US20080048399A1 - Leaf Seal Arrangement - Google Patents

Leaf Seal Arrangement Download PDF

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Publication number
US20080048399A1
US20080048399A1 US11/632,453 US63245305A US2008048399A1 US 20080048399 A1 US20080048399 A1 US 20080048399A1 US 63245305 A US63245305 A US 63245305A US 2008048399 A1 US2008048399 A1 US 2008048399A1
Authority
US
United States
Prior art keywords
leaf seal
leaf
arrangement
edge
chamfer
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
US11/632,453
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English (en)
Inventor
Richard Nicholson
Terence Jones
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Assigned to ROLLS-ROYCE PLC reassignment ROLLS-ROYCE PLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: JONES, TERENCE, NICHOLSON, RICHARD
Publication of US20080048399A1 publication Critical patent/US20080048399A1/en
Abandoned legal-status Critical Current

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Classifications

    • 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
    • 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
    • F16J15/3284—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
    • F16J15/3292—Lamellar structures
    • 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
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor

Definitions

  • the present invention relates to leaf seal arrangements and more particularly to such leaf seal arrangements utilised with regard to rotating shafts.
  • leaf seals have been designed to overcome premature wear and reduced operational life of brush seals. These leaf seals comprise substituting metal leaves for the bristles of the brush seal arrangement described above. A depth of leaves in the axial direction are provided which are compliant in the radial direction but stiff in the axial direction. Stiffness in the axial direction removes the necessity for a supporting backing ring and therefore any tendency for the leaf seal element to lock in position as differential pressure is applied across the seal arrangement. It is the locking of the seal elements in position which causes most contact wear between the shaft and edges of the seal leaves.
  • a conventional leaf seal eliminates the axial bending issues associated with brush seals by virtue of the inherent axial stiffness of a leaf compared with a single bristle.
  • the method of stacking leaves together will create voids between leaves that will become leakage paths; so front and rear plates are employed to limit this flow. It is observed that the positioning of these plates can alter basic leaf behaviour: a close front plate or a close radial clearance front plate will promote an up-lift blow up force on the leaf, whereas a closer rear plate or closer radial clearance rear plate will promote a downward blow down force on the leaf.
  • the geometry will be defined to promote one or other fundamental characteristic and increased leakage will result from a fundamentally blow-up design arrangement, and increased wear from a fundamentally blow down arrangement.
  • the leaf edges adjacent the shaft will be presented with a slight air gap therebetween such that these leaves essentially ride on the air leakage through that gap to inhibit premature contact wear of the leaf seal elements upon the rotating shaft.
  • the air gap must be as narrow as possible such that air leakage is the minimum necessary to create such air riding effect but limiting actual leakage across the seal.
  • typically a number of leaf seal arrangements will be provided in adjacent positions along the axial length of the shaft to further limit through their depth leakage across the combined assembly. Nevertheless, close proximity between the leaf seal element edges and the shaft increases the possibility of contact and therefore wear.
  • a leaf seal arrangement comprising leaf seal elements projected within a housing, at least some of the leaf seal elements having an edge chamfer and the housing having an edge portion associated with the edge chamfer whereby, in use, deflection of the leaf seals varies any control gap between the edge chamfers and the edge portion to vary the resistance by the leaf seal element to deflection.
  • the leaf seal elements project radially within the housing.
  • leaf seal elements Normally all the leaf seal elements have the same chamfer edge whereby opposite sides of the leaf seal are not parallel with one another.
