US20150184531A1 - Gasket device for the bearing of a turbomachine, comprising two elastic seals - Google Patents

Gasket device for the bearing of a turbomachine, comprising two elastic seals Download PDF

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Publication number
US20150184531A1
US20150184531A1 US14/412,336 US201314412336A US2015184531A1 US 20150184531 A1 US20150184531 A1 US 20150184531A1 US 201314412336 A US201314412336 A US 201314412336A US 2015184531 A1 US2015184531 A1 US 2015184531A1
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US
United States
Prior art keywords
gasket
bearing
turbomachine
supporting jacket
sleeve
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.)
Abandoned
Application number
US14/412,336
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English (en)
Inventor
Jonathan Boris Baptista
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 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 SAS filed Critical SNECMA SAS
Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BAPTISTA, Jonathan Boris
Publication of US20150184531A1 publication Critical patent/US20150184531A1/en
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SNECMA
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Assignors: SNECMA
Abandoned 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
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/18—Sealings between relatively-moving surfaces with stuffing-boxes for elastic or plastic packings
    • F16J15/24—Sealings between relatively-moving surfaces with stuffing-boxes for elastic or plastic packings with radially or tangentially compressed packing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
    • F16J15/3268—Mounting of sealing rings
    • F16J15/3276—Mounting of sealing rings with additional static sealing between the sealing, or its casing or support, and the surface on which it is mounted
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/224—Carbon, e.g. graphite

