EP2846002A1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

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Publication number
EP2846002A1
EP2846002A1 EP14150517.2A EP14150517A EP2846002A1 EP 2846002 A1 EP2846002 A1 EP 2846002A1 EP 14150517 A EP14150517 A EP 14150517A EP 2846002 A1 EP2846002 A1 EP 2846002A1
Authority
EP
European Patent Office
Prior art keywords
housing
sealing ring
outer sealing
gas turbine
turbine according
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.)
Granted
Application number
EP14150517.2A
Other languages
German (de)
English (en)
Other versions
EP2846002B1 (fr
Inventor
Walter Gieg
Petra Kufner
Rudolf Stanka
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP14150517.2A priority Critical patent/EP2846002B1/fr
Priority to US14/584,811 priority patent/US9416676B2/en
Publication of EP2846002A1 publication Critical patent/EP2846002A1/fr
Application granted granted Critical
Publication of EP2846002B1 publication Critical patent/EP2846002B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D11/08—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
    • 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
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such 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
    • 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
    • F01D11/127—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 a deformable or crushable structure, e.g. honeycomb
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/10—Basic functions
    • F05D2200/11—Sum
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3212—Application in turbines in gas turbines for a special turbine stage the first stage of a turbine
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49231—I.C. [internal combustion] engine making
    • Y10T29/49233—Repairing, converting, servicing or salvaging
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/53—Means to assemble or disassemble
    • Y10T29/53983—Work-supported apparatus

