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US20120107136A1 - Sealing plate and rotor blade system - Google Patents

Sealing plate and rotor blade system Download PDF

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Publication number
US20120107136A1
US20120107136A1 US13/258,011 US201013258011A US2012107136A1 US 20120107136 A1 US20120107136 A1 US 20120107136A1 US 201013258011 A US201013258011 A US 201013258011A US 2012107136 A1 US2012107136 A1 US 2012107136A1
Authority
US
United States
Prior art keywords
sealing plate
metal sheets
turbine
rotor
rotor blade
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
US13/258,011
Other languages
English (en)
Inventor
Tobias Buchal
Sascha Dungs
Winfried Esser
Birgit Grüger
Oliver Lüsebrink
Mirko Milazar
Nicolas Savilius
Oliver Schneider
Peter Schröder
Waldemar Socha
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Socha, Waldemar, GRUEGER, BIRGIT, DUNGS, SASCHA, BUCHAL, TOBIAS, ESSER, WINFRIED, LUESEBRINK, OLIVER, SAVILIUS, NICOLAS, SCHNEIDER, OLIVER, SCHROEDER, PETER, MILAZAR, MIRKO
Publication of US20120107136A1 publication Critical patent/US20120107136A1/en
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
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding

Definitions

  • the invention refers to a sealing plate for forming a ring consisting of sealing plates for the rotor of a gas turbine, which sealing plate is formed principally from a multiplicity of metal sheets.
  • the invention refers to a rotor blade system, especially for a gas turbine, having a number of rotor blades which are arranged annularly on a turbine disk, wherein a number of sealing plates are arranged on a side surface of the turbine disk. It furthermore refers to a gas turbine having such a rotor blade system.
  • Gas turbines are used in many fields for driving generators or driven machines.
  • the energy content of a fuel is utilized for producing rotational movement of a turbine shaft.
  • the fuel is combusted in a combustion chamber, wherein compressed air is supplied from an air compressor.
  • the operating medium, under high pressure and at high temperature, which is produced in the combustion chamber as a result of the combustion of the fuel, is directed in this case through a turbine unit—which is connected downstream to the combustion chamber—where it expands, performing work.
  • a number of rotor blades which are customarily assembled into blade groups or blade rows, are arranged on this shaft.
  • a turbine disk on which the rotor blades are fastened by means of their blade root, are customarily provided for each turbine stage.
  • stator blades which are connected to the turbine casing and assembled to form stator-blade rows, are customarily arranged between adjacent rotor blade rows.
  • the combustion chamber of the gas turbine can be constructed as a so-called annular combustion chamber in which a large number of burners, which are arranged around the turbine shaft in the circumferential direction, open into a common combustion chamber space which is enclosed by a high temperature-resistant surrounding wall.
  • the combustion chamber is designed in its entirety as an annular structure.
  • provision may also be made for a multiplicity of combustion chambers.
  • first stator blade row of a turbine unit which together with the immediately subsequent rotor blade row, as seen in the flow direction of the operating medium, forms a first turbine stage of the turbine unit, to which further turbine stages are customarily connected downstream.
  • the sealing plates fulfill even further functions. On the one hand, they form the axial fixing of the turbine blades by means of corresponding fastening elements, and on the other hand, they seal not only the turbine disk against penetration of hot gas from outside but also avoid escape of cooling air which is guided inside the turbine disk and is customarily passed on for cooling of the turbine blades themselves.
  • Such sealing plates with integrated sealing wing are customarily produced by vacuum investment casting (for example in the lost-wax investment casting process).
  • a certain overmeasure is to be provided in order to be able to compensate for process-induced dimensional inaccuracies.
  • these, however, can frequently be produced from alloys which, near net shape, cannot be produced in a process other than in the described vacuum investment casting.
  • the invention is therefore based on the object of disclosing a sealing plate and a rotor blade system which, with a highest possible efficiency of a gas turbine, allows in each case a simplified construction at the same time.
  • the invention is based in this case on the consideration that a particularly simple producibility of the sealing plate would be achievable if the previously customary investment casting process with subsequent mechanical after-machining could be either simplified or completely replaced by another production process.
