EP1510657A1 - Abreibbare Vorrichtung für das Bläsergehäuse einer Gasturbine - Google Patents
Abreibbare Vorrichtung für das Bläsergehäuse einer Gasturbine Download PDFInfo
- Publication number
- EP1510657A1 EP1510657A1 EP04292043A EP04292043A EP1510657A1 EP 1510657 A1 EP1510657 A1 EP 1510657A1 EP 04292043 A EP04292043 A EP 04292043A EP 04292043 A EP04292043 A EP 04292043A EP 1510657 A1 EP1510657 A1 EP 1510657A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- layer
- blades
- blower
- fan
- abradable
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 239000006260 foam Substances 0.000 claims abstract description 41
- 239000000126 substance Substances 0.000 claims abstract description 36
- 239000012634 fragment Substances 0.000 claims abstract description 4
- 239000011521 glass Substances 0.000 claims description 8
- 239000011324 bead Substances 0.000 claims description 6
- 150000003949 imides Chemical class 0.000 claims description 4
- 229920001296 polysiloxane Polymers 0.000 claims description 4
- 239000003822 epoxy resin Substances 0.000 claims description 3
- 229920000647 polyepoxide Polymers 0.000 claims description 3
- 239000010410 layer Substances 0.000 description 43
- 210000003462 vein Anatomy 0.000 description 7
- 241000195940 Bryophyta Species 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 235000011929 mousse Nutrition 0.000 description 5
- 241000264877 Hippospongia communis Species 0.000 description 4
- 238000007664 blowing Methods 0.000 description 3
- 230000008439 repair process Effects 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 229920000784 Nomex Polymers 0.000 description 2
- 241001639412 Verres Species 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000000295 complement effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 235000021183 entrée Nutrition 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 239000004763 nomex Substances 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 241001080024 Telles Species 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000002313 adhesive film Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
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
- 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
- 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
Definitions
- the invention relates to the field of gas turbine engines, and more particularly engine fan casings gas turbine.
- a blower disc is on the rotor part at the engine inlet and precedes the blower discs of the compressor.
- This blisk blower can accelerate the air before entering the stages of the compressor.
- This bladed blower disc is likely to receive foreign objects such as ice cubes, birds or others.
- this blisk is susceptible to deform, to cause an unbalance on the tree of support of the blower and cyclic loads and vibrations communicated by the shaft support bearings blower to the fixed parts of the turbomachine, to which these support bearings are connected.
- the present invention improves the situation.
- the invention relates to a rotational axis turbomachine comprising a fan casing and a paddle blower movable, a game extending between the inner surface of the housing and the free ends of the blades, a bearing of the fan being connected to fixed parts of the turbomachine by connections such as in case of load on the blades of the blowing, these bonds break and the axis of rotation of the blower oscillates around the axis of rotation of the turbomachine.
- the housing includes, glued on its inner surface and on at least one part of the playing area, a layer of thermoformable foam placed opposite the ends of the blades of the blowing, the thermoformable foam layer being partially covered with a layer of abradable substance, the thickness of the layer of abradable substance being such that the free ends of the blades of the fan do not reach the foam layer during operation normal turbomachine, and in case of load on the blowing, the free ends of the blades fragment at least partially all the layers of abradable and thermoformable foam.
- FIG. 1 represents a turbomachine section T according to its rotation axis.
- This cut includes a blower V to accelerate the air before entering the floors a compressor C, then a high-pressure compressor CC.
- the blower V comprises a disk provided with blades 17 connected by screwing at the front end BA of an AV blower shaft mounted on a PAV front bearing and a PAR rear bearing as detailed in the application FR 2 752 024.
- the bearings before and backing are supported by support pieces connected to a fixed part of the turbomachine (stator), at least one of the bearings being connected by sufficiently fragile links to break when an excessive load on a dawn of the blower. Such a bearing is called "fuse bearing".
- These weak links may be screw connections whose section is reduced over part of the length of the screw for example.
- FIG. part of a turbomachine T comprising a fan V followed of a compressor C.
- This part of a turbomachine comprises a housing 10 forming the stator portion S of the fan V and a housing forming the rotor part R of the turbomachine.
- the tree of the rotor part of the turbomachine is driven by rotation by a turbine located downstream of the compressor.
- the axis rotation is noted B.
- the outer surface of the housing of the rotor part and the inner surface of the part housing stator delimit a "flow vein" for the flow air.
- On the rotor R is fixed the blisk 18 of the blower V comprising vanes 17.
- the bladed disc of blower is located at the engine inlet and precedes the bladed discs of the compressor.
- the tree of the blower is supposed to be supported by at least one PAV front bearing forming a fuse bearing.