Definitions

  • the present invention relates to the field of turbomachines. It relates to a gasket device for a turbomachine bearing, as well as the turbomachine including such a device.
  • the invention is applicable to any type of terrestrial or aeronautical turbomachines, in particular to aircraft turbomachines such as turbofans and turboprop engines. More preferentially, the invention is applicable to a twin spool axial flow turbofan.
  • a turbomachine bearing supporting a shaft rotating inside a fixed case includes a balling bearing arranged in an enclosure where the lubrication thereof is ensured.
  • any oil migration should be avoided toward some compartments of the turbomachine and the tightness should thus be ensured at the separation between the oil containing bearing enclosure and an air-neighbouring enclosure which must be kept free of oil.
  • FIG. 1 illustrates an example of use of such a segmented gasket, also called segmented radial seal (SRS), including in particular a static sealing ring consisting of carbon segments.
  • a shaft 1 is rotatably supported by a bearing, carried by a case 2 , including a balling bearing 3 .
  • a sleeve 4 rotatably integral with the shaft 1 is sandwiched between the balling bearing 3 and the shaft 1 , according to arrangements known per se in the application to turbomachines.
  • the balling bearing 3 is comprised in an enclosure 5 where both air and oil are present for lubricating the balling bearing 3 ensured in a known manner per se are present.
  • the shaft 1 is surrounded by a so-called air enclosure 6 which should remain free of oil because any oil upwelling in some compartments of the turbomachine would be detrimental to a proper operation.
  • a sealing device 10 is thus provided between the shaft 1 and the case 2 at the separation between the oil enclosure 5 and the air enclosure 6 .
  • the sealing device 10 includes a static sealing ring 7 , consisting of carbon segments which are held together using a circumferential spring 22 , this spring 22 tightening the carbon segments against the sleeve 4 .
  • the static sealing ring 7 is associated with a rotating surface 8 , that can include grooves 12 to provide for lift. This rotating surface 8 is extended to a cylindrical surface 9 , in relation with a labyrinth oil outlet system 11 to prevent oil particles from reaching the carbon segments.
  • the static sealing ring 7 is kept in a metal supporting jacket 14 (or support 14 ) by the circumferential spring 22 and axial springs 21 , pressed against a ring 18 which is held in the support 14 by a stop joint 20 .
  • the support 14 is centred without tightening by means of an O-ring 19 placed between the support 14 and a case element 24 acting as a cover and thus enabling the static part of the gasket device 10 to be attached to the case 2 of the turbomachine.
  • Dynamic tightness is achieved between the respective cooperating cylindrical faces 16 and 17 of the carbon segments 7 and of the rotating surface 8 .
  • Static tightness is achieved between the carbon segments 7 and the static face 23 of the support 14 , located at the labyrinth oil outlet ring 11 , to avoid any radial leak.
  • the static sealing ring 7 should be mounted so as to retain in use a high concentricity with respect to the rotor and a perpendicularity with respect to the static face 23 .
  • the invention aims at overcoming at least partly the abovementioned needs and drawbacks relating to prior art embodiments.
  • one purpose of the invention is to provide a gasket device for a turbomachine bearing having two elastic seals.
  • Said bearing includes a balling bearing mounted between a sleeve integral with a shaft and a case.
  • the sleeve has a rotating surface and the case includes a case element acting as a cover for the gasket device.
  • the gasket device is able to separate an oil enclosure of the balling bearing from an air enclosure of the turbomachine. It includes:
  • a segmented gasket including in particular one or more carbon segments, which seal is mounted in association with a rotating surface of the sleeve, to ensure in particular most of the tightness of the device,
  • a supporting jacket for holding the segmented gasket, which jacket is mounted between the sleeve and the case element, the supporting jacket including a first groove accommodating a first elastic seal for centring the supporting jacket over the case element, in particular for aligning the axis of the supporting jacket with the axis of the case element.
  • the gasket device for the turbomachine bearing is characterised in that the supporting jacket includes a second groove accommodating a second elastic seal for centring the supporting jacket over the case element.
  • the solution provided by the invention can enable various drawbacks of known prior art solutions to be avoided while ensuring the tightness searched for between an air enclosure and an oil enclosure.
  • it can for example be possible to overcome difficulties relating to the radial clearance opening because of existing differences between the materials of the turbomachine components in terms of expansion.
  • the centring of the supporting jacket over the case element through two elastic seals can enable case vibrations to be dampened, and thus axial wear of the carbon segments of the segmented gasket to be reduced.
  • the gasket device according to the invention can further include one or more of the following characteristics taken alone or according to any possible technical combinations.
  • the first and second grooves can be identical, having in particular the same dimensions and shape.
  • the first and second grooves are advantageously formed on the part of the supporting jacket which is located facing the case element.
  • the supporting jacket can include more than two grooves each accommodating an elastic seal for centring the supporting jacket over the case element, in particular at least three, at least four, or even five grooves each accommodating an elastic seal.
  • the first and second elastic seals can have the same dimensions.
  • the first and second elastic seals can have the same diameter.
  • the first and second elastic seals advantageously contact the case element.
  • the first and second elastic seals can be of any type, being in particular O-rings.
  • the first and second elastic seals can be selected such that the maximum radial clearance opening between the case element and the elastic seals, when the turbomachine is in use, is within the range of admissible minimum and maximum values because of design requirements for crushing an elastic seal, in particular an O-ring.
  • the first and second elastic seals can be fit upon assembling the gasket device with the maximum admissible crush value.
  • the first and second grooves can be spaced apart from each other by a distance being higher, lower or equal to the width of at least one of the first and second grooves, in particular to the width of each of the first and second grooves.
  • the gap between the first and second grooves can be maximum to make the centring of the supporting jacket over the case element optimum.
  • the first and second elastic seals can be made of any type of elastic material, in particular of an elastomeric material.
  • the rotating surface of the sleeve can be extended by a cylindrical surface, and the supporting jacket can include a labyrinth oil outlet system in relation with the cylindrical surface.
  • the segmented gasket can include a sealing ring including a set of one or more carbon segments, that can be held together by a circumferential spring and/or pressed against the supporting jacket by one or more axial springs pressing against a stop joint, in particular a stop ring (of the SRS type or face joints).
  • Yet another object of the invention is to provide a turbomachine characterised in that it includes a gasket s device such as previously defined.
  • FIG. 1 represents, in a cross-section view through a plane passing through the axis of rotation of the shaft, a part of a turbomachine bearing including an enclosure gasket device according to prior art, and
  • FIG. 2 represents an enlarged view of a turbomachine bearing similar to that of FIG. 1 , however including a gasket device according to the invention.
  • FIG. 2 An exemplary embodiment of the invention relating to a gasket device for a turbomachine bearing will be described hereinafter in reference to FIG. 2 .
  • the turbomachine bearing is similar to that described in reference to FIG. 1 .
  • the bearing includes a balling bearing 3 mounted between a sleeve 4 integral with a shaft 1 and a case 2 , the sleeve 4 having a rotating surface 8 and the case 2 including a case element 24 acting as a cover for the gasket device 10 .
  • the gasket device 10 is able to separate an oil enclosure 5 from the balling bearing 3 and an air enclosure 6 from the turbomachine.
  • the sealing device 10 represented in FIG. 2 differs from that represented in FIG. 1 in that it includes a supporting jacket 14 including two housings 25 each accommodating an elastic seal 19 , in accordance with the invention.
  • the gasket device 10 includes a segmented gasket 7 , consisting of a static sealing ring of carbon segments held together by a circumferential spring 22 , which is mounted in association with the rotating surface 8 of the sleeve 4 to ensure most of the tightness of the gasket device 10 .
  • the latter also includes a supporting jacket 14 (or support 14 ) for holding the segmented gasket 7 , this support 14 being mounted between the sleeve 4 and the case element 24 .
  • the support 14 includes first and second grooves 25 accommodating first and second elastic seals 19 respectively that enable the support 14 to be centred over the case element 24 .
  • the first and second grooves 25 can be identical and the first and second elastic seals 19 can be O-rings with the same diameter, made of an elastomeric material.
  • both O-rings 19 can be spaced apart from each other as much as possible.
  • the distance D which separates the first and second grooves 25 can be as great as possible, being in particular equal or higher than the width W of the first and second grooves 25 .
  • the centring of the support 14 to the case element 24 can be made easier, and even be made when cold, the support 14 being for example able to be mounted in its bore according to the H7g6 fitting defined by the system of ISO fittings.
  • the support 14 could include more than two grooves 25 each associated with an elastic seal 19 .
  • the grooves 25 and/or the elastic seals 19 can be identical or not.
US14/412,336 2012-07-06 2013-07-04 Gasket device for the bearing of a turbomachine, comprising two elastic seals Abandoned US20150184531A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1256544A FR2993024B1 (fr) 2012-07-06 2012-07-06 Dispositif de joint d'etancheite de palier de turbomachine avec deux joints elastiques
FR1256544 2012-07-06
PCT/FR2013/051591 WO2014006338A1 (fr) 2012-07-06 2013-07-04 Dispositif de joint d'etancheite de palier de turbomachine avec deux joints elastiques