  • casting processes other than the described vacuum investment casting are not a possibility on account of the selected materials for the sealing plates. Therefore, the sealing plate should not be produced in an archetypal process, such as casting, but in a forming process.
  • the sealing plates should be produced from a multiplicity of basic parts by means of forming. This can be achieved in a particularly simple manner by forming of prefabricated metal sheets, that is to say the sealing plate should be produced from a multiplicity of metal sheets.
  • the sealing plate in this case comprises two metal sheets which are arranged a distance apart and parallel to the plane of the sealing plate. These form the respective end faces of the sealing plate and via the distance between the two metal sheets the thickness of the sealing plate can be accurately selected. In this case, a gap remains between the metal sheets and can be utilized for conducting cooling air and therefore for internal cooling of the sealing plate.
  • a particularly simple construction of the sealing plate is therefore possible, and on the other hand, as a result of active component cooling, the sealing plate can stand up to the most adverse circumstances during operation so that particularly high temperatures during operation of the gas turbine become possible and therefore particularly high efficiency is achieved.
  • an intermediate metal sheet with a number of cutouts is arranged between the metal sheets in this case.
  • Such an intermediate metal sheet stabilizes the connection between the metal sheets of the sealing plate which function as end faces and enables a precise, specific choice of the distance.
  • a conducting of cooling air through the interior of the sealing plate still remains possible with the described advantages.
  • the respective metal sheet, on the side facing the middle of the turbine disk advantageously has a bend in this case.
  • a bend which can be simply produced by forming, enables the sealing plate to be fixed in a groove provided for it on the side facing the middle of the turbine disk and so to ensure a secure retention of the sealing plate and of the rotor blades on the turbine disk.
  • This offers the advantage that despite the altered construction of the sealing plate the previously used fastening devices on the turbine disk do not have to be modified and therefore a particularly simple construction of the rotor blade system with sealing plate and turbine disk is possible.
  • the respective metal sheet advantageously has a number of cooling air holes.
  • the cooling air holes should be facing the turbine disk in this case so that a cooling air feed through the turbine disk into the sealing plate is possible, and on the outlet side provision should be made for cooling air holes which point towards adjacent components or attached metal sheets of the sealing plate, for example, so that active cooling of these components is also possible.
  • the sealing plate advantageously comprises a metal sheet which points from the plane of the sealing plate. This should reach up to the adjacent rotor blade row and so prevent penetration of hot gas in the direction of the turbine shaft in order to protect the components which are provided there.
  • the various metal sheets are welded and/or soldered to each other.
  • a particularly simple construction of the sealing plate consisting of a multiplicity of metal sheets is possible.
  • the construction of the sealing plate which is achieved in this way, especially with a triple-layer design with two metal sheets forming the end faces and an intermediate metal sheet with cutouts for cooling air, is in a position to provide a tongue-in-groove connection for sealing a plurality of sealing plates, lying next to each other, in the circumferential direction.
  • a groove and/or a tongue is advantageously arranged in the region of an edge of the respective sealing plate.
  • Such a groove in the case of a triple-layer design of the sealing plate in the style described above is simply possible by shortening the intermediate metal sheet on the edge or a tongue is possible by lengthening the intermediate metal sheet on the edge. As a result, a particularly good and simple to realize seal in the circumferential direction between a plurality of sealing plates is possible.
  • a gas turbine advantageously comprises such a rotor blade system and also a gas and steam turbine plant comprises a gas turbine with such a rotor blade system.
  • the advantages which are achieved using the invention are especially that as a result of the construction of the sealing plate by means of a multiplicity of metal sheets a particularly simple design and construction of the sealing plate become possible.
