EP1510657A1 - Abreibbare Vorrichtung für das Bläsergehäuse einer Gasturbine - Google Patents

Abreibbare Vorrichtung für das Bläsergehäuse einer Gasturbine Download PDF

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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Withdrawn
Application number
EP04292043A
Other languages
English (en)
French (fr)
Inventor
Eric Marie Pierre Gerain
Eric Celerier
François Jacques Brefort
Pierre Yves Maillard
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1510657A1 publication Critical patent/EP1510657A1/de
Withdrawn legal-status Critical Current

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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)
EP04292043A 2003-08-18 2004-08-12 Abreibbare Vorrichtung für das Bläsergehäuse einer Gasturbine Withdrawn EP1510657A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0309989A FR2859002A1 (fr) 2003-08-18 2003-08-18 Dispositif abradable sur carter de soufflante d'un moteur de turbine a gaz
FR0309989 2003-08-18

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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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)

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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

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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

Patent Citations (7)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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
US20050089390A1 (en) 2005-04-28
RU2004125186A (ru) 2006-01-27
CA2478788A1 (fr) 2005-02-18
JP2005061419A (ja) 2005-03-10
RU2282039C2 (ru) 2006-08-20
CN1590712A (zh) 2005-03-09
FR2859002A1 (fr) 2005-02-25

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