US3801220A - Sealing element for a turbo-machine - Google Patents

Sealing element for a turbo-machine Download PDF

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Publication number
US3801220A
US3801220A US00207897A US3801220DA US3801220A US 3801220 A US3801220 A US 3801220A US 00207897 A US00207897 A US 00207897A US 3801220D A US3801220D A US 3801220DA US 3801220 A US3801220 A US 3801220A
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US
United States
Prior art keywords
packing
strips
layers
extending gaps
strip
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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.)
Expired - Lifetime
Application number
US00207897A
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English (en)
Inventor
W Beckershoff
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.)
Brown Boveri Sulzer Turbomaschinen AG
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Brown Boveri Sulzer Turbomaschinen AG
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    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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

Definitions

  • An arrangement for packing expansion joints on turbo-machines and particularly packing the axially extending gaps provided between adjacent blading of a blade row and circumferentially extending gaps provided between each blade row and an adjacent row of blade segments which serve to provide axial spacing between adjacent rows of blading on the rotor of the machine includes two sets of packing strips inserted respectively in grooves provided along the confronting sides of the blading which establish the axially and circumferentially extending gaps that form intersections with each other.
  • Each packing strip of each set is constituted by two layers which are shifted in a longitudinal direction relative to each other such that one layer of each strip of each set continues across each intersection while an end of the other layer of each strip of one set terminates at an intersection at the side of and is joined to the layer of the other set which continues across that intersection, thus providing a complete sealing not only along the axially and circumferentially ABSTRACT Q extending gaps but also at their intersections.
  • Fig.2 PRIOR ART SEALING ELEMENT FOR A TURBO-MACHINE
  • This invention relates to an improvement for a packing element for expansion joints on turbo-machines of the type which consists of packing strips inserted into grooves of the parts to be sealed from each other, the individual packing strips having cutouts or lobes which are fitted one into the other at least partially at mutually crossing points.
  • Unsealed heat expansion joints usually have within the same machine somewhat different sizes, whereby the heating in uncooled machines aswell as the cooling effect in cooled machines may turn out to be different. This sometimes brings about warping at stationary or rotating parts, which later leads to damage to the machines.
  • the principal object of the present invention is to avoid the above disadvantages and to exclude, almost completely, any leakages between the parts forming the flow channel of a turbo-machine.
  • the packing strip is formed with at least two layers, the first of which is shifted relatively to the second layer in the longitudinal direction of the packing strip by at least the amount of the butt joint between the contiguous packing strips, and that the packing strips are fitted together in the circumferential direction and the axial direction, the lobes of the first layer slidingly inserted in the cutouts being covered at the intersections by the relatively offset second layer of the packing strip.
  • Another form of construction is characterized by an approximately elastically deformable edge zone of the individual layers of the packing strips on the sides toward the bottom of the groove.
  • a special embodiment of the invention provides that plastically deformable packing inserts are inserted in the groove, on the groove bottom.
  • An advantageous form of construction is characterized according to the invention by the length of the packing strips, which in the axial direction and in the circumferential direction corresponds approximately to the length of the parts to be sealed from each other, minus one strip width.
  • the advantages of the invention reside, on the one hand, in that a separate securing of the packing strips against shifting becomes unnecessary, since the packing strips are mutually anchored by the intersecting layers of the packing strips, and on the other hand, in that even the radial gaps or passageways at the intersections are sealed almost completely.
