FIG. 2 mainly in that the conduit 24 is not provided with a flap valve or constriction. Instead, a valve 29, for example a slide valve, is fitted on the conduit 16 that connects the outlet 17 of the collector 11 to the inlet of the first line 20 of the ejector 19.

The valve 29 comprises an inlet connected to the outlet 17 of the collector 11 by means of a portion of the conduit 16, and an outlet connected to the inlet of the first line 20 of the ejector 19 by means of another portion of the conduit 16. The valve 29 further comprises an internal member 30, which can move between a closed position of the aforementioned outlet and/or inlet of the valve 29, and a position in which the inlet and the outlet of the valve 29 are in fluid communication. The member 30 is biased by a spring into the closed position of the valve 29. The movement of this member 30 is controlled by pressurised gas, which in this case is a portion of the pressurised gas bled from the engine by the aforementioned bleeding means. To do so, the conduit 24 connecting the bleeding means to the ejector 19 can comprise a bypass 31 connected to a cavity in the valve 29 in which the member is movably fitted. The valve 29 is intended to open when the pressure of the bled gas is greater than or equal to a predetermined threshold value, which depends in particular on the spring rate of the spring in the above example, and which is preferably determined so as to precisely control the time at which the drained liquids are discharged, in particular so that said discharge does not occur as soon as the engine is ignited.

Alternatively, and as shown by dashed lines in FIG. 5, the conduit 31 can be connected, by its end opposite the valve, to means for bleeding air from the compressor of the engine.

The alternative embodiment in FIG. 6 differs from the embodiment in FIG. 2 mainly in that the conduit 24 is connected to means for bleeding pressurised gas, not from the compressor of the engine but from a system (not shown) for removing gas from the engine. Thus, the liquids are discharged into the jet nozzle 9 by means of the system for removing gas from the engine.

The alternative embodiment in FIG. 7 differs from the embodiment in FIG. 3 mainly in that the conduit 24 connecting the second line 21 of the ejector to the bleeding means is provided with a constriction 28 in its flow cross-section (instead of the flap valve 25 of FIG. 3). This constriction 28 has the same function as the constriction described with reference to FIG. 4.

The alternative embodiment in FIG. 8 differs from the embodiment in FIG. 2 mainly in that the conduit 24 connecting the second line 21 of the ejector to the bleeding means is provided with a constriction 28 in its flow cross-section (instead of the flap valve 25 in FIG. 2). This constriction 28 has the same function as the constriction described with reference to FIG. 4.

The alternative embodiment in FIG. 9 differs from the embodiment in FIG. 3 mainly in that the conduit 24 connecting the second line 21 of the ejector 19 to the bleeding means is provided with an electrically controlled valve 32 (instead of the flap valve 25 in FIG. 3). This valve 32 is intended to open to allow the bled pressurised gas to pass through when said valve is activated by a command sent by an engine computer, for example.

In the alternative embodiment in FIG. 10, the pumping means 13 of the draining device comprise an electrical or mechanical pump 33 fitted on the conduit 16, one end of which pump is connected to the outlet 17 of the collector 11 and the opposite end leads into the jet nozzle 9. When activated, this pump 33 carries the liquids from the collector 11 to the jet nozzle 9. The delivery of this pump is also calibrated so as to set a delivery threshold, beyond which the monitoring device indicates anomalous functioning of the engine. This variant does not need a valve, a constriction or air to be bled. The draining device likewise comprises monitoring means 14 of the above type.

Claims

1. Device for draining liquids for an aircraft engine, comprising a collector designed to collect liquids drained from the engine, said device comprising means for pumping the liquids held in the collector and for discharging said liquids, and monitoring means designed to indicate when the liquids have been collected by the collector in an anomalous manner, said monitoring means being designed to be activated when the flow rate of collected liquids is greater than the delivery of the pumping means.

2. Device according to claim 1, wherein the pumping means comprise an electric, mechanical or pneumatic pump, or a jet pump ejector, this ejector comprising a first line for the flow of drained liquids, one end of which forms an inlet for the liquids held in the collector and the other end of which forms an outlet for discharging the liquids, and a second line for atomising pressurised gas, which line extends around or inside the first line and is designed so that the atomised gas leaving said second line forces the liquids to be discharged through the outlet of the first line.

3. Device according to claim 2, wherein the first line is connected to a valve.

4. Device according to claim 2, wherein the second line comprises a gas inlet that is connected to means for bleeding pressurised gas.

5. Device according to claim 1, wherein the pumping means are incorporated in the collector or are located at a distance from the collector and connected to a liquid outlet thereof by a conduit.

6. Device according to claim 1, wherein the monitoring means comprise a visual and/or electrical alarm designed to be visible to an operator inspecting the collector or to emit a signal intended for the cockpit of the aircraft.

7. Device according to claim 1, wherein the collector comprises an overflow designed to let liquids escape from the collector when the flow of collected liquids is greater than the delivery of the pumping means.

8. Aircraft engine, comprising an exhaust nozzle for combustion gases, said engine comprising at least one device according to claim 1, the outlet of the pumping means leading into the jet nozzle directly or by a conduit.

9. Engine according to claim 8, wherein the pumping means are connected to means for bleeding gas from a compressor or from a system for removing gas from the engine.

10. Method for inspecting an engine according to claim 8, said method comprising maintaining the engine after the means for monitoring the device have been activated.