Classifications

• • 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
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
  • F05B2260/00—Function
  • F05B2260/30—Retaining components in desired mutual position
  • F05B2260/301—Retaining bolts or nuts
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/40—Organic materials
  • F05D2300/44—Resins
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/603—Composites; e.g. fibre-reinforced
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/614—Fibres or filaments
• • 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
  • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
  • F16B5/01—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening elements specially adapted for honeycomb panels
• • 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
  • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
  • F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
• • 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

• the present invention relates to turbine engines for aircraft and, more specifically, the connection between the air inlet and the fan casing of such a turbine engine.
• the inner wall of the air inlet and the blower housing are metallic and the rear end of said inner wall of the air inlet and the front end of said blower housing bear cooperating protruding peripheral flanges for securing said air inlet and said housing by means of fastening elements (screws, bolts, etc.) whose axes are parallel to the longitudinal axis of the turbine engine and which pass through said flanges.
• the present invention aims to overcome this disadvantage.
• the aircraft turbine engine having a longitudinal axis and comprising:
• blower supplied with air by said air inlet and enclosed in a casing, also tubular, the rear end of said inner wall of the air inlet and the front end of said fan casing being secured to one another by means of fastening elements, such as screws, bolts or analogous, is remarkable in that:
• At least one of said parts which are said internal wall of the air inlet and said casing of the blower is made of a fiber / resin composite material
• said rear end of said inner wall of the air inlet and said front end of said fan casing are uniform, without projections adapted to serve for securing said inner wall and said casing, such as peripheral flanges or the like;
• the axes of said fasteners are, with said longitudinal axis of the turbine engine, an angle at least equal to 60 °.
• Both said inner wall of the air inlet and said blower housing may be made of fiber / resin composite material and said axes of the fasteners may at least approximately be orthogonal to said longitudinal axis of the turbine engine.
• said rear end of the inner wall of the air inlet and said front end of the blower housing fit into each other and said fasteners pass through. the nested portions of said front and rear ends.
• the rear end of said inner wall of the air inlet can penetrate into the front end of said blower housing or, conversely, the front end of said blower housing.
• the blower enters the rear end of said inner wall of the air inlet.
• said interlocking can be achieved with direct contact between said front and rear ends, or with the interposition of at least one spacer ring between said front and rear ends.
• said fixing means also pass through the spacer ring (s).
• the contact surface may be cylindrical or conical.
• said rear end of said inner wall of the air inlet and said front end of said blower housing are secured to one another by means of a connecting ring (in a single piece or in several evenly distributed segments) into which they penetrate, fastening elements pass through the parts facing said ring and said rear end of said inner wall of the air inlet, and other fasteners pass through the facing portions of said ring and said forward end of said blower housing.
• a connecting ring in a single piece or in several evenly distributed segments
• fastening elements pass through the parts facing said ring and said rear end of said inner wall of the air inlet
• other fasteners pass through the facing portions of said ring and said forward end of said blower housing.
• the contact surface between said connecting ring, on the one hand, and said front and rear end, on the other hand may be cylindrical or conical.
• said connecting ring may comprise a transverse partition.
• fastening elements are bolts whose nuts are captive of one or the other of said front and rear ends;