  • the layers have a reinforcement of the cross-section area at the intersection where the greatest radial loads and expansion forces engage.
  • the cooling effect is improved in cooled turbomachines, the heat damming effect being influenced much more favorably at the intermediate sections or segments provided for this purpose, because the transfer of heat occurs now only be conduction, and not by radiation acting directly on the housing or rotor.
  • Another advantage of the invention is to be seen in that the packing strips are mutually strutted during every operational state by the narrow slideways of the lobes and cutouts, whereby the wear tendency is reduced.
  • turbo-machines packed according to the invention can, for example, be installed in the direct circuit of a gas-cooled atomic reactor. Also for the transport or poisonous or corrosionfavoring substances an advantage becomes attainable, since on the one hand a loss of the cooling gas or an admixture thereof into .the operating gas is practically avoided, and on the other hand the need for corrosionproof material is considerably reduced since the parts made of corrosion-resistant material are limited to the parts coming into direct contact with the aggressive operating gas.
  • FIG. 1 is an axial section througha turbo-rotor according to prior art
  • FIG. 2 is a radial section along line A-A in FIG. 1;
  • FIG. 1 there is marked by the reference symbol 1 the rotor of a turbo-machine, where in annular grooves 2 the blades 3 are inserted and anchored by means of their T-shaped'feet 4. Between the individual blade rows 5 and 5, intermediate sections 7 are inserted in annular grooves .6; between the blade feet 4 and the intermediate sections 7 there is thus formed a gap 8, which in uncooled machines permits penetration of the operating medium into the interstice 10. Thereby the rotor l is heated directly by the operating medium,
  • cooling gas must be supplied in large quantities and at a higher pressure than that at the pointin the flow channel 11' corresponding to the respective gap 8, to suppress the unhindered entrance of hot or operating gas into the interstice 10.
  • FIG. 2 shows a radial section through the turbo-rotor 1 along line A-A in FIG. 1, similar parts having been marked by corresponding reference symbols.
  • packing strips 9 have been provided, which are inserted in the axial direction at the circumference between the blade feet 4 and the intermediate sections not shown.
  • corresponding grooves 12 have been provided, which now extend in the axial direction instead of in circumferential direction like the grooves 12 (see FIG. 1).
  • FIG. 3 The section along line C-C in FIG. 1 shows the viewer a lattice-work or grid formed by the packing strips 9 and 9'. From this it is visible that there are still passageways 15 between the butt joints 13 of the packing strips 9 and 9' and also at the intersections 14.
  • FIG. 4 shows a detail of a radial section through a rotor 1 on a larger scale, a packing strip 16 of the form according to the invention being inserted in the groove 12 along the circumference.
  • the blade feet 4 are separated by the gap 8, which is blocked in radial direction by the first layer 17 of the packing strip 16.
  • the second layer 18 thereof is displaced in the example shown by approximately one blade division in the circumferential direction.
  • the length of the individual packing strips 16 is equal to double the division of the blade row less the strip width and double the width of gap 8.
  • the segment length is analogously taken as division.
  • the packing strip length in the axial direction is determined in the same manner as above, except that instead of the division measured at the blade row the distance between the blade rows 5 and 5' is considered.
  • the individual layers 19 and 20 of the packing strips 16' are inserted in axial direction, and this so that between the butt joints of the individual layers of the packing strips 16 a corresponding layer of the packing strip 16' is inserted crosswise.
  • FIG. 5 shows a transverse section of the packing strip 16 along line DD of FIG. 4, forces which in the operating state act on the layers 17 and 18 being indicated by the arrows.
  • the layers 17 and 18 of the packing strips are pressed firmly against one another at the mutual contact areas of the edge zones 22 as soon as the edges of the packing strips get into the zone of the groove base radius.