Publications (1)

Publication Number Publication Date
US20150184531A1 true US20150184531A1 (en) 2015-07-02

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US14/412,336 Abandoned US20150184531A1 (en) 2012-07-06 2013-07-04 Gasket device for the bearing of a turbomachine, comprising two elastic seals

Country Status (10)

Country Link
US (1) US20150184531A1 (fr)
EP (1) EP2870323B1 (fr)
JP (1) JP2015522773A (fr)
CN (1) CN104411922B (fr)
BR (1) BR112014033075A2 (fr)
CA (1) CA2879837A1 (fr)
FR (1) FR2993024B1 (fr)
IN (1) IN2014DN11166A (fr)
RU (1) RU2015103936A (fr)
WO (1) WO2014006338A1 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130142628A1 (en) * 2009-12-22 2013-06-06 Nuo Sheng Abradable seal with axial offset
US10041579B2 (en) * 2014-12-04 2018-08-07 Rolls-Royce Deutschland Ltd & Co Kg Device with a torque-proof first structural component and a second structural component that is connected at least in certain parts in a rotatable manner to the first structural component
US10100918B2 (en) 2014-12-04 2018-10-16 Rolls-Royce Deutschland Ltd & Co Kg Device with a torque-proof first structural component and a second structural component that is connected at least in certain parts in a rotatable manner to the first structural component
US10316891B2 (en) * 2016-11-23 2019-06-11 Rolls-Royce Deutschland Ltd & Co Kg Device with a torque-proof first structural component and a second structural component that is connected to the first structural component in a rotable manner at least in certain areas
EP3660273A1 (fr) * 2018-11-30 2020-06-03 Rolls-Royce Corporation Ensemble joint d'étanchéité et procédé d'étanchéification
EP3693555A1 (fr) * 2019-02-05 2020-08-12 United Technologies Corporation Joint mécanique à amortisseur
US11033915B2 (en) 2016-08-04 2021-06-15 Ntn Corporation Air turbine drive spindle
US20220018291A1 (en) * 2020-07-16 2022-01-20 Raytheon Technologies Corporation Gas turbine engine including seal assembly with abradable coating including magnetic particles
US20220018289A1 (en) * 2020-07-16 2022-01-20 Raytheon Technologies Corporation Gas turbine engine including seal assembly with abradable coating including magnetic particles embedded in polymer
US20220018290A1 (en) * 2020-07-16 2022-01-20 Raytheon Technologies Corporation Gas turbine engine including seal assembly with abradable coating and cutter
US11261754B2 (en) * 2017-02-07 2022-03-01 Safran Aircraft Engines Shell for reducing overpressure in the vicinity of the upstream seal of a turbojet bearing housing

