EP1094199A1 - Rotor pour une turbine à gaz - Google Patents

Rotor pour une turbine à gaz Download PDF

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Publication number
EP1094199A1
EP1094199A1 EP00810930A EP00810930A EP1094199A1 EP 1094199 A1 EP1094199 A1 EP 1094199A1 EP 00810930 A EP00810930 A EP 00810930A EP 00810930 A EP00810930 A EP 00810930A EP 1094199 A1 EP1094199 A1 EP 1094199A1
Authority
EP
European Patent Office
Prior art keywords
cooling air
rotor
blade root
cavities
recesses
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
EP00810930A
Other languages
German (de)
English (en)
Other versions
EP1094199B1 (fr
Inventor
Alexander Dr. Beeck
Herbert Brandl
Hartmut Haehnle
Beat Von Arx
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.)
GE Vernova GmbH
Original Assignee
ABB Schweiz AG
Alstom SA
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 ABB Schweiz AG, Alstom SA filed Critical ABB Schweiz AG
Publication of EP1094199A1 publication Critical patent/EP1094199A1/fr
Application granted granted Critical
Publication of EP1094199B1 publication Critical patent/EP1094199B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a rotor for a gas turbine according to the preamble of the claim 1.
  • Such a rotor is e.g. known from US-A-4,505,640.
  • FIG. 1 A section of a rotor of the type mentioned at the outset is exemplary in FIG. 1 shown.
  • the rotor 10 comprises a rotor disk 11, on the circumference of which one A large number of rotor teeth, which run essentially in the axial direction 15 mutually separate receiving slots 13 are arranged. In the slots 13 come coming from below in the rotor disc 11 extending Cooling air inlets 14, through the cooling air for cooling the rotor blades 16 provided.
  • the rotor blades 16, each of an airfoil 17, one Blade root 19 and a platform arranged above the blade root 19 18, are with the blade root 19 in the axial direction in the receiving slots 13 inserted and are detachably held there, with a positive connection usually through a fir-tree-like design ("fir-tree") of the cross-sectional profile is achieved.
  • fir-tree fir-tree-like design
  • the cooling air (or some other suitable one) brought in by means of the cooling air supply 14 Cooling medium) is through channels (not shown) in the interior of the blade root 19 led into the interior of the (hollow) airfoil 17, flows there and is then through outlet openings on the airfoil 17 and / or on the platform 18 left out.
  • the rotor blades 16 do not have to for thermal reasons only the actual airfoil 17 due to the cooling medium flowing inside are cooled, but also the blade root 19 and the above the Platform 18 arranged on the blade root.
  • US-A-4,012,167, US-A-5,639,216 and US-A-5,848,876 proposed, for example, horizontally running inside the platform
  • Such internal cooling of the platform is, however, manufacturing-related very complex because it is difficult, for example with cast Blades to form corresponding channels.
  • cooling air that flows past the attachment for Use cooling of the platform or at least to flush the cavities.
  • the amount of cooling air is because of the fit between the blade root and Recording slot depends and is more like a leak, indefinitely.
  • the essence of the invention is between the outside of the blade root and form the inside of the receiving slot cooling air channels, the can be easily manufactured as recesses, for example, and the cooling medium lead directly from the cooling air supply into the cavities.
  • a preferred embodiment of the rotor according to the invention is characterized in that that the cooling air channels at least partially as recesses in the Blade root and / or receiving slot are formed. These recesses can be formed in a particularly simple manner directly during casting or through subsequent material removal can be produced.
  • the cooling air channels are formed as recesses, which run vertically between the mouth of the cooling air supply and the cavities.
  • Cooling air channels are formed as recesses, which on the one hand from the Mouth of the cooling air supply horizontally outwards to one end of the Blade root and on the other hand vertically up to the front Cavities run that the front recesses to the outside are sealed by cover plates that axially secure the rotor blades
  • cover plates that axially secure the rotor blades
  • Axial locking plates arranged on the face side in the receiving slots are provided, and that the axial locking plates are used as cover plates become.
  • a cooling air duct is formed as a recess, which from the mouth of the cooling air supply leads horizontally outwards to an end face of the blade root, that for axially securing the rotor blade in the receiving slot on one end arranged axial locking plate is provided, and that the axial locking plate is so shaped that between the axial locking plate and the front of the blade root vertically up into the cavities extending cooling air duct is formed.
  • the formation of the cooling air channels can at least in part through a comparatively simple shaping of the axial locking plates be effected.
  • FIG. 2 shows a rotor with additional ones in a representation comparable to FIG. 1 vertical cooling air channels according to a first embodiment of the invention reproduced.
  • the same parts have the same reference numerals provided, as in Fig. 1.
  • the cavities 21 below the platform 18 are here supplied with cooling air directly by means of vertical cooling air channels 22.
  • the cooling air ducts 22 run directly from the mouth of the cooling air supply 14 in the bottom of the receiving slot 13 to the cavity 21 and flush the cavity 21 with cooling air and simultaneously cool the underside of the platform 18.
  • the cooling air ducts 22 are located in the vertical center plane of the rotor blade 160 and are made by recesses formed in the blade root 19, either when casting the rotor blade 160 molded in or later formed by material removal (e.g. milling) become.
  • the cross section of the cooling air channels 22 is in accordance with the required Cooling air volume designed.
  • cooling air channels on the blade root to be formed by corresponding recesses is shown in Figs. 3 and 4.
  • cooling air channels 23, 24 running vertically through cutouts are kept free, is led upwards into the cavities 21 by the cooling air.
  • To the outside Limitation of the cooling air channels 23, 24 is used to axially secure the rotor blade 161 axial locking plate inserted into corresponding grooves 27, 28 26.
  • To connect the vertical cooling air channels 23, 24 with the mouth of the A further horizontal cooling air duct 25 is provided for the cooling air supply 14 through a recess or recess on the underside of the blade root 19 is formed.
  • the cooling air then flows according to the arrows in Fig. 4 from the Cooling air supply 14 and via the cooling air channels 25 and 23 or 24 upwards in the cavities 21 below the platform 18.
  • blade root in the one shown in FIG. 1 Maintain shape and the additional cooling air channels through complementary Recesses or recesses in the receiving slots 13 of the To form rotor disk 11.
  • FIGS. 5 to 8 Another type, the cooling air channels according to the invention in the area of the blade root Forming 19 is shown in FIGS. 5 to 8.
  • the recesses necessary for this are not provided on the blade root 19 itself, but on one end for axially securing the rotor blade 162 used axial locking plate 260 or 261.
  • the vertical cooling air channels 30 through in the axial locking plate molded beads 29 and 29 'formed (one of the beads is assigned to a blade root).
  • the invention results in manufacturing technology that is particularly simple A defined flushing of the cavities below the platforms, through which the entry of hot gas is reliably prevented, as well as a good one Cooling of the platforms themselves.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00810930A 1999-10-18 2000-10-10 Rotor pour une turbine à gaz Expired - Lifetime EP1094199B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19950109 1999-10-18
DE19950109A DE19950109A1 (de) 1999-10-18 1999-10-18 Rotor für eine Gasturbine

