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EP2853685A1 - Elément d'insertion et turbine à gaz - Google Patents

Elément d'insertion et turbine à gaz Download PDF

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Publication number
EP2853685A1
EP2853685A1 EP13185947.2A EP13185947A EP2853685A1 EP 2853685 A1 EP2853685 A1 EP 2853685A1 EP 13185947 A EP13185947 A EP 13185947A EP 2853685 A1 EP2853685 A1 EP 2853685A1
Authority
EP
European Patent Office
Prior art keywords
insert element
ring segment
gas turbine
shroud
blade row
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.)
Withdrawn
Application number
EP13185947.2A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Michael HÄNDLER
Kevin KAMPKA
Christian Kowalski
Christian Kowalzik
Nihal Kurt
Stefan Schmitt
Peter Schröder
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP13185947.2A priority Critical patent/EP2853685A1/fr
Priority to JP2016516887A priority patent/JP6227765B2/ja
Priority to EP14758840.4A priority patent/EP3022395B1/fr
Priority to CN201480052860.8A priority patent/CN105593470B/zh
Priority to US15/023,391 priority patent/US10018051B2/en
Priority to PCT/EP2014/068359 priority patent/WO2015043876A1/fr
Publication of EP2853685A1 publication Critical patent/EP2853685A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • 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
    • F01D5/12—Blades
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2260/83—Testing, e.g. methods, components or tools therefor