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FR3024492B1 (fr) 2014-07-29 2019-08-23 Safran Aircraft Engines Element comprenant un stator et un rotor de turbomachine avec un joint d'etancheite et test de ce joint
CN105240060B (zh) * 2015-10-13 2016-11-30 山东钢铁股份有限公司 一种汽轮机轴承座支撑装置
US10626743B2 (en) * 2016-06-30 2020-04-21 General Electric Company Segmented face seal assembly and an associated method thereof
CN110537041B (zh) * 2017-03-09 2022-05-24 江森自控科技公司 背对背轴承密封系统
CN107314113B (zh) * 2017-08-08 2019-04-30 东台市岳东橡胶密封件厂 一种径向和轴向双密封的机械密封静环安装结构
CN108278204B (zh) * 2018-02-07 2023-12-19 宁波汇峰聚威科技股份有限公司 一种涡旋压缩机的密封装置
FR3079013B1 (fr) * 2018-03-14 2021-02-26 Safran Aircraft Engines Dispositif annulaire d'etancheite
CN110529503A (zh) * 2019-08-02 2019-12-03 中国航发贵阳发动机设计研究所 一种用于发动机主轴轴承滑油的密封结构

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US5161943A (en) * 1991-03-11 1992-11-10 Dresser-Rand Company, A General Partnership Swirl control labyrinth seal
US6098753A (en) * 1998-06-05 2000-08-08 Pratt & Whitney Canada Corp. System for delivering pressurized lubricant fluids to an interior of a rotating hollow shaft
US6164660A (en) * 1998-04-16 2000-12-26 Saint-Gobain Performance Plastics Corporation Rebuildable radial lip seal
US6196790B1 (en) * 1998-12-17 2001-03-06 United Technologies Corporation Seal assembly for an intershaft seal in a gas turbine engine
US20030047879A1 (en) * 2001-09-10 2003-03-13 Bowen Willard L. Rotary sealing device
US20040200215A1 (en) * 2001-10-16 2004-10-14 Woollenweber William E. Bearing system for high-speed rotating machinery
US20080031750A1 (en) * 2004-07-09 2008-02-07 Alexandre Gomilar Turbocharger Housing, Turbocharger And A Multi-Turbocharger Boosting System
US20080237994A1 (en) * 2007-03-27 2008-10-02 Rolls-Royce Plc Sealed joint
US20090200793A1 (en) * 2008-02-07 2009-08-13 National Coupling Company, Inc. Crown seal with integral sealing projections for undersea hydraulic couplings
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US8043051B2 (en) * 2007-05-23 2011-10-25 Baker Hughes Incorporated System, method, and apparatus for stackable multi-stage diffuser with anti-rotation lugs

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Publication number Priority date Publication date Assignee Title
US3331609A (en) * 1965-04-07 1967-07-18 Edwin W Plumb Rotary fluid seal
US5161943A (en) * 1991-03-11 1992-11-10 Dresser-Rand Company, A General Partnership Swirl control labyrinth seal
US6164660A (en) * 1998-04-16 2000-12-26 Saint-Gobain Performance Plastics Corporation Rebuildable radial lip seal
US6098753A (en) * 1998-06-05 2000-08-08 Pratt & Whitney Canada Corp. System for delivering pressurized lubricant fluids to an interior of a rotating hollow shaft
US6196790B1 (en) * 1998-12-17 2001-03-06 United Technologies Corporation Seal assembly for an intershaft seal in a gas turbine engine
US20030047879A1 (en) * 2001-09-10 2003-03-13 Bowen Willard L. Rotary sealing device
US20040200215A1 (en) * 2001-10-16 2004-10-14 Woollenweber William E. Bearing system for high-speed rotating machinery
US20080031750A1 (en) * 2004-07-09 2008-02-07 Alexandre Gomilar Turbocharger Housing, Turbocharger And A Multi-Turbocharger Boosting System
US20100111681A1 (en) * 2006-08-18 2010-05-06 Susumu Nakano Bearing device of gas turbine power generation equipment and gas turbine power generation equipment
US20080237994A1 (en) * 2007-03-27 2008-10-02 Rolls-Royce Plc Sealed joint
US8043051B2 (en) * 2007-05-23 2011-10-25 Baker Hughes Incorporated System, method, and apparatus for stackable multi-stage diffuser with anti-rotation lugs
US20090200793A1 (en) * 2008-02-07 2009-08-13 National Coupling Company, Inc. Crown seal with integral sealing projections for undersea hydraulic couplings

