WO2016060686A1 - Boulon de broche de turbine à gaz doté d'un manchon ajusté par contraction - Google Patents

Boulon de broche de turbine à gaz doté d'un manchon ajusté par contraction Download PDF

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Publication number
WO2016060686A1
WO2016060686A1 PCT/US2014/061134 US2014061134W WO2016060686A1 WO 2016060686 A1 WO2016060686 A1 WO 2016060686A1 US 2014061134 W US2014061134 W US 2014061134W WO 2016060686 A1 WO2016060686 A1 WO 2016060686A1
Authority
WO
WIPO (PCT)
Prior art keywords
bolt
sleeve
spindle
shoulder
axial
Prior art date
Application number
PCT/US2014/061134
Other languages
English (en)
Inventor
Manish S. GURAO
Kevin M. LIGHT
Robert T. Brooks
Original Assignee
Siemens Aktiengesellschaft
Siemens Energy, Inc.
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 Aktiengesellschaft, Siemens Energy, Inc. filed Critical Siemens Aktiengesellschaft
Priority to PCT/US2014/061134 priority Critical patent/WO2016060686A1/fr
Publication of WO2016060686A1 publication Critical patent/WO2016060686A1/fr

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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
    • 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
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/332—Maximum loads or fatigue criteria

Definitions

  • the present invention relates generally to rotor structures in gas turbine engines and, more particularly, to a rotor structure including a spindle bolt structure for reducing fatigue in turbine spindle bolts of gas turbine engines.
  • Turbomachines such as gas turbine engines, generally include a compressor section, a combustor section and a turbine section.
  • a rotor is typically provided extending axially through the sections of the gas turbine engine and includes structure supporting rotating blades in the compressor and turbine sections.
  • a portion of the rotor extending through the turbine section comprises a plurality of turbine disks joined together wherein each turbine disk is adapted to support a plurality of turbine blades.
  • a portion of the rotor extending through the compressor section comprises a plurality of compressor disks joined together wherein each compressor disk is adapted to support a plurality of compressor blades.
  • the portions of the rotor in the turbine and compressor sections are connected by a torque tube.
  • the turbine disks are joined together by a plurality of spindle bolts extending longitudinally through the turbine disks in the axial direction.
  • the spindle bolts are subjected to stresses which may comprise preload stresses and stresses resulting from thrust, centrifugal force, and/or thermal effects.
  • a spindle bolt structure in a gas turbine engine, the gas turbine engine including a rotor including plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk.
  • the spindle bolt structure comprises a spindle bolt having a shaft portion extending through the turbine disks and disposed offset from a rotational axis of the turbine disks.
  • the seal disk includes an upstream axial face and an opposing downstream axial face, and a bolt hole extending between the upstream and downstream axial faces.
  • the spindle bolt extends through the bolt hole and includes a bolt shoulder having a diameter greater than a diameter of the shaft portion and having opposing axial bolt shoulder ends located within the bolt hole.
  • a cylindrical sleeve is provided having an interior sleeve surface positioned in engagement with an outer surface of the bolt shoulder and having an outer sleeve surface engaged on the seal disk within the bolt hole for locating the shaft portion out of contact with the seal disk and effecting a reduction in fretting fatigue of the spindle bolt, wherein the sleeve includes opposing axial sleeve ends that are axially aligned with the axial bolt shoulder ends.
  • An inner surface of the sleeve can engage an outer surface of the bolt shoulder in an interference fit to effect retention of the sleeve on the bolt shoulder.
  • the sleeve can be formed of a different material than the spindle bolt and can be affixed to the bolt shoulder by a shrink fit to effect a stress in the sleeve that is transverse to the axial direction.
  • the sleeve can be formed of INCONEL ® X-750.
  • the bolt shoulder ends can be defined by a radius extending continuously radially outward from the shaft portion to the outer bolt shoulder surface.
  • the sleeve ends can be formed with a radius in a radial outward direction that is a continuation of the radius of the bolt shoulder ends.
  • the sleeve can be engaged with the seal disk an axial distance that is about 75% of the axial distance between the opposing upstream and downstream axial faces of the seal disk.
  • a spindle bolt structure in a gas turbine engine, the gas turbine engine including a rotor including plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk.
  • the spindle bolt structure comprises a spindle bolt having a shaft portion extending through the turbine disks and disposed offset from a rotational axis of the turbine disks.
  • the seal disk includes an upstream axial face and an opposing downstream axial face, and a bolt hole extending between the upstream and downstream axial faces.