  • edge chamfer is a straight inward truncation or outward slope from the leaf seal.
  • the edge portion of the housing comprises an inward bulbous foot directed towards the edge chamfer.
  • the leaf seal elements are angularly presented within the housing in use towards a rotating shaft.
  • the edge portion is normally arranged in use to be at a high pressure side of the arrangement.
  • a leaf seal combination comprising a plurality of leaf seal arrangements as described above.
  • an engine incorporating a leaf seal arrangement and/or a leaf seal combination as described above.
  • FIG. 1 is a schematic part cross-section of a conventional leaf seal arrangement in the direction of a shaft axis
  • FIG. 2 is a schematic part cross-section of a conventional leaf seal arrangement as depicted in FIG. 1 ;
  • FIG. 3 is a schematic part cross-section of a first embodiment of a leaf seal arrangement depicted in the direction of a rotating shaft;
  • FIG. 4 is a schematic part cross-section of the first embodiment of a leaf seal arrangement depicted in FIG. 3 ;
  • FIG. 5 is a schematic part cross-section of a second embodiment of a leaf seal arrangement depicted in the direction of a rotating shaft;
  • FIG. 6 is a schematic part cross-section of the second embodiment of a leaf seal arrangement depicted in FIG. 5 .
  • FIG. 7 is a schematic part cross-section of an engine.
  • the present invention defines an arrangement that will change the blow up or blow down behaviour based on leaf position. For example, it may be advantageous to define a seal initially in “blow up” configuration to accommodate the increased shaft diameter (caused for example by centrifugal growth) that accompanies increased pressure difference. However, it is often desirous to limit the blow up characteristic, and even to cause some blow down to then promote less leakage at the changed operating condition. This can be accomplished by so profiling the front and or back of the leaf profile to deliver a pre-determined set of controlling clearances at given leaf directions. Simple chamfers, or more complex compound chamfers or curves may be used depending on the forces required for the operation.
  • the arrangement 1 comprises a number of leaf seal elements 2 secured within a housing 3 which has side plates 4 , 5 to constrain and present the leaf seal elements 2 .
  • the elements 2 are stacked such that small nearly regular triangular gaps 6 are formed towards an outer seal diameter of the leaves 2 . Without further additional features these gaps 6 represent leakage pathways across the seal arrangement 1 .
  • the side plates 4 , 5 are provided in order to restrict flow into and out of the packed assembly of leaf seal elements 2 side-by-side in the housing 3 .
  • the leaves 2 project towards the rotating shaft 7 at an angled configuration which is substantially inwardly radial such that the leaf seal elements 2 in contact with the surface of the rotating shaft 7 are positioned to minimise leakage.
  • the inner diameter 8 of the side plates 4 , 5 is chosen such that the available inlet area is minimised.
  • the gap between the inner diameter 8 of the side plates 4 , 5 to the rotating shaft 7 is limited but is maintained such that there is adequate axial clearance for shaft 7 rotational eccentricities.
  • leaf seal elements 2 are subjected to leaf forces which tend to raise (blow up) or lower (blow down) the elements 2 into engagement with the shaft 7 . These leaf forces are generated by the choice of clearances, the operational sealing pressure drop across the seal arrangement 1 from an upstream side 9 to a downstream side 10 and the rotational speed of the shaft 7 . As indicated previously, a particular problem relates to excessive downward pressure by the leaf seal elements 2 upon the shaft 7 whereby there is premature wearing of those leaf seal elements 2 and therefore degradation in seal arrangement 1 performance.
  • the rotating shaft may be subject to a number of rotational eccentricities which may displace the relative position of a contact surface 11 in the direction of arrowheads A. Such displacement will place pressure upon the leaf seal elements 2 causing flexing to accommodate these displacements. Flexing of the leaf seal elements 2 will generally cause leakage in the area 12 between leaf seal elements 2 , but nevertheless due to the constraint of the side plates 4 , 5 , this leakage will be constricted and may force locked engagement between the ends of the leaf seal elements 2 and the surface 11 causing greater wear between these elements 2 and that surface 11 .
