Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
  • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
  • B64C1/1407—Doors; surrounding frames
  • B64C1/1453—Drain masts
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D29/00—Power-plant nacelles, fairings or cowlings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
  • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
  • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
  • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/32—Application in turbines in gas turbines
  • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2250/00—Geometry
  • F05D2250/70—Shape
  • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/60—Fluid transfer
  • F05D2260/602—Drainage

Definitions

• the present invention relates to a drained fluid retention device for a propulsion unit, these fluids being, for example, oil, water and / or fuel.
• An aircraft propulsion unit is generally equipped with means for draining fluids (oil, water and / or fuel) from the engine to prevent these fluids from accumulating and disrupting the operation of the engine. Drainage of oil and fuel is achieved due to dynamic seal technologies (pumps, AGB, metering, cylinders, etc.) that do not provide a perfect seal. It is therefore necessary to drain the fluids that pass through the dynamic seals to avoid leaks in the engine. Water is drained to avoid retention areas that often lead to corrosion.
• fluids oil, water and / or fuel
• the drained fluids can be discharged directly to the outside.
• the fluid drainage means of the engine can also be connected by supply means, such as ducts, to a retention box having a drained fluid storage cavity.
• This retention box is located in the propulsion unit. It is attached to the engine and is generally located in the lower part of the propulsion unit so that the drained fluids flow by gravity in the supply means into the storage cavity.
• the propulsion assembly further comprises a drainage mast for the evacuation of drained fluids to the outside.
• This mast is carried by the nacelle and protrudes outwardly of the nacelle. It is also located in the lower part of the propulsion unit, next to the retention box, and recovers fluids coming out of the box.
• the mast includes one end lower having a fluid discharge port to the outside of the nacelle. When the storage cavity of the retention box is emptied, the fluids are evacuated to the opening of the mast and are evacuated to the outside of the propulsion unit.
• the opening kinematics of the covers do not allow manual access to the retention box, nor does it allow for a sealed hydraulic connection between the supply means and this box. It would be conceivable not to equip these propellant sets of retention box, the aforementioned supply means would then have their outlets that lead directly opposite the mast and that would discharge the drained fluids at the mast as and when these fluids are collected. However, some aircraft manufacturers wish their turbomachines are equipped with drained fluid retention boxes, in particular to better control the moment of evacuation of these fluids to the outside of the propulsion unit.
• the drainage mast is attached to a removable cap of the nacelle, which has a cylinder-shaped portion and which is articulated along one of its longitudinal edge about a substantially horizontal axis.
• the hood can be moved from a closed position of the nacelle in which the mast is in the lower position and has a substantially vertical orientation, to an open position of the nacelle (for example for a maintenance operation) in which the hood has been moved at an angle of about + 90 ° about its axis of articulation and the mast is in a lateral position and has a substantially horizontal orientation.
• the mast comprises fluids in its cavity, they would pour on the ground during movement and opening of the hood, which is problematic.
• the nacelle hood of one of the turbomachines is movable at an angle of about + 90 ° around its axis of articulation and the nacelle hood of the other turbomachine is movable at an angle of about -90 ° around its axis of articulation. Even if a solution was identified to retain the fluids in the mast of a hood, this solution would not necessarily be effective to retain the fluids in the mast of the other hood.
• the present invention provides a simple, effective and economical solution to this problem.
• the invention proposes a device for retaining drained fluids for a propulsion assembly, comprising a body defining a cavity for storing drained fluids having a volume V1 when the device is in a first position, for example substantially vertical, this cavity having an upper opening through which the fluids are fed into the cavity, characterized in that it comprises two walls at this opening, a first wall configured to define a volume V3 for storing fluids in the cavity, when the device is in a second position located at a positive angle of the first position about a substantially horizontal axis, and a second wall configured to define a volume V2 of storage of fluids in the cavity, when the device is in a third position located at a negative angle of the first position about a substantially horizontal axis, each volume V2 and V3 being at least equal to the volume V1.