  • the spindle bolt extends through the bolt hole and includes a cylindrical bolt shoulder having a diameter greater than a diameter of the shaft portion and having opposing axial bolt shoulder ends located within the bolt hole.
  • a cylindrical sleeve is provided having an interior sleeve surface affixed in a shrink fit engagement with an outer surface of the bolt shoulder and having an outer sleeve surface engaged on the seal disk within the bolt hole for locating the shaft portion out of contact with the seal disk and effecting a reduction in fretting fatigue of the spindle bolt, wherein the sleeve includes opposing axial sleeve ends and an axial length of the sleeve between the sleeve ends that is located between the axial bolt shoulder ends.
  • the sleeve can be formed of a different material than the spindle bolt for effecting a shrink fitting operation affixing the sleeve to the bolt shoulder and effecting a stress in the sleeve that is transverse to the axial direction.
  • the sleeve can be formed of INCONEL ® X-750.
  • the sleeve ends can be axially aligned with the bolt shoulder ends.
  • the bolt shoulder ends can be defined by a radius extending continuously radially outward from the shaft portion to the outer bolt shoulder surface.
  • the sleeve ends can be formed with a radius in a radial outward direction that is a continuation of the radius of the bolt shoulder ends.
  • the sleeve can be engaged with the seal disk an axial distance that is about 75% of the axial distance between the opposing upstream and downstream axial faces of the seal disk.
  • a method of providing a spindle bolt structure for use in a rotor including a plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk.
  • the method includes providing a spindle bolt having a shaft portion configured to extend through the turbine disks at a location disposed offset from a rotational axis of the turbine disks; providing a bolt shoulder on the spindle bolt, the bolt shoulder having a diameter greater than a diameter of the shaft portion and having opposing axial bolt shoulder ends for positioning within a bolt hole defined between upstream and downstream faces of a seal disk; and affixing a sleeve to the bolt shoulder.
  • the step of affixing the sleeve to the bolt shoulder including: heating the sleeve to a temperature greater than the bolt shoulder to expand the sleeve; positioning the sleeve axially over the bolt shoulder; and cooling the sleeve to contract the sleeve and affix the sleeve to the bolt shoulder in a shrink fit engagement.
  • the sleeve can be formed of a different material than the spindle bolt.
  • the sleeve can have an axial length defined between opposing sleeve ends and, following cooling the sleeve, the sleeve ends are located adjacent to the bolt shoulder ends.
  • the bolt shoulder ends can be defined by a radius extending continuously radially outward from the shaft portion to an outer bolt shoulder surface, and the method can further include: grinding the sleeve ends to form the sleeve ends with a radius in a radial outward direction that is a continuation of the radius of the bolt shoulder ends.
  • Fig. 1 is an elevational cross-section view of a gas turbine engine illustrating an area of potential spindle bolt failure determined in accordance with an aspect of the present invention
  • Fig. 2 is an enlarged elevational cross-section view of a seal disk portion of the rotor in the gas turbine engine of Fig. 1 ;
  • Fig. 3A is an elevational cross-section view of a seal disk portion of a rotor illustrating a spindle bolt structure in accordance with the present invention
  • Fig. 3B is a perspective partial cross-sectional view of a seal disk end of the spindle bolt structure shown in Fig. 3A;
  • Fig. 4 is a diagram illustrating a process for forming a spindle bolt structure in accordance with an aspect of the present invention.
  • Fig. 5 is a modified Goodman diagram illustrating a comparison of stresses in the spindle bolt structure of Fig. 3A to the stresses in the spindle bolt structure of Figs. 1 and 2.
  • a gas turbine engine 10 including a
  • the compressor section 12 comprises a plurality of stages, each stage comprising a compressor disk 18 forming a portion of a rotor 20, and each compressor disk 18 supporting a row of compressor blades 22. Compressed exit air from the
  • compressor section 12 is supplied to a combustor shell 24 of the combustor section 14 and is directed to a combustor 26 where the air is mixed with fuel and ignited to produce hot working gases for producing power in the turbine section 16.
  • the turbine section 16 includes a plurality of turbine stages, illustrated as first through fourth stages 28a, 28b, 28c, 28d.
  • Each of the turbine stages 28a, 28b, 28c, 28d comprises a respective one of first through fourth turbine disks 30a, 30b, 30c, 30d that define a portion of the rotor 20, and each of the turbine disks 30a, 30b, 30c, 30d supports a plurality of blades 32 for converting the energy of the hot working gases into rotational movement of the rotor 20.