  • FIGS. 3 and 4 illustrate a first embodiment of a leaf seal arrangement in accordance with the present invention.
  • the arrangement 30 comprises a number of leaf seal elements 32 presented as previously at an angular radial projection towards a rotating shaft 37 within a housing 33 .
  • the housing 33 comprises side plates 34 , 35 to constrain and present the leaf seal elements 32 towards the rotating shaft 37 .
  • the housing 33 through the side plates 34 , 35 has an inner diameter 38 such that there is a minimum inlet area 31 to accommodate for rotational eccentricities.
  • an upstream side plate 34 of the housing 33 towards the high pressure side 39 has an edge portion 40 which extends axially inward of the housing 33 to engage a chamfer edge 41 of the seal element 32 .
  • the leaf seal element 32 is therefore of a non parallel nature. Due to the cut away or truncated nature of the chamfer edge 41 it will be appreciated that as the seal element 32 flexes in a direction 42 then a control gap X increases. An increased control gap X adjusts the presented aerodynamic force and allows the radial force to be adjusted to match the deflection required in terms of eccentric rotation in the shaft 37 .
  • control gap X decreases when there is movement in the direction of arrowhead 43 as the chamfer edge 41 moves towards the edge portion 40 .
  • the control gap X decreases when there is movement in the direction of arrowhead 43 as the chamfer edge 41 moves towards the edge portion 40 .
  • the appropriate position will equate to a steady state condition for the arrangement.
  • FIGS. 5 and 6 illustrate a second embodiment of a leaf seal arrangement 50 in accordance with the present invention.
  • the arrangement 50 again comprises leaf seal elements 52 arranged in an angular radial projection from an housing 53 about a rotating shaft 57 .
  • Side plates 54 , 55 are provided within which the leaf seal elements 52 are presented.
  • a bulbous edge portion 60 is provided which extends axially inwards of the housing 53 for association with a chamfer edge 61 in order that a control gap XX between that edge 60 and the chamfer edge 61 varies dependent upon deflection of the leaf seal element 52 .
  • the bulbous edge portion 40 , 60 and opposed chamfer edge 41 , 61 that allows control of the control gap X, XX whereby leakage through that control gap X, XX ensures that there is variation in the radial resistive force to deflection, that is to say, susceptibility to blow up or blow down forces. This variation is matched with the deflection required in the leaf seal elements 32 , 52 dependent upon rotating shaft 37 , 57 eccentricity and/or pressure differentials across the seal arrangement 30 , 50 .
  • edge portion 40 , 60 and chamfer edge 41 , 61 size and shape the necessary responses and adjustments in radial force can be tuned as required by a particular installation.
  • edge portion 40 , 60 and chamfer edge 41 , 61 could be provided both as illustrated at the upstream leading edge of the seal arrangements 30 , 50 and/or at the downstream or trailing edge sides of the arrangements 30 , 50 , that is to say in the side plates 35 , 55 .
  • varying deflection responsivity can be provided to the leaf seal elements 32 , 52 whereby there is less lockdown contact, that is to say excessive blow down pressure, between those elements 32 , 52 and the shaft 37 , 57 with detrimental abrasion leading to premature failure of seal arrangements 30 , 50 .
  • edge portions 40 , 60 in association with chamfer edges 41 , 61 provides a further design choice, in addition to the material type from which the leaf seal elements 32 , 52 are made, and their thickness and shaping, in order to achieve a desired sealing efficiency and operational life.
  • edge portion 40 , 60 and chamfer edge 41 , 61 relative positioning for non parallel response need not be linear about the shaft 57 .
  • the progress of the control gap X, XX widening or narrowing dependent upon leaf seal element 32 , 52 deflection may not provide a uniform unitary alteration in control gap X, XX width with displacement whereby radial force can be varied non uniformly with deflection.