• said fixing elements are connected to one of said front or rear ends by means of plastically deformable members making it possible to absorb at least part of the energy percussion of the fan casing by a broken blade thereof;
• - Centering means are used to accurately position, around the longitudinal axis of the turbine engine, one of said front or rear ends relative to the other.
• the composite material constituting said inner wall of the air inlet and said blower housing may comprise carbon fibers, boron, glass, silicon carbide, etc ... and said inner wall and said housing may be obtained by any known process (filament winding, winding, removal of impregnated fibers or impregnated fabrics, etc.).
• FIG. 1 shows, in partial schematic partial section, the front part of a known turbine engine.
• FIG. 2 shows, also in partial schematic partial section, an example of connection between the rear end of the air intake and the front end of the fan casing, in the known turbine engine of FIG. 1.
• Figures 3 to 8 illustrate several examples of connection between the rear end of the air inlet and the front end of the fan casing in a turbine engine according to the present invention.
• FIG. 9 is a partial top view of the example of joining of FIG. 8.
• FIG. 10 is a plan view of a plastically deformable ring used in the embodiment of FIG. 8.
• Figure 1 1 corresponds to a section along line X1-X1 of Figure 9.
• the known type of turbine engine 1 whose front part is schematically and partially shown in FIG. 1, comprises a longitudinal axis LL.
• This front portion essentially comprises a tubular air inlet 2 and a blower 3.
• the tubular air inlet 2 has a leading edge 4 and is provided with a tubular metal inner wall 5, for example made of aluminum, internally carrying a tubular acoustic attenuation coating 6.
• An outer cover 7 surrounds said air inlet and delimits with said inner wall 5 a chamber 8 with an annular section, closed by an annular rear wall 9 on the opposite side to said leading edge 4.
• the fan 3 comprises blades 10 and is surrounded by a fan casing 11 constituted by a metal tubular piece 12, for example made of aluminum, and internally carrying a tubular acoustic attenuation coating 13.
• the rear end 2R of the air inlet 2 and the front end 1 1A of the fan casing January 1 are assembled to one another along a joint plane J.
• the assembly of the rear ends 2R and before 11A is obtained by two cooperating annular flanges 14 and 15 projecting outwardly from the inner wall 5 and the tubular part. 12 and pressed against each other by bolts 16 of axes 11 parallel to the longitudinal axis LL and through bores 17 and 18 opposite, made in said flanges 14 and 15.
• the annular flange 14 is attached to the inner wall 5 and is secured thereto by bolts 19 and 20.
• the flange 15 is machined in one piece with the workpiece tubular 12.
• each bolt 1 6 is associated with a ring 21 traversed by said bolt 16 and secured thereto by the flange 15.
• the rings 21 are made so that they can be compressed axially plastically. Thus, when a blade 10 of the fan 3 breaks and hits the casing 11, the energy of the percussion can be at least partly absorbed by said rings 21.
• FIGS. 3 to 8 show, in a view comparable to FIG. 2, exemplary embodiments according to the present invention in which the internal wall of the air inlet 2 and the fan casing 11 are made by tubular parts. of composite fiber / resin material, respectively 5.1 to 5.6 and 12.1 to 12.6, devoid of projecting flanges at the ends 2R and 1 1A and assembled by fastening elements 22.1 to 22.3 and 32.4, 34.4 orthogonal to the longitudinal axis LL of the turbine engine 1.
• the composite tubular piece 5.1 forming the inner wall of the air inlet 2 and carrying the internal acoustic attenuation coating 6, has a diameter smaller than that of the tubular piece composite 12.1, forming the fan casing 11 and carrying the internal acoustic attenuation coating 13, so that the 5.1 R rear end of the composite part 5.1 can penetrate, preferably soft friction, in the front end 12.1 A of the composite part 12.1.
• the composite parts 5.1 and 12.1 are assembled by transverse bolts 22.1, whose x.1 -x.1 axes are orthogonal to the longitudinal axis L-L of the turbine engine 1 and which cross the 5.1 R ends and 12.1 A opposite.
• the nuts 23.1 of the bolts 22.1 are made prisoner of the inner wall of the composite part 5.1, for example by screws 24.1, only represented by center lines.
