WO2014041297A1 - Procede de montage d'un panneau acoustique dans un carter d'une turbomachine et turbomachine comportant un panneau acoustique - Google Patents
Procede de montage d'un panneau acoustique dans un carter d'une turbomachine et turbomachine comportant un panneau acoustique Download PDFInfo
- Publication number
- WO2014041297A1 WO2014041297A1 PCT/FR2013/052085 FR2013052085W WO2014041297A1 WO 2014041297 A1 WO2014041297 A1 WO 2014041297A1 FR 2013052085 W FR2013052085 W FR 2013052085W WO 2014041297 A1 WO2014041297 A1 WO 2014041297A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- acoustic panel
- turbomachine
- acoustic
- tangential
- casing
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 4
- 239000006260 foam Substances 0.000 claims description 5
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000007423 decrease Effects 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 102220047090 rs6152 Human genes 0.000 description 1
- 238000013517 stratification Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
-
- 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
- F02C7/24—Heat or noise insulation
-
- 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
-
- 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
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
-
- 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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/827—Sound absorbing structures or liners
-
- 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 the field of noise reduction generated by a turbomachine and, more particularly, the attachment of an acoustic panel to the inner surface of a casing of an aircraft turbomachine.
- an aircraft turbine engine makes it possible to axially accelerate an upstream flow of air downstream in order to generate a thrust for the aircraft on which the turbomachine is mounted.
- the terms "upstream” and “downstream” are defined with respect to the flow direction of the air flow in the turbomachine.
- the terms “inside” and “outside” are defined relative to the axis of the turbomachine.
- a longitudinal cylinder has an inner surface facing its axis and an outer surface opposite to its inner surface.
- a turbomachine comprises a rotary shaft which is terminated upstream by a fan wheel so as to drive it in rotation inside a fan casing of the turbomachine.
- the fan wheel also called “fan”
- the fan wheel is conventionally rotated by a shaft of the low pressure body.
- a fan casing 1 extends longitudinally along the axis of the turbomachine and has a generally annular section.
- an acoustic panel 2 on the inner surface of the fan casing 1.
- Such a turbomachine is for example known from the application FR 1 1/59105 of the company SNECMA.
- An acoustic panel 2 conventionally comprises an outer layer composed of a honeycomb structure and an inner skin composed of a stratification of glass folds. In order to facilitate its mounting and attachment to the fan casing 1, the acoustic panel 2 does not have an annular shape but is sectored. With reference to FIG. 1, the acoustic panel 2 comprises four acoustic modules 3A, 3B, 3C, 3D which fit tangentially with each other to form a circumferential annular acoustic panel 2. For this purpose, each acoustic module 3A, 3B, 3C, 3D has at its lateral ends tangential connection means 41. In addition, each acoustic module 3A, 3B, 3C, 3D is traversed radially not fixing screws which 42 to allow its radial attachment to the fan casing 1 as shown in Figure 1.
- the tangential connection means 41 at the interfaces between the acoustic modules 3A, 3B, 3C, 3D as well as the fixing screws 42 generate noise during operation of the turbomachine which has a drawback since the turbomachine must respect of the acoustic standards increasingly severe.
- the use of fixing screws 4 increases the mass of the turbomachine which has another disadvantage.
- the invention relates to a method for mounting a cylindrical acoustic panel on the inner surface of an annular casing of an axial turbomachine, the acoustic panel comprising at least one longitudinal slot of defining two opposite ends, the method comprising the following steps:
- a step of inserting the acoustic panel into the fan casing in the close state a step of deploying the opposite ends so as to increase the cylinder radius of the acoustic panel
- a cylindrical acoustic panel whose outer diameter of cylinder corresponds to the inner diameter of the housing can be mounted in the fan.
- the acoustic panel can be mounted in the casing effortlessly and without risk of damage since the acoustic panel has a small footprint following the decrease of its cylinder radius to the close state .
- the bonding step allows to lighten the turbomachine compared to the prior art while improving the acoustic attenuation.
- the acoustic panel thus has a uniform interior surface.
- the method comprises a step of filling the slot by closure means after the deployment step.
- the longitudinal slot useful during the approaching step, can be filled so that the acoustic panel allows an acoustic attenuation homogeneous to its circumference.
- a second end of the acoustic panel comprises a tangential step and the first end of the acoustic panel extends externally to said step in the close state.