  • possibly the chamfer edge 40 , 41 may have a curved or otherwise recessed shape illustrated by broken lines 44 , 64 whereby the variation in the control gap X, XX alters non uniformly with deflection in the direction of arrowheads 42 , 43 ; 62 , 63 .
  • a seal combination can be provided which is more sympathetic to rotating shaft 37 , 57 eccentricities.
  • by enabling variation and adjustment in the radial force it is possible to ensure that the multiplicity of leaf seal elements combined together in a seal pack formed in the housings 33 , 53 can retain the desired pre positioned leaf seal element attitude upon the rotating shaft 37 , 57 to optimise leakage behaviour and operational life due to lower wear.
  • the present invention has particular applicability with regard to gas turbine engines used in any application. It will be appreciated that these engines are generally multi shafted with cascades of compressors and turbines which require seal isolation between each stage. In such circumstances leaf seal arrangements provided in appropriate combinations are utilised to provide such stage isolation. Seal arrangements 30 , 50 will be combined in a cascade along the axial length of rotating shafts in order to provide the necessary sealing isolation.
  • a gas turbine engine is generally indicated at 110 , and comprises, in axial flow series, an air intake 111 , a propulsive fan 112 , an intermediate pressure compressor 113 , a high pressure compressor 114 , combustion equipment 115 , a high pressure turbine 116 , an intermediate pressure turbine 117 , a low pressure turbine 118 and an exhaust nozzle 119 .
  • the gas turbine engine 110 works in a conventional manner so that air entering the intake 111 is accelerated by the fan 112 which produces two air flows: a first air flow into the intermediate pressure compressor 113 and a second air flow which provides propulsive thrust.
  • the intermediate pressure compressor comprises the air flow directed into it before delivering that air to the high pressure compressor 114 where further compression takes place.
  • the compressed air exhausted from the high pressure compressor 114 is directed into the combustion equipment 115 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 116 , 117 and 118 before being exhausted through the nozzle 119 to provide additional propulsive thrust.
  • the high, intermediate and low pressure turbine 116 , 117 and 118 respectively drive the high and intermediate pressure compressors 114 and 113 , and the fan 112 by suitable interconnecting shafts.
  • Leaf seal arrangements and combinations in accordance with the present invention can be utilised about the inter-connecting shafts in order to isolate and prevent leakage of gases between the compressor stages and turbine stages.
  • front and back plates may have features in order to help in defining the radius where the controlling orifice occurs. This feature may be at the innermost diameter, or at some other radial position.
  • the blow up or blow down behaviour can be tailored and optimised for a wider range of operating conditions than is possible with straight-sided leaves.
  • movements/control as follows.
  • the leaf element edge For a shaft movement upward into contact, the leaf element edge is moved/pushed up so that with an upstream control edge there is leaf movement away as blow up increases, with a downstream control edge there is greater blow down with higher leaf to shaft force, with a modified downstream control edge blow down increases to a limit so that a desirable/controllable leaf to shaft force increase is achieved but this is limited to possibly ensure ‘light load’ at greatest shaft movement and finally, with a compound control, that is to say both upstream and downstream control edges, blow up initially increases with initial leaf movement away from the shaft until the downstream edge begins to control with a blow down push into the shaft for a stable position.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Sealing Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Gasket Seals (AREA)
US11/632,453 2004-08-07 2005-07-06 Leaf Seal Arrangement Abandoned US20080048399A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB0417613.7 2004-08-07
GBGB0417613.7A GB0417613D0 (en) 2004-08-07 2004-08-07 A leaf seal arrangement
PCT/GB2005/002647 WO2006016098A1 (en) 2004-08-07 2005-07-06 A leaf seal arrangement

