WO2014068261A1 - Carter de turbomachine - Google Patents
Carter de turbomachine Download PDFInfo
- Publication number
- WO2014068261A1 WO2014068261A1 PCT/FR2013/052624 FR2013052624W WO2014068261A1 WO 2014068261 A1 WO2014068261 A1 WO 2014068261A1 FR 2013052624 W FR2013052624 W FR 2013052624W WO 2014068261 A1 WO2014068261 A1 WO 2014068261A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- wall
- panel
- tabs
- housing
- members
- Prior art date
Links
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 230000007547 defect Effects 0.000 claims description 2
- 238000003466 welding Methods 0.000 claims description 2
- 238000009413 insulation Methods 0.000 abstract description 13
- 238000011144 upstream manufacturing Methods 0.000 description 8
- 238000012423 maintenance Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000000295 complement effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
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
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F01D25/04—Antivibration arrangements
-
- 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
- B64D29/06—Attaching of 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
- F01D25/243—Flange connections; Bolting arrangements
-
- 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
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
- F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
-
- 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
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
-
- 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
-
- 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 a turbomachine casing, in particular a turbomachine such as a turbojet or an airplane turboprop.
- a fan casing typically comprises a substantially cylindrical wall which extends around the fan blades of the turbomachine and whose inner surface is covered with acoustic insulation panels.
- These panels generally comprise an annular honeycomb structure whose inner and outer faces are each covered with a skin which can be multi-perforated to improve the acoustic treatment. They are intended to absorb the sound waves generated by the fan of the turbomachine.
- EP-A1 -2,318,679, EP-A1-2,088,290 and FR-A1-2,965,859 describe acoustic insulation panels of this type.
- An acoustic insulation panel of a turbomachine is generally sectored, that is to say formed of several panel sectors arranged circumferentially end to end and secured to the housing wall by gluing or by fixing screws which are extend radially with respect to the longitudinal axis of the turbomachine.
- Fastening the sectors by screwing has drawbacks because it requires the use of many fastening screws which, on the one hand, increase the mass of the turbomachine and are likely to damage the blades of the fan in case of loss or breakage .
- a housing wall may have deformations and have an internal surface that is not perfectly cylindrical. This is particularly the case of a crankcase composite material which, because of its method of manufacture, may have relatively large manufacturing tolerances.
- the acoustic panels which are fixed on a housing wall of this type do not make it possible to compensate for the aforementioned tolerances.
- thermosetting glue This is particularly the case of acoustic insulation panels which are glued to the housing wall by means of a thermosetting glue. This bonding is long to implement (several hours in a large autoclave) and, in case of damage to the panel, it is necessary to remove the engine to replace the panel.
- the present invention overcomes at least some of the aforementioned drawbacks simply, efficiently and economically.
- turbomachine casing having a longitudinal axis and having a substantially cylindrical wall and an annular acoustic insulation monobloc panel mounted inside the wall, about said longitudinal axis, the panel having a radially annular surface.
- the wall comprises on its inner annular surface first projecting members which bear parallel to said longitudinal axis on second members projecting from the outer annular surface. of the panel and which are attached to these second members in a removable manner.
- the present invention therefore proposes a new system for attaching a monobloc acoustic insulation panel to a casing wall.
- the panel is formed of a single annular piece (called OPB, acronym for One Piece Barriel), there is no acoustic impedance discontinuity on its entire surface.
- the panel fixing means do not significantly increase the casing and do not cross the entire radial dimension of the panel. They do not create acoustic insulation discontinuities.
- the invention facilitates assembly and allows the disassembly of the panel, in particular under the wing of an aircraft equipped with the turbomachine (that is to say without removing the motor), and furthermore optimizes the vein tolerances by allowing any cracks in the crankcase wall (+/- 2mm up to +/- 0.4 mm) to be taken up in a particular case of realization of the invention).
- the one-piece panel may comprise an annular honeycomb structure whose inner and outer faces are covered with a skin, the inner skin being preferentially multi-perforated.
- the first members may be attached to the second members by means of the screw-nut type.
- These means of the screw-nut type advantageously extend parallel to the longitudinal axis of the housing.
- the mounting tool and disassembly of the panel then comprises a screwing / unscrewing tool which is intended to be inserted axially between the housing wall and the panel.
- the first and second members comprise fixing lugs. These tabs may be integrally formed with the wall and the panel, respectively, or may be attached to the wall and the panel, respectively, for example by gluing, welding, screwing or riveting.