Definitions

  • the present invention relates to an insert element for attachment to a ring segment of a turbine of a gas turbine, which is designed for operation with a shroud having a shroud row.
  • the present invention relates to a gas turbine.
  • cover-lift Due to the shroud, it is necessary to perform a so-called cover-lift, ie a lift-off of the complete upper housing part during interventions on the blade row, which are made for example for maintenance or testing purposes.
  • a cover lift is associated with great effort.
  • the present invention has for its object to overcome these disadvantages and to provide an insert element with which it is possible to operate a blade row without shroud in the gas turbine.
  • the insert element according to the invention for fastening to a ring segment of a turbine of a gas turbine has a concave-shaped front side and a rear side with at least one shaping for positioning on the ring segment.
  • the ring segment is designed for operation with a shroud having a shroud row.
  • the insert element has at least one channel extending from the front side to an upper side.
  • the insert element can be fastened with appropriate screws or bolts in a simple manner to the ring segment.
  • the insert element has at least one coaxial with the channel arranged reduction on the front side.
  • the fastening means in particular the head of a screw, can thereby be sunk in the contour of the insert element.
  • the insert element has an upper molding and a lower molding.
  • the formations serve for easier, faster and more accurate positioning of the insert element before securing the insert element to the ring segment.
  • the assembly is simplified and possible with less effort.
  • the insert element is preferably integrated in a gas turbine.
  • the gas turbine according to the invention comprises a turbine with a blade row and a ring segment arranged around the blade row.
  • the ring segment is for operation with a shroud row having a shroud educated.
  • the insert element is attached to the ring segment.
  • a gas turbine is advantageously provided which is suitable for operation with a blade row without shroud.
  • the upper housing of the gas turbine need not be lifted (cover lift). An access from the outlet side is sufficient.
  • the gas turbine according to the invention is therefore particularly suitable for experimental purposes in which frequent changes to the blades are made. With the present gas turbine these experiments could be constructed and carried out much faster.
  • gas turbine according to the invention can be converted in a simple manner for operation with a blade row with shroud by the at least one insert element is removed from the ring segment.
  • FIG. 1 a gas turbine 10 according to the invention is sketched in an exemplary embodiment.
  • the gas turbine 10 according to the invention comprises a turbine 11 in which at least one blade row 12 is arranged.
  • To this blade row 12 around a ring segment 13 is arranged according to the invention.
  • the blade row 12 is arranged rotatably about a rotation axis 20.
  • the blade row 12 is particularly the one located downstream of the other blade rows.
  • the fourth blade row of the turbine 11 of the gas turbine 10th is particularly the one located downstream of the other blade rows.
  • the gas turbine 10 has at least one insert element 14 fastened to the ring segment 13.
  • the arrangement of the insert member 14 in the ring segment is sketched in an exemplary embodiment in a sectional view.
  • the insert element 14 covers a recess 23 in the ring segment 13.
  • This recess 23 has the ring segment 13 for the operation of the gas turbine 10 with a blade row having a shroud.
  • the ring segment 13 can be adapted to the blade row 12, which has no shroud.
  • the insert element 14 shown in a single view comprises a concave front side 15 and a back side 16.
  • the insert element 14 according to the invention has at least one projection 17, 18 for positioning on the ring segment 13.
  • the insert element 14 comprises an upper molding 17 and two lower moldings 18. With the lower moldings 18, the insert element 14 can be pushed into an undercut 24 of the annular segment 13 in a first assembly step M1. Subsequently, the insert element 14 can be folded in a second assembly step M2 to the ring segment 13. With the upper molding 17, the insert member 14 is then positioned in its mounting position. The insert element 14 shown has two channels extending from the front side 15 to an upper side 22 21 on. In a third assembly step M3, the insert element 14 can now be screwed to the ring segment 13. The means for screwing are guided through the channels 21. The insert element 14 is firmly connected to the ring segment 13 after only three assembly steps. In the assembled state, the insert element 14 preferably ends flush with the ring segment 13.
  • the front side 15 of the insert element 14 according to the invention is designed to be concave and thus adapted to the ring segment 13 arranged around the blade row 12.
  • the illustrated insert element 14 has at the front side 15 in each case a countersink 19 per channel 21.
  • the depressions 19 are each arranged coaxially with the channels 21.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13185947.2A 2013-09-25 2013-09-25 Elément d'insertion et turbine à gaz Withdrawn EP2853685A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP13185947.2A EP2853685A1 (fr) 2013-09-25 2013-09-25 Elément d'insertion et turbine à gaz
JP2016516887A JP6227765B2 (ja) 2013-09-25 2014-08-29 ガスタービン及び取付方法
EP14758840.4A EP3022395B1 (fr) 2013-09-25 2014-08-29 Elément d'insertion et turbine à gaz
CN201480052860.8A CN105593470B (zh) 2013-09-25 2014-08-29 燃气涡轮机和安装方法
US15/023,391 US10018051B2 (en) 2013-09-25 2014-08-29 Gas turbine and mounting method
PCT/EP2014/068359 WO2015043876A1 (fr) 2013-09-25 2014-08-29 Élément rapporté, segment annulaire, turbine à gaz, procédé de montage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13185947.2A EP2853685A1 (fr) 2013-09-25 2013-09-25 Elément d'insertion et turbine à gaz

Publications (1)

Publication Number Publication Date
EP2853685A1 true EP2853685A1 (fr) 2015-04-01

Family

ID=49293459

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13185947.2A Withdrawn EP2853685A1 (fr) 2013-09-25 2013-09-25 Elément d'insertion et turbine à gaz
EP14758840.4A Not-in-force EP3022395B1 (fr) 2013-09-25 2014-08-29 Elément d'insertion et turbine à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP14758840.4A Not-in-force EP3022395B1 (fr) 2013-09-25 2014-08-29 Elément d'insertion et turbine à gaz

Country Status (5)

Country Link
US (1) US10018051B2 (fr)
EP (2) EP2853685A1 (fr)
JP (1) JP6227765B2 (fr)
CN (1) CN105593470B (fr)
WO (1) WO2015043876A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11753938B2 (en) 2017-04-05 2023-09-12 Siemens Energy Global GmbH & Co. KG Method for sealing an annular gap in a turbine, and turbine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0132182A1 (fr) * 1983-07-07 1985-01-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif d'étanchéité d'aubages mobiles de turbomachine
GB2206651A (en) * 1987-07-01 1989-01-11 Rolls Royce Plc Turbine blade shroud structure
US20040120803A1 (en) * 2002-12-23 2004-06-24 Terrence Lucas Turbine shroud segment apparatus for reusing cooling air
EP2458152A2 (fr) * 2010-11-29 2012-05-30 Alstom Technology Ltd Turbine à gaz de type à flux axial