• the device according to the invention is particularly advantageous because the walls mounted at the opening retain the drained fluids in the storage cavity and thus prevent them from spilling during the displacement of the device, regardless of the direction of movement of the device. , that is to say for example the opening direction of the nacelle cover carrying this device.
• the storage volumes defined by the walls are at less equal to the volume of the cavity, which allows to retain all fluids even when the cavity is full.
• positive angle means a rotational displacement angle in one direction about an axis of rotation
• negative angle is an angle of displacement in rotation in the opposite direction about an axis of rotation
• the walls of the device are at least partly superimposed on one another and define between them a space.
• the two walls may be respectively upper and lower walls.
• the upper wall may define a fluid introduction port in said space.
• This orifice is preferably offset on one side with respect to a median vertical plane of the cavity. As will be described in detail in the following, this increases the storage volume of fluids in the cavity.
• the bottom wall may extend below the orifice of the upper plate and define a fluid passage from the space to the cavity.
• the fluids that pass through the hole of the upper wall thus fall on the bottom wall and are conveyed to the cavity through the passage defined by the bottom wall.
• This passage may be formed by a notch on a peripheral edge of the bottom wall.
• This passage is preferably offset relative to the median vertical plane of the cavity, on the opposite side to that of the aforementioned orifice of the upper wall. This also makes it possible to increase the volume of storage of fluids in the cavity, as will be described in detail in the following.
• the bottom wall may be inclined relative to the top wall. In operation of the propulsion unit, it is preferably inclined with respect to a horizontal plane so that the fluids that fall on the bottom wall flow on it by gravity to the aforementioned passage.
• the device may comprise a conduit for evacuating the overflow of the cavity, an end of this duct opening into said space.
• the walls are preferably plates or sheets. They can have a parallelepipedic general shape. The walls can be fixed by welding or brazing on the body.
• the present invention also relates to a propulsion unit, characterized in that it comprises a device as described above, this device being fixed to a removable nacelle cover, which is articulated around a substantially horizontal axis to a component of the propulsion system.
• the device may be in the form of a mast which is carried by the nacelle of the propulsion unit and which projects on the outer surface of the nacelle.
• This mast can have an aerodynamic profile.
• FIG. 1 is a schematic perspective view of a propulsion system of aircraft according to the invention.
• FIG. 2 is a partial schematic perspective view in axial section of the propulsion unit of Figure 1, on a larger scale;
• FIGS. 3 and 4 are very partial schematic views in cross-section of a turbomachine nacelle hood, and represent two different positions of this hood respectively closing and opening the nacelle,
• FIGS. 5 to 7 are very schematic cross-sectional views of a fluid retention device according to the invention, and represent three different positions of this device respectively: vertical position, first horizontal position (the device being moved 90 ° in one direction), and second horizontal position (the device being moved 90 ° in the opposite direction), and
• FIG. 8 is schematic perspective views of an embodiment of the device according to the invention.
• the terms upstream and downstream refer to the flow direction of the gases in a propulsion unit
• the radially inner and outer terms refer to the longitudinal angle of the propulsion unit
• the lower and upper terms are used to describe elements of a part when the latter is in a substantially vertical position.
• FIG. 1 represents a propulsion unit 10 of an aircraft comprising a motor 12 (such as a turbofan engine, schematically represented by dotted lines) surrounded by a nacelle 14.
• a motor 12 such as a turbofan engine, schematically represented by dotted lines
• the engine 12 comprises, from upstream to downstream, in the direction of flow of the gases (from left to right in the drawing), a fan, a compressor, a combustion chamber, a turbine and a gas ejection nozzle. combustion.
• the nacelle 14 comprises an air inlet, hoods and an inverter, which define the outer surface of the propulsion unit.
• the propulsion unit 10 comprises a device 16 for retaining drained fluids, this device being in the form of a mast 16 which has a substantially radial orientation and which projects on the external surface of the nacelle 14. This mast is located in the lower part of the propulsion unit, at six o'clock (6 o'clock) by analogy with the dial of a clock.
• the propulsion unit comprises means for draining these fluids (such as drains) which are connected by means for supplying fluids such as ducts 18 to the holding pylon 16.
