EP2118445A1 - Rotor d'une turbine à gaz - Google Patents

Rotor d'une turbine à gaz

Info

Publication number
EP2118445A1
EP2118445A1 EP08716878A EP08716878A EP2118445A1 EP 2118445 A1 EP2118445 A1 EP 2118445A1 EP 08716878 A EP08716878 A EP 08716878A EP 08716878 A EP08716878 A EP 08716878A EP 2118445 A1 EP2118445 A1 EP 2118445A1
Authority
EP
European Patent Office
Prior art keywords
rotor
tie rod
support wheel
turbine
parts
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
EP08716878A
Other languages
German (de)
English (en)
Other versions
EP2118445B1 (fr
Inventor
Guido Ahaus
Ulrich Ehehalt
Karsten Kolk
Francois Benkler
Harald Hoell
Walter Loch
Harald Nimptsch
Oliver Schneider
Peter-Andreas Schneider
Peter Schröder
Vyacheslav Veitsman
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 EP08716878A priority Critical patent/EP2118445B1/fr
Publication of EP2118445A1 publication Critical patent/EP2118445A1/fr
Application granted granted Critical
Publication of EP2118445B1 publication Critical patent/EP2118445B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/13—Two-dimensional trapezoidal
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components

Definitions

  • the invention relates to a rotor according to the preamble of
  • Claim 1 The invention further relates to a thermal
  • Thermal turbomachinery includes steam and gas turbines as well as rotary compressors. These usually have a rotatably mounted rotor surrounded by a stationary housing.
  • the fixed components of a thermal turbomachine are collectively referred to as a stator.
  • a flow channel extending in the axial direction of the turbomachine for a compressible flow medium is arranged.
  • blades On the rotor usually in the flow channel projecting and combined into blade groups or blade rows blades blades are attached.
  • the blades serve to drive the rotor shaft by momentum transfer from a hot and pressurized flow medium.
  • the thermal energy of the flow medium is thus converted in its relaxation in mechanical energy that can be used for example to drive an electric generator.
  • the rotor shaft z. B. driven by an electric or internal combustion engine or otherwise.
  • the rotor blades arranged on the rotor serve to compress the flow medium in the flow channel, which at the same time warms up during this process.
  • mechanical energy is converted into thermal energy of the flow medium.
  • the rotor of a gas turbine which is also referred to as a rotor, is usually exposed to high mechanical and thermal stress.
  • the rotor components forming the rotor are heavily stressed. Nevertheless, in order to be able to ensure operational safety on the one hand and to keep the manufacturing costs of the runner within acceptable limits on the other hand, a large number of design options have been proposed in the past.
  • a proposed embodiment of the rotor for example, by the production of a part feasible.
  • a production method is comparatively complicated in the production process.
  • no order-independent prefabrication and no parallel processing of individual parts is possible, resulting in high production throughput times.
  • a larger axial distance between the adjacent blade rings must be taken in order to produce with appropriate tools necessary for attachment of the blade contours can.
  • these production-related relatively large distances between the blade rings deteriorate the rotor dynamics.
  • each rotor part has an axially extending recess through which the tensioned tie rod can extend.
  • Function of the rotor can affect and cause damage to the turbine.
  • the invention is therefore based on the object of specifying a rotor of the type mentioned above, which ensures safe operation of the gas turbine even with increasing overall length. Furthermore, the vibration amplitudes of the tie rod, especially in the region of the central hollow shaft should be kept as small as possible. This object is achieved by the tie rod is supported in its central region. In this case, the support wheel arranged between the turbine-side section and the compressor-side section constitutes a rotor component supporting the tie rod.
  • the invention is based on the consideration that for a reduction of the oscillation of the tie rod this should be supported on one of the rotor components, wherein the thermally induced different expansions of the rotor components should still be compensated.
  • the fact should be taken into account that due to the increasing requirements with respect to the performance of the turbine whose length increases, whereby the natural frequency of the tie rod approaches the operating speed of the gas turbine.
  • the reduction of Switzerlanderschwingungen is achieved by the tie rod is supported by the support wheel.
  • the jockey wheel constitutes a further, supporting rotor component, wherein the jockey wheel is preferably connected to the tie rod in a region in which the amplitudes of the vibrations occurring during operation of the turbine reach their maximum values, as seen in the axial direction of the rotor ,
  • the jockey wheel is arranged between the turbine-side section of the rotor and the compressor-side section of the rotor, i. H. at the place of maximum deflection of the tie rod in case of possibly occurring Switzerlandankerschwingungen.
  • this area may be between the compressor section and the turbine section. This allows a support of the tie rod to a vibration particularly effective position.
  • the support of the tie rod is preferably achieved by non-positively and / or positively with the support wheel connected to the tie rod.
  • the support wheel can be shrunk on the tie rod.
  • This type of connection is particularly suitable, since thus a particularly rigid connection between the support wheel and the tie rod is made possible in a simple manner.
  • the thermally induced different expansions of the rotor components occurring during operation of the gas turbine, in particular between the support wheel and the tie rod can be compensated in an advantageous manner, preferably by providing at least one of the rotor components with a profile.
  • the connection between the tie rod and the support wheel be set elastically, such that the differential volume is largely compensated due to the different heating of the rotor components.
  • the hub of the support wheel is provided with a profile seen in the longitudinal section of the rotor crowned profile. With such a connection side compliant hub shape, stresses and cracks in the rotor component can be prevented.
  • the spherical profile of Stauerradnabe can also be described in other words: the cylindrical surface of the tie rod opposite surface of the Ceiankerbohrung the support wheel is - seen in the axial direction - arched, the curvature is directed to the outer surface.
  • the support wheel is connected to two adjacently arranged rotor parts by means of a Hirth gearing.
  • a Hirth gearing Using such an axially effective connection, the torques acting on the rotor can be transmitted and forwarded via the support wheel.
  • a radial guide for receiving different thermal and centrifugal deformations is ensured by means of the Hirth gearing. In particular, thus the occurrence of vibrations during operation of the gas turbine due to a thermally induced non-uniform expansion of the support wheel can be reduced.