Publications (2)

Publication Number Publication Date
EP1094199A1 true EP1094199A1 (fr) 2001-04-25
EP1094199B1 EP1094199B1 (fr) 2005-05-04

Family

ID=7926019

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810930A Expired - Lifetime EP1094199B1 (fr) 1999-10-18 2000-10-10 Rotor pour une turbine à gaz

Country Status (3)

Country Link
US (1) US6416282B1 (fr)
EP (1) EP1094199B1 (fr)
DE (2) DE19950109A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1355042A3 (fr) * 2002-04-18 2005-03-30 Siemens Aktiengesellschaft Aube de turbine
CN102365425A (zh) * 2009-03-27 2012-02-29 西门子公司 密封板和动叶片系统
DE102012005772A1 (de) 2011-03-22 2012-09-27 Alstom Technology Ltd. Rotorscheibe für eine Turbine sowie Rotor und Turbine mit einer solchen Rotorscheibe
CN107120144A (zh) * 2016-02-25 2017-09-01 通用电气公司 转子轮和叶轮插入件
CN113236370A (zh) * 2021-05-25 2021-08-10 杭州汽轮动力集团有限公司 一种燃气轮机涡轮高压动叶片的冷却结构

Families Citing this family (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040169013A1 (en) * 2003-02-28 2004-09-02 General Electric Company Method for chemically removing aluminum-containing materials from a substrate
GB0307043D0 (en) * 2003-03-26 2003-04-30 Rolls Royce Plc A method of and structure for enabling cooling of the engaging firtree features of a turbine disk and associated blades
GB2409240B (en) * 2003-12-18 2007-04-11 Rolls Royce Plc A gas turbine rotor
GB0503676D0 (en) * 2005-02-23 2005-03-30 Rolls Royce Plc A lock plate arrangement
US7507075B2 (en) * 2005-08-15 2009-03-24 United Technologies Corporation Mistake proof identification feature for turbine blades
US7371044B2 (en) * 2005-10-06 2008-05-13 Siemens Power Generation, Inc. Seal plate for turbine rotor assembly between turbine blade and turbine vane
US7500832B2 (en) * 2006-07-06 2009-03-10 Siemens Energy, Inc. Turbine blade self locking seal plate system
US7766606B2 (en) * 2006-08-17 2010-08-03 Siemens Energy, Inc. Turbine airfoil cooling system with platform cooling channels with diffusion slots
ATE439922T1 (de) * 2007-01-09 2009-09-15 Siemens Ag Biegevorrichtung zum einbiegen eines sicherungsbleches eines rotors einer turbine
US7566201B2 (en) * 2007-01-30 2009-07-28 Siemens Energy, Inc. Turbine seal plate locking system
FR2918414B1 (fr) * 2007-07-06 2013-04-12 Snecma Dispositif d'alimentation en air de ventilation des aubes de turbine basse pression d'un moteur a turbine a gaz ; segment pour l'arret axial et la ventilation des aubes de turbine basse pression
RU2355890C1 (ru) * 2007-11-29 2009-05-20 Открытое акционерное общество "Авиадвигатель" Высокотемпературная многоступенчатая газовая турбина
EP2146055B2 (fr) * 2008-07-17 2022-01-19 Ansaldo Energia S.P.A. Élément d'étanchéité pour une turbine à gaz, turbine à gaz dotée dudit élément d'étanchéité et procédé de refroidissement dudit élément d'étanchéité
FR2939833B1 (fr) * 2008-12-17 2015-06-05 Turbomeca Dispositif de ventilation de fond de logement de disque de turbine