Definitions

  • the present invention relates to a gas turbine having a housing, an outer sealing ring, which is releasably attachable to the housing, and a clamping element for radially clamping the outer sealing ring and the housing against each other.
  • the document proposes to arrange a radial flange of the sealing ring axially positively between the C-clip and the housing.
  • the C-clip is acted upon by the gas force in the flow direction and thus clamps the radial flange of the sealing ring against the housing.
  • An object of one embodiment of the present invention is to provide an improved gas turbine.
  • a gas turbine in particular an aircraft engine gas turbine, a housing, an outer sealing ring, which is detachably attachable to the housing, in particular fixed, and a clamping element for radially clamping the outer sealing ring and the housing against each other, the in one embodiment, the outer sealing ring and the housing radially braced against each other and so frictionally secured together.
  • An anti-rotation device for preventing rotation or positive limiting a relative movement in the circumferential direction between the housing and outer sealing ring has one or more in the circumferential direction of each other, preferably at least substantially equidistant, spaced housing grooves, which extend in an embodiment, at least substantially, in the axial direction.
  • the groove (s) may be radially open or closed radially, with radially outwardly open grooves advantageously can be advantageous manufacturing and / or assembly technology, radially outwardly closed grooves, however, can advantageously protect the rotation.
  • housing grooves in each case engage one or more radial flanges of the outer sealing ring and (twist) secure the housing and outer sealing ring in a form-fitting manner in the circumferential direction.
  • a radial tension or a frictional engagement between the housing and the outer sealing ring and thus wear can be reduced.
  • the one or more radial flanges are arranged with play in the axial direction in the housing or the grooves.
  • the one or more radial flanges may be arranged with play in the circumferential direction in the housing or the grooves.
  • the assembly can be simplified and / or manufacturing tolerances and / or thermal deformations can be compensated.
  • the housing groove (s) is / are open at the end side opposite to the throughflow direction.
  • the housing groove (s) opens or opens into a housing front side in the direction of flow or open in this.
  • the sealing ring can advantageously be pulled axially out of its mounting position out of the housing front or housing because its radial flange (e) need not be removed from a groove closed against the direction of flow For example, by initial tilting or the like.
  • an axial length of the housing groove (s) from a housing front side in the direction of flow is greater than an axial wall thickness of the radial flange or the radial flanges.
  • the outer sealing ring is divided or segmented into two or more ring segments.
  • advantageously the production, assembly and / or disassembly can be improved.
  • the clamping element is annular, ring-shaped in another embodiment.
  • the clamping element may be formed in several parts and two or more, over the circumference, in particular at least substantially equidistant, distributed ring segments, wherein the sum of the circumferential lengths of the ring segments of the circumferential length of rotation, but also, in particular, may be lower.
  • the clamping element may have one or more so-called C-clips.
  • the clamping element in one embodiment has a, in particular C- or U-shaped, cross-section with a radially outer limb, which is supported on an outer circumferential surface of the housing, and a radially inner limb, which is supported on an inner circumferential surface of the outer sealing ring element, wherein the radially outer leg, the radially inner leg and / or a connection between the two legs is elastically deformed so as to radially clamp housing and outer sealing ring against each other.
  • the gas turbine has a rotor which is arranged radially opposite the outer sealing ring element in the housing.
  • the rotor or the outer sealing ring element may in particular be a first, a gas inlet next or in the flow direction first rotor or a foremost, a gas inlet next or in the flow direction first outer sealing ring element.
  • the rotor or the outer-sealing-ring element may be the first of the high-pressure turbine or the low-pressure turbine.
  • the housing may be the housing of the high-pressure turbine or the low-pressure turbine.
  • Fig. 3 shows a part of a gas turbine according to Fig. 2 of the US 2007/0231132 A1 , to the description of which reference is made and the contents of which are incorporated in the present disclosure.
  • the gas turbine of Fig. 3 has a housing 1 'to which an outer sealing ring 2' is attached with a Honigwabendichtung.
  • a C-clip 3 ' clamps an annular Radial flange 20 'of the sealing ring axially positive fit against the housing.
  • the C-clip is acted upon by the gas force on a preceding vane 12 in the flow direction and thus clamps the radial flange of the sealing ring against the housing.
  • Fig. 1 shows in Fig. 3 corresponding representation of a section along the line II in Fig. 2 a portion of an aircraft engine gas turbine according to an embodiment of the present invention.
  • Fig. 2 shows a section along the line II-II in Fig. 1 , Corresponding elements are designated by the same reference numerals distinguished by an apostrophe.
  • This comprises a housing 1, an outer sealing ring 2, which is releasably secured to the housing, and a clamping element 3, which is the outer sealing ring and the housing radially (vertically in Fig. 1 ) clamped against each other and so frictionally secured together.
  • Housing 1 and outer sealing ring 2 have an anti-rotation with a plurality of circumferentially spaced apart housing grooves 10 which extend in the axial direction (horizontally in Fig. 1, 2 ). In the radial direction, the grooves are radially outward (top in FIG Fig. 1 ) open.
  • each housing groove 10 of the housing 1 engages in each case a radial flange 20 of the outer sealing ring 2, thus securing the housing and outer sealing ring in a form-fitting manner in the circumferential direction (vertically in FIG Fig. 2 ).
  • the radial flanges are arranged with play s a in the axial direction in the housing grooves.
  • the radial flanges also play in the circumferential direction to the housing grooves, which in Fig. 2 is recognizable.
  • the housing grooves are frontally opposite to the direction of flow (to the left in Fig. 1, 2 ) open.
  • the housing grooves opens or open into a housing front side 11 in the direction of flow.
  • the sealing ring 2 can advantageously be axially opposite Flow direction (to the left in Fig. 1, 2 ) from his in Fig. 1, 2 shown mounting position out of the housing end face 11 and the housing 1 are pulled out.
  • the axial length t 1 of the housing grooves 10 from the housing front side 11 in the direction of flow is greater than the axial wall thickness t 2 of the radial flanges 20.
  • the outer sealing ring is divided into several ring segments or segmented (not shown).
  • the clamping element is formed in several parts ring segment-shaped and has a plurality of distributed over the circumference ring segments in the form of C-clips. Accordingly, the clamping element has an in Fig. 1 recognizable C-shaped cross-section with a radially outer leg 31, which is supported on an outer peripheral surface of the housing 1, and a radially inner leg 32, which is supported on an inner peripheral surface of the outer sealing ring element 2, wherein the radially outer leg, the radially inner leg and / or a connection between the two legs is elastically deformed so as to radially clamp housing and outer sealing ring against each other.
  • the gas turbine has a first rotor 18 in the direction of flow (in FIG Fig. 1 not shown, cf. For this Fig. 3 ).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
EP14150517.2A 2013-09-06 2014-01-09 Turbine à gaz Active EP2846002B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14150517.2A EP2846002B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz
US14/584,811 US9416676B2 (en) 2013-09-06 2014-12-29 Gas turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP13183274.3A EP2846001B1 (fr) 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé
EP14150517.2A EP2846002B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz