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2685429A (en) * 1950-01-31 1954-08-03 Gen Electric Dynamic sealing arrangement for turbomachines
US3656862A (en) 1970-07-02 1972-04-18 Westinghouse Electric Corp Segmented seal assembly
JP2659950B2 (ja) 1987-03-27 1997-09-30 株式会社東芝 ガスタービンシユラウド
US5195868A (en) * 1991-07-09 1993-03-23 General Electric Company Heat shield for a compressor/stator structure
US5165848A (en) * 1991-07-09 1992-11-24 General Electric Company Vane liner with axially positioned heat shields
US5174714A (en) * 1991-07-09 1992-12-29 General Electric Company Heat shield mechanism for turbine engines
JPH08277701A (ja) 1995-04-04 1996-10-22 Ishikawajima Harima Heavy Ind Co Ltd タービン静翼支持構造
DE19756734A1 (de) * 1997-12-19 1999-06-24 Bmw Rolls Royce Gmbh Passives Spalthaltungssystem einer Gasturbine
GB2388407B (en) * 2002-05-10 2005-10-26 Rolls Royce Plc Gas turbine blade tip clearance control structure
US6877952B2 (en) * 2002-09-09 2005-04-12 Florida Turbine Technologies, Inc Passive clearance control
DE102004016222A1 (de) * 2004-03-26 2005-10-06 Rolls-Royce Deutschland Ltd & Co Kg Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine
US7278820B2 (en) 2005-10-04 2007-10-09 Siemens Power Generation, Inc. Ring seal system with reduced cooling requirements
FR2922589B1 (fr) * 2007-10-22 2009-12-04 Snecma Controle du jeu en sommet d'aubes dans une turbine haute-pression de turbomachine
FR2964145B1 (fr) * 2010-08-26 2018-06-15 Safran Helicopter Engines Procede d'accrochage de blindage sur carter de turbine et ensemble d'accrochage pour sa mise en oeuvre
EP2835504A1 (fr) 2013-08-09 2015-02-11 Siemens Aktiengesellschaft Elément d'insertion et turbine à gaz

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0132182A1 (fr) * 1983-07-07 1985-01-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif d'étanchéité d'aubages mobiles de turbomachine
GB2206651A (en) * 1987-07-01 1989-01-11 Rolls Royce Plc Turbine blade shroud structure
US20040120803A1 (en) * 2002-12-23 2004-06-24 Terrence Lucas Turbine shroud segment apparatus for reusing cooling air
EP2458152A2 (fr) * 2010-11-29 2012-05-30 Alstom Technology Ltd Turbine à gaz de type à flux axial

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11753938B2 (en) 2017-04-05 2023-09-12 Siemens Energy Global GmbH & Co. KG Method for sealing an annular gap in a turbine, and turbine
EP3574188B1 (fr) * 2017-04-05 2024-02-28 Siemens Energy Global GmbH & Co. KG Procédé permettant de fermer de manière étanche un interstice annulaire dans une turbine ainsi que turbine

Also Published As

Publication number Publication date
JP6227765B2 (ja) 2017-11-08
WO2015043876A1 (fr) 2015-04-02
EP3022395B1 (fr) 2017-08-16
CN105593470A (zh) 2016-05-18
JP2016535188A (ja) 2016-11-10
EP3022395A1 (fr) 2016-05-25
CN105593470B (zh) 2017-05-31
US10018051B2 (en) 2018-07-10
US20160201497A1 (en) 2016-07-14

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