EP2025867A1 - Rotor für eine axial durchströmbare Strömungsmaschine - Google Patents

Rotor für eine axial durchströmbare Strömungsmaschine Download PDF

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Publication number
EP2025867A1
EP2025867A1 EP07015785A EP07015785A EP2025867A1 EP 2025867 A1 EP2025867 A1 EP 2025867A1 EP 07015785 A EP07015785 A EP 07015785A EP 07015785 A EP07015785 A EP 07015785A EP 2025867 A1 EP2025867 A1 EP 2025867A1
Authority
EP
European Patent Office
Prior art keywords
rotor
drum
discs
disks
compressor
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Withdrawn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
EP07015785A
Other languages
German (de)
English (en)
French (fr)
Inventor
Douglas James Arrell
Harald Hoell
David W. Hunt
Karsten Dr. Kolk
Harald Nimptsch
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 EP07015785A priority Critical patent/EP2025867A1/de
Priority to EP08787065A priority patent/EP2173972B1/de
Priority to RU2010108465/06A priority patent/RU2479725C2/ru
Priority to PL08787065T priority patent/PL2173972T3/pl
Priority to CN2008801027856A priority patent/CN101779000B/zh
Priority to US12/672,794 priority patent/US8459951B2/en
Priority to ES08787065T priority patent/ES2404579T3/es
Priority to PCT/EP2008/060480 priority patent/WO2009021927A1/de
Priority to JP2010519474A priority patent/JP5235996B2/ja
Publication of EP2025867A1 publication Critical patent/EP2025867A1/de
Withdrawn legal-status Critical Current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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties

Definitions

  • the invention relates to a rotor for an axial flow-through turbomachine, with a plurality of stacked rotor disks, which are clamped together axially by means of at least one tie rod.
  • the rotor disks used in the rotor are known to carry on their outer sides in a ring arranged blades, by means of which a working medium compressible or by means of which the energy contained in a working medium can be converted into the rotational movement of the rotor.
  • the adjacent stacked rotor discs are braced together by at least one tie rod.
  • the tie rod extends through the rotor discs and is biased by nuts screwed end. The tie rod ensures the firm juxtaposition of the rotor discs.
  • a welded-together rotor can have an outer drum-shaped heat-insulating jacket for protecting the inner region of the rotor.
  • the object of the invention is therefore to provide a rotor for an axially flow-through turbomachine, preferably for a high pressure compressor with a pressure ratio of greater than 1:16 and a comparatively large compressor mass flow, in which, while maintaining the concept with stacked adjacent rotor discs cost design can be specified , At the same time, the rotor should have a particularly long life. Furthermore, the efficiency of the compressor should be further improved.
  • a rotor of the type mentioned in which an at least two adjacent rotor discs annularly encompassing drum is provided with an endless surface on its inner surface web, which web is axially braced between two of the encompassed rotor discs.
  • a multi-part rotor as seen in its radial direction, is thus proposed, in which the inner rotor disks can be made of a different material than the drum provided on the outside.
  • the most suitable materials can thus be selected for the different loads of drum and rotor disks.
  • both the drum and the encompassed rotor discs can each be made of a material with which a particularly long life of the component can be achieved.
  • a slip-laden relative movement between the outside arranged drum and radially further inwardly arranged rotor discs is thus not possible, whereby a total of transmitted between the components to be transmitted torques and forces can be passed lossless.
  • the drum allows the sealing of gaps between the two rotor disks, so that at this point in the prior art possibly existing leakage flow can be suppressed here. This increases the efficiency of the compressor.
  • the rotor disks can also be better examined for possibly existing material inclusions, imperfections and / or cracks by means of the known ultrasonic methods than the rotor disks with a larger diameter known from the prior art.
  • the two - seen in the axial direction of the rotor - the outer of the rotor disks encompassed by the drum are hooked to it for receiving centrifugal forces.
  • the drum thus encompasses at least two rotor disks, wherein each of the two outer rotor disks, seen in the axial direction, each provide an entanglement at their outer peripheries which can be brought into engagement with a corresponding hook or groove provided on the inside of the drum.
  • the direction of entanglement is selected so that the centrifugal forces acting on the drum can be at least partially absorbed by the rotor disks.
  • the centrifugal force occurring in this section of the rotor can be evenly distributed from the drum to the rotor discs arranged radially further inside. Due to the required mountability of the stackable construction with radially inward arranged rotor disks and radially outwardly arranged drum, it is necessary that at least the two outer rotor disks are hooked to the drum. In an arrangement in which the drum engages around only two rotor disks, thus both rotor disks are hooked to the drum.
  • the drum is formed of a heat-resistant material than the rotor disks.
  • this is a particularly inexpensive rotor can be specified because the heat-resistant and cost-intensive material is only to use for the drum.
  • the construction according to the invention is preferably used in the rear stages of an axial compressor, in which particularly high temperatures in the range of greater than 400 ° C occur during the compression process. With a more heat resistant drum, the life of the rotor can at least be maintained, if not extended even further. Since a lower temperature prevails in the interior of the rotor due to the temperature gradients in the drum material than in the air to be compressed, it may be sufficient that the rotor disks are made of a material which meets lower requirements in terms of temperature resistance.
  • the material of the rotor discs can be a cheaper than the material of the drum.
  • the drum may be made of a nickel-based alloy and the rotor disks encompassed by it may be made of a heat-resistant steel or alloy.
  • the web has two opposite flange-like end faces, which abut against flange-like end faces of adjacent rotor disks.
  • the end face of the rotor discs is positively against the end face of the web.
  • the positive connection can be produced by means of a Hirth toothing.
  • the drum has at least one groove for receiving at least one blade.
  • the groove is formed as a circumferential groove, so that in the circumferential groove all blades of a blade ring can be used. The use of circumferential grooves allows a particularly large number of blades per ring. In addition, the circumferential grooves are cheaper to manufacture than axially extending slots for blades.
  • the number of circumferential grooves can be greater than the number of rotor disks encompassed by the drum. So far, it was in the prior art so that each rotor blade stage a rotor disk was provided with a circumferential groove. This caused a comparatively large axial space for mounting the blades on the rotor. Despite the use of the modular rotor concept with rotor disks, the solution proposed can achieve a comparatively short axial installation space for the rotor and for the housing since, for example when using two rotor disks, it is possible to provide three circumferential grooves on the outer circumference of the drum. can be used in the respective blades of different blade rings.
  • the outside of the drum for receiving arranged in wreath blades is formed, wherein the number of mountable blade rings can be greater than the number of rotor disks encompassed by the drum.
  • the invention is particularly useful when the rotor is used in a compressor with a pressure ratio greater than 1:16, the compressor preferably being the compressor of a stationary gas turbine used for power generation.
  • the rated power of the gas turbine is greater than 50 MW.