- PAV front bearing forming a fuse bearing.
- the blades of the fan against the housing 10 he been developed 3 panels glued inside this fan casing 10, these panels being composed of a honeycomb structure nomex filled with abradable material, glued to a glass cloth, itself glued to a nest aluminum bee, the whole being glued to the housing of blower.
- the thickness of these panels makes it possible to conserve the flow vein so that in normal operation, the end of the blades of the blower disc does not enter in contact with these panels.
- the invention overcomes these disadvantages.
- Figure 2B illustrates a portion of turbomachine T comprising the fan V followed by the compressor C.
- the blisk 18 of the blower V comprising vanes 17.
- FIG 3 showing in detail the housing 10 positioned opposite the ends of the blades of the discs 18.
- the housing 10 has a general shape of a truncated cone whose axis of symmetry coincides with the axis of rotation B of the turbomachine.
- the casing 10 of the blower V comprises a first part of truncated cone 20 connected to a ring of diametral step 21 itself connected to a second part of the truncated cone 22.
- the inner surface of the first part of the truncated cone 20 delimits the flow vein of the air.
- the ends of the vanes are placed opposite the inner surface of the second part of the truncated cone 22 and are separated from this inner surface by a space internal ring 15. This is a game e, for example 20 mm between the inner surface of the fan case and the free ends of the blades.
- the layer of foam thermoformable 19 has a shape complementary to that of the inner annular space so as to fill the latter.
- the foam layer has an axial width lg corresponding at least to the axial width lc along the axis B of the free end of the blades 17 of the fan V.
- thermoformable foam layer 19 is covered with a layer of abradable substance 14, on at least the width axial lc of the ends of the blades. The thickness of the layer of abradable substance is such that the free ends fan blades do not reach the foam during normal operation of the engine.
- the layer of thermoformable foam covered with abradable substance completely fills the annulus internally and is machined so that there is no discontinuity with the inner surface of the first part of cone, the flow vein being thus preserved.
- the thickness of the substance layer abradable is such that there is a game between the ends free of the blades of the blower and the layer of substance abradable during normal engine operation, this game being small enough to limit the passage of air in order to maintain a dynamic flow of air whose trajectory is forced by the blades of the fan.
- panels acoustics 13 In downstream of this layer can be positioned panels acoustics 13 so as to preserve the continuity of the flow vein.
- the width lg is greater than the width lc and the inner annular space 15 is delimited by an upstream stop.
- crankcase blower may consist of a single piece (frustoconical, cylindrical or other) with symmetry of revolution covered on its inner surface with a protective screen consisting of a layer of thermoformable foam, itself partially covered with an abradable substance.
- a protective screen consisting of a layer of thermoformable foam, itself partially covered with an abradable substance.
- abradable layers are placed opposite the ends of the blades.
- fan housing has a clearance between its inner surface and the free ends of the blades so as to stick a certain layer thickness on the inner surface of the casing, for example of the order of 20 mm.
- the vein flow is retained by the establishment, upstream and downstream downstream of the protective layers, acoustic panels by example.
- Crankcase protection in case of breakage of the connection brittle fuse bearing, is made by the screen consisting of thermo-formable foam and the abradable substance.
- the bearings of the fan shaft are no longer connected to the fixed parts of the turbomachine and the axis of rotation of the fan oscillates around the axis of rotation B of the turbomachine.
- the ends of the blades come to dig the screen by fragmentation of matter.
- the presence of the thermoformable foam layer offers resistance to the removal of less material than the layer of abradable substance, allowing spraying of all the layers of abradable "big game" in case of rupture of the fuses of the bearing.
- thermoformable it consists of preformed sectors.
- the thermoformable foam layer is a layer of polyacrylic imide foam.
- the layer of abradable substance can be epoxy resin filled with glass beads, silicone loaded with glass beads or any other material having the abrasion properties of an abradable substance.
- the layer of abradable substance adheres to the thermoformable foam layer by its properties adhesive and diffusion in the cells of the foam thermoformable.
- thermoformable foam allows simple shaping, machining can be done before formatting, by example for a conical part of a fan casing, evolutionary profile.
- the repair of abradable layers "big game” can be done without equipment requiring a workshop specific, which saves time and money.
- the invention is not limited to the embodiments of fixing device described above, only as a example, but it encompasses all the variants that consider the skilled person in the context of the claims below.
