EP1873355A1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP1873355A1
EP1873355A1 EP06013266A EP06013266A EP1873355A1 EP 1873355 A1 EP1873355 A1 EP 1873355A1 EP 06013266 A EP06013266 A EP 06013266A EP 06013266 A EP06013266 A EP 06013266A EP 1873355 A1 EP1873355 A1 EP 1873355A1
Authority
EP
European Patent Office
Prior art keywords
blade
shroud
rotor
turbine
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.)
Withdrawn
Application number
EP06013266A
Other languages
German (de)
English (en)
Inventor
Robert Howell
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
Priority to EP06013266A priority Critical patent/EP1873355A1/fr
Publication of EP1873355A1 publication Critical patent/EP1873355A1/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Withdrawn legal-status Critical Current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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • the present invention relates to a turbine blade, in particular to a gas turbine blade having a shroud at its tip end.
  • a fuel is burned in a burner assembly to produce hot pressurized exhaust gases which are then fed to a turbine stage where they, while expending and cooling, transfer momentum to turbine blades of a rotor thereby imposing rotational movement on the rotor.
  • a usual turbine stage comprises alternating cascades of turbine blades fixed to and rotating with the rotor and stationary turbine vanes.
  • a cascade of turbine blades is formed by a blade ring with a number of turbine blades spread regularly around the circumference of the rotor.
  • the efficiency of the gas turbine engine depends on the efficiency of transforming momentum from the expanding and cooling exhaust gases to the turbine blades.
  • a rotor with shrouded rotor blades is, e.g., shown in US 5,211,540 .
  • Shroud curl occurs when the shroud of the blade has been exposed to hot gases over a longer period of time, hence during operation in the load range. Curl is caused by creep in the material leading to plastic deformation.
  • the purpose of the shroud is twofold. Besides preventing leakage over the blade tip and improving the efficiency of the turbine, it also improves the dynamic/vibration qualities of the blade. Depending on the shape of the contact surface between the shroud vibrations e.g. dynamic movements can be prevented or damped out. Furthermore due to the contact between the shrouds the Eigen frequencies of the individual blades are increase compared to if they are moving freely. During barrelling and start-up the shrouds may not be in full contact.
  • An inventive turbine rotor blade has a root end by which it can be fixed to a turbine rotor hub and a tip end remote from the root end which carries a shroud segment.
  • the rotor blade is adapted to form a blade ring together with further rotor blades fixed to the rotor hub.
  • the shroud segments of the blade ring's rotor blades together form a shroud ring which circumferentially surrounds the rotor hub.
  • the shroud segment comprises a projection so as to allow for overlapping the shroud segment of a neighbouring rotor blade in the blade ring in circumferential direction of the rotor.
  • the shroud has a short side and a long side in circumferential direction with respect to the rotor.
  • the projection is formed in the long side so as to allow for overlapping the short side of a neighbouring rotor blade's shroud segment on the short side's radial inner side. Since the long side is more flexible than the short side, a curl would occur on the long side rather than on the short side. When the long side is located radial inwards with respect to the short side in the overlapping zone, the less flexible short side prevents the long side from curling outwards.
  • the overlapping can be realized by giving the shroud's end faces in circumferential direction contours which are inverse to each other, e.g. stepped, sloped or teethed contours.
  • the contours of the end faces can be continued through the fin's circumferential end faces.
  • An inventive turbine rotor comprises a rotor hub and at least one blade ring having a number of inventive turbine blades fixed to the rotor hub.
  • the shroud segments of the rotor blades form a shroud ring.
  • Figure 1 shows a first embodiment of the inventive turbine rotor blade in a view onto the rotor blade's leading edge.
  • Figure 2 shows the rotor blades shown in Figure 1 seen from radially outwards.
  • Figure 3 shows a second embodiment of the inventive turbine rotor blade.
  • Figure 4 shows a third embodiment of the inventive turbine rotor blade.
  • Figure 5 shows a fourth embodiment of the inventive turbine rotor blade.
  • Figure 6 shows a fifth embodiment of the inventive turbine rotor blade.
  • FIG. 1 shows a section of a blade ring 1 comprising a number of inventive turbine blades 3.
  • Each turbine blade 3 has a root end 5 by which it is fixed to a rotor hub 7.
  • the rotor hub 7 and the blade rings fixed thereto form a rotor for a gas turbine engine.
  • the turbine blade 3 Remote from the root end 5 the turbine blade 3 comprises a tip end 9, to which a shroud segment 11 is fixed.
  • the shroud segments 11 of the blade ring's turbine blades 3 form a shroud ring which extends circumferentially around the rotor hub 7.
  • each shroud segment 11 has, in circumferential direction, a long side 21 and a short side 23.
  • the slope is such that the long side 21 overlaps the short side of a neighbouring shroud segment 11 radially inwards.
  • the short side 23 then prevents the more flexible long side 21 from curling outwards, e.g. in a transition mode of the gas turbine engine of which the rotor is a part.
  • a fin 13 extends radially outwards.
  • the slope in the shroud segment's end faces 15, 17 is continued in the circumferential end faces 25, 27 of the fins 13.
  • a second embodiment of the inventive turbine rotor blade 3 is shown in Figure 3.
  • the second embodiment differs from the first embodiment in that the circumferential end faces 15, 17 of the shroud segment 11 and the circumferential end faces 25, 27 of the fin 13 are not sloped, but stepped.
  • a third embodiment of the inventive turbine rotor blade is shown in Figure 4. This embodiment differs from the embodiment shown in Figure 1 in that the end faces 15, 17 of the shroud segment 11 and the end faces 25, 27 of the fin 13 have a dove tail structure at the long side 21 and a spike structure at the short side which is inverse to the dove tail structure of the long side 21.
  • Figure 5 shows a fourth embodiment of the inventive turbine rotor blade 3.
  • the fourth embodiment differs from the first embodiment in that the end faces 15, 17 of the shroud segment 11 and the end faces 25, 27 of the fin 13 are teethed.
  • the teething at the short side's end faces 15, 25 is inverse to the teething at the long side's end faces 17, 27.
  • a fifth embodiment of the inventive turbine rotor blade 3 is shown in Figure 6.
  • the fifth embodiment differs from the first embodiment in that the circumferential end faces 15, 17 of the shroud segment 11 and the circumferential end phases 25, 27 of the fin 13 show a Z-notch structure.
  • the overlapping structures are present in the end faces of the shroud segments 11 and in the end faces of the fins 13 throughout the embodiments, the overlapping structures could be confined to the end faces of the shroud segments 11. In this case the dove tail and the spike of the third embodiment, or the Z-notch structure of the fifth embodiment would be located completely in the end faces 15 and 17 of the shroud segment 11.
  • the curling of the shroud can be reduced compared to state of the art shrouds.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06013266A 2006-06-27 2006-06-27 Aube de turbine Withdrawn EP1873355A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06013266A EP1873355A1 (fr) 2006-06-27 2006-06-27 Aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06013266A EP1873355A1 (fr) 2006-06-27 2006-06-27 Aube de turbine