  • the support wheel is provided with cooling holes, which are preferably arranged uniformly around the hub.
  • a rib structure is formed due to the recesses introduced for cooling in the support wheel, which allows the passage of a cooling medium in the axial direction of the rotor. Furthermore, the surface of the support wheel can be increased on the one hand by the introduced openings and a smooth transport of the cooling air can be made possible within the rotor by means of cooling air openings formed in this way.
  • the tie rod can be surrounded by a number of concentrically arranged cooling separation tubes for a suitable guidance of cooling medium, whereby these divide the channel formed between the tie rod and the rotor components encompassing it into a number of radially adjacent partial cooling channels. This ensures that the cooling of the rotor components, in particular the cooling requirement of the respective turbine stage can be carried out accordingly.
  • the cooling air separation tubes are axially divided into two sections for receiving the support wheel, such that their ends pointing in the direction of the support wheel can be guided into provided, introduced in the support wheel receiving grooves.
  • the cooling air separation pipes thus realize on the one hand an improved heat dissipation, and on the other hand, the heat capacity of this rotor component can be reduced.
  • a so-called middle hollow shaft is arranged, which is axially divided into at least two pipe sections in the case of the use of a support wheel according to the invention.
  • the pipe sections are substantially the same length.
  • the advantages achieved by the invention are, in particular, that a particularly reliable operation of the gas turbine is made possible by the support wheel connected to the tie rod with their increasing overall length.
  • the vibration amplitudes can be kept particularly small by the appropriate support of the tie rod.
  • a targeted increase in the natural frequency of the tie rod with comparatively little effort can be realized through this system.
  • the thermally induced relative movements between the tie rod and the rotor part formed as a support wheel can be compensated particularly well.
  • necessary cooling is ensured by means extending in the axial direction of the rotor cooling air, even with passage of cooling air with different pressures and temperatures, which are separated by separable tubes feasible.
  • FIG. 1 shows a longitudinal section through a turbine rotor according to the invention
  • FIG. 3 shows a schematic representation of a support wheel
  • FIG. 4 shows a section of the support wheel in longitudinal section, 5 shows a detailed detail of FIG. 4
  • a rotor 2 of a gas turbine with a number of individual, held together by a tie rod 4 and assembled into a unit rotor parts 6 is shown in Figure 1 in a longitudinal section.
  • the rotor 2 has a compressor-side section 1 and a turbine-side section 3, each having a number of rotor parts 6.
  • the respective rotor parts 6 designed as rotor disks are connected on the connection side, i. provided on the front side with symmetrical to the central axis M of the rotor 2 extending recesses in the manner of a Hirth serration, wherein the resulting contours are formed corresponding to the contours of the respective adjacent rotor part 6, whereby a concentric
  • Each of the rotor parts 6 is provided for the spaced passage of the tie rod 4 with an axially extending bore 10.
  • a middle hollow shaft 11 is arranged between the compressor-side rotor parts 6 and the turbine-side rotor parts 6. End of the tie rod 4 is bolted to a rotor part 7, 9, whereby all interposed rotor parts 6 are held together and clamped.
  • the present between the rotor parts 6 recesses 8 serve to guide a cooling medium for cooling the rotor components by cooling air is supplied via a cooling channel formed between the tie rod 4 and the rotor part 6.
  • rotor parts 6 In order to be able to support the tie rod 4 in a suitable manner by rotor components surrounding it, ie rotor parts 6, it is possible to support between two rotor parts 6, preferably between two rotor parts 6. on the rotor side 2 of the rotor 2 and the turbine-side section 3 of the rotor 2, another rotor part 6 designed as a support wheel 14 is inserted.
  • the previously one-piece central hollow shaft 11 has been divided into two pipe sections IIa, IIb, between which the support wheel 14 is preferably clamped.
  • the support wheel 14 in this case represents a further rotor component.
  • the rotor parts 6 and the support wheel 14 are clamped together by tie rods 4, wherein the support wheel 14, in contrast to the other rotor parts 6 is additionally positively and / or positively connected to the tie rod 4 ,
  • the intermediate hollow shaft 11 comprising at least two pipe sections IIa, IIb is arranged between that compressor-side rotor part 6a, which is arranged closest to the turbine-side section 3 and the turbine-side rotor part 6b, which is arranged closest to the compressor-side section 1, between which the Support wheel 14 is clamped.
  • FIG. 2 shows a cross section through the compressor outlet-side section of the rotor 2 in detail.
  • three rotor parts designed as rotor disks 6 of the compressor-side portion 1 of the rotor 2 are shown.
  • the compressor-side rotor part, which faces the turbine-side section 3 - not shown - is referred to as 6a.
  • On the front side is located on the rotor part 6a one of the two pipe sections IIa of the central hollow shaft 11 at. Radially further inside there are also two cooling air separation pipes 13 is shown.
  • Thede Kunststofftrennrohre 13 are axially divided into two sections for receiving the support wheel 14, such that their pointing in the direction of the support wheel 14 ends can be performed in designated, introduced in the support wheel 14 receiving grooves.
  • FIG. 3 shows a support wheel 14 provided with cooling openings 12, wherein the depth of the recesses 12 serving as cooling openings 12 corresponds to the material thickness of the support wheel 14 at this location.
  • the recesses 12 are introduced uniformly distributed over the cross section of the support wheel 14, so that a uniform cooling of the support wheel 14 can be done and thus stresses and uneven deformations are avoided.
  • the heat transfer to the cooling medium is particularly effective, since due to the introduced by the introduced into the wheel body 15 recesses 12 increased cooling surface more heat can be removed.
  • a serration 18 is provided on both sides of the outer rim of the support wheel 14 on both sides.
  • the consisting of two axial pipe sections middle hollow shaft 11 is then on both sides of the support wheel 14 with a corresponding Hirth toothing.
  • the hub 16 of the support wheel 14 has a profile on the tension armature side with a convex shape. This can be done in a particularly simple manner by a centrally inserted into the hub 16 circumferential groove 20 and the rounding of the front side to the Tie rod circumferential edges can be realized.
  • This tie-side profile of the hub 16 allows compensation of the occurring during operation of the gas turbine differential deformations of tie rods 4 and support wheel 14. Furthermore, this redistribution of the