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9347459B2 (en) * 2009-12-22 2016-05-24 Nuovo Pignone S.P.A. Abradable seal with axial offset
US20130142628A1 (en) * 2009-12-22 2013-06-06 Nuo Sheng Abradable seal with axial offset
US10041579B2 (en) * 2014-12-04 2018-08-07 Rolls-Royce Deutschland Ltd & Co Kg Device with a torque-proof first structural component and a second structural component that is connected at least in certain parts in a rotatable manner to the first structural component
US10100918B2 (en) 2014-12-04 2018-10-16 Rolls-Royce Deutschland Ltd & Co Kg Device with a torque-proof first structural component and a second structural component that is connected at least in certain parts in a rotatable manner to the first structural component
US11033915B2 (en) 2016-08-04 2021-06-15 Ntn Corporation Air turbine drive spindle
US10316891B2 (en) * 2016-11-23 2019-06-11 Rolls-Royce Deutschland Ltd & Co Kg Device with a torque-proof first structural component and a second structural component that is connected to the first structural component in a rotable manner at least in certain areas
US11261754B2 (en) * 2017-02-07 2022-03-01 Safran Aircraft Engines Shell for reducing overpressure in the vicinity of the upstream seal of a turbojet bearing housing
EP3660273A1 (fr) * 2018-11-30 2020-06-03 Rolls-Royce Corporation Ensemble joint d'étanchéité et procédé d'étanchéification
US11255436B2 (en) 2018-11-30 2022-02-22 Rolls-Royce Corporation Circumferential archbound carbon seal on ceramic runner
EP3693555A1 (fr) * 2019-02-05 2020-08-12 United Technologies Corporation Joint mécanique à amortisseur
US11035253B2 (en) 2019-02-05 2021-06-15 Raytheon Technologies Corporation Face seal with damper
US20220018291A1 (en) * 2020-07-16 2022-01-20 Raytheon Technologies Corporation Gas turbine engine including seal assembly with abradable coating including magnetic particles
US20220018289A1 (en) * 2020-07-16 2022-01-20 Raytheon Technologies Corporation Gas turbine engine including seal assembly with abradable coating including magnetic particles embedded in polymer
US20220018290A1 (en) * 2020-07-16 2022-01-20 Raytheon Technologies Corporation Gas turbine engine including seal assembly with abradable coating and cutter
US11293351B2 (en) * 2020-07-16 2022-04-05 Raytheon Technologies Corporation Gas turbine engine including seal assembly with abradable coating including magnetic particles embedded in polymer
US11313280B2 (en) * 2020-07-16 2022-04-26 Raytheon Technologies Corporation Gas turbine engine including seal assembly with abradable coating and cutter
US11313281B2 (en) * 2020-07-16 2022-04-26 Raytheon Technologies Corporation Gas turbine engine including seal assembly with abradable coating including magnetic particles

Also Published As

Publication number Publication date
RU2015103936A (ru) 2016-08-27
WO2014006338A1 (fr) 2014-01-09
EP2870323B1 (fr) 2017-10-11
CN104411922A (zh) 2015-03-11
CA2879837A1 (fr) 2014-01-09
FR2993024A1 (fr) 2014-01-10
BR112014033075A2 (pt) 2017-06-27
CN104411922B (zh) 2016-08-24
EP2870323A1 (fr) 2015-05-13
JP2015522773A (ja) 2015-08-06
FR2993024B1 (fr) 2014-08-08
IN2014DN11166A (fr) 2015-10-02

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