- the invention does not apply only to the shaped casing frustoconical but may apply in the case of all other forms of housing, for example cylindrical.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0309989 | 2003-08-18 | ||
FR0309989A FR2859002A1 (fr) | 2003-08-18 | 2003-08-18 | Dispositif abradable sur carter de soufflante d'un moteur de turbine a gaz |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1510657A1 true EP1510657A1 (de) | 2005-03-02 |
Family
ID=34089846
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04292043A Withdrawn EP1510657A1 (de) | 2003-08-18 | 2004-08-12 | Abreibbare Vorrichtung für das Bläsergehäuse einer Gasturbine |
Country Status (7)
Country | Link |
---|---|
US (1) | US20050089390A1 (de) |
EP (1) | EP1510657A1 (de) |
JP (1) | JP2005061419A (de) |
CN (1) | CN1590712A (de) |
CA (1) | CA2478788A1 (de) |
FR (1) | FR2859002A1 (de) |
RU (1) | RU2282039C2 (de) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2116695A2 (de) * | 2008-05-06 | 2009-11-11 | Rolls-Royce plc | Schutzplatte für das Bläsergehäuse einer Gasturbine |
WO2013007937A2 (fr) | 2011-07-13 | 2013-01-17 | Snecma | Procede de fabrication d'un carter de soufflante de turbomachine muni de revetement acoustique. |
EP2623724A1 (de) * | 2012-02-06 | 2013-08-07 | United Technologies Corporation | Konforme Auskleidung für Gebläseabschnitt eines Gasturbinenmotors |
CN104141631A (zh) * | 2013-05-10 | 2014-11-12 | 航空技术空间股份有限公司 | 具有可磨损材料的涡轮机定子内壳体 |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2426287B (en) * | 2005-05-18 | 2007-05-30 | Rolls Royce Plc | Blade containment structure |
US20080063508A1 (en) * | 2006-09-08 | 2008-03-13 | Barry Barnett | Fan case abradable |
FR2918120B1 (fr) * | 2007-06-28 | 2009-10-02 | Snecma Sa | Turbomachine a double soufflante |
GB2483060B (en) * | 2010-08-23 | 2013-05-15 | Rolls Royce Plc | A turbomachine casing assembly |
FR2997444B1 (fr) * | 2012-10-31 | 2018-07-13 | Snecma | Moyeu de carter pour une turbomachine |
DE102013212252A1 (de) * | 2013-06-26 | 2014-12-31 | Siemens Aktiengesellschaft | Turbine und Verfahren zur Anstreiferkennung |
GB201313594D0 (en) | 2013-07-30 | 2013-09-11 | Composite Technology & Applic Ltd | Fan Track Liner |
CN103615321B (zh) * | 2013-11-28 | 2015-12-30 | 沈阳黎明航空发动机(集团)有限责任公司 | 一种防止异物进入发动机机匣封闭腔的方法 |
AT516322B1 (de) * | 2014-10-10 | 2017-04-15 | Facc Ag | Fangehäuse für ein Flugzeugtriebwerk |
US10213883B2 (en) * | 2016-02-22 | 2019-02-26 | General Electric Company | System and method for in situ repair of gas turbine engine casing clearance |
FR3075761A1 (fr) * | 2017-12-21 | 2019-06-28 | Airbus Operations | Partie anterieure de nacelle d'un ensemble propulsif comportant un cadre de rigidification incline |
FR3086020B1 (fr) * | 2018-09-13 | 2020-12-25 | Safran Aircraft Engines | Systeme de retenue axiale d'une bague de roulement |
CN111577463B (zh) * | 2020-05-25 | 2021-08-17 | 中国航发沈阳发动机研究所 | 一种发动机进气机匣结构 |
CN114055805B (zh) * | 2020-08-10 | 2023-09-08 | 中国航发商用航空发动机有限责任公司 | 航空发动机风扇易磨环的制造方法 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3843278A (en) * | 1973-06-04 | 1974-10-22 | United Aircraft Corp | Abradable seal construction |
US5160248A (en) * | 1991-02-25 | 1992-11-03 | General Electric Company | Fan case liner for a gas turbine engine with improved foreign body impact resistance |
US5388959A (en) * | 1993-08-23 | 1995-02-14 | General Electric Company | Seal including a non-metallic abradable material |
US5431532A (en) * | 1994-05-20 | 1995-07-11 | General Electric Company | Blade containment system |
US5885056A (en) * | 1997-03-06 | 1999-03-23 | Rolls-Royce Plc | Gas Turbine engine casing construction |
EP0952310A2 (de) * | 1998-04-20 | 1999-10-27 | United Technologies Corporation | Durchschlagsicheres Bläsergehäuse für ein Mantelstromtriebwerk |