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Un rotor (2) d'une turbomachine thermique, en particulier d'une turbine à gaz, avec un nombre de parties de rotor individuelles, maintenues ensemble par un tirant d'ancrage (4) et rassemblées en une unité, doit également lors d'une longueur hors tout croissante de la turbine à gaz garantir un fonctionnement fiable et sûr. A cette occasion, la fréquence propre du tirant d'ancrage (4) doit être déplacée vers les plus hautes fréquences par comparaison avec la vitesse de rotation de la turbine. A cet effet, le tirant d'ancrage (4) est supporté par la liaison des composants de rotor environnants formés du tirant d'ancrage et des disques de rotor. A cette occasion, la roue d'appui représente en combinaison avec l'arbre creux (11) en deux parties un composant de rotor supportant supplémentaire.
EP08716878A 2007-03-12 2008-02-15 Rotor d'une turbine à gaz Not-in-force EP2118445B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08716878A EP2118445B1 (fr) 2007-03-12 2008-02-15 Rotor d'une turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07005079A EP1970530A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique
EP08716878A EP2118445B1 (fr) 2007-03-12 2008-02-15 Rotor d'une turbine à gaz
PCT/EP2008/051872 WO2008110429A1 (fr) 2007-03-12 2008-02-15 Rotor d'une turbine à gaz

