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
  • F01D25/24—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
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
  • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
• • 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
  • F05D2230/00—Manufacture
  • F05D2230/60—Assembly methods
• • 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
  • F05D2250/20—Three-dimensional
  • F05D2250/28—Three-dimensional patterned
  • F05D2250/283—Three-dimensional patterned honeycomb
• • 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
  • F05D2260/96—Preventing, counteracting or reducing vibration or noise
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
  • F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
  • F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• Turbomachine such as a turbojet engine or an airplane turboprop engine
• the present invention relates to a turbomachine, such as a turbojet or an airplane turboprop, comprising a fan casing whose substantially cylindrical wall surrounds in particular the vanes of the fan.
• the inner surface of a fan casing conventionally comprises annular acoustic insulation panels. These panels generally have an annular honeycomb structure, formed of adjacent cells, whose inner and outer faces are each covered with a skin. These panels are intended to absorb the sound waves generated by the fan of the turbomachine.
• the housing more particularly comprises an upstream panel, located upstream of the blades of the fan, a median panel, located opposite the blades of the fan, and a downstream panel, located downstream of the blades of the fan.
• the median panel conventionally comprises a layer of abradable material against which the radially outer ends of the blades are intended to rub in operation.
• the cells of the honeycomb structure of the upstream panel have a relatively large section and the inner skin of this panel is generally multi-perforated.
• the median panel generally has smaller section cells than the upstream panel, so as to increase its resistance to mechanical stresses.
• each panel has denser areas at their upstream and downstream edges. This increase in density is obtained by filling the corresponding cells with a foam which, by polymerizing, provides a high mechanical strength to the relevant edges of the panels.
• each panel is attached to the annular wall by means of fasteners located at the upstream and downstream portions of each panel.
• the upstream and median panels are fixed to the annular wall by means of a thermosetting glue film.
• the heating of the adhesive film may for example be carried out in an autoclave.
• the adhesive may be a heat-sensitive adhesive capable of fixing the panel on said wall when the glue is heated to a first temperature and able to release the panel when the glue is heated to a second temperature.
• a heat-sensitive adhesive capable of fixing the panel on said wall when the glue is heated to a first temperature and able to release the panel when the glue is heated to a second temperature.
• the invention aims in particular to provide a simple, effective and economical solution to this problem.
• a turbomachine such as a turbojet or an airplane turboprop, comprising a substantially cylindrical wall fan casing surrounding the blades of the fan, and at least two annular sound insulation panels mounted radially to inside said wall, a first panel being mounted upstream of the fan, a second panel being located downstream of the first panel and carrying an inner layer of abradable material located opposite the radially outer ends of the blades of the fan, characterized in that the two annular panels form a single structural assembly.
• the downstream edge of the first panel is attached to the upstream edge of the second panel, for example by gluing.
• the two panels thus form a single structural assembly, easier to handle and fix inside the housing wall.
• the adhesive bonding is easy to implement and does not require the presence of dense areas at the downstream edge of the first panel or at the upstream edge of the second panel.
• each panel comprises an annular honeycomb structure formed of adjacent cells, the inner and outer surfaces of said annular structure being covered respectively with an inner skin and an outer skin.
• the cells of the first panel have a larger section than the cells of the second panel.
• At least a portion of the inner skin of the first panel and / or the second panel has perforations.
• Such perforations can further improve the sound insulation.