  • the production costs and material costs are low in this case in comparison to other methods.
  • the flexible material pairing the material use and costs arising therefrom can be reduced.
  • the active component cooling by means of conducting cooling air in the sealing plate lower restrictions for the hot gas temperature in a gas turbine ensue and a higher efficiency can be achieved overall.
  • FIG. 1 shows a half-section through a rotor blade system
  • FIG. 2 shows a section through a sealing plate after the casting process
  • FIG. 3 shows a cross section through a sealing plate after mechanical after-machining
  • FIG. 4 shows a cross section through a sealing plate which is produced from a plurality of metal sheets
  • FIG. 5 shows a top view of an intermediate metal sheet for a sealing plate
  • FIG. 6 shows a top view of a sealing plate which is produced from a multiplicity of metal sheets
  • FIG. 7 shows a half-section through a gas turbine.
  • FIG. 1 shows a rotor blade system 1 as a section through the outer circumference of a turbine disk 6 , attached on a turbine shaft, of a rotor blade stage of a gas turbine according to the prior art.
  • a rotor blade 12 is arranged in a rotor blade retaining slot 30 by its blade root 32 in this case.
  • the blade root 32 of the rotor blade 12 is of a firtree shape in cross section and corresponds to the firtree shape of the rotor blade retaining slot 30 .
  • the schematic representation of the contour of the rotor blade root 32 and that of the rotor blade retaining slot 30 is reproduced in a manner rotated by 90° compared with the rest of the view of FIG. 2 . Therefore, the depicted rotor blade retaining slot 30 extends between the side surfaces 34 of the turbine disk 6 .
  • stator blades 36 Adjacently provided in each case are stator blades 36 , not shown in more detail, which are arranged upstream and downstream of the rotor blade 12 —as seen in the flow direction of the operating medium of the gas turbine.
  • the stator blades 36 are arranged radially in rings in this case.
  • sealing plates 40 are inserted in each case on the sidewalls 34 in an encompassing shingle-like manner. These are retained by their upper side in a groove 42 which is introduced into the rotor blade 12 and by their lower side are fixed by means of a locking bolt, which is not shown in more detail.
  • the sealing plates 40 fulfill a plurality of tasks in this case.
  • the sealing wings 46 which extend essentially in the axial and azimuthal directions, they seal the gap between turbine disk 36 and adjacent stator blades 36 against penetration of hot operating medium M from the turbine.
  • the sealing plates 40 also ensure axial fixing of the blade root 32 in the rotor blade retaining slot 30 and so secure these against axial displacement.
  • the axial and azimuthal securing is already achieved as a result of the firtree shape of the rotor blade retaining slot 30 .
  • the sealing plates 40 prevent escape of cooling air which is introduced through cooling air passages 48 , via the turbine disk 36 , into the blade root 32 and into the rotor blade 12 .
  • FIGS. 2 and 3 schematically show a cross section perpendicular to the plane 49 of a sealing plate 40 according to the prior art in two different stages of the production process.
  • the sealing plate 40 in this case is first cast with a specific dimension.
  • a vacuum investment casting process is customarily used and then the sealing plates 40 , after casting, are compressed by means of hot-isostatic pressing for eliminating porosity.
  • a mechanical after-machining is then carried out in order to bring the sealing plate 40 to the finished contour shown in FIG. 3 .
  • the sealing plate 40 should therefore be produced from a multiplicity of metal sheets 50 , as shown in FIG. 4 .
  • the sealing plate 40 according to FIG. 4 in this case initially comprises two metal sheets 50 , which are arranged a distance apart parallel to the plane 49 of the sealing plate, between which an intermediate metal sheet 52 is introduced. Therefore, a triple-layer construction of the sealing plate 40 is created as a whole.
  • the metal sheets 50 comprise bends 54 in this case, which simulate the previously cast shape of the sealing plate 40 .
  • the intermediate metal sheet 52 is not solidly constructed but comprises a number of cutouts 56 which are also shown in top view in FIG. 5 . As a result, a feed of cooling air K through cooling air holes 58 is possible, enabling active cooling of the sealing plate 40 .
  • the sealing plate 40 comprises a metal sheet 50 which points from the plane 49 of the sealing plate, faulting a sealing wing 46 .
  • a further supporting metal sheet 60 is provided in this case.