  • the invention can in principle in each Section of a compressor can be used. Since the problems mentioned in the prior art occur especially with large rotor disks with an outer diameter of 1200 mm and larger, it is particularly advantageous if in particular such large rotor disks are replaced by the construction according to the invention with compressor disks smaller outer diameter and with a surrounding drum , Thus, the drum according to the invention preferably has an outer diameter of 1200 mm and larger.
  • the invention can also be used in the sections of the compressor, where - if only compressor discs without a drum would be used - this would have a smaller outer diameter than 1200 mm. Thus, drum outer diameter smaller than 1200 mm are possible.
  • FIG. 1 shows a section through the longitudinal section of a plurality of rotor disks 10 comprehensive rotor 12 of a gas turbine, not shown.
  • the section of the rotor 12 is chosen so that it lies in the high pressure region of the axial compressor of the gas turbine.
  • the rotor discs 14, 16 are manufactured in a known configuration and have at their outer peripheries 18 each have a circumferential groove extending in the circumferential direction 20, which are provided for receiving blades of the compressor.
  • the rotor disks 14, 16 are flange-like against each other at a contact surface 22, wherein in this contact surface 22nd a Hirth toothing is provided for the positive connection.
  • Axially to the rotor disk 16 adjacent two further rotor disks 24, 26 are provided, which compared to the rotor disks 14, 16 have a smaller outer diameter.
  • the two rotor discs 24, 26 are encompassed by a longitudinally section T-shaped drum 28.
  • the drum 28 has on its inner side 30 a radially inwardly directed endless circumferential ridge 32, which is provided with two opposite end surfaces 34.
  • the end faces 34 rest on the one hand on the rotor disk 24 and on the other hand on the rotor disk 26 on contact surfaces 36, 38 at.
  • the contact surfaces 36, 38 are structured such that in each case a positive connection in the form of a serration is provided.
  • Each of the rotor disks 24, 26 has in its outer region an axially extending circumferential hooks 40, 42.
  • the annular hooks 40, 42 each engage in an open towards the end face of the drum 28, arranged in this endless circumferential groove 44, 46 a.
  • the grooves 44, 46 thus each form a receptacle for the hooks 40, 42 arranged on the rotor disks 24, 26.
  • the drum 28 has on its outer side also in the circumferential direction extending blade holding grooves 48, 50, 52, in each of which blades of a blade ring can be used.
  • the blades have for this purpose to the blade holding grooves 48, 50, 52 corresponding formed blade roots.
  • the blades which can be inserted in the grooves 48, 50, 52 belong to the blade stages which carry out the last pressure increases in the medium to be compressed. Accordingly, the blade holding grooves 48, 50, 52 are arranged the last three compressor blade rings of the compressor. Due to the occurring during the compression of the medium high temperatures in the region of the drum 28, this is made of a heat-resistant material than the encompassed by the drum 28 and thus radially further inside rotor disks 24, 26.
  • the rotor disks 24, 26 can thus be made of a less temperature-resistant material, as in their
  • the axial distance between the grooves 48 and 50 and between the grooves 50 and 52 in comparison is less than the distance when using three individual rotor disks instead of the drum 28, so that axial Space can be saved in the compressor.
  • the saving of axial space overall allows the construction of a cheaper gas turbine or the construction of a cheaper compressor.
  • each of the rotor disks 24, 26 is hooked to the inside 30 of the drum 28. Even a slight placement of the two axially opposite ends 54, 56 of the drum 28 can thus be avoided.
  • the mechanical centrifugal loads resulting from the blades may be at least partially transmitted from the drum 28 to the rotor disks 24, 26 so that the mechanical loads on the drum 28 remain within the allowable limits of the drum material.
  • tie rod 58 extending centrally through the rotor disks 10
  • tension rods arranged concentrically around the machine axis 60 in order to press the rotor disks firmly against one another.
  • FIG. 2 shows the same section of the gas turbine as FIG. 1 , wherein like components are labeled with identical reference numerals.
  • FIG. 2 In contrast to FIG. 1 has the in FIG. 2 illustrated drum 28 on a modified web 32.
  • the web 32 according to the in FIG. 2 illustrated second embodiment of the drum 28 extends inwardly not only to those end faces 34 which abut against the contact surfaces 22 of the adjacent rotor disks 24, 26, but beyond this range.
  • the web 32 may also comprise a further hub region 62, the radial end of which lies substantially further inward than the contact surfaces 22 of the rotor disks 24, 26. In this way, a greater load capacity of the drum 28 can be achieved.
  • the invention thus relates to a rotor 12 for an axially flow-through turbomachine with a plurality of stacked rotor disks 10, 14, 16, 24, 26, which are braced by means of at least one tie rod 58 with each other.
  • a particularly inexpensive rotor 12 with a compact design, which is designed in particular for particularly high pressure ratios with comparatively large compressor mass flows, it is proposed that an at least two adjacent rotor disks 24, 26 annularly encompassing drum 28 having a continuous on its inner surface 30 web 32nd is provided, which web 32 between two of the encompassed rotor disks 24, 26 is axially braced.
  • Only the drum 28 may be made of a more heat-resistant material.
  • the encompassed by her rotor discs 24, 26, however, can be made of a cheaper material, resulting in cost savings.
  • the drum 28 can carry at least one blade ring more than rotor disks 24, 26, which are encompassed by it.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP07015785A 2007-08-10 2007-08-10 Rotor für eine axial durchströmbare Strömungsmaschine Withdrawn EP2025867A1 (de)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP07015785A EP2025867A1 (de) 2007-08-10 2007-08-10 Rotor für eine axial durchströmbare Strömungsmaschine
EP08787065A EP2173972B1 (de) 2007-08-10 2008-08-08 Rotor für eine axial durchströmbare strömungsmaschine
RU2010108465/06A RU2479725C2 (ru) 2007-08-10 2008-08-08 Ротор для лопаточной машины с осевым потоком
PL08787065T PL2173972T3 (pl) 2007-08-10 2008-08-08 Wirnik dla osiowej maszyny przepływowej
CN2008801027856A CN101779000B (zh) 2007-08-10 2008-08-08 轴流式流体机械的转子
US12/672,794 US8459951B2 (en) 2007-08-10 2008-08-08 Rotor for an axial flow turbomachine
ES08787065T ES2404579T3 (es) 2007-08-10 2008-08-08 Rotor para una turbomáquina de flujo axial
PCT/EP2008/060480 WO2009021927A1 (de) 2007-08-10 2008-08-08 Rotor für eine axial durchströmbare strömungsmaschine
JP2010519474A JP5235996B2 (ja) 2007-08-10 2008-08-08 軸流流体機械におけるロータ