Publications (1)

Publication Number Publication Date
EP1873355A1 true EP1873355A1 (fr) 2008-01-02

Family

ID=37116016

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06013266A Withdrawn EP1873355A1 (fr) 2006-06-27 2006-06-27 Aube de turbine

Country Status (1)

Country Link
EP (1) EP1873355A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009105460A2 (fr) * 2008-02-21 2009-08-27 Borgwarner Inc. Ventilateur de refroidissement avec élément annulaire partiel
WO2012041651A1 (fr) * 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Segment de couronne d'aubes, turbomachine et procédé de fabrication correspondant
EP2460979A1 (fr) * 2010-12-03 2012-06-06 MTU Aero Engines GmbH Segment d'aube d'une turbomachine avec de surfaces d'appui
EP2612996A1 (fr) * 2012-01-04 2013-07-10 General Electric Company Dispositif et procédé pour aligner des talons d'extrémité
EP2669477A1 (fr) * 2012-05-31 2013-12-04 Alstom Technology Ltd Carénage pour aubes
WO2014116342A3 (fr) * 2012-11-13 2014-10-16 United Technologies Corporation Verrouillage de support
WO2014143445A3 (fr) * 2013-02-10 2014-12-31 United Technologies Corporation Enveloppe de recouvrement d'aube fixe à incidence variable
WO2017154852A1 (fr) * 2016-03-08 2017-09-14 三菱重工コンプレッサ株式会社 Ensemble d'aubes de rotor de turbine
US10738634B2 (en) * 2018-07-19 2020-08-11 Raytheon Technologies Corporation Contact coupled singlets
FR3107921A1 (fr) * 2020-03-04 2021-09-10 Safran Aircraft Engines Procede pour remboiter des talons d’aubes d’une roue de rotor dans une turbomachine d’aeronef

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB155156A (en) * 1920-01-08 1920-12-16 Schneider & Cie Improved hooping bands for the movable blades of steam or gas turbines
US1371328A (en) * 1920-07-21 1921-03-15 Schneider & Cie Hooping-band for the movable blades of steam or gas turbines
US1423466A (en) * 1920-10-02 1922-07-18 Westinghouse Electric & Mfg Co Interlocking blade shroud
US1527781A (en) * 1921-05-09 1925-02-24 Edmund S R Brandt Segmental turbine band
GB532372A (en) * 1938-08-27 1941-01-22 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
CH418360A (de) * 1962-11-21 1966-08-15 Ass Elect Ind Turbomaschine
US3545882A (en) * 1968-01-17 1970-12-08 Rolls Royce Pressure exchanger rotor
US3986792A (en) * 1975-03-03 1976-10-19 Westinghouse Electric Corporation Vibration dampening device disposed on a shroud member for a twisted turbine blade
US20020071764A1 (en) * 2000-12-11 2002-06-13 General Electric Company Turbine bucket cover and brush seal
US6491498B1 (en) * 2001-10-04 2002-12-10 Power Systems Mfg, Llc. Turbine blade pocket shroud
US20030012655A1 (en) * 2002-06-07 2003-01-16 Tomoyoshi Sasaki Turbine rotor blades assembly and method for assembling the same
WO2004022923A1 (fr) * 2002-09-02 2004-03-18 Hitachi, Ltd. Aube mobile de turbine
EP1413712A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Virole pour une turbine avec joint d'extrémité