- the wall and the panel may each comprise at least one annular row of legs regularly distributed around the longitudinal axis of the housing. For example, they can each understand two annular rows of legs, the legs of the first row being preferably angularly offset legs of the second row to facilitate their attachment. Each row comprises for example twelve legs.
- At least a portion of the tabs may have a substantially L-shaped shape.
- These tabs may comprise a substantially planar or cylindrical part intended to be fixed or integral with one of the elements of the wall and the panel, and a substantially radial portion comprising a orifice intended to be traversed by a fixing means.
- the legs of the wall may be at least partially housed in recesses of the inner annular surface of the wall, and / or the tabs of the panel may be at least partly housed in recesses in the outer annular surface of the panel.
- the tabs each comprise a radial bearing surface on another tab and a planar or substantially cylindrical centering surface intended to cooperate with said other tab.
- the flat or cylindrical surfaces of the lugs of the wall are preferably machinable to correct a possible defect of cylindricity of the inner annular surface of the wall.
- the panel In the mounting position, the panel may be separated from the wall by an annular space, which for example has a thickness or radial dimension of about 10 mm.
- the present invention also relates to a turbomachine, such as a turbojet engine or a turboprop engine, characterized in that it comprises a casing as described above.
- FIG. 1 is a schematic half-view in axial section of a fan casing of a turbomachine according to the invention
- FIG. 2 is a front view from the upstream of the casing of Figure 1 (axial arrow II of Figure 1);
- - Figure 3 is a partial schematic half-view of an acoustic insulation panel in axial section (longitudinal axis of the housing thus);
- 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 line V-V of Figure 4 (section perpendicular to the longitudinal axis of the housing);
- FIG. 6 is a schematic view corresponding to Figure 5 and showing an alternative embodiment of the invention.
- FIG. 7 is a schematic view corresponding to Figure 4 and showing another embodiment of the invention.
- FIG. 1 showing a fan casing 10 of a turbomachine, such as a turbojet engine or an airplane turboprop, this casing forming part of a nacelle which surrounds the engine of the turbomachine and inside 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 according to the invention, respectively upstream and median, and a downstream panel 22 which is sectorized according to the prior art.
- 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.
- annular panels 18, 20 annular monoblocs that is to say, not sectored
- the invention overcomes these disadvantages by means of annular panels 18, 20 annular monoblocs (that is to say, not sectored) which are fixed on the wall 12 by a new technology that allows the disassembly of the panels, particularly under the wing of an airplane during a maintenance operation.
- 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. (Axis 70 Figure 4) and radial on tabs 28 of the wall 12, these tabs having holes for passing means 32 of the screw-nut type.
- FIG. 3 represents an exemplary embodiment of a panel 18, 20 according to the invention, this panel comprising 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, particularly in the area 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 (see Figure 1).
- 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 may have a thickness or radial dimension of the order of 10mm.
- In 100 is located the longitudinal axis of the casing which is also that of the cylindrical wall 12 and the panel 18, 20.
- the panel 18,20 extends around the longitudinal axis 100.
- 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 outwardly and which comprises a through-hole for the passage of the screw 32 (axis 70).
- 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 tabs 28 carried by the wall 12 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 inward and which comprises a through hole aligned with the orifice of the lug 26 for the passage of the screw 32 for fixing these lugs.
- This portion 54 comprises a radial axial support surface 56 (axis 70 parallel to the axis 100 of the housing) on the radial surface 48 of the lug 26 and a plane or substantially cylindrical bearing surface 58 on the cylindrical surface 46 of the paw 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 these 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 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.
- FIG. 7 represents an alternative embodiment of the invention which differs from the embodiment previously described in that the tabs 126, 128 are here formed by folded sheets in L.
- the tab 126 carried by the panel 1 18, 120 comprises a longitudinal portion fixed on the outer skin of the panel and a radial portion in axial support (axis 170 parallel to that 100 of the housing) on a radial portion of the other leg 128, a longitudinal portion is fixed on the inner surface of the wall of casing 1 12.
- the radial portions of the tabs 126, 128 each comprise an orifice.
- the orifice of the lug 128 receives a crimped nut 133.
- a screw 132 is engaged axially (axis 170) in the orifice of the lug 126 and is then screwed into the nut 133 carried by the lug 128 to fix the lugs together. .