• the turbomachine may comprise upstream fastening means located at the upstream portion of the first panel, downstream fastening means located at the downstream portion of the second panel, and medial fastening means located at the level of the junction area between the first and second panels, said fixing means for fixing said panels to the housing wall.
• first panel and the second panel form a single panel.
• this single panel can be fixed to the casing wall by means of upstream fixing means located at the upstream portion of the panel, and downstream fixing means located at the downstream portion of the panel. sign.
• first and second panels are formed of a single panel increases the mechanical strength of the latter. It is thus possible to reduce the number of fastening means used and, consequently, the mass of the turbomachine.
• the panels can also be attached to the housing wall by means of a glue film.
• the adhesive may be a heat-sensitive adhesive capable of fixing the panel on said wall when the adhesive is at a first temperature and able to release the panel when the adhesive is heated to a second temperature.
• FIG. 2 is a front view from the upstream of the housing of Figure 1;
• FIG. 3 is a partial schematic half-view in axial section of an acoustic insulation panel of the fan casing of FIG. 1;
• FIG. 4 is a view on a larger scale of the detail 4 of FIG. 1, and represents means for fixing an acoustic insulation panel;
• FIG. 5 is a schematic sectional view along the line V-V of Figure 4.
• FIG. 6 is a schematic half-view in axial section of a fan casing of a turbomachine according to an embodiment not belonging to the invention
• Figure 7 is a schematic front view from the upstream of the housing of Figure 6;
• FIG. 8 is a schematic view of a portion of the adhesive film of the housing of Figures 6 and 7;
• FIG. 9 is a perspective view of a first and a second panel, glued to each other so as to form a single structural assembly attached to the wall of a fan casing via fastening means according to a first embodiment of the invention
• FIG. 10 is a view corresponding to FIG. 9, illustrating a second embodiment of the invention in which the first and second panels are formed of a single panel,
• FIGS 1 1 and 12 are views respectively corresponding to Figures 9 and 10, in which the panels are fixed to the wall of the housing by gluing, according to two embodiments of the invention.
• FIG. 1 represents a fan casing 10 of a turbomachine, such as a turbojet engine or an airplane turboprop, this casing being part of a nacelle which surrounds the engine of the turbomachine and inside of which rotates a fan which generates a secondary air flow flowing between the nacelle and the engine and forms part of the thrust produced by the turbomachine.
• a turbomachine such as a turbojet engine or an airplane turboprop
• the housing 10 comprises a substantially cylindrical wall 12 which has at its longitudinal ends annular flanges 14, 16 for fixing.
• the downstream flange 14 is fixed by screw-nut means to a flange (not shown) of an intermediate casing and the upstream flange 16 is fixed by screw-nut means to a flange (not shown) of an air intake sleeve in the nacelle.
• the casing comprises annular panels 18, 20, 22 of sound insulation which cover the inner cylindrical surface of the wall 12 and which are fixed to this wall.
• the wall 12 carries three annular panels 18, 20, 22, two panels 18, 20 monoblock respectively upstream and median, and a downstream panel 22 which is sectored.
• the downstream panel 22 comprises panel sectors which are arranged circumferentially end to end and which are fixed on the wall 12 by screws 24 passing radially through the sectors and engaged in openings in the wall 12.
• the annular panels 18, 20 are monobloc (that is to say non-sectored) and are fixed on the wall 12 by a technology that allows the disassembly of the panels, especially under the wing of an aircraft during a flight. maintenance operation.
• Panels 18, 20 have denser zones 62 at their upstream and downstream edges. This increase in density is obtained by filling the corresponding cells with a foam which, by polymerizing, provides a high mechanical strength to the relevant edges of the panels.
• the panels 18, 20 are mounted inside the wall 12 and fixed to this wall by means of the screw-nut type, each panel comprising lugs 26 of axial support. and radial on tabs 28 of the wall 12, these tabs having through holes means 32 of the screw-nut type.
• FIG. 3 represents an exemplary embodiment of a panel 18, 20 having an annular honeycomb structure 34 whose inner and outer faces are each covered with a skin 36, 38 laminated, the inner skin 36 having multiperforations 40.