Publications (2)

Publication Number Publication Date
EP2846002A1 true EP2846002A1 (fr) 2015-03-11
EP2846002B1 EP2846002B1 (fr) 2019-11-20

Family

ID=49123719

Family Applications (3)

Application Number Title Priority Date Filing Date
EP13183274.3A Active EP2846001B1 (fr) 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé
EP14150518.0A Active EP2846003B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz, procédés de montage et de démontage associés d'un rotor d'une turbine à gaz
EP14150517.2A Active EP2846002B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz

Family Applications Before (2)

Application Number Title Priority Date Filing Date
EP13183274.3A Active EP2846001B1 (fr) 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé
EP14150518.0A Active EP2846003B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz, procédés de montage et de démontage associés d'un rotor d'une turbine à gaz

Country Status (3)

Country Link
US (5) US10125627B2 (fr)
EP (3) EP2846001B1 (fr)
ES (3) ES2935815T3 (fr)

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DE102013224199A1 (de) * 2013-11-27 2015-05-28 MTU Aero Engines AG Gasturbinen-Laufschaufel
US20170089213A1 (en) 2015-09-28 2017-03-30 United Technologies Corporation Duct with additive manufactured seal
US10370996B2 (en) 2016-08-23 2019-08-06 United Technologies Corporation Floating, non-contact seal with offset build clearance for load imbalance
US10385715B2 (en) 2016-08-29 2019-08-20 United Technologies Corporation Floating, non-contact seal with angled beams
US10550708B2 (en) 2016-08-31 2020-02-04 United Technologies Corporation Floating, non-contact seal with at least three beams
DE102016222608A1 (de) 2016-11-17 2018-05-17 MTU Aero Engines AG Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine
JP6684698B2 (ja) * 2016-12-12 2020-04-22 三菱重工エンジン＆ターボチャージャ株式会社 ターボチャージャ
US20190218928A1 (en) * 2018-01-17 2019-07-18 United Technologies Corporation Blade outer air seal for gas turbine engine
CN108533333B (zh) * 2018-05-05 2023-10-13 宁波天生密封件有限公司 一种汽轮机插管密封装置及其使用方法
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
DE102018210600A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Mantelringanordnung für eine strömungsmaschine
FR3083563B1 (fr) * 2018-07-03 2020-07-24 Safran Aircraft Engines Module d'etancheite de turbomachine d'aeronef
FR3092861B1 (fr) * 2019-02-18 2023-02-10 Safran Aircraft Engines Ensemble de turbomachine comportant un taquet sur un jonc d'etancheite
IT201900014736A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di tenuta integrali per pale trattenute in un rotore a tamburo esterno anulare girevole in una turbomacchina.
CN113814915B (zh) * 2020-06-18 2022-11-04 中国航发商用航空发动机有限责任公司 固定夹具、装配组件及组装方法

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Also Published As

Publication number Publication date
US20180347388A1 (en) 2018-12-06
US9416676B2 (en) 2016-08-16
EP2846001A1 (fr) 2015-03-11
US11268398B2 (en) 2022-03-08
EP2846001B1 (fr) 2023-01-11
USRE48320E1 (en) 2020-11-24
ES2752555T3 (es) 2020-04-06
EP2846003A1 (fr) 2015-03-11
EP2846003B1 (fr) 2019-10-16
US20150192026A1 (en) 2015-07-09
ES2762511T3 (es) 2020-05-25
US9822657B2 (en) 2017-11-21
EP2846002B1 (fr) 2019-11-20
ES2935815T3 (es) 2023-03-10
US20150071769A1 (en) 2015-03-12
US20150192028A1 (en) 2015-07-09
US10125627B2 (en) 2018-11-13

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