EP1512838A2 - Rotor pour turbine à vapeur ou à gaz - Google Patents

Rotor pour turbine à vapeur ou à gaz Download PDF

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Publication number
EP1512838A2
EP1512838A2 EP04018654A EP04018654A EP1512838A2 EP 1512838 A2 EP1512838 A2 EP 1512838A2 EP 04018654 A EP04018654 A EP 04018654A EP 04018654 A EP04018654 A EP 04018654A EP 1512838 A2 EP1512838 A2 EP 1512838A2
Authority
EP
European Patent Office
Prior art keywords
cavity
rotor
blades
pockets
section
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Withdrawn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
EP04018654A
Other languages
German (de)
English (en)
Other versions
EP1512838A3 (fr
Inventor
Hans-Otto Dr Jeske
Günter Dr. Neumann
Hans-Egon Brock
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.)
MAN Energy Solutions SE
Original Assignee
MAN Turbo 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 MAN Turbo AG filed Critical MAN Turbo AG
Publication of EP1512838A2 publication Critical patent/EP1512838A2/fr
Publication of EP1512838A3 publication Critical patent/EP1512838A3/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Withdrawn legal-status Critical Current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
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the invention relates to a rotor of a steam or gas turbine with the features of the preamble of claim 1.
  • Steam turbines are mainly used as power plant turbines Electricity generation and as industrial turbines for driving Generators, pumps, blowers and compressors.
  • the Steam turbine is a heat engine with rotating Running parts, in which the enthalpy gradient of the continuously flowing Steam in one or more stages in mechanical work is converted.
  • the blading of the rotating running part of the turbine should the heat content of the steam as lossless as possible in Convert speed energy and the occurring Forces transmitted to the shaft and the housing of the turbine.
  • the deflection takes place in the fixed guide vane stage, then back through the to flow next blade stage.
  • the turbine is repeated several times.
  • the profile length the blades and guide vanes increase in the flow direction. Thereby increases the flowed space with the result that the Reduce pressure and the temperature of the steam. Big turbines are divided into a high, medium and low pressure part.
  • each shovel is a compromise between fluidic, strength, vibration and economic demands.
  • the blade profiles are available usually geometrically graded tendon lengths available.
  • the Shovels in a turbine are stressed and versatile loaded. To ensure a long service life and To avoid damage, the blades must be adjusted accordingly safely designed and designed.
  • a blade must z. B. have sufficient strength to the burden of the occurring centrifugal forces and the bending due absorb the torque to be transferred. Further Stress factors are the temperature at the entrance from to maximum 530 ° C and in the low pressure range due to the wetness of the steam occurring erosion corrosion at the profile entry sides.
  • the cover plates with a made small angle twist to the blade root. After your Installation in the turbine rotor, the blades are under one certain torsional stress, which compensates for the formation of gaps and thereby ensuring the vibration damping.
  • the solution is However, technically expensive and difficult to design.
  • the blades for their application have a certain Minimum length to generate a torsional stress at all to be able to.
  • the tension builds up due to wear at the contact surfaces and fatigue from. Then that is Vibration damping no longer available.
  • the invention is based on the object, the generic Blades of the turbine rotor with a safe acting To provide cushioning that easy and low cost too finished is.
  • the invention is also applicable to blades which are installed in high-speed turbines as well on blades, which have a small overall length and a small one Have cover plate height.
  • a substantially cavity closed on all sides in the form of a drop or a pear.
  • the blade attached to the rotor has a pin in it Shape and size is adapted to the cavity.
  • the pencil can be a cylindrical or, similar to the bag, also a have profiled shape. What is important is that the pen with his Cross-section and its length fits easily into the cavity. He should therefore have a game on all sides, so that the Dividing surfaces of the blades when installed to the plant come.
  • the material combination between blade and pin is after selected low wear.
  • the invention has the following advantages. Every pin fits individually with uniform contact pressure through Thermal expansion and centrifugal force resulting gap between the Blades on. At standstill, the level can be casual relax. The operation of the invention remains over the total operating life of the built-in stage of the blades certainly received. The production is simple and can with low Costs are carried out.
  • the blade preferably in the high or Medium-pressure part of a turbine is used, consists of a Blade foot 1, which has a conical shape and in the illustrated Case is designed as a plug-in foot, as well as from a streamlined airfoil 2 and one at the profile end of the airfoil 2 arranged cover plate 3, with their both dividing surfaces on the same radial plane with the lying on both inclined foot surfaces.
  • the cross section of Blade foot 1 and cover plate 3 is in Fig. 3 as a rectangle shown.
  • the invention is also in the same way for Blades with a rhomboidal cross section applicable.
  • the blade roots 1 are in an adapted circumferential groove of the Rotor 6 of the turbine used radially and in the illustrated case 4 held by two conical pins 7 in the rotor 6.
  • the shape of the blade roots 1 can also deviate from the illustration z. B. be designed as a single or double hammer head.
  • the blade roots 1 and the cover plates 3 in a row arranged blades are in the installed state of FIG. 5 close together, with a gap A small width ( Figure 9).
  • the pockets 5 of two adjacent cover plates 3 are in illustrated case mirror symmetry to each other and formed together form a substantially closed cavity. However, the function of the invention is retained even if the two adjacent pockets 5 opposite to the representation one form asymmetric cavity.
  • the asymmetry can be through Tolerances in the height and depth of the pockets 5 at their Production arise. But they can also be different Wedge angle in the two adjacent pockets 5 are selected.
  • To get the last bucket (end bucket) in one step It may be necessary to fit the two bags formed to the blade profile side of this blade open must be in order to collide with the two inserted Avoid pins 4 of neighboring blades. Also by it creates an asymmetric cavity.
  • the cavity formed by the pockets 5 narrows in radial direction of the rotor 6 wedge-shaped. As in FIGS. 11 and 12 to recognize the cavity is drop-shaped, wherein The cross-section of the cavity initially on a largest Extended cross-section, and then again together in a wedge shape to run.
  • the largest cross section is smaller as the largest cross-section of the cavity, but larger than its smallest cross section.
  • the pin 4 is at both ends bevelled by an unwanted clamping in the cavity in To avoid longitudinal direction.
  • the shape of the pin can be cylindrical (FIG. 12) or profiled (FIG. 11) and the shape of the pockets 5 be adjusted.
  • Fig. 8 and 9 the function of the invention is shown. at a machine standstill (Fig. 8), the position of the pins 4 in the cavity determined by gravity, so that the pin 4 lies at the bottom of the cavity. In the operating state (FIG. 9) All pins 4 in the cavity through the on the pins 4th acting centrifugal force pushed outwards. The existing one Gap A between the cover plates 3 of two adjacent Blades is bridged by the pin 4, and the Vibrations on the blade are caused by the contact or Friction surfaces between cover plate 3 and pin 4 damped.
  • the height of the cavity is determined by the wedge angle, the forming the pockets 5 with each other.
  • pockets are 5 shown, in which the two wedge surfaces smaller than 90 ° are arranged to each other. The pocket height is thereby minimized.
  • This embodiment can be small Deckplatten devisn be used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04018654A 2003-09-02 2004-08-06 Rotor pour turbine à vapeur ou à gaz Withdrawn EP1512838A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10340773 2003-09-02
DE10340773A DE10340773A1 (de) 2003-09-02 2003-09-02 Rotor einer Dampf- oder Gasturbine