  • the rotor 20 further comprises a torque tube 34 extending between the compressor section 12 and the turbine section 16 for transferring output power from the turbine section 16 to the compressor section 12, where a portion of the output power is used to drive the compressor disks 18 and blades 22, and the remaining portion of the output power is used to drive an output device, such as electrical generator (not shown) in a power generation plant.
  • a torque tube 34 extending between the compressor section 12 and the turbine section 16 for transferring output power from the turbine section 16 to the compressor section 12, where a portion of the output power is used to drive the compressor disks 18 and blades 22, and the remaining portion of the output power is used to drive an output device, such as electrical generator (not shown) in a power generation plant.
  • the rotor 20 includes a seal disk 36 at a location between the turbine section 16 and the combustor section 14, supported between the first stage turbine disk 30a and the torque tube 34.
  • the seal disk 36 defines and upstream axial face 54 and a downstream axial face 56 and includes a rotating seal 38 cooperating with a stationary seal structure 40 adjacent to the combustor shell 24 and forming a seal between the turbine section 16 and the combustor section 14.
  • a spindle bolt structure comprises a plurality of spindle bolts 42 (only one shown) that extend through the turbine disks 30a-d, and pass through the seal disk 36 and an end portion 80 (Fig. 2) of the torque tube 34.
  • the spindle bolts 42 are disposed circumferentially around and are offset from a rotational axis 43 of the turbine disks 30a-d.
  • the spindle bolts 42 include a first terminal end 45 adjacent the compressor side of the disks 30a-d at the torque tube 34, and an opposing second terminal end 47 adjacent an exhaust side of the turbine disks 30a-d wherein the first terminal end 45 typically includes a retaining nut 44 engaged against the end 80 of the torque tube 34 (see also Fig. 2).
  • the spindle bolts 42 define a connecting structure spanning the turbine section 16 to join the turbine disks 30a-d of the portion of the rotor 20 extending through the turbine section 16.
  • the rotor 20 is supported for rotation on a downstream bearing 46 adjacent to the fourth stage rotor disk 30d at an exhaust section 48 of the gas turbine engine 10, and is further supported for rotation on an upstream bearing 50 adjacent to an inlet section 52 of the engine 10.
  • a failure of a spindle bolt 42 may occur in existing turbine engines 10 having a rotor construction, such as is described above with reference to Fig. 1 .
  • a failure of a spindle bolt 42 may occur in the area generally indicated along an incremental length section F A (Fig. 2), located within the seal disk 36.
  • F A incremental length section
  • Various factors are typically anticipated in specifying the design for the spindle bolts 42 in order to ensure that the spindle bolts 42 are capable of withstanding stresses exerted in the rotors 20. Such factors include possible effects from stresses induced by loads due to thrust, a centrifugal force, or thermal effects.
  • a preload stress is typically present on the spindle bolts 42, which comprises a stress induced by a predetermined tension applied on the bolts 42 during assembly of the rotor 20 for maintaining the turbine disks 30a-d, seal disk 36 and torque tube 34 joined together.
  • spindle bolts 42 Known design practice permits specification of the spindle bolts 42 to withstand the conventionally anticipated stresses experienced by the spindle bolts 42 as a result of forces generated by thrust, rotation of the rotor 20 and thermal effects, which are generally referenced herein as baseline or mean stresses. That is, the mean stresses generated by thrust, rotation of the rotor 20 and thermal effects, and substantially due to centrifugal forces with rotation of the rotor 20, are generally predictable, permitting the spindle bolts 42 to be designed, including a factor of safety, to withstand these predicted stresses.
  • the rotor 20 normally experiences a sag between the bearings 46, 50, resulting in a certain amount of axial elongation of the spindle bolts 42 as the bolts 42 each rotate with the rotor 20 from top-dead-center (TDC) to bottom-dead-center (BDC).
  • TDC top-dead-center
  • BDC bottom-dead-center
  • a cyclically occurring bolt stretch or elongation can occur in the axial direction (Fig. 2) of the spindle bolt 42, extending from a stationary end at the nut 44 to a location generally adjacent to the downstream axial face 56 of the seal disk 36, as depicted by the axial length A L in Figs. 1 and 2.
  • the axial length section A L generally will exhibit a minimum axial elongation at TDC, and a maximum axial elongation at BDC. It is believed that an aspect contributing to failure of the spindle bolt 42 comprises high cycle fatigue (HCF) that can result in a fretting effect (fretting fatigue) associated with the cyclically occurring lengthwise or axial movement of the spindle bolt 42 relative to the spindle bolt hole 58 in the seal disk 36 and the torque tube 34 as the length of the seal bolt 42 changes in the axial length section A L .
  • the fretting effect comprises an alternating stress, S, produced by high traction forces formed at an interface between the contacting surfaces of the spindle bolt 42 and the spindle bolt hole 58.
  • a spindle bolt structure 60 including a modified spindle bolt 42a which is provided in accordance with the present invention to reduce the fatigue stress and associated crack propagation in the spindle bolt 42a that could be produced as a result of the relative movement between the surfaces of the spindle bolt 42a and the spindle bolt hole 58 defined in the seal disk 36.
  • the spindle bolt 42a includes a shaft portion 68 corresponding to a portion of the spindle bolt 42a that does not contact an inner surface 78 of the seal disk 36 defined by the bolt hole 58.
  • a bolt shoulder 62 s extends radially outward from an outer surface of the shaft portion 68, and is defined by an axially extending portion of the spindle bolt 42a having opposing axial bolt shoulder ends 64, 66 that are located within the bolt hole 58 between the upstream and downstream axially facing surfaces 54, 56 of the seal disk 36.
  • the bolt shoulder 62 s defines a diameter, D s , that is greater than a diameter, D B , of the shaft portion 68 of the spindle bolt 42a, and the diameter D s , is less than a diameter, D H , defined by the bolt hole 58.
  • the spindle bolt 42a may include additional shoulder portions, such as is illustrated by a bolt shoulder 62 T for cooperating within a hole in the torque tube (not illustrated in Fig. 3A). It may be understood that plural shaft portions 68 may be provided located between spaced shoulder portions (not shown) formed along the length of the spindle bolt 42a.
  • the spindle bolt structure 60 includes a cylindrical sleeve 70 positioned on the spindle bolt 42a.
  • the sleeve 70 defines an interior sleeve surface 72 positioned in engagement with an outer surface 74 of the bolt shoulder 62 s , and the sleeve 70 defines an outer sleeve surface 76 engaged on the inner surface 78 of the seal disk 36 within the bolt hole 36.
  • the sleeve 70 includes opposing axial sleeve ends 82, 84 that are axially aligned with the axial bolt shoulder ends 64, 66.
  • the sleeve 70 provides a substantial thickness of material separating the bolt shoulder 62 s from the inner surface 78 of the seal disk 36, and can define a radial thickness or height, H-i , that is greater than the radial distance or height, H 2 , of the outer bolt shoulder surface 74 from the shaft portion 68.
  • the sleeve thickness, H-i is preferably designed with reference to thick pressure vessel theories.
  • the sleeve 70 can be designed such that the radial thickness h is greater than 1/20 times the mean diameter of the sleeve 70.
  • the sleeve 70 is engaged with the seal disk 36 along a substantial axial extent of the bolt hole 58, and includes a length of the sleeve 70 between the bolt shoulder ends 64, 66 that can be engaged with the seal disk 36 an axial distance, D-i , that is about 75% of the axial distance, D 2 , between the opposing upstream and downstream axial faces 54, 56 of the seal disk 36.
  • the sleeve 70 operates to locate the shaft portion 68 of the spindle bolt 68 in spaced relation to the inner surface 78 of the seal disk 36, and forms an interface between the bolt shoulder 62 s and the inner surface 78 of the seal disk 36 for effecting a reduction in fretting fatigue of the spindle bolt 42a. That is, the sleeve 70, which does not carry the axial tension of the spindle bolt 42a, can absorb and isolate the spindle bolt 42a from energy associated with the HCF loading, such that the operational life of the spindle bolt 42a can be extended.
  • the inner surface 72 of the sleeve 70 can engage the outer surface 74 of the bolt shoulder 62 s in an interference fit to effect retention of the sleeve 70 on the bolt shoulder 62 s .
  • the sleeve 70 can be formed of a different material than the spindle bolt 42a and is affixed to the bolt shoulder 62 s by a shrink fit.
  • the spindle bolt 42a can be formed of a high-strength, corrosion-resistant, nickel-chromium based alloy, such as INCONEL ® 718 (UNS N07718/W.Nr.
  • the sleeve 70 can be formed of a precipitation-hardenable nickel-chromium based alloy, such as INCONEL ® X-750 (UNS N07750/W. Nr.
  • the shrink fit of the sleeve on the spindle bolt 42a creates a stress in the sleeve 70 that is transverse to the axial direction, i.e., a stress can be formed in the sleeve 70 extending in the circumferential direction perpendicular to the axial direction of the spindle bolt 42a.
  • the sleeve 70 can eliminate or substantially decrease the likelihood of bolt fracture by separating the bolt 42a from contact with the seal disk 36, and addressing the three modes of bolt fracture that include: 1 ) crack initiation, that can be caused by high contact stress and fretting fatigue on the bolt 2) crack propagation, occurring under HCF and resulting from a high mean stress in the bolt due to bolt preload, and 3) fracture, occurring under tension.
  • the spindle bolt structure 60 is configured such that a crack can initiate on the outer sleeve surface 76, where it comes in contact with the seal disk 36, due to stress and fretting.
  • a crack will not initiate on the bolt surface 74, such that the sleeve 70 eliminates crack initiation on the bolt 42a.
  • the sleeve 70 will not fracture.
  • the likelihood of a bolt fracture can be eliminated or substantially decreased.
  • each of the sleeve ends 82, 84 that can be axially aligned with the bolt shoulder ends 64, 66 and can additionally extend axially away from the bolt shoulder ends 64, 66 in a direction toward the axial center of the sleeve 70.
  • the bolt shoulder ends 64, 66 are defined by a radius extending continuously radially outward from the shaft portion 68 to the outer bolt shoulder surface 74.
  • the sleeve ends 82, 84 are formed with a radius in a radial outward direction that is a continuation of the radius of the bolt shoulder ends 64, 66, such that a continuous smooth radius, R, is formed at each end of the bolt shoulder 62 s and sleeve 70 from the shaft portion 68 to the outer sleeve surface 76.
  • the radius, R can have a radius center, R c , located radially outward from the inner surface 78 of the seal disk 36 defined by the bolt hole 58.
  • the radius, R is provided to reduce or limit stresses at the ends 82, 84 of the sleeve 70.
  • a spindle bolt is provided and a bolt shoulder is provided on the spindle bolt (100).
  • a sleeve is provided (102), and the sleeve is heated to a temperature greater than the bolt shoulder to expand the sleeve (104).
  • the sleeve is positioned axially over the bolt shoulder (106) with the ends of the sleeve axially aligned adjacent to the ends of the bolt shoulder.
  • the sleeve is cooled to contract the sleeve in a shrink fit engagement on the bolt shoulder (108), affixing the sleeve to the bolt shoulder in an interference fit.
  • the ends of the sleeve are then ground to contour the sleeve ends with a radius in a radial outward direction that is a continuation of the radius of the bolt shoulder ends (1 10).
  • Fig. 5 is a modified Goodman diagram illustrating a comparison of the alternating stress in the spindle bolt 42 of Fig. 2, identified by data point O, and the alternating stress in the spindle bolt 42a of the spindle bolt structure 60 in
  • the axes of the diagram provide a comparison of the spindle bolt structures on a normalized basis of arbitrary units (Au).
  • the line 86 comprises a separation line defining a separation between a safe zone of operation 88 below the line, and a dangerous zone of operation 90 above the line, where any data points depicting operation in the dangerous zone of operation 90 would indicate a likely failure of the component.
  • the difference between the length of the lines A L and O L represents the increase in the margin of safety of the alternating stress, as provided by the spindle bolt structure 60 of the present invention.
  • the present invention provides a substantial improvement (increase) in the margin of safety of the alternating stress, as provided by including the sleeve 70 in the construction of the spindle bolt structure 60.
  • the location of the line 86 may vary during operation of the gas turbine engine, for example by shifting to the left, and the additional margin of safety depicted by data point A represents a reduction in alternating stress that is believed to ensure that the spindle bolt structure 60 remains in the safe operating zone 88 during varying operating conditions of the engine.

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

Abstract

Structure de boulon de broche (60) comprenant un boulon (42a) de broche possédant une partie arbre (68) s'étendant dans des disques (30a, 30b, 30c, 30d) de turbine d'un moteur à turbine à gaz (10). Le boulon (42a) de broche s'étend dans le trou (58) pour boulon d'un disque d'étanchéité (36) et comprend un épaulement (62s) de boulon ayant un diamètre (Ds) supérieur à un diamètre de la partie arbre (DB) et ayant des extrémités d'épaulement de vis boulon axiales opposées (64, 66) situées dans le trou (58) pour boulon. Un