FR2832191A1 (fr) * | 2001-11-14 | 2003-05-16 | Snecma Moteurs | Aube de soufflante a sommet fragilise |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3656862A (en) * | 1970-07-02 | 1972-04-18 | Westinghouse Electric Corp | Segmented seal assembly |
FR2467977A1 (fr) * | 1979-10-19 | 1981-04-30 | Snecma | Dispositif de securite en cas de rupture d'element rotatif de turbomachine |
FR2468741A1 (fr) * | 1979-10-26 | 1981-05-08 | Snecma | Perfectionnements aux anneaux a joint d'etancheite refroidi par l'air pour roues de turbine a gaz |
US4349313A (en) * | 1979-12-26 | 1982-09-14 | United Technologies Corporation | Abradable rub strip |
US4478552A (en) * | 1982-11-08 | 1984-10-23 | Thompson Stanley E | Method and apparatus for fan blade tip clearance |
US6364603B1 (en) * | 1999-11-01 | 2002-04-02 | Robert P. Czachor | Fan case for turbofan engine having a fan decoupler |
US6334617B1 (en) * | 2000-03-02 | 2002-01-01 | United Technologies Corporation | Composite abradable material |
US6899339B2 (en) * | 2001-08-30 | 2005-05-31 | United Technologies Corporation | Abradable seal having improved durability |
US6652222B1 (en) * | 2002-09-03 | 2003-11-25 | Pratt & Whitney Canada Corp. | Fan case design with metal foam between Kevlar |
-
2003
- 2003-08-18 FR FR0309989A patent/FR2859002A1/fr active Pending
-
2004
- 2004-08-02 US US10/902,781 patent/US20050089390A1/en not_active Abandoned
- 2004-08-12 EP EP04292043A patent/EP1510657A1/de not_active Withdrawn
- 2004-08-17 JP JP2004237742A patent/JP2005061419A/ja not_active Withdrawn
- 2004-08-17 RU RU2004125186/06A patent/RU2282039C2/ru not_active IP Right Cessation
- 2004-08-17 CA CA002478788A patent/CA2478788A1/fr not_active Abandoned
- 2004-08-18 CN CN200410056784.6A patent/CN1590712A/zh active Pending
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3843278A (en) * | 1973-06-04 | 1974-10-22 | United Aircraft Corp | Abradable seal construction |
US5160248A (en) * | 1991-02-25 | 1992-11-03 | General Electric Company | Fan case liner for a gas turbine engine with improved foreign body impact resistance |
US5388959A (en) * | 1993-08-23 | 1995-02-14 | General Electric Company | Seal including a non-metallic abradable material |
US5431532A (en) * | 1994-05-20 | 1995-07-11 | General Electric Company | Blade containment system |
US5885056A (en) * | 1997-03-06 | 1999-03-23 | Rolls-Royce Plc | Gas Turbine engine casing construction |
EP0952310A2 (de) * | 1998-04-20 | 1999-10-27 | United Technologies Corporation | Durchschlagsicheres Bläsergehäuse für ein Mantelstromtriebwerk |
FR2832191A1 (fr) * | 2001-11-14 | 2003-05-16 | Snecma Moteurs | Aube de soufflante a sommet fragilise |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2116695A2 (de) * | 2008-05-06 | 2009-11-11 | Rolls-Royce plc | Schutzplatte für das Bläsergehäuse einer Gasturbine |
EP2116695A3 (de) * | 2008-05-06 | 2013-07-03 | Rolls-Royce plc | Schutzplatte für das Bläsergehäuse einer Gasturbine |
US8578697B2 (en) | 2008-05-06 | 2013-11-12 | Rolls-Royce Plc | Fan section |
WO2013007937A2 (fr) | 2011-07-13 | 2013-01-17 | Snecma | Procede de fabrication d'un carter de soufflante de turbomachine muni de revetement acoustique. |
EP2623724A1 (de) * | 2012-02-06 | 2013-08-07 | United Technologies Corporation | Konforme Auskleidung für Gebläseabschnitt eines Gasturbinenmotors |
EP2775104A1 (de) * | 2012-02-06 | 2014-09-10 | United Technologies Corporation | Konforme Auskleidung für Gebläseabschnitt eines Gasturbinenmotors |
CN104141631A (zh) * | 2013-05-10 | 2014-11-12 | 航空技术空间股份有限公司 | 具有可磨损材料的涡轮机定子内壳体 |
Also Published As
Publication number | Publication date |
---|---|
RU2282039C2 (ru) | 2006-08-20 |
FR2859002A1 (fr) | 2005-02-25 |
RU2004125186A (ru) | 2006-01-27 |
US20050089390A1 (en) | 2005-04-28 |
JP2005061419A (ja) | 2005-03-10 |
CA2478788A1 (fr) | 2005-02-18 |
CN1590712A (zh) | 2005-03-09 |
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