  • the packing strips 16 and 16 are provided at the edge zones 22, but not at the mutual contact areas of thelayers 17 and 18, with a slightly rounded 45 bevel. It is thereby achieved that material displaced by plastic deformation finds sufiicient space to give way and that besides the gripping forces act onthe edg zone 22 in an evenly distributed manner.
  • FIG. 6 a parallel perspective representation of an intersection 14.
  • the packing strips 16 and 16' again are composed of the individual layers 17, 18 and 19, 20, which are arranged in a staggered manner relative to each other.
  • the mere staggering of the individual layers 17 to 20 of the packing strips does not, however, achieve perfect tightness between flow channel 11 and interstice 10, which in the present FIG. 6 must be conceived above or respectively below the intersection 14.
  • the gap or joint8 is defined by the blade feet 4 and intermediate sections 7, the thin solid lines 24 and the broken lines 25 indicating the contours of the expansion joint 8.
  • the visible representation being limited to the upper layer 17 of the packing strip 16 and to the upper layer 19 of the packing strip 16.
  • lobes 27 corresponding to the cutouts 26.
  • These cutouts 26 and lobes 27 are arranged in like manner .with respect to all packing strip layers 17 to 20, so that expediently they can be simply exchanged for one another. This can be the case also when the axial lengths of the rotor blades are different than those of the intermediate sections 7.
  • the cutouts 26 in the individual layers of the packing strips 16 and 16' are provided with large curvatures, the radii of which preferably correspond to half the width of the cutout 26, so as to avoid as much as possible an additional notch effect at the individual layers 17 to 20 of the packing strips 16 and 16'.
  • the lobes 27 are likewise rounded, their form being adapted to that of the cutouts 26 and the width of the lobes being chosen so that the lobes 27 are guided for lateral sliding in the cutouts 26.
  • the width of the lobes 27 must, however, be greater in every state than the maximum width of the expansion joints 8 between parts to be packed.
  • the length of the lobes 27 is at least as great as the butt joints 23, so that a close guiding of the lobes 27 in the .cutouts 26 during every operating state is ensured.
  • the arrows indicate the possible path of the cooling gas or operating medium which remains open by the minimum gaps necessary for the adaptation of the gripping forces during operation. It can be seen that now any radial and axial passage of the medium is blocked in all directions.
  • FIG. 7 shows another embodiment of the invention, as used, for example, in gas turbine rotor packings.
  • insert 30 which simply absorbs the gripping forces by defonnation and yet insures sealing.
  • FIG. 8 shows the same construction as FIG. 7, the difference being that the packing strips 16 and the gap 8 have been changed by the temperature rise in the materials and the insert 30 is deformed in order to improve the tightness. This is achieved because the gas no longer flows along the longitudinal gap in the bottom of the groove to the next butt joint 23 between the packing strips 16, since the packing strips 16 form a tight strip offering gapless packing at the edge zones 22 clamped in the groove bottom.
  • the combination comprising a first set of packing strips inserted in grooves provided along those confronting sides of the blading which establish the axially extending gaps, a second set of packing strips inserted in grooves provided along those confronting sides of the blading which establish the circumferentially extending gaps that intersect said axially extending gaps, each' of said packing strips of each set being constituted by two layers which are shifted in a longitudinal direction relative to each other such that one layer of each strip of each set continues acrosseach intersection of said axial and circumferentially extending gaps while an end of the other layer of each strip of one set terminates at an intersection at the side of the layer of the other set which continues across said intersection, and means for inter
  • a packing arrangement for turbo-machines as defined in claim 1 wherein said means for interconnecting the layers of the strips of said first and second sets in axial and circumferential directions are constituted by inter-engaging lobes and cutouts provided on the layers.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Devices (AREA)
  • Gasket Seals (AREA)
US00207897A 1970-12-18 1971-12-14 Sealing element for a turbo-machine Expired - Lifetime US3801220A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1878370A CH525419A (de) 1970-12-18 1970-12-18 Dichtungsvorrichtung für Turbomaschinen