Publications (2)

Publication Number Publication Date
EP1512838A2 true EP1512838A2 (fr) 2005-03-09
EP1512838A3 EP1512838A3 (fr) 2006-07-19

Family

ID=34129641

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04018654A Withdrawn EP1512838A3 (fr) 2003-09-02 2004-08-06 Rotor pour turbine à vapeur ou à gaz

Country Status (5)

Country Link
US (1) US7104758B2 (fr)
EP (1) EP1512838A3 (fr)
JP (1) JP2005076638A (fr)
DE (1) DE10340773A1 (fr)
RU (1) RU2347913C2 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1944466A1 (fr) * 2007-01-10 2008-07-16 Siemens Aktiengesellschaft Accouplement de deux aubes mobiles
WO2010000228A2 (fr) * 2008-07-04 2010-01-07 Man Turbo Ag Aube et turbomachine pourvue d'une aube
DE102009048957A1 (de) 2009-10-10 2011-04-14 Mtu Aero Engines Gmbh Verfahren zum Schmelzschweißen eines einkristallinen Werkstücks mit einem polykristallinen Werkstück und Rotor
WO2012072069A1 (fr) * 2010-11-30 2012-06-07 Mtu Aero Engines Gmbh Moyen d'amortissement pour amortir le mouvement d'une aube d'une turbomachine
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
WO2023247856A1 (fr) * 2022-06-22 2023-12-28 Safran Aircraft Engines Ensemble aubage de turbomachine comportant des moyens de limitations de vibrations entre plateformes