  • the cooling air holes 58 are oriented on the discharge side so that cooling air K which discharges from the sealing plate 40 flows onto, and so also cools, the sealing wing 46 and additional adjacent components.
  • the individual metal sheets 50 are welded to each other, which enables a particularly simple construction of the sealing plate 40 .
  • the metal sheets 50 can also be high-temperature soldered.
  • the sealing plate 40 is shown once more in top view in FIG. 6 .
  • the intermediate metal sheet 52 is displaced in the circumferential direction in relation to the two metal sheets 50 which are oriented in parallel so that on one edge 62 of the sealing plate 40 a groove 64 is formed and on the opposite edge 66 a tongue 68 is formed.
  • adjacent sealing plates 40 can be sealed in the circumferential direction by means of a tongue-in-groove connection.
  • a gas turbine 101 has a compressor 102 for combustion air, a combustion chamber 104 and also a turbine unit 106 for driving the compressor 102 and for driving a generator or a driven machine, which is not shown.
  • the turbine unit 106 and the compressor 102 are arranged on a common turbine shaft 108 which is also referred to as a turbine rotor to which the generator or the driven machine is also connected, and which is rotatably mounted around its center axis 109 .
  • the combustion chamber 104 which is constructed in the style of an annular combustion chamber is equipped with a number of burners 110 for combusting a liquid fuel or gaseous fuel.
  • the turbine unit 106 has a rotor blade system 1 having a number of rotatable rotor blades 12 which are connected to the turbine shaft 108 .
  • the rotor blades 12 are arranged on the turbine shaft 108 in a ring-like manner and therefore form a number of rotor blade rows.
  • the turbine unit 106 comprises a number of fixed stator blades 36 which are also fastened in a ring-like manner on a stator blade carrier 110 of the turbine unit 106 , forming stator blade rows.
  • the rotor blades 12 in this case serve for driving the turbine shaft 108 as a result of impulse transfer from the operating medium M which flows through the turbine unit 106 .
  • the stator blades 36 serve for flow guiding of the operating medium M between two consecutive rotor blade rows or rotor blade rings in each case, as seen in the flow direction of the operating medium M.
  • a consecutive pair consisting of a ring of stator blades 36 or a stator blade row and a ring of rotor blades 12 or a rotor blade row, in this case is also referred to as a turbine stage.
  • each stator blade 36 has a blade root 118 which, as a wall element, is arranged for the fixing of the respective stator blade 36 on the stator blade carrier 110 of the turbine unit 106 .
  • the blade root 118 in this case is a thermally comparatively heavily loaded component which forms the outer limit of a hot gas passage for the operating medium M which flows through the turbine unit 106 .
  • a ring segment 121 is arranged in each case on a stator blade carrier 110 of the turbine unit 106 .
  • the outer surface of each ring segment 121 is also exposed in this case to the hot operating medium M which flows through the turbine unit 106 and by means of a gap is at a distance in the radial direction from the outer end of the rotor blades 12 which lie opposite it.
  • the ring segments 121 which are arranged between adjacent stator blade rows serve in this case especially as cover elements which protect the inner casing in the stator blade carrier 110 , or other installed components in the casing, against theimal overstress as a result of the hot operating medium M which flows through the turbine 106 .
  • the combustion chamber 104 is designed as a so-called annular combustion chamber in the exemplary embodiment, in which a multiplicity of burners 110 , which are arranged circumferentially around the turbine shaft 108 , open into a common combustion chamber space.
  • the combustion chamber 104 is designed in its entirety as an annular structure which is positioned around the turbine shaft 108 .
  • a sealing plate 40 for a rotor blade system 1 which is produced from various metal sheets 50 , offers on the one hand a particularly simple and inexpensive production, and on the other hand a particularly high efficiency of a gas turbine 101 can be achieved as a result of the active component cooling.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/258,011 2009-03-27 2010-03-25 Sealing plate and rotor blade system Abandoned US20120107136A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09004469A EP2236759A1 (fr) 2009-03-27 2009-03-27 Système d'aube
EP09004469.4 2009-03-27
PCT/EP2010/053917 WO2010108983A1 (fr) 2009-03-27 2010-03-25 Plaque d'étanchéité et système d'aubes mobiles