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB155156A (en) * 1920-01-08 1920-12-16 Schneider & Cie Improved hooping bands for the movable blades of steam or gas turbines
US1371328A (en) * 1920-07-21 1921-03-15 Schneider & Cie Hooping-band for the movable blades of steam or gas turbines
US1423466A (en) * 1920-10-02 1922-07-18 Westinghouse Electric & Mfg Co Interlocking blade shroud
US1527781A (en) * 1921-05-09 1925-02-24 Edmund S R Brandt Segmental turbine band
GB532372A (en) * 1938-08-27 1941-01-22 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
CH418360A (de) * 1962-11-21 1966-08-15 Ass Elect Ind Turbomaschine
US3545882A (en) * 1968-01-17 1970-12-08 Rolls Royce Pressure exchanger rotor
US3986792A (en) * 1975-03-03 1976-10-19 Westinghouse Electric Corporation Vibration dampening device disposed on a shroud member for a twisted turbine blade
US20020071764A1 (en) * 2000-12-11 2002-06-13 General Electric Company Turbine bucket cover and brush seal
US6491498B1 (en) * 2001-10-04 2002-12-10 Power Systems Mfg, Llc. Turbine blade pocket shroud
US20030012655A1 (en) * 2002-06-07 2003-01-16 Tomoyoshi Sasaki Turbine rotor blades assembly and method for assembling the same
WO2004022923A1 (fr) * 2002-09-02 2004-03-18 Hitachi, Ltd. Aube mobile de turbine
EP1413712A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Virole pour une turbine avec joint d'extrémité

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009105460A2 (fr) * 2008-02-21 2009-08-27 Borgwarner Inc. Ventilateur de refroidissement avec élément annulaire partiel
WO2009105460A3 (fr) * 2008-02-21 2009-11-12 Borgwarner Inc. Ventilateur de refroidissement avec élément annulaire partiel
US8550782B2 (en) 2008-02-21 2013-10-08 Borgwarner Inc. Partial ring cooling fan
WO2012041651A1 (fr) * 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Segment de couronne d'aubes, turbomachine et procédé de fabrication correspondant
CN103119249A (zh) * 2010-09-30 2013-05-22 西门子公司 叶片环扇段、流体机械及其制造方法
EP2460979A1 (fr) * 2010-12-03 2012-06-06 MTU Aero Engines GmbH Segment d'aube d'une turbomachine avec de surfaces d'appui
EP2612996A1 (fr) * 2012-01-04 2013-07-10 General Electric Company Dispositif et procédé pour aligner des talons d'extrémité
US10006296B2 (en) 2012-05-31 2018-06-26 General Electric Technology Gmbh Shroud for pre-twisted airfoils
CN103452596A (zh) * 2012-05-31 2013-12-18 阿尔斯通技术有限公司 用于预扭转翼型件的围带
CN103452596B (zh) * 2012-05-31 2015-11-18 阿尔斯通技术有限公司 用于涡轮机的叶片和增大从该叶片装配的环的频率的方法
JP2013249842A (ja) * 2012-05-31 2013-12-12 Alstom Technology Ltd プレツイステッド翼用のシュラウド
EP2669477A1 (fr) * 2012-05-31 2013-12-04 Alstom Technology Ltd Carénage pour aubes
WO2014116342A3 (fr) * 2012-11-13 2014-10-16 United Technologies Corporation Verrouillage de support
US9587504B2 (en) 2012-11-13 2017-03-07 United Technologies Corporation Carrier interlock
US10107122B2 (en) 2013-02-10 2018-10-23 United Technologies Corporation Variable vane overlap shroud
WO2014143445A3 (fr) * 2013-02-10 2014-12-31 United Technologies Corporation Enveloppe de recouvrement d'aube fixe à incidence variable
WO2017154852A1 (fr) * 2016-03-08 2017-09-14 三菱重工コンプレッサ株式会社 Ensemble d'aubes de rotor de turbine
US20190078447A1 (en) * 2016-03-08 2019-03-14 Mitsubishi Heavy Industries Compressor Corporation Turbine rotor blade assembly
US10781700B2 (en) * 2016-03-08 2020-09-22 Mitsubishi Heavy Industries Compressor Corporation Turbine rotor blade assembly
US10738634B2 (en) * 2018-07-19 2020-08-11 Raytheon Technologies Corporation Contact coupled singlets
FR3107921A1 (fr) * 2020-03-04 2021-09-10 Safran Aircraft Engines Procede pour remboiter des talons d’aubes d’une roue de rotor dans une turbomachine d’aeronef
WO2021176168A1 (fr) * 2020-03-04 2021-09-10 Safran Aircraft Engines Procédé pour remboiter des talons d'aubes d'une roue de rotor dans une turbomachine d'aéronef
US11988111B2 (en) 2020-03-04 2024-05-21 Safran Aircraft Engines Method for refitting blade shrouds of a rotor wheel in an aircraft turbomachine

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