- This operation is performed for each pair of legs 126, 128 so as to secure the panel 1 18, 120 to the wall January 12.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/440,388 US9863270B2 (en) | 2012-11-05 | 2013-11-04 | Turbomachine casing |
CN201380057717.3A CN104769233B (zh) | 2012-11-05 | 2013-11-04 | 涡轮机壳体 |
GB1507129.3A GB2521575B (en) | 2012-11-05 | 2013-11-04 | Turbomachine casing |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1260495A FR2997726B1 (fr) | 2012-11-05 | 2012-11-05 | Carter de turbomachine |
FR1260495 | 2012-11-05 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014068261A1 true WO2014068261A1 (fr) | 2014-05-08 |
Family
ID=47598948
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2013/052624 WO2014068261A1 (fr) | 2012-11-05 | 2013-11-04 | Carter de turbomachine |
Country Status (5)
Country | Link |
---|---|
US (1) | US9863270B2 (fr) |
CN (1) | CN104769233B (fr) |
FR (1) | FR2997726B1 (fr) |
GB (1) | GB2521575B (fr) |
WO (1) | WO2014068261A1 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2016146924A1 (fr) * | 2015-03-16 | 2016-09-22 | Snecma | Ensemble pour turbomachine d'aéronef comprenant un carter de soufflante équipé d'un revêtement acoustique intégrant un raidisseur de carter de soufflante |
FR3059362A1 (fr) * | 2016-11-30 | 2018-06-01 | Safran Aircraft Engines | Carter de turbomachine comportant une structure acoustique et un element abradable |
FR3100561A1 (fr) * | 2019-09-10 | 2021-03-12 | Safran Aircraft Engines | Fixation d’une virole acoustique a une enveloppe de carter pour une turbomachine d’aeronef |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
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FR3005100B1 (fr) * | 2013-04-26 | 2015-05-01 | Snecma | Carter de turbomachine |
US10267191B2 (en) * | 2015-08-07 | 2019-04-23 | Pratt & Whitney Canada Corp. | Turboprop engine assembly with combined engine and cooling exhaust |
US10240522B2 (en) | 2015-08-07 | 2019-03-26 | Pratt & Whitney Canada Corp. | Auxiliary power unit with combined cooling of generator |
US10253726B2 (en) | 2015-08-07 | 2019-04-09 | Pratt & Whitney Canada Corp. | Engine assembly with combined engine and cooling exhaust |
FR3051828B1 (fr) * | 2016-05-24 | 2018-05-11 | Safran Aircraft Engines | Procede de fabrication d'un carter a revetement abradable de turbomachine |
US11060551B1 (en) * | 2017-10-31 | 2021-07-13 | Lockheed Martin Corporation | Snap alignment guard for nut plate ring |
US11015636B2 (en) * | 2018-07-03 | 2021-05-25 | Raytheon Technologies Corporation | Nut strip assembly with array of captured nuts |
FR3092136B1 (fr) | 2019-01-29 | 2021-10-22 | Safran Aircraft Engines | Carter de soufflante pour une turbomachine d’aeronef |
FR3095420B1 (fr) * | 2019-04-26 | 2023-04-21 | Safran Nacelles | Entrée d’air de nacelle et nacelle comportant une telle entrée d’air |
FR3098543B1 (fr) | 2019-07-10 | 2021-07-02 | Safran Aircraft Engines | Procede de fabrication d’un carter pour une turbomachine d’aeronef |
EP3999722B1 (fr) | 2019-07-15 | 2024-02-21 | Safran Aircraft Engines | Procede de fabrication d'un carter pour une turbomachine d'aeronef |
FR3100834B1 (fr) | 2019-09-12 | 2023-07-07 | Safran Aircraft Engines | Virole annulaire acoustique de turbomachine et procede de fabrication associe |
FR3106610B1 (fr) | 2020-01-29 | 2023-04-14 | Safran Aircraft Engines | Carter de turbomachine d’aeronef et son procede de fabrication |
FR3106612B1 (fr) | 2020-01-29 | 2022-07-22 | Safran Aircraft Engines | Carter de turbomachine d’aeronef et son procede de fabrication |
FR3106611B1 (fr) | 2020-01-29 | 2023-02-24 | Safran Aircraft Engines | Carter de turbomachine d’aeronef et son procede de fabrication |