Publications (1)

Publication Number Publication Date
US20120107136A1 true US20120107136A1 (en) 2012-05-03

Family

ID=40912036

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/258,011 Abandoned US20120107136A1 (en) 2009-03-27 2010-03-25 Sealing plate and rotor blade system

Country Status (6)

Country Link
US (1) US20120107136A1 (fr)
EP (2) EP2236759A1 (fr)
JP (1) JP5336649B2 (fr)
CN (1) CN102365425B (fr)
ES (1) ES2517921T3 (fr)
WO (1) WO2010108983A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160273370A1 (en) * 2015-03-20 2016-09-22 Rolls-Royce Plc Bladed rotor arrangement and a lock plate for a bladed rotor arrangement
US20180291751A1 (en) * 2017-04-11 2018-10-11 Doosan Heavy Industries & Construction Co., Ltd. Retainer for gas turbine blade, turbine unit and gas turbine using the same
US20190078439A1 (en) * 2017-09-13 2019-03-14 Doosan Heavy Industries & Construction Co., Ltd. Structure for cooling turbine blades and turbine and gas turbine including the same

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3021692B1 (fr) * 2014-05-27 2016-05-13 Snecma Platine d'etancheite a fonction de fusible
WO2017113258A1 (fr) * 2015-12-30 2017-07-06 Siemens Aktiengesellschaft Turbine à gaz, couvercle d'étanchéité et leur procédé de fabrication
CN109746631A (zh) * 2017-11-02 2019-05-14 西门子公司 用于燃气轮机的密封盖板的制造方法、装置和存储介质
CN114215611B (zh) * 2021-12-01 2023-07-14 东方电气集团东方汽轮机有限公司 一种燃气轮机透平动叶轴向定位用气封装配体

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US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US3010696A (en) * 1955-09-26 1961-11-28 Rolls Royce Bladed rotor with means to supply fluid to passages in the blades
GB905582A (en) * 1960-05-26 1962-09-12 Rolls Royce Improvements relating to the sealing of blades in a bladed rotor
GB947553A (en) * 1962-05-09 1964-01-22 Rolls Royce Gas turbine engine
US3490852A (en) * 1967-12-21 1970-01-20 Gen Electric Gas turbine rotor bucket cooling and sealing arrangement
US3807898A (en) * 1970-03-14 1974-04-30 Secr Defence Bladed rotor assemblies
US4309145A (en) * 1978-10-30 1982-01-05 General Electric Company Cooling air seal
US5030063A (en) * 1990-02-08 1991-07-09 General Motors Corporation Turbomachine rotor
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5954477A (en) * 1996-09-26 1999-09-21 Rolls-Royce Plc Seal plate
US6065932A (en) * 1997-07-11 2000-05-23 Rolls-Royce Plc Turbine
US6439844B1 (en) * 2000-12-11 2002-08-27 General Electric Company Turbine bucket cover and brush seal
US6786695B2 (en) * 2002-11-14 2004-09-07 General Electric Company Rod and groove for sealing or adjusting axial location of turbine parts and methods of use
US6857849B2 (en) * 2001-12-22 2005-02-22 Alston Technology Ltd. Membrane seals
US7186078B2 (en) * 2003-07-04 2007-03-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
US7465149B2 (en) * 2006-03-14 2008-12-16 Rolls-Royce Plc Turbine engine cooling
US20090004012A1 (en) * 2007-06-27 2009-01-01 Caprario Joseph T Cover plate for turbine rotor having enclosed pump for cooling air