- the acoustic panel having an outer layer of honeycomb and an inner skin, the outer layers of the ends facing the acoustic panel are in contact in the close state.
- the first end extends instead of the longitudinal slot so as to reduce the perimeter of the acoustic panel and, consequently, its cylinder radius.
- the first end of the acoustic panel extends outwardly tangential walking so that the inner surface of the acoustic panel remains continue in the deployed position.
- the inner surface of an acoustic panel is important because it forms the first means of attenuation of acoustic waves emitted by the turbomachine.
- the invention further relates to an assembly of a casing of an axial turbomachine and an acoustic panel bonded to the inner surface of said casing, the acoustic panel comprising at least one longitudinal slot so as to define two opposite ends and means for plugging the longitudinal slot, wherein, a second end of the acoustic panel comprising a tangential step, the closure means are disposed radially between said step and the inner surface of the housing.
- the tangential step is formed in the inner skin.
- the tangential step consists of the inner skin.
- the acoustic panel is an annular piece which optimizes the acoustic attenuation by limiting the number of noise generating interfaces.
- the annular acoustic panel has only one longitudinal slot.
- the acoustic panel is an angular sector.
- the closure means are in the form of an expansive foam.
- FIG. 1 is a schematic cross-sectional representation of a fan casing in which is mounted an acoustic panel according to the prior art
- Figure 2 is a schematic cross-sectional representation of a fan casing in which is mounted an acoustic panel according to the invention in the close state during assembly;
- FIG. 3 is a schematic cross-sectional representation of a fan casing in which is mounted an acoustic panel according to the invention in the deployed state;
- Figure 4 is a schematic close representation of the ends of the acoustic panel, the ends being shown apart for the sake of clarity;
- Figure 5 is a schematic close representation of the ends of the acoustic panel in the close state during assembly.
- Figure 6 is a schematic close representation of the ends of the acoustic panel in the deployed state.
- the turbomachine comprises a fan casing 1 extending longitudinally along the axis of the turbomachine and has a cross section of circular shape with a predetermined inner radius R1.
- the fan casing 1 is adapted to envelop a blower wheel integral with an axial shaft of the turbomachine (not shown).
- the inner surface of the fan casing 1 is covered with a monobloc cylindrical acoustic panel 5 of annular shape and extending longitudinally with respect to the axis of the turbomachine.
- An acoustic panel 5 which is monosector advantageously makes it possible to reduce the noise generated by comparison with an acoustic panel comprising modules.
- the outer radius of the acoustic panel 5 corresponds to the inner radius of the fan casing 1. Indeed, no radial clearance thus exists between the fan casing 1 and the acoustic panel 5 when the latter is deployed as shown in Figure 3.
- the acoustic panel 5 has an outer layer 6 honeycomb and an inner skin 7 formed, in this example, laminating folds, preferably glass or carbon.
- the constitution of such an acoustic panel 5 is known to those skilled in the art and will not be detailed further.
- the outer layer 6 has a radial thickness of the order of 35 mm while the inner skin has a radial thickness of the order of 1 to 2 mm.
- the acoustic panel 5 comprises at least one longitudinal slot 8 so as to define two facing ends 5A, 5B as shown in Figures 2 to 6.
- the acoustic panel 5 has a single longitudinal slot 8 to maintain optimum efficiency.
- the second end 5B of the acoustic panel 5 comprises a tangential step 10 which extends perpendicularly to an axial plane passing through the second end 5B.
- the tangential step 10 extends in continuity with the inner skin 7 of the second end 5B.
- walking tangential 10 is made of the inner skin 7 and has the same radial thickness as the latter.
- the tangential step 10 is projecting tangentially over a length of 10 mm and has a radial thickness of the order of 1 to 2 mm.
- the tangential step 10 extends in this example over the entire length of the longitudinal slot 8.
- acoustic panel 5 with its tangential step 10
- cuts are made on a one-piece circumferential acoustic panel.
- a first cut along an axial plane is formed so as to form the longitudinal slot 8.
- the two ends 5A, 5B of the acoustic panel 5 are planar.
- a second cut is made so as to remove a portion L of the outer layer 6 of the second end 5B without affecting the inner skin 7.
- the inner skin 7 remains in position.
- a portion L of the order of 10 mm is removed from the outer layer 6 of the second end 5B of the acoustic panel 5.