Publications (1)

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US3801220A true US3801220A (en) 1974-04-02

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Family Applications (1)

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US00207897A Expired - Lifetime US3801220A (en) 1970-12-18 1971-12-14 Sealing element for a turbo-machine

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US (1) US3801220A (de)
JP (1) JPS5421883B1 (de)
CH (1) CH525419A (de)
DE (1) DE2120171C3 (de)

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4265594A (en) * 1978-03-02 1981-05-05 Bbc Brown Boveri & Company Limited Turbine blade having heat localization segments
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
US4484858A (en) * 1981-12-03 1984-11-27 Hitachi, Ltd. Turbine rotor with means for preventing air leaks through outward end of spacer
US4655687A (en) * 1985-02-20 1987-04-07 Rolls-Royce Rotors for gas turbine engines
US4659289A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine side plate assembly
US4688988A (en) * 1984-12-17 1987-08-25 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US4749333A (en) * 1986-05-12 1988-06-07 The United States Of America As Represented By The Secretary Of The Air Force Vane platform sealing and retention means
US5374161A (en) * 1993-12-13 1994-12-20 United Technologies Corporation Blade outer air seal cooling enhanced with inter-segment film slot
US5865600A (en) * 1995-11-10 1999-02-02 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor
US5961286A (en) * 1996-12-27 1999-10-05 Asea Brown Boveri Ag Arrangement which consists of a number of fixing slots and is intended for fitting a rotor or a stator of a fluid-flow machine with blades
US6079944A (en) * 1997-10-21 2000-06-27 Mitsubishi Heavy Industries, Ltd. Gas turbine stationary blade double cross type seal device
US6086329A (en) * 1997-03-12 2000-07-11 Mitsubishi Heavy Industries, Ltd. Seal plate for a gas turbine moving blade
US6261053B1 (en) * 1997-09-15 2001-07-17 Asea Brown Boveri Ag Cooling arrangement for gas-turbine components
US6416276B1 (en) * 1999-03-29 2002-07-09 Alstom (Switzerland) Ltd Heat shield device in gas turbines
US20040051254A1 (en) * 2002-09-13 2004-03-18 Siemens Westinghouse Power Corporation Multidirectional turbine shim seal
US20040179937A1 (en) * 2001-09-25 2004-09-16 Erhard Kreis Seal arrangement for reducing the seal gaps within a rotary flow machine
US20050089398A1 (en) * 2003-10-28 2005-04-28 Martin Jutras Leakage control in a gas turbine engine
US20050173871A1 (en) * 2004-02-09 2005-08-11 Siemens Westinghouse Power Corporation Seal usable between thermally movable components
US20060083620A1 (en) * 2004-10-15 2006-04-20 Siemens Westinghouse Power Corporation Cooling system for a seal for turbine vane shrouds
US20060239814A1 (en) * 2005-02-07 2006-10-26 Mitsubishi Heavy Industries, Ltd Gas turbine having a sealing structure
US20100178173A1 (en) * 2006-10-17 2010-07-15 Scott Charlton Turbine blade assembly
US20120274034A1 (en) * 2011-04-27 2012-11-01 Richard Bouchard Seal arrangement for segmented gas turbine engine components
RU2564741C2 (ru) * 2011-07-01 2015-10-10 Альстом Текнолоджи Лтд Лопатка турбины и ротор турбины
US20170218784A1 (en) * 2016-02-03 2017-08-03 General Electric Company Spline seal for a gas turbine engine
US10215043B2 (en) * 2016-02-24 2019-02-26 United Technologies Corporation Method and device for piston seal anti-rotation
US10822988B2 (en) * 2015-12-21 2020-11-03 Pratt & Whitney Canada Corp. Method of sizing a cavity in a part
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
US10907487B2 (en) 2018-10-16 2021-02-02 Honeywell International Inc. Turbine shroud assemblies for gas turbine engines
US20230383667A1 (en) * 2022-05-31 2023-11-30 Pratt & Whitney Canada Corp. Joint between gas turbine engine components with bonded fastener(s)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2816791C3 (de) * 1977-05-03 1981-05-07 Vereinigte Edelstahlwerke Ag (Vew), Wien Gekühlter Läufer für eine axial durchströmte Turbine
FR2758856B1 (fr) * 1997-01-30 1999-02-26 Snecma Joint d'etancheite a plaquettes empilees glissant dans des fentes de reception
ATE483891T1 (de) 2006-12-19 2010-10-15 Alstom Technology Ltd Strömungsmaschine, insbesondere gasturbine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2858103A (en) * 1956-03-26 1958-10-28 Westinghouse Electric Corp Gas turbine apparatus

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2858103A (en) * 1956-03-26 1958-10-28 Westinghouse Electric Corp Gas turbine apparatus