FR3127014A1 (fr) | 2021-09-15 | 2023-03-17 | Safran Aircraft Engines | Procede de fabrication d’un carter pour une turbomachine d’aeronef |
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FR2926791A1 (fr) * | 2008-01-29 | 2009-07-31 | Aircelle Sa | Entree d'air pour nacelle d'aeronef, et ensemble propulsif comprenant une telle entree d'air |
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FR2898870B1 (fr) * | 2006-03-24 | 2008-05-23 | Aircelle Sa | Structure de virole d'entree d'air |
GB2478312B (en) * | 2010-03-02 | 2012-08-22 | Gkn Aerospace Services Ltd | Seamless acoustic liner |
FR2961788B1 (fr) * | 2010-06-29 | 2012-06-15 | Aircelle Sa | Nacelle de turboreacteur |
US9169728B2 (en) * | 2011-12-08 | 2015-10-27 | General Electric Company | Dynamic load reduction system |
FR3005100B1 (fr) | 2013-04-26 | 2015-05-01 | Snecma | Carter de turbomachine |
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- 2013-11-04 GB GB1507129.3A patent/GB2521575B/en active Active
- 2013-11-04 US US14/440,388 patent/US9863270B2/en active Active
- 2013-11-04 WO PCT/FR2013/052624 patent/WO2014068261A1/fr active Application Filing
- 2013-11-04 CN CN201380057717.3A patent/CN104769233B/zh active Active
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EP0898063A1 (fr) * | 1997-08-19 | 1999-02-24 | AEROSPATIALE Société Nationale Industrielle | Ensemble réducteur de bruit pour turboréacteur d'aéronef |
EP1083300A2 (fr) * | 1999-09-07 | 2001-03-14 | General Electric Company | Carter de soufflante avec structure de rétention à double paroi |
GB2361747A (en) * | 2000-04-28 | 2001-10-31 | Gen Electric | Fan casing with radially movable liner |
EP1591643A1 (fr) * | 2004-04-27 | 2005-11-02 | Airbus France | Ensemble réducteur de bruit pour turboréacteur d'aéronef |
FR2926791A1 (fr) * | 2008-01-29 | 2009-07-31 | Aircelle Sa | Entree d'air pour nacelle d'aeronef, et ensemble propulsif comprenant une telle entree d'air |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2016146924A1 (fr) * | 2015-03-16 | 2016-09-22 | Snecma | Ensemble pour turbomachine d'aéronef comprenant un carter de soufflante équipé d'un revêtement acoustique intégrant un raidisseur de carter de soufflante |
FR3033839A1 (fr) * | 2015-03-16 | 2016-09-23 | Snecma | Ensemble pour turbomachine d'aeronef comprenant un carter de soufflante equipe d'un revetement acoustique integrant un raidisseur de carter de soufflante |
US10233837B2 (en) | 2015-03-16 | 2019-03-19 | Snecma | Assembly for an aircraft turbine engine comprising a fan casing equipped with an acoustic liner incorporating a fan casing stiffener |
FR3059362A1 (fr) * | 2016-11-30 | 2018-06-01 | Safran Aircraft Engines | Carter de turbomachine comportant une structure acoustique et un element abradable |
US10584606B2 (en) | 2016-11-30 | 2020-03-10 | Safran Aircraft Engines | Turbomachine case comprising an acoustic structure and an abradable element |
FR3100561A1 (fr) * | 2019-09-10 | 2021-03-12 | Safran Aircraft Engines | Fixation d’une virole acoustique a une enveloppe de carter pour une turbomachine d’aeronef |
WO2021048473A1 (fr) * | 2019-09-10 | 2021-03-18 | Safran Aircraft Engines | Fixation d'une virole acoustique a une enveloppé de carter pour une turbomachine d'aéronef |
US11905839B2 (en) | 2019-09-10 | 2024-02-20 | Safran Aircraft Engines | Attachment of an acoustic shroud to a housing shell for an aircraft turbine engine |
Also Published As
Publication number | Publication date |
---|---|
FR2997726A1 (fr) | 2014-05-09 |
US9863270B2 (en) | 2018-01-09 |
GB201507129D0 (en) | 2015-06-10 |
GB2521575A (en) | 2015-06-24 |
CN104769233B (zh) | 2017-04-05 |
FR2997726B1 (fr) | 2018-03-02 |
US20150267555A1 (en) | 2015-09-24 |
GB2521575B (en) | 2016-06-29 |
CN104769233A (zh) | 2015-07-08 |
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