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2005/002647 A-371-Of-International WO2006016098A1 (en) 2004-08-07 2005-07-06 A leaf seal arrangement

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US12/259,934 Continuation US8162323B2 (en) 2004-08-07 2008-10-28 Leaf seal arrangement

Publications (1)

Publication Number Publication Date
US20080048399A1 true US20080048399A1 (en) 2008-02-28

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Family Applications (2)

Application Number Title Priority Date Filing Date
US11/632,453 Abandoned US20080048399A1 (en) 2004-08-07 2005-07-06 Leaf Seal Arrangement
US12/259,934 Expired - Fee Related US8162323B2 (en) 2004-08-07 2008-10-28 Leaf seal arrangement

Family Applications After (1)

Application Number Title Priority Date Filing Date
US12/259,934 Expired - Fee Related US8162323B2 (en) 2004-08-07 2008-10-28 Leaf seal arrangement

Country Status (9)

Country Link
US (2) US20080048399A1 (ko)
EP (1) EP1774208B1 (ko)
JP (1) JP4927731B2 (ko)
KR (1) KR101201375B1 (ko)
CN (1) CN101014790B (ko)
AU (1) AU2005271101B2 (ko)
CA (1) CA2575005C (ko)
GB (1) GB0417613D0 (ko)
WO (1) WO2006016098A1 (ko)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080309018A1 (en) * 2007-04-14 2008-12-18 Rolls-Royce Plc Seal arrangement
US20090309311A1 (en) * 2007-04-30 2009-12-17 General Electric Company Methods and apparatus to facilitate sealing in rotary machines
US20090322035A1 (en) * 2008-06-25 2009-12-31 Rolls-Royce Plc Sealing device
US20100025936A1 (en) * 2004-08-07 2010-02-04 Rolls-Royce Plc Leaf Seal Arrangement
US20110182729A1 (en) * 2009-11-11 2011-07-28 Siva Sivakumaran Leaf seals
US20130058766A1 (en) * 2011-09-06 2013-03-07 General Electric Company Systems, Methods, and Apparatus for a Labyrinth Seal
US20130249169A1 (en) * 2007-03-24 2013-09-26 Cross Manufacturing Company (1938) Limited Seal
US20130320627A1 (en) * 2012-05-31 2013-12-05 Rolls-Royce Plc Leaf seal
US20140205440A1 (en) * 2013-01-18 2014-07-24 General Electric Company Compliant plate seals for rotary machines
US20150001805A1 (en) * 2013-06-28 2015-01-01 Rolls-Royce Plc Leaf seal
US20170306778A1 (en) * 2014-10-10 2017-10-26 Nuovo Pignone Srl Seal for a gap between an outer and an inner cylindrical surface
US10174844B2 (en) * 2014-12-16 2019-01-08 Mitsubishi Hitachi Power Systems, Ltd. Shaft seal mechanism
US20190145320A1 (en) * 2016-05-09 2019-05-16 Mitsubishi Hitachi Power Systems, Ltd. Seal segment and rotary machine
US20190162120A1 (en) * 2016-05-09 2019-05-30 Mitsubishi Hitachi Power Systems, Ltd. Seal segment and rotary machine
US10731499B2 (en) 2015-02-20 2020-08-04 Mitsubishi Hitachi Power Systems, Ltd. Seal device for turbine, turbine, and thin plate for seal device

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GB0613543D0 (en) * 2006-07-07 2006-08-16 Rolls Royce Plc Leaf seal arrangement
US7419164B2 (en) * 2006-08-15 2008-09-02 General Electric Company Compliant plate seals for turbomachinery
US20080048398A1 (en) * 2006-08-24 2008-02-28 United Technologies Corporation Gap sealing arrangement
EP2105640B1 (de) 2008-03-28 2011-04-27 Alstom Technology Ltd Blattdichtung für Turbomaschine
GB2462255A (en) * 2008-07-28 2010-02-03 Alstom Technology Ltd A leaf seal for a rotary machine
DE102010001345B4 (de) * 2010-01-28 2013-09-19 Trelleborg Sealing Solutions Germany Gmbh Drehdurchführung
JP5693292B2 (ja) * 2011-02-25 2015-04-01 三菱重工業株式会社 軸シール機構
MX2013011804A (es) * 2011-04-12 2013-10-25 Saint Gobain Portador electricamente calentable y elemento de calentamiento de panel, asi como metodo para producir los mismos.
US20120315138A1 (en) * 2011-06-10 2012-12-13 General Electric Company Compliant plate seal assembly for a turbo machine
GB201121440D0 (en) 2011-12-14 2012-01-25 Rolls Royce Plc Improved leaf seal
GB201207837D0 (en) * 2012-05-04 2012-06-20 Rolls Royce Plc Leaf seal
JP6012505B2 (ja) * 2013-02-22 2016-10-25 三菱重工業株式会社 軸シール装置及び回転機械
EP3055512B1 (en) * 2013-10-11 2019-07-31 United Technologies Corporation Non-linearly deflecting brush seal land
JP6125412B2 (ja) 2013-11-22 2017-05-10 三菱重工業株式会社 軸シール装置、回転機械、及び軸シール装置の製造方法
CN109073029A (zh) * 2016-02-24 2018-12-21 日立汽车系统株式会社 液压缸装置及其制造方法
US11415227B2 (en) 2019-08-21 2022-08-16 Raytheon Technologies Corporation Non-contact seal assembly with chamfered seal shoe
US20210062669A1 (en) * 2019-08-26 2021-03-04 United Technologies Corporation Hydrostatic seal with seal stops
US11988167B2 (en) * 2022-01-03 2024-05-21 General Electric Company Plunger seal apparatus and sealing method