- the length of the portion L is made so as to remove an integer of The cells of the outer layer 6 of the acoustic panel 5.
- a portion L corresponding to the length of two cells of the outer layer 6 have been removed. Following the cuts, the outer layers 6 of the ends 5A, 5B are separated by the longitudinal slot 8.
- Such a method of manufacturing an acoustic panel 5 is simple to implement and guarantees continuity of the inner skin 7 when it is mounted in the fan casing 1. Indeed, the acoustic panel 5 is obtained from a one-piece circumferential panel perfectly adapted to the dimensions of the fan casing 1, no part of the inner skin 7 having been removed.
- the method comprises a step of approaching the facing ends 5A, 5B so as to reduce the cylinder radius of the acoustic panel 5.
- the first end 5A of the acoustic panel 5 extends externally to the tangential step 10, preferably, the outer layers 6 of the ends 5A, 5B are in contact to minimize the transverse bulk of the acoustic panel 5.
- the inner skin 7 of the first end 5A is superimposed radially with the inner skin 7 of the second end 5B.
- the radius R1 of the acoustic panel 5 in the deployed state decreases from an AR value to a radius value RO close state.
- the AR value is the mounting set. To set the value of the mounting set AR, it is sufficient to adjust the length L of the portion of the outer layer 6 to be removed at the second end 5B. Indeed, the mounting set AR depends on the length L by the following relation:
- the acoustic panel 5 is introduced into the fan casing 1 without coming into contact with the inner surface of the fan casing 1 as illustrated in FIG. 2.
- the method comprises a step of deploying the facing ends 5A, 5B so as to increase the cylinder radius of the acoustic panel 5 so that its outer surface matches the inner surface of the fan casing 1.
- the inner skin 7 of the first end 5A is aligned with the inner skin 7 of the second end 5B, the cylinder radius of the acoustic panel 5 then being equal to R1.
- the inner skins 7 are at the same radial distance from the axis of the turbomachine to form an acoustic panel 5 whose inner surface is annular and continuous.
- the method further comprises a step of fixing the acoustic panel 5 to the fan casing 1 by gluing.
- Glue may be applied to the inner surface of the fan casing 1 and / or the outer surface of the acoustic panel 5.
- the application of glue may be carried out before or after the insertion of the acoustic panel 5 into the fan case 1. Thanks to the bonding, there is no fastening means capable of vibrating during operation of the turbomachine to generate noise.
- the method comprises a step of filling the slot 8 by closure means 9 after the deployment step.
- the closure means 9 are in the form of an expansive foam but it goes without saying that other means could be suitable.
- the filling step is performed during the bonding step.
- the expansive foam is arranged radially between the tangential step 1 0 and the inner surface of the fan casing 1 so as to fill the portion L of the outer layer 6 that has been removed during of the second cut.
- the expansive foam is located between the outer layers 6 of the ends 5A, 5B of the acoustic panel 5.
- the length of the portion L of the outer layer 6 to form the longitudinal slot 8 results from a compromise between, on the one hand, an acoustic efficiency requiring a reduced length for the longitudinal slot 8 and, on the other hand, an easy
- the invention has been presented for a one-piece circumferential cylindrical acoustic panel, but the invention also applies to an acoustic panel comprising a plurality of acoustic modules connected together, each acoustic module forming an angular cylindrical sector. acoustic panel.
- Each angular sector has a small footprint which facilitates its mounting in the casing of the turbomachine.
- Each angular sector comprises connecting means so as to allow its cooperation with an adjacent angular sector.
- the invention has been presented for a fan casing, but the invention also applies to any turbomachine casing, for example, an exhaust casing.