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US3834831A (en) * 1973-01-23 1974-09-10 Westinghouse Electric Corp Blade shank cooling arrangement
US3853425A (en) * 1973-09-07 1974-12-10 Westinghouse Electric Corp Turbine rotor blade cooling and sealing system
FR2694046B1 (fr) * 1992-07-22 1994-09-23 Snecma Dispositif d'étanchéité et de rétention pour un rotor entaillé de brochages recevant des pieds d'aubes.
JP2000310101A (ja) * 1999-04-27 2000-11-07 Mitsubishi Heavy Ind Ltd ガスエキスパンダ
DE19950109A1 (de) * 1999-10-18 2001-04-19 Asea Brown Boveri Rotor für eine Gasturbine
JP3864157B2 (ja) * 2003-12-05 2006-12-27 本田技研工業株式会社 軸流型タービンホイール
EP1944472A1 (fr) * 2007-01-09 2008-07-16 Siemens Aktiengesellschaft Partie axiale d'un rotor de turbine, élément d'étanchéité pour un rotor équipé d'aubes de rotor d'une turbine et rotor de turbine
US7566201B2 (en) * 2007-01-30 2009-07-28 Siemens Energy, Inc. Turbine seal plate locking system

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US3010696A (en) * 1955-09-26 1961-11-28 Rolls Royce Bladed rotor with means to supply fluid to passages in the blades
GB905582A (en) * 1960-05-26 1962-09-12 Rolls Royce Improvements relating to the sealing of blades in a bladed rotor
GB947553A (en) * 1962-05-09 1964-01-22 Rolls Royce Gas turbine engine
US3490852A (en) * 1967-12-21 1970-01-20 Gen Electric Gas turbine rotor bucket cooling and sealing arrangement
US3807898A (en) * 1970-03-14 1974-04-30 Secr Defence Bladed rotor assemblies
US4309145A (en) * 1978-10-30 1982-01-05 General Electric Company Cooling air seal
US5030063A (en) * 1990-02-08 1991-07-09 General Motors Corporation Turbomachine rotor
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5954477A (en) * 1996-09-26 1999-09-21 Rolls-Royce Plc Seal plate
US6065932A (en) * 1997-07-11 2000-05-23 Rolls-Royce Plc Turbine
US6439844B1 (en) * 2000-12-11 2002-08-27 General Electric Company Turbine bucket cover and brush seal
US6857849B2 (en) * 2001-12-22 2005-02-22 Alston Technology Ltd. Membrane seals
US6786695B2 (en) * 2002-11-14 2004-09-07 General Electric Company Rod and groove for sealing or adjusting axial location of turbine parts and methods of use
US7186078B2 (en) * 2003-07-04 2007-03-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
US7465149B2 (en) * 2006-03-14 2008-12-16 Rolls-Royce Plc Turbine engine cooling
US20090004012A1 (en) * 2007-06-27 2009-01-01 Caprario Joseph T Cover plate for turbine rotor having enclosed pump for cooling air

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160273370A1 (en) * 2015-03-20 2016-09-22 Rolls-Royce Plc Bladed rotor arrangement and a lock plate for a bladed rotor arrangement
US10041362B2 (en) * 2015-03-20 2018-08-07 Rolls-Royce Plc Bladed rotor arrangement and a lock plate for a bladed rotor arrangement
US20180291751A1 (en) * 2017-04-11 2018-10-11 Doosan Heavy Industries & Construction Co., Ltd. Retainer for gas turbine blade, turbine unit and gas turbine using the same
US10648350B2 (en) * 2017-04-11 2020-05-12 DOOSAN Heavy Industries Construction Co., LTD Retainer for gas turbine blade, turbine unit and gas turbine using the same
US20190078439A1 (en) * 2017-09-13 2019-03-14 Doosan Heavy Industries & Construction Co., Ltd. Structure for cooling turbine blades and turbine and gas turbine including the same
US10662777B2 (en) * 2017-09-13 2020-05-26 DOOSAN Heavy Industries Construction Co., LTD Structure for cooling turbine blades and turbine and gas turbine including the same

Also Published As

Publication number Publication date
JP2012522161A (ja) 2012-09-20
JP5336649B2 (ja) 2013-11-06
WO2010108983A1 (fr) 2010-09-30
EP2411631A1 (fr) 2012-02-01
ES2517921T3 (es) 2014-11-04
EP2236759A1 (fr) 2010-10-06
EP2411631B1 (fr) 2014-09-03
CN102365425B (zh) 2015-08-19
CN102365425A (zh) 2012-02-29

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