• the mast 16 is carried by a hood 14 'of the nacelle, this hood 14' having here a semi-cylindrical shape and being articulated by one of its longitudinal edges 20 around a substantially horizontal axis 22.
• the cover 14 ' can be rotated about the axis 22 from a closed position of the nacelle, shown in Figure 3, to an open position of the nacelle, shown in Figure 4.
• the angle between these two extreme positions may be of the order of 90 °.
• the mast 16 In the closed position of Figure 3, the mast 16 is located under the ducts 18 integral with the engine and its median plane P has a substantially vertical orientation. In the open position Figure 4, the mast 16 is located on the side (left in the drawing) and its median plane P has a substantially horizontal orientation.
• the ducts 18 integral with the engine do not prevent the fluids contained in the mast 16 from spilling to the ground.
• the propulsion unit located on the other side of the aircraft would include a nacelle whose mast would be located from the other side (right) when the hood is in the open position of the nacelle.
• the present invention proposes to overcome the drawbacks of the prior art through a mast or retention device which ensures the retention of the drained fluids that it contains, regardless of the position (opening or closing) of the cover carrying this device .
• FIGS 5 to 7 show very schematically a device 1 10 for retention of drained fluids according to the invention.
• the device 1 10 comprises a body 1 12 defining a cavity 1 14 for storing the drained fluids, this body comprising in its upper part an opening 1 16 through which the fluids are intended to be introduced into the cavity 1 14.
• two walls 1 18, 120 are mounted at the opening 1 16 and are intended to ensure the retention of fluids in the cavity in the aforementioned positions, that is to say when the device is substantially horizontal.
• the walls 1 18, 120 are respectively mounted one above the other and are therefore superimposed. They define between them a space 122 for the flow of drained fluids penetrating into the device.
• the upper wall 1 18 extends above the opening 1 16 and comprises a port 124 for introducing the fluids into the cavity.
• the wall 1 18 is substantially horizontal when the device 1 10 is in its operating position, that is to say in the position of FIG. 5.
• the bottom wall 120 is inclined with respect to the upper wall
• the upper part of the wall 120 is situated directly under the orifice 124 and its lower part defines with the body a passage 126 for the circulation of the fluids from the space 122 to the cavity 1 14.
• the orifice 124 of the upper wall 1 18 is offset on one side with respect to the vertical median plane P of the device, and the passage 126 defined by the lower wall 120 is shifted from the other side with respect to this plane P.
• the cavity 1 14 defined by the body has a volume V1.
• This volume V1 is defined when the device 1 10 has a vertical orientation, as shown in Figure 5.
• This volume V1 depends in particular on the shape and dimensions of the body but also the position of means 128 for discharging the overflow of the cavity. In the example shown, these means 128 open into the space 122 between the walls 1 18, 120.
• the bottom wall 120 is configured to define a volume V2 for storing fluids in the cavity 1 14, when the device 1 10 is oriented substantially horizontally, in the position shown in Figure 6 (moving the cover carrying the device + 90 ° for example around its axis of rotation).
• This volume V2 depends in particular on the shape and dimensions of the body but also on the position, the shape and the dimensions of the passage 126 defined by the wall 120. The offset of the passage 126 with respect to the plane P thus makes it possible to increase the volume V2.
• This volume V2 is greater than or equal to the volume V1.
• the upper wall 1 18 is configured to define a fluid storage volume V 3 in the cavity 1 14, when the device 1 10 is oriented substantially horizontally, in the position shown in FIG. 7 (movement of the cover carrying the device of -90 ° for example around its axis of rotation).
• This volume V3 depends in particular on the shape and dimensions of the body but also on the position, the shape and the dimensions of the orifice 124 and the means 128. The offset of the orifice 124 with respect to the plane P thus makes it possible to 'increase the volume V3.
• This volume V3 is greater than or equal to the volume V1.