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1557534A1 (fr) * 2004-01-20 2005-07-27 Siemens Aktiengesellschaft Aube de turbine à gaz et turbine à gaz avec une telle aube
DE102005030516A1 (de) * 2005-06-28 2007-01-04 Man Turbo Ag Rotor für eine Turbine sowie Verfahren und Vorrichtung zur Herstellung des Rotors
GB2449493B (en) * 2007-05-25 2009-08-12 Rolls Royce Plc Vibration damper assembly
US8257044B2 (en) * 2007-09-11 2012-09-04 Hitachi, Ltd. Steam turbine rotor blade assembly
US8137072B2 (en) * 2008-10-31 2012-03-20 Solar Turbines Inc. Turbine blade including a seal pocket
US8393869B2 (en) 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
DE102009013348A1 (de) * 2009-03-16 2010-09-23 Man Turbo Ag Vorrichtung und Verfahren zum Verbinden einer Schaufel mit einer Rotorwelle einer Strömungsmaschine
US8834123B2 (en) * 2009-12-29 2014-09-16 Rolls-Royce Corporation Turbomachinery component
FR2963381B1 (fr) * 2010-07-27 2015-04-10 Snecma Etancheite inter-aubes pour une roue de turbine ou de compresseur de turbomachine
US8790086B2 (en) * 2010-11-11 2014-07-29 General Electric Company Turbine blade assembly for retaining sealing and dampening elements
US8834125B2 (en) 2011-05-26 2014-09-16 United Technologies Corporation Hybrid rotor disk assembly with a ceramic matrix composite airfoil for a gas turbine engine
US8936440B2 (en) 2011-05-26 2015-01-20 United Technologies Corporation Hybrid rotor disk assembly with ceramic matrix composites platform for a gas turbine engine
US8851853B2 (en) * 2011-05-26 2014-10-07 United Technologies Corporation Hybrid rotor disk assembly for a gas turbine engine
JP2012251503A (ja) 2011-06-03 2012-12-20 Hitachi Ltd 蒸気タービン
EP2690254B1 (fr) * 2012-07-27 2017-04-26 General Electric Technology GmbH Fixations de pied de pale de rotor de turbine
ITCO20130004A1 (it) * 2013-02-20 2014-08-21 Nuovo Pignone Srl Metodo per realizzare una girante da segmenti a settore
EP2803821A1 (fr) * 2013-05-13 2014-11-19 Siemens Aktiengesellschaft Dispositif d'aube, système d'aubes et procédé de fabrication associé d'un système d'aubes
US20160208623A1 (en) 2013-09-26 2016-07-21 Franco Tosi Meccanica S.P.A. Rotor stage of axial turbine with an adaptive regulation to dynamic stresses
DE102014214271A1 (de) * 2014-07-22 2016-01-28 MTU Aero Engines AG Turbomaschinenschaufel
US10392951B2 (en) 2014-10-02 2019-08-27 United Technologies Corporation Vane assembly with trapped segmented vane structures
JP6991912B2 (ja) 2018-03-28 2022-01-13 三菱重工業株式会社 回転機械
US11536144B2 (en) * 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures

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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1944466A1 (fr) * 2007-01-10 2008-07-16 Siemens Aktiengesellschaft Accouplement de deux aubes mobiles
US8974187B2 (en) 2008-07-04 2015-03-10 Man Diesel & Turbo Se Rotor blade and flow engine comprising a rotor blade
WO2010000228A2 (fr) * 2008-07-04 2010-01-07 Man Turbo Ag Aube et turbomachine pourvue d'une aube
WO2010000228A3 (fr) * 2008-07-04 2010-12-29 Man Diesel & Turbo Se Aube et turbomachine pourvue d'une aube
CN102084091B (zh) * 2008-07-04 2016-03-02 曼柴油机和涡轮机欧洲股份公司 动叶片以及带有动叶片的流体机械
CN102084091A (zh) * 2008-07-04 2011-06-01 曼柴油机和涡轮机欧洲股份公司 动叶片以及带有动叶片的流体机械
DE102009048957A1 (de) 2009-10-10 2011-04-14 Mtu Aero Engines Gmbh Verfahren zum Schmelzschweißen eines einkristallinen Werkstücks mit einem polykristallinen Werkstück und Rotor
DE102009048957C5 (de) * 2009-10-10 2014-01-09 Mtu Aero Engines Gmbh Verfahren zum Schmelzschweißen eines einkristallinen Werkstücks mit einem polykristallinen Werkstück und Rotor
DE102009048957B4 (de) * 2009-10-10 2011-09-01 Mtu Aero Engines Gmbh Verfahren zum Schmelzschweißen eines einkristallinen Werkstücks mit einem polykristallinen Werkstück und Rotor
WO2011042006A1 (fr) 2009-10-10 2011-04-14 Mtu Aero Engines Gmbh Procédé de soudage par fusion d'une pièce monocristalline et d'une pièce polycristalline, et rotor
WO2012072069A1 (fr) * 2010-11-30 2012-06-07 Mtu Aero Engines Gmbh Moyen d'amortissement pour amortir le mouvement d'une aube d'une turbomachine
US9506372B2 (en) 2010-11-30 2016-11-29 Mtu Aero Engines Gmbh Damping means for damping a blade movement of a turbomachine
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
WO2023247856A1 (fr) * 2022-06-22 2023-12-28 Safran Aircraft Engines Ensemble aubage de turbomachine comportant des moyens de limitations de vibrations entre plateformes
FR3137127A1 (fr) * 2022-06-22 2023-12-29 Safran Aircraft Engines Ensemble aubagé de turbomachine comportant des moyens de limitations de vibrations entre plateformes

Also Published As

Publication number Publication date
RU2347913C2 (ru) 2009-02-27
EP1512838A3 (fr) 2006-07-19
US20050047917A1 (en) 2005-03-03
US7104758B2 (en) 2006-09-12
JP2005076638A (ja) 2005-03-24
RU2004126590A (ru) 2006-02-10
DE10340773A1 (de) 2005-03-24

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