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07015785A EP2025867A1 (de) 2007-08-10 2007-08-10 Rotor für eine axial durchströmbare Strömungsmaschine

Publications (1)

Publication Number Publication Date
EP2025867A1 true EP2025867A1 (de) 2009-02-18

Family

ID=38871761

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07015785A Withdrawn EP2025867A1 (de) 2007-08-10 2007-08-10 Rotor für eine axial durchströmbare Strömungsmaschine
EP08787065A Not-in-force EP2173972B1 (de) 2007-08-10 2008-08-08 Rotor für eine axial durchströmbare strömungsmaschine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08787065A Not-in-force EP2173972B1 (de) 2007-08-10 2008-08-08 Rotor für eine axial durchströmbare strömungsmaschine

Country Status (8)

Country Link
US (1) US8459951B2 (ja)
EP (2) EP2025867A1 (ja)
JP (1) JP5235996B2 (ja)
CN (1) CN101779000B (ja)
ES (1) ES2404579T3 (ja)
PL (1) PL2173972T3 (ja)
RU (1) RU2479725C2 (ja)
WO (1) WO2009021927A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3358133A1 (en) * 2017-02-03 2018-08-08 Doosan Heavy Industries & Construction Co., Ltd. Disk assembly for gas turbine compressor

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130017092A1 (en) * 2011-07-11 2013-01-17 General Electric Company Rotor assembly for gas turbines
US20130264779A1 (en) * 2012-04-10 2013-10-10 General Electric Company Segmented interstage seal system
CN105275499B (zh) * 2015-06-26 2016-11-30 中航空天发动机研究院有限公司 一种具有离心增压和封严效果的双辐板涡轮盘盘心进气结构
US12037926B2 (en) 2016-02-05 2024-07-16 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor discs
KR101896436B1 (ko) * 2017-04-12 2018-09-10 두산중공업 주식회사 보강디스크를 포함하는 압축기 및 이를 포함하는 가스터빈
US11339662B2 (en) * 2018-08-02 2022-05-24 Siemens Energy Global GmbH & Co. KG Rotor comprising a rotor component arranged between two rotor disks
EP4013950B1 (de) * 2019-10-18 2023-11-08 Siemens Energy Global GmbH & Co. KG Rotor mit zwischen zwei rotorscheiben angeordnetem rotorbauteil

Citations (8)

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CH238207A (de) * 1943-02-15 1945-06-30 Oerlikon Maschf Aus mehreren Teilen zusammengesetzter Trommelläufer für Dampf- und Gasturbinen.
GB602656A (en) * 1944-12-20 1948-06-01 Oerlikon Maschf Improvements in or relating to rotary drums for turbines and compressors
DE898100C (de) * 1942-08-13 1953-11-26 Heinrich Dr-Ing Vorkauf Gekuehlter Gasturbinenlaeufer
GB755290A (en) * 1953-07-02 1956-08-22 Siemens Ag Improvements in or relating to gas turbine rotors
FR2566835A1 (fr) * 1984-06-27 1986-01-03 Snecma Dispositif de fixation de secteurs d'aubes sur un rotor de turbomachine
EP0846844A1 (de) * 1996-12-04 1998-06-10 Asea Brown Boveri AG Rotorzusammenbau mit kraftschlüssig und gleichzeitig form- bzw. materialschlüssig verbundenen Rotorscheiben
US6094905A (en) * 1996-09-25 2000-08-01 Kabushiki Kaisha Toshiba Cooling apparatus for gas turbine moving blade and gas turbine equipped with same
EP1672172A1 (en) * 2004-12-17 2006-06-21 United Technologies Corporation Turbine engine rotor stack