• FIGS. 8 and 9 show an embodiment of the retention device 1 10 according to the invention, this device 1 10 being here in the form of a mast comprising a top plate 130 for fastening to the hood of the nacelle and a part lower profile 132 intended to extend substantially radially projecting on the outer surface of the cover.
• the plate 130 and the profiled portion 132 are here formed by a body 1 12 monobloc.
• the profiled portion 132 is hollow and internally comprises a housing defining the major part of the cavity of the device.
• the plate 130 has a substantially parallelepipedal shape and is arranged substantially horizontally in the operating position. It comprises substantially in its middle a recess 134 of substantially parallelepiped shape, which extends above the housing of the profiled portion 132 and communicates with this housing to define the cavity of the device.
• the recess 134 opens on the upper surface 136 of the plate 130 and forms the opening 1 16 of the cavity.
• the plate 130 further comprises a conduit 146 for discharging the overflow of the cavity, which opens into the recess 134.
• the conduit 146 is formed in the thickness of the plate 130 and its upper end opens on the upper surface. 136 of the stage.
• the device 1 10 comprises two walls 1 18, 120 which are here in the form of plates and are mounted in or on the recess 134 of the device.
• the upper plate 18 is shown in FIG. 8, which also shows the bottom plate 120. Only the bottom plate 120 is shown in FIG.
• the upper plate 1 18 ( Figure 8) has a generally rectangular shape and is intended to be fixed, for example by welded assembly, to the plate 130, to cover the recess 134. It extends substantially parallel to the upper surface 136 platinum and is therefore substantially horizontal in operation.
• the upper plate 1 18 covers here almost all of the upper surface 136 of the plate, and closes the upper end of the conduit 146. A seal between the plate 1 18 and the upper surface 136 of the plate can be provided to ensure the good retention of fluids in the three positions.
• This plate 120 comprises an orifice 124 for introducing fluids drained into the cavity.
• this orifice 124 has an elongated shape along one of the sides of the recess 134.
• the lower plate 120 (FIGS. 8 and 9) has a generally rectangular shape and is intended to be mounted inside the recess 134.
• the plate 120 is preferably fixed, for example by welding, to the plate 1 18.
• the plates 1 18, 120 define between them a space 122 for the flow of drained fluids (FIG. 8) into which an end of the overflow 146 opens (FIG. 9).
• the plate 120 defines a passage 126 for the fluids drained from the space 122 to the cavity.
• the passage 126 is situated on the opposite side to the orifice 124, with respect to the plane P.
• the plate 120 is inclined with respect to the plate 1 18.
• the drained fluids are conveyed through the conduits 18 and flow through the orifice 124 of the plate 1 18. They fall on the lower plate 120 and flow by gravity to the passage 126, then into the cavity.
• the maximum volume of fluids stored in the cavity corresponds to the volume until the fluids reach the level of the plate 120 .
• the device 1 10 comprising the volume of fluids is moved in a first horizontal position such as that shown in FIG. 6 (and has undergone a displacement of + 90 ° for example - its median plane P being horizontal), the major part or the entire volume of fluids is retained by the lower plate 120 and the remainder is passed through the passage 126 in the inter-plate space 122.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Aviation & Aerospace Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Wind Motors (AREA)
• Loading And Unloading Of Fuel Tanks Or Ships (AREA)
• Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
• Warehouses Or Storage Devices (AREA)

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• 2013
  • 2013-12-04 FR FR1362079A patent/FR3014134B1/fr active Active
• 2014
  • 2014-12-02 EP EP14825401.4A patent/EP3077289A1/fr not_active Ceased
  • 2014-12-02 CN CN201480065647.0A patent/CN105793159B/zh active Active
  • 2014-12-02 CA CA2931310A patent/CA2931310C/fr active Active
  • 2014-12-02 WO PCT/FR2014/053136 patent/WO2015082833A1/fr active Application Filing
  • 2014-12-02 RU RU2016121184A patent/RU2667109C1/ru active
  • 2014-12-02 US US15/100,225 patent/US10301973B2/en active Active
  • 2014-12-02 BR BR112016012226-7A patent/BR112016012226B1/pt active IP Right Grant

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