• the panel may further comprise a layer of abradable material, in particular in the zone of the panel surrounding the fan blades, as is the case of the panel 20 which comprises under its inner skin 36 an inner layer 42 of abradable material (figure 1 ).
• the cells 64 of the honeycomb structure of the panel 18 have a relatively large section.
• the panel 20 generally has cells of smaller section than the panel 18, so as to increase its resistance to mechanical stresses generated in particular by the friction of the radially outer ends of the vanes against the layer of abradable material 42.
• each panel 18, 20 is formed in one piece without discontinuity, the tabs 26 being fixed to the outer skin 38 of the panel and being located in an annular space 40 extending between the panel 18 , 20 and the wall 12.
• This annular space 40 may have a thickness or radial dimension of the order of 10 mm.
• Each panel 18, 20 is equipped with two annular rows of tabs, an upstream row of tabs 26, 28 and a downstream row of tabs 26 ', 28'.
• the legs of each row are regularly distributed around the longitudinal axis of the housing and are diametrically opposed two by two.
• the tabs 26, 28 of the upstream row are further angularly offset tabs 26 ', 28' of the downstream row, relative to the longitudinal axis of the housing ( Figure 2).
• Each row comprises for example twelve tabs 26, 26 ', 28, 28'.
• the tabs 26 carried by the panel 18, 20 have a substantially L-shaped shape and each comprise a longitudinal portion 42 applied to the outer skin 38 of the panel and fixed to this skin by screws 43 cooperating with crimped nuts of the self-braking type ( Figure 5).
• This longitudinal portion 42 has a cylinder-shaped portion and matches the outer shape of the panel.
• the portion 42 of the tab 26 is connected at one of its longitudinal ends to a substantially radial portion 44 which extends outwards and which comprises a through-hole through which the screw 32 passes.
• the portion 42 of the tab 26 comprises a radially outer bearing surface 46 of cylindrical shape and the radial portion 44 comprises a radial bearing surface 48.
• the portion 44 of the tab 26 has a circumferential dimension smaller than that of its portion 42.
• the legs 28 carried by the wall 1 2 each comprise a substantially planar radially outer portion 50 applied to the radially inner surface of the wall 12 and fixed thereto by screws 52 cooperating with crimped nuts of the self-braking type, and a part 54 extending radially inwards and which comprises a through hole aligned with the orifice of the lug 26 for the passage of the screw 32 for fixing these tabs.
• This portion 54 comprises a radial bearing surface 56 on the radial surface 48 of the lug 26 and a planar or substantially cylindrical bearing surface 58 on the cylindrical surface 46 of the lug 26.
• the portion 54 of the tab 28 has a circumferential dimension less than that of its portion 50. Moreover, the portion 50 of the tab 28 is partly engaged in a recess 60 of shape complementary to the wall 12.
• the panels 18, 20 previously described may be mounted within the wall 12 of the housing as follows.
• Each panel 18, 20 is disposed upstream of the wall 12, coaxially with it, and is angularly positioned around the longitudinal axis of the housing so that its lugs 26, 26 'are aligned axially with those 28, 28' crankcase. The panel is then moved in axial translation downstream until it is housed inside the wall 12 and that its lugs 26, 26 'are axially supported on those 28, 28' of the housing.
• a tool such as a ratchet equipped with an extension is then used to screw the screws 32 in the tabs to secure the panel to the housing.
• This tool is inserted axially from upstream in the annular space 40 extending between the panel and the wall.
• such an embodiment requires the use of many fastening means 26, 28, 26 ', 28', 32, which increases the mass of the assembly. Furthermore, the presence of dense areas 62 at the panels 18, 20 is also detrimental in terms of mass. Finally, the number of panels to mount and fix inside the wall 12 of the housing is important, which is long and tedious.
• FIG. 6 to 8 illustrate an embodiment not belonging to the invention.
• This embodiment differs from that described above in that the panels 18, 20 (sectored or monobloc) are fixed by a adhesive film 66 on the inner surface of the wall 12.
• the adhesive film 66 is heat-sensitive. Indeed, it is able to fix the panels 18, 20 on said wall 12 when the glue is at a first temperature and able to release the panels 18, 20 of said wall 12 when the glue is heated to a second temperature. Such an adhesive film 66 thus allows easy disassembly and assembly of the panels 18, 20.