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- 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 (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/426,936 US9657644B2 (en) | 2012-09-12 | 2013-09-11 | Method for mounting an acoustic panel in a housing of a turbomachine and turbomachine comprising an acoustic panel |
GB1504014.0A GB2519915B (en) | 2012-09-12 | 2013-09-11 | Method for mounting an acoustic panel in a housing of a turbomachine and turbomachine comprising an acoustic panel |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1258548A FR2995360B1 (fr) | 2012-09-12 | 2012-09-12 | Procede de montage d'un panneau acoustique dans un carter d'une turbomachine et turbomachine comportant un panneau acoustique |
FR1258548 | 2012-09-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014041297A1 true WO2014041297A1 (fr) | 2014-03-20 |
Family
ID=47178148
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2013/052085 WO2014041297A1 (fr) | 2012-09-12 | 2013-09-11 | Procede de montage d'un panneau acoustique dans un carter d'une turbomachine et turbomachine comportant un panneau acoustique |
Country Status (4)
Country | Link |
---|---|
US (1) | US9657644B2 (fr) |
FR (1) | FR2995360B1 (fr) |
GB (1) | GB2519915B (fr) |
WO (1) | WO2014041297A1 (fr) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB201406277D0 (en) | 2014-04-08 | 2014-05-21 | Rolls Royce Deutschland | A gas turbine inlet |
DE102018107096A1 (de) * | 2018-03-26 | 2019-09-26 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinentriebwerk und Paneel für ein Gasturbinentriebwerk |
CN112912610B (zh) * | 2018-09-20 | 2024-05-17 | 赛峰飞机发动机公司 | 涡轮机或短舱上的声学管理 |
FR3108680B1 (fr) * | 2020-03-30 | 2022-02-18 | Safran Aircraft Engines | Fixation d’une virole acoustique a une enveloppe de carter pour une turbomachine d’aeronef |
US11887571B2 (en) | 2020-09-11 | 2024-01-30 | Rtx Corporation | Acoustic attenuation structures |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1159105A (fr) | 1955-08-12 | 1958-06-23 | English Electric Valve Co Ltd | Tube amplificateur à ondes progressives |
GB2273131A (en) * | 1992-12-04 | 1994-06-08 | Grumman Aerospace Corp | Engine inlet acoustic barrel |
WO2010007263A1 (fr) * | 2008-06-25 | 2010-01-21 | Aircelle | Panneau acoustique pour une tuyère d'éjection |
GB2468484A (en) * | 2009-03-09 | 2010-09-15 | Aircelle Ltd | An acoustic attenuation member for an aircraft |
WO2011027072A1 (fr) * | 2009-09-04 | 2011-03-10 | Aircelle | Ensemble structurant pour une tuyère d'éjection |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5594216A (en) * | 1994-11-29 | 1997-01-14 | Lockheed Missiles & Space Co., Inc. | Jet engine sound-insulation structure |
US20010048048A1 (en) * | 1999-01-13 | 2001-12-06 | Brian L Riedel | Backside fitting attachment for nacelle acoustic panels |
US6439340B1 (en) * | 2000-11-17 | 2002-08-27 | Astech Manufacturing, Inc. | Acoustically treated structurally reinforced sound absorbing panel |
FR2840647B1 (fr) * | 2002-06-05 | 2004-10-29 | Airbus France | Dispositif pour le raccordement de deux pieces tubulaires de turboreacteur d'aeronef |
-
2012
- 2012-09-12 FR FR1258548A patent/FR2995360B1/fr active Active
-
2013
- 2013-09-11 WO PCT/FR2013/052085 patent/WO2014041297A1/fr active Application Filing
- 2013-09-11 GB GB1504014.0A patent/GB2519915B/en active Active
- 2013-09-11 US US14/426,936 patent/US9657644B2/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1159105A (fr) | 1955-08-12 | 1958-06-23 | English Electric Valve Co Ltd | Tube amplificateur à ondes progressives |
GB2273131A (en) * | 1992-12-04 | 1994-06-08 | Grumman Aerospace Corp | Engine inlet acoustic barrel |
WO2010007263A1 (fr) * | 2008-06-25 | 2010-01-21 | Aircelle | Panneau acoustique pour une tuyère d'éjection |
GB2468484A (en) * | 2009-03-09 | 2010-09-15 | Aircelle Ltd | An acoustic attenuation member for an aircraft |
WO2011027072A1 (fr) * | 2009-09-04 | 2011-03-10 | Aircelle | Ensemble structurant pour une tuyère d'éjection |
Also Published As
Publication number | Publication date |
---|---|
GB201504014D0 (en) | 2015-04-22 |
FR2995360B1 (fr) | 2018-06-15 |
US20150285151A1 (en) | 2015-10-08 |
US9657644B2 (en) | 2017-05-23 |
GB2519915A (en) | 2015-05-06 |
FR2995360A1 (fr) | 2014-03-14 |
GB2519915B (en) | 2018-06-06 |
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