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DE1075380B (de) * 1952-05-22 1960-02-11 Siemens-Schuckertwcrkc Aktiengesellschaft, Berlin und Erlangen Flüssigkeitsgekühlter, aus Scheiben und Ringen aufgebauter Läufer für Gasturbinen
FR2272259B1 (ja) * 1974-05-21 1977-03-11 Alsthom Cgee
RU2033525C1 (ru) 1989-12-25 1995-04-20 Научно-производственное объединение "Турбоатом" Сварной барабанный ротор турбомашины
US5632600A (en) * 1995-12-22 1997-05-27 General Electric Company Reinforced rotor disk assembly
JP3149774B2 (ja) * 1996-03-19 2001-03-26 株式会社日立製作所 ガスタービンロータ
EP0921273B1 (en) * 1997-06-11 2003-12-03 Mitsubishi Heavy Industries, Ltd. Rotor for gas turbines
JP3475838B2 (ja) * 1999-02-23 2003-12-10 株式会社日立製作所 タービンロータ及びタービンロータのタービン動翼冷却方法
DE19914227B4 (de) 1999-03-29 2007-05-10 Alstom Wärmeschutzvorrichtung in Gasturbinen
US6283712B1 (en) * 1999-09-07 2001-09-04 General Electric Company Cooling air supply through bolted flange assembly

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE898100C (de) * 1942-08-13 1953-11-26 Heinrich Dr-Ing Vorkauf Gekuehlter Gasturbinenlaeufer
CH238207A (de) * 1943-02-15 1945-06-30 Oerlikon Maschf Aus mehreren Teilen zusammengesetzter Trommelläufer für Dampf- und Gasturbinen.
GB602656A (en) * 1944-12-20 1948-06-01 Oerlikon Maschf Improvements in or relating to rotary drums for turbines and compressors
GB755290A (en) * 1953-07-02 1956-08-22 Siemens Ag Improvements in or relating to gas turbine rotors
FR2566835A1 (fr) * 1984-06-27 1986-01-03 Snecma Dispositif de fixation de secteurs d'aubes sur un rotor de turbomachine
US6094905A (en) * 1996-09-25 2000-08-01 Kabushiki Kaisha Toshiba Cooling apparatus for gas turbine moving blade and gas turbine equipped with same
EP0846844A1 (de) * 1996-12-04 1998-06-10 Asea Brown Boveri AG Rotorzusammenbau mit kraftschlüssig und gleichzeitig form- bzw. materialschlüssig verbundenen Rotorscheiben
EP1672172A1 (en) * 2004-12-17 2006-06-21 United Technologies Corporation Turbine engine rotor stack

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3358133A1 (en) * 2017-02-03 2018-08-08 Doosan Heavy Industries & Construction Co., Ltd. Disk assembly for gas turbine compressor
US10787908B2 (en) 2017-02-03 2020-09-29 DOOSAN Heavy Industries Construction Co., LTD Disk assembly for gas turbine compressor

Also Published As

Publication number Publication date
EP2173972A1 (de) 2010-04-14
RU2479725C2 (ru) 2013-04-20
CN101779000B (zh) 2013-04-17
JP5235996B2 (ja) 2013-07-10
PL2173972T3 (pl) 2013-08-30
CN101779000A (zh) 2010-07-14
EP2173972B1 (de) 2013-03-06
US8459951B2 (en) 2013-06-11
WO2009021927A1 (de) 2009-02-19
JP2010535973A (ja) 2010-11-25
RU2010108465A (ru) 2011-09-20
ES2404579T3 (es) 2013-05-28
US20110318184A1 (en) 2011-12-29

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