US8206119B2 (en) * 2009-02-05 2012-06-26 General Electric Company Turbine coverplate systems
US8251668B2 (en) * 2009-06-30 2012-08-28 General Electric Company Method and apparatus for assembling rotating machines
US8616832B2 (en) * 2009-11-30 2013-12-31 Honeywell International Inc. Turbine assemblies with impingement cooling
GB201000982D0 (en) * 2010-01-22 2010-03-10 Rolls Royce Plc A rotor disc
GB201002679D0 (en) * 2010-02-17 2010-04-07 Rolls Royce Plc Turbine disk and blade arrangement
US8602737B2 (en) 2010-06-25 2013-12-10 General Electric Company Sealing device
FR2965291B1 (fr) * 2010-09-27 2015-01-23 Snecma Ensemble unitaire de disques de rotor pour une turbomachine
US8864471B2 (en) 2011-08-12 2014-10-21 Hamilton Sundstrand Corporation Gas turbine rotor with purge blades
US9181810B2 (en) 2012-04-16 2015-11-10 General Electric Company System and method for covering a blade mounting region of turbine blades
US9366151B2 (en) 2012-05-07 2016-06-14 General Electric Company System and method for covering a blade mounting region of turbine blades
US9546556B2 (en) * 2012-09-26 2017-01-17 United Technologies Corporation Turbine blade root profile
FR3003494B1 (fr) * 2013-03-19 2015-06-19 Snecma Brut de fonderie pour la realisation d'une aube de rotor de turbomachine et aube de rotor fabriquee a partir de ce brut
EP2860349A1 (fr) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Aube de turbine et turbine à gaz
GB201417038D0 (en) 2014-09-26 2014-11-12 Rolls Royce Plc A bladed rotor arrangement
GB201417039D0 (en) * 2014-09-26 2014-11-12 Rolls Royce Plc A bladed rotor arrangement and a lock plate for a bladed rotor arrangement
EP3034795B1 (fr) 2014-12-17 2019-02-27 Ansaldo Energia Switzerland AG Plaque de serrure avec rainures radiales
EP3109402A1 (fr) * 2015-06-26 2016-12-28 Alstom Technology Ltd Procédé de refroidissement d'un rotor de turbomachine et ledit rotor
GB2547906B (en) * 2016-03-02 2019-07-03 Rolls Royce Plc A bladed rotor arrangement
US20180112544A1 (en) * 2016-10-26 2018-04-26 Siemens Aktiengesellschaft Turbine rotor blade, turbine rotor arrangement and method for manufacturing a turbine rotor blade
KR20180114765A (ko) * 2017-04-11 2018-10-19 두산중공업 주식회사 가스터빈 블레이드의 리테이너, 이를 이용한 터빈유닛 및 가스터빈
US10920598B2 (en) * 2017-05-02 2021-02-16 Rolls-Royce Corporation Rotor assembly cover plate
KR20190029963A (ko) * 2017-09-13 2019-03-21 두산중공업 주식회사 터빈 블레이드의 냉각구조 및 이를 포함하는 터빈 및 가스터빈
US10328352B1 (en) 2018-01-17 2019-06-25 Gail Tam Water slide extension system
US10731475B2 (en) * 2018-04-20 2020-08-04 Raytheon Technologies Corporation Blade with inlet orifice on aft face of root
EP3788236B1 (fr) * 2018-08-02 2023-06-21 Siemens Energy Global GmbH & Co. KG Rotor pourvu d'une pièce disposée entre deux disques de rotor
CN112459849B (zh) * 2020-10-27 2022-08-30 哈尔滨广瀚燃气轮机有限公司 一种用于燃气轮机涡轮叶片的冷却结构
KR102790892B1 (ko) * 2021-11-30 2025-04-02 두산에너빌리티 주식회사 터빈 블레이드, 이를 포함하는 터빈 및 가스터빈