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GB0417613D0 (en) * 2004-08-07 2004-09-08 Rolls Royce Plc A leaf seal arrangement
US7419164B2 (en) * 2006-08-15 2008-09-02 General Electric Company Compliant plate seals for turbomachinery
GB0707224D0 (en) * 2007-04-14 2007-05-23 Rolls Royce Plc A seal arrangement
US7976026B2 (en) * 2007-04-30 2011-07-12 General Electric Company Methods and apparatus to facilitate sealing in rotary machines
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US5524846A (en) * 1993-12-21 1996-06-11 The Boeing Company Fire protection system for airplanes
US6267381B1 (en) * 1998-01-30 2001-07-31 Rolls-Royce Plc Resilient strip seal arrangement
US6343792B1 (en) * 1998-07-13 2002-02-05 Mitsubishi Heavy Industries, Ltd. Shaft seal and turbine using the same
US6808179B1 (en) * 1998-07-31 2004-10-26 Concepts Eti, Inc. Turbomachinery seal
US6196550B1 (en) * 1999-02-11 2001-03-06 Alliedsignal Inc. Pressure balanced finger seal
US20030071423A1 (en) * 2000-02-12 2003-04-17 Karl Urlichs Rotor seal with folding strip
US6742782B2 (en) * 2000-04-08 2004-06-01 Mtu Aero Engines Gmbh Seal of non-hermetic design
US20020105146A1 (en) * 2001-02-08 2002-08-08 Mitsubishi Heavy Industries, Ltd. Shaft seal and gas turbine
US7066468B2 (en) * 2001-02-08 2006-06-27 Mitsubishi Heavy Industries, Ltd. Shaft seal and gas turbine
US6644667B2 (en) * 2001-02-23 2003-11-11 Cmg Tech, Llc Seal assembly and rotary machine containing such seal
US20040150165A1 (en) * 2001-02-23 2004-08-05 Grondahl Clayton M. Seal assembly and rotary machine containing such seal
US6811154B2 (en) * 2003-02-08 2004-11-02 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Noncontacting finger seal
US7226053B2 (en) * 2003-05-21 2007-06-05 Mitsubishi Heavy Industries, Ltd. Shaft seal mechanism, shaft seal mechanism assembling structure and large size fluid machine

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8162323B2 (en) * 2004-08-07 2012-04-24 Rolls-Royce Plc Leaf seal arrangement
US20100025936A1 (en) * 2004-08-07 2010-02-04 Rolls-Royce Plc Leaf Seal Arrangement
US20130249169A1 (en) * 2007-03-24 2013-09-26 Cross Manufacturing Company (1938) Limited Seal
US9915351B2 (en) * 2007-03-24 2018-03-13 Cross Manufacturing Company (1938) Limited Seal
US20080309018A1 (en) * 2007-04-14 2008-12-18 Rolls-Royce Plc Seal arrangement
US7976026B2 (en) * 2007-04-30 2011-07-12 General Electric Company Methods and apparatus to facilitate sealing in rotary machines
US20090309311A1 (en) * 2007-04-30 2009-12-17 General Electric Company Methods and apparatus to facilitate sealing in rotary machines
US20090322035A1 (en) * 2008-06-25 2009-12-31 Rolls-Royce Plc Sealing device
US20110182729A1 (en) * 2009-11-11 2011-07-28 Siva Sivakumaran Leaf seals
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JP2008509369A (ja) 2008-03-27
CN101014790A (zh) 2007-08-08
JP4927731B2 (ja) 2012-05-09
US20100025936A1 (en) 2010-02-04
CA2575005C (en) 2010-09-14
CA2575005A1 (en) 2006-02-16
KR101201375B1 (ko) 2012-11-14
AU2005271101B2 (en) 2010-01-28
US8162323B2 (en) 2012-04-24
EP1774208B1 (en) 2014-09-17
KR20070045233A (ko) 2007-05-02
WO2006016098A1 (en) 2006-02-16
GB0417613D0 (en) 2004-09-08
AU2005271101A1 (en) 2006-02-16
EP1774208A1 (en) 2007-04-18
CN101014790B (zh) 2010-12-08

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