• the composite tubular piece 5.2 forming the inner wall of the air inlet 2 and carrying the internal acoustic attenuation coating 6, has a diameter greater than that of the tubular part.
• composite 12.2 forming the fan casing 11 and carrying the acoustic attenuation coating.
• the rear end 5.2R of the composite part 5.2 is internally conical, while the front end 12.2A of the composite part 12.2 is externally conical.
• the front end 12.2A can enter the rear end 5.2R, the contact surface 25 of said ends then being tapered.
• the composite parts 5.2 and 12.2 are assembled by transverse bolts 22.2, whose x.2-x.2 axes are orthogonal to the longitudinal axis LL of the turbine engine 1 and which cross the ends 5.2R and 12.2A opposite.
• the nuts 23.2 of the bolts 22.2 are trapped 26.2 parts reported inside the front end 12.2A.
• transverse bolts 22.3 whose x.3-x.3 axes are orthogonal to the longitudinal axis L-L of the turbine engine 1 and which serve to secure said composite parts 5.3 and 12.3.
• the nuts 23.3 of the bolts 22.3 are trapped in parts 26.3 attached to the front end 12.3A.
• the rear end 5.4R of a composite part 5.4 forming the internal air intake wall 2 and carrying the acoustic attenuation coating 6, and the front end 12.4A of a composite part 12.4, forming the fan casing 1 1 and carrying the acoustic attenuation coating 13, are connected to each other by means of a connecting ring 30 in the ends. opposite sides of which they fit together.
• the connecting ring 30 has a transverse wall 31, at least approximately representing the joint plane J, and transverse bolts 32.4, 33.4 and 35.4, whose respective axes x4-x4, x5-x5 and x6-x6 are orthogonal to the longitudinal axis LL of the turbine engine 1, ensure the joining of the parts 5.4 and 12.4 via said connecting ring 30.
• At least some of the nuts of the bolts 32.4, 33.4 and 34.4 are prisoners of the room 5.4 or the room 12.4 and the annular rear wall 9 can be secured to the piece 5.4 by the bolts 34.4.
• FIG. 7 is very close to that of FIG. 6, with the difference that the connecting ring 35, which replaces the fitting ring 30, does not have a transverse wall (similar to the wall 31 ).
• FIGS. 8, 9 and 11 the rearward ends 5.6R and before 12.6R of two tubular composite parts 5.6 and 12.6 (respectively forming the inner wall of the inlet d 2 and the fan casing 1 1 and respectively bearing acoustic attenuation coatings 6 and 13) are secured to one another by a connecting ring 36 without transverse wall and by bolts 32.4, 33.4 and 34.4 .
• the bolts 32.4 which secure the ring 36 of the composite part 12.6, are connected to the connecting ring 36 by plastically deformable members 37.
• Each member 37 comprises a central ring 38 intended to be crossed by a bolt 32.4 and connected to an outer ring 39 by plastically deformable spokes 40, said outer ring being adapted to be secured to the ring 36, for example in holes 41 thereof.
• the ring 36 may allow, by nature or by conformation, a plastic deformation in case of blade rupture.
• FIGS. 8, 9 and 11 comprises centering fingers 42, making it possible to precisely fix the relative position of the pieces 12.6 and 5.6 around the longitudinal axis LL. .
• Some of the bores traversed by said fasteners may be oblong to partially absorb percussion energy in case of breakage of a blade 10.
• the air intake according to the present invention has no impedance break, which improves the overall attenuation of the acoustic treatment.

Landscapes

• 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)
• Laminated Bodies (AREA)
• Supercharger (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=37771030

Family Applications (1)

Country Status (9)

Families Citing this family (14)

Family Cites Families (18)

• 2006
  • 2006-07-12 FR FR0606336A patent/FR2903733B1/fr not_active Expired - Fee Related
• 2007
  • 2007-07-04 CN CNA200780026132XA patent/CN101490391A/zh active Pending
  • 2007-07-04 WO PCT/FR2007/001133 patent/WO2008006960A2/fr not_active Ceased
  • 2007-07-04 JP JP2009518919A patent/JP4982561B2/ja not_active Expired - Fee Related
  • 2007-07-04 BR BRPI0713170-4A patent/BRPI0713170A2/pt not_active Application Discontinuation
  • 2007-07-04 US US12/307,874 patent/US8142144B2/en active Active
  • 2007-07-04 EP EP07803839A patent/EP2038533A2/fr not_active Withdrawn
  • 2007-07-04 CA CA2656206A patent/CA2656206C/fr not_active Expired - Fee Related
  • 2007-07-04 RU RU2009104706/06A patent/RU2398122C1/ru not_active IP Right Cessation

Non-Patent Citations (1)

Also Published As

Similar Documents

Legal Events