Cited By (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
US4265594A (en) * 1978-03-02 1981-05-05 Bbc Brown Boveri & Company Limited Turbine blade having heat localization segments
US4484858A (en) * 1981-12-03 1984-11-27 Hitachi, Ltd. Turbine rotor with means for preventing air leaks through outward end of spacer
US4659289A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine side plate assembly
US4688988A (en) * 1984-12-17 1987-08-25 United Technologies Corporation Coolable stator assembly for a gas turbine engine
US4655687A (en) * 1985-02-20 1987-04-07 Rolls-Royce Rotors for gas turbine engines
US4749333A (en) * 1986-05-12 1988-06-07 The United States Of America As Represented By The Secretary Of The Air Force Vane platform sealing and retention means
US5374161A (en) * 1993-12-13 1994-12-20 United Technologies Corporation Blade outer air seal cooling enhanced with inter-segment film slot
US5865600A (en) * 1995-11-10 1999-02-02 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor
US5961286A (en) * 1996-12-27 1999-10-05 Asea Brown Boveri Ag Arrangement which consists of a number of fixing slots and is intended for fitting a rotor or a stator of a fluid-flow machine with blades
US6086329A (en) * 1997-03-12 2000-07-11 Mitsubishi Heavy Industries, Ltd. Seal plate for a gas turbine moving blade
US6261053B1 (en) * 1997-09-15 2001-07-17 Asea Brown Boveri Ag Cooling arrangement for gas-turbine components
US6079944A (en) * 1997-10-21 2000-06-27 Mitsubishi Heavy Industries, Ltd. Gas turbine stationary blade double cross type seal device
JP3462732B2 (ja) 1997-10-21 2003-11-05 三菱重工業株式会社 ガスタービン静翼のダブルクロスシール装置
US6416276B1 (en) * 1999-03-29 2002-07-09 Alstom (Switzerland) Ltd Heat shield device in gas turbines
US20040179937A1 (en) * 2001-09-25 2004-09-16 Erhard Kreis Seal arrangement for reducing the seal gaps within a rotary flow machine
US7175387B2 (en) * 2001-09-25 2007-02-13 Alstom Technology Ltd. Seal arrangement for reducing the seal gaps within a rotary flow machine
US20040051254A1 (en) * 2002-09-13 2004-03-18 Siemens Westinghouse Power Corporation Multidirectional turbine shim seal
US6883807B2 (en) * 2002-09-13 2005-04-26 Seimens Westinghouse Power Corporation Multidirectional turbine shim seal
US20050089398A1 (en) * 2003-10-28 2005-04-28 Martin Jutras Leakage control in a gas turbine engine
US7128522B2 (en) 2003-10-28 2006-10-31 Pratt & Whitney Canada Corp. Leakage control in a gas turbine engine
US20050173871A1 (en) * 2004-02-09 2005-08-11 Siemens Westinghouse Power Corporation Seal usable between thermally movable components
US7562880B2 (en) * 2004-02-09 2009-07-21 Siemens Energy, Inc. Seal usable between thermally movable components
US20060083620A1 (en) * 2004-10-15 2006-04-20 Siemens Westinghouse Power Corporation Cooling system for a seal for turbine vane shrouds
US7217081B2 (en) 2004-10-15 2007-05-15 Siemens Power Generation, Inc. Cooling system for a seal for turbine vane shrouds
US7549845B2 (en) * 2005-02-07 2009-06-23 Mitsubishi Heavy Industries, Ltd. Gas turbine having a sealing structure
US20060239814A1 (en) * 2005-02-07 2006-10-26 Mitsubishi Heavy Industries, Ltd Gas turbine having a sealing structure
US20100178173A1 (en) * 2006-10-17 2010-07-15 Scott Charlton Turbine blade assembly
RU2415272C2 (ru) * 2006-10-17 2011-03-27 Сименс Акциенгезелльшафт Узел лопаток турбины, газовая турбина, содержащая такой узел, и способ сборки узла лопаток турбины
CN101529054B (zh) * 2006-10-17 2012-06-20 西门子公司 涡轮叶片组件
US8545181B2 (en) * 2006-10-17 2013-10-01 Siemens Aktiengesellschaft Turbine blade assembly
US9534500B2 (en) * 2011-04-27 2017-01-03 Pratt & Whitney Canada Corp. Seal arrangement for segmented gas turbine engine components
US20120274034A1 (en) * 2011-04-27 2012-11-01 Richard Bouchard Seal arrangement for segmented gas turbine engine components
RU2564741C2 (ru) * 2011-07-01 2015-10-10 Альстом Текнолоджи Лтд Лопатка турбины и ротор турбины
US10822988B2 (en) * 2015-12-21 2020-11-03 Pratt & Whitney Canada Corp. Method of sizing a cavity in a part
US20170218784A1 (en) * 2016-02-03 2017-08-03 General Electric Company Spline seal for a gas turbine engine
US10494943B2 (en) * 2016-02-03 2019-12-03 General Electric Company Spline seal for a gas turbine engine
US10215043B2 (en) * 2016-02-24 2019-02-26 United Technologies Corporation Method and device for piston seal anti-rotation
US10865652B2 (en) 2016-02-24 2020-12-15 United Technologies Corporation Method and device for piston seal anti-rotation
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
US10907487B2 (en) 2018-10-16 2021-02-02 Honeywell International Inc. Turbine shroud assemblies for gas turbine engines
US20230383667A1 (en) * 2022-05-31 2023-11-30 Pratt & Whitney Canada Corp. Joint between gas turbine engine components with bonded fastener(s)
US12018567B2 (en) * 2022-05-31 2024-06-25 Pratt & Whitney Canada Corp. Joint between gas turbine engine components with bonded fastener(s)

Also Published As

Publication number Publication date
DE2120171A1 (de) 1972-06-22
CH525419A (de) 1972-07-15
DE2120171C3 (de) 1974-01-03
DE2120171B2 (de) 1973-06-14
JPS5421883B1 (de) 1979-08-02

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