• This film 66 comprises a conductive wire 68, for example based on carbon, whose ends 70, 72 are connected to the terminals of a power supply.
• the wire 68 is embedded in the polymer matrix formed by the adhesive film 66.
• the passage of an electric current in the wire 68 causes it to overheat.
• the wire 68 can be arranged in a serpentine and extend over the entire surface of the film 66.
• the adhesive film 66 In normal operation, the adhesive film 66 is subjected to low temperatures. In this case, the film 66 performs its function of fixing the panels 18, 20 on the wall 12.
• Such an embodiment thus facilitates the repair of a fan casing 10, since it allows the quick and easy disassembly of the panels 18, 20, in particular in the event of maintenance under the wing of an aircraft (this is ie without removing the engine). Such an embodiment also applies to the case of mounting panels 18, 20 at the factory.
• the invention proposes a turbomachine in which the two annular panels 18, 20 form one and the same structural assembly.
• the invention proposes to bond the downstream edge of the panel 18 to the upstream edge of the panel 20.
• the corresponding glue film is referenced 74.
• the cells 64 of the panel 18 have a larger section than the cells 64 of the second panel 20.
• edges of the panels 18, 20 intended to be glued to each other do not necessarily include dense areas 62. Only the upstream edge of the panel 18 and the downstream edge of the panel 20 then comprise a dense area 62.
• the assembly formed of the panels 18, 20 comprises upstream fastening means 26, located at the upstream portion of the panel 18, downstream fastening means 26 ', located at the downstream portion of the panel 20, and the median fastening means 26 ", located at the junction zone 74 between the panels 18, 20, said fastening means 26, 26 ', 26" for fixing said panels 18, 20 to the wall 12 of the housing.
• FIG. 10 illustrates a second embodiment of the invention, in which a single panel 76 provides both the function of the panel 18 and the function of the panel 20.
• This panel 76 has dimensions similar to those of the formed assembly by panels 18 and 20 in Figure 9. It supports, as before, a layer of abradable material 42 and has dense areas 62 at its edges upstream and downstream.
• the panel 76 has a structure similar to that of the panels 18, 20, the cells 64 all having the same section. Of course, it is possible to vary the section of the cells depending on their position in the panel 76, if the mechanical stresses involved require it.
• the panel 76 comprises upstream fixing means 26 situated at the upstream portion of the panel 76, and downstream fixing means 26 'located at the downstream portion of the panel 76.
• FIG. 11 illustrates a third embodiment similar to that of FIG. 9, in which the panels 18 and 20 are fixed to the wall 1 2 of the casing with the aid of a glue film 66 (not shown in FIG. Figure 1 1) similar to that described with reference to Figures 6 to 8.
• FIG. 12 illustrates a third embodiment similar to that of FIG. 10, in which the panel 76 is fixed on the wall 1 2 of the casing with the aid of an adhesive film 66 (not shown in FIG. Figure 12) similar to that described with reference to Figures 6 to 8.
• the mass of the assembly is reduced by comparison with the prior art, either by the reduced number of dense areas 62 or by the reduced number of fixing means. Furthermore, the fact of having a single structural assembly, providing the same functions as the panels 18 and 20 of the prior art, facilitates its assembly and disassembly.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (1)

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ID=48225059

Family Applications (1)

Country Status (9)

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Family Cites Families (17)

• 2013
  • 2013-03-15 FR FR1352353A patent/FR3003303B1/fr active Active
• 2014
  • 2014-03-12 EP EP14715361.3A patent/EP2971738A1/de not_active Withdrawn
  • 2014-03-12 CA CA2905793A patent/CA2905793A1/fr not_active Abandoned
  • 2014-03-12 RU RU2015138543A patent/RU2015138543A/ru not_active Application Discontinuation
  • 2014-03-12 US US14/775,141 patent/US20160032834A1/en not_active Abandoned
  • 2014-03-12 WO PCT/FR2014/050566 patent/WO2014140483A1/fr active Application Filing
  • 2014-03-12 BR BR112015023057A patent/BR112015023057A8/pt not_active IP Right Cessation
  • 2014-03-12 JP JP2015562284A patent/JP2016513773A/ja active Pending
  • 2014-03-12 CN CN201611151155.0A patent/CN106979040A/zh active Pending
  • 2014-03-12 CN CN201480015664.3A patent/CN105051360A/zh active Pending

Non-Patent Citations (2)

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