Publications (2)

Publication Number Publication Date
EP2118445A1 true EP2118445A1 (fr) 2009-11-18
EP2118445B1 EP2118445B1 (fr) 2011-12-21

Family

ID=38329568

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07005079A Withdrawn EP1970530A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique
EP08716878A Not-in-force EP2118445B1 (fr) 2007-03-12 2008-02-15 Rotor d'une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07005079A Withdrawn EP1970530A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique

Country Status (7)

Country Link
US (1) US8641365B2 (fr)
EP (2) EP1970530A1 (fr)
JP (1) JP5027890B2 (fr)
CN (1) CN101631932B (fr)
AT (1) ATE538287T1 (fr)
RU (1) RU2419724C1 (fr)
WO (1) WO2008110429A1 (fr)

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EP3575550A1 (fr) * 2018-05-31 2019-12-04 Rolls-Royce Corporation Moteur à turbine à gaz comportant un système d'arbre à sécurité intégrée et procédé correspondant

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EP2826956A1 (fr) * 2013-07-17 2015-01-21 Siemens Aktiengesellschaft Rotor pour une turbomachine thermique
EP2826957A1 (fr) 2013-07-17 2015-01-21 Siemens Aktiengesellschaft Rotor pour une turbomachine thermique
CN103603693A (zh) * 2013-12-05 2014-02-26 罗亚军 空心轴新动力发动机
KR101509382B1 (ko) 2014-01-15 2015-04-07 두산중공업 주식회사 댐핑 클램프를 구비한 가스 터빈
EP2933433A1 (fr) * 2014-04-15 2015-10-21 Siemens Aktiengesellschaft Procédé de montage et/ou de démontage d'une section de rotor d'une turbomachine, dispositif de montage et disque de rotor associés
EP3054089A1 (fr) * 2015-02-05 2016-08-10 Siemens Aktiengesellschaft Rotor creux d'une turbomachine avec bouclier thermique
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KR101772334B1 (ko) 2016-07-07 2017-08-28 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
KR101794451B1 (ko) 2016-07-07 2017-11-06 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
KR101834647B1 (ko) * 2016-07-07 2018-04-13 두산중공업 주식회사 디스크 조립체 및 그를 포함하는 터빈
EP3269926B1 (fr) * 2016-07-07 2020-10-07 Doosan Heavy Industries & Construction Co., Ltd. Ensemble de disque et turbine le comprenant
CN106121733B (zh) * 2016-08-12 2019-01-11 上海电气燃气轮机有限公司 一种用于重型燃气轮机的混合转子结构及组装方法
CN107269316A (zh) * 2017-08-17 2017-10-20 中南大学 一种燃气轮机中心拉杆式转子的锥形轮盘结构
CN113978901B (zh) * 2021-11-08 2023-01-31 安徽晋煤中能化工股份有限公司 一种汽轮机转子运输固定装置
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EP3575550A1 (fr) * 2018-05-31 2019-12-04 Rolls-Royce Corporation Moteur à turbine à gaz comportant un système d'arbre à sécurité intégrée et procédé correspondant
US10934844B2 (en) 2018-05-31 2021-03-02 Rolls-Royce Corporation Gas turbine engine with fail-safe shaft scheme

Also Published As

Publication number Publication date
EP1970530A1 (fr) 2008-09-17
CN101631932B (zh) 2013-01-16
RU2419724C1 (ru) 2011-05-27
WO2008110429A1 (fr) 2008-09-18
EP2118445B1 (fr) 2011-12-21
JP5027890B2 (ja) 2012-09-19
US8641365B2 (en) 2014-02-04
JP2010520967A (ja) 2010-06-17
US20100166559A1 (en) 2010-07-01
CN101631932A (zh) 2010-01-20
ATE538287T1 (de) 2012-01-15

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