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2639511A1 (de) * 1975-09-08 1977-03-17 Gen Electric Kuehlluftleckstromausnutzung
EP0043300A2 (fr) * 1980-06-30 1982-01-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Perfectionnement aux systèmes de ventilation des aubes et disques de turbines
US4523890A (en) * 1983-10-19 1985-06-18 General Motors Corporation End seal for turbine blade base
US5415526A (en) * 1993-11-19 1995-05-16 Mercadante; Anthony J. Coolable rotor assembly
US5800124A (en) * 1996-04-12 1998-09-01 United Technologies Corporation Cooled rotor assembly for a turbine engine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
US2873947A (en) * 1953-11-26 1959-02-17 Power Jets Res & Dev Ltd Blade mounting for compressors, turbines and like fluid flow machines
US2858103A (en) * 1956-03-26 1958-10-28 Westinghouse Electric Corp Gas turbine apparatus
US3266770A (en) * 1961-12-22 1966-08-16 Gen Electric Turbomachine rotor assembly
US3318573A (en) * 1964-08-19 1967-05-09 Director Of Nat Aerospace Lab Apparatus for maintaining rotor disc of gas turbine engine at a low temperature
CA2198225C (fr) 1994-08-24 2005-11-22 Leroy D. Mclaurin Ailette de turbine a gaz avec plate-forme de refroidissement
US5630703A (en) * 1995-12-15 1997-05-20 General Electric Company Rotor disk post cooling system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2639511A1 (de) * 1975-09-08 1977-03-17 Gen Electric Kuehlluftleckstromausnutzung
EP0043300A2 (fr) * 1980-06-30 1982-01-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Perfectionnement aux systèmes de ventilation des aubes et disques de turbines
US4523890A (en) * 1983-10-19 1985-06-18 General Motors Corporation End seal for turbine blade base
US5415526A (en) * 1993-11-19 1995-05-16 Mercadante; Anthony J. Coolable rotor assembly
US5800124A (en) * 1996-04-12 1998-09-01 United Technologies Corporation Cooled rotor assembly for a turbine engine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1355042A3 (fr) * 2002-04-18 2005-03-30 Siemens Aktiengesellschaft Aube de turbine
CN102365425A (zh) * 2009-03-27 2012-02-29 西门子公司 密封板和动叶片系统
CN102365425B (zh) * 2009-03-27 2015-08-19 西门子公司 密封板和动叶片系统
DE102012005772A1 (de) 2011-03-22 2012-09-27 Alstom Technology Ltd. Rotorscheibe für eine Turbine sowie Rotor und Turbine mit einer solchen Rotorscheibe
CN107120144A (zh) * 2016-02-25 2017-09-01 通用电气公司 转子轮和叶轮插入件
CN113236370A (zh) * 2021-05-25 2021-08-10 杭州汽轮动力集团有限公司 一种燃气轮机涡轮高压动叶片的冷却结构

Also Published As

Publication number Publication date
US6416282B1 (en) 2002-07-09
DE19950109A1 (de) 2001-04-19
DE50010213D1 (de) 2005-06-09
EP1094199B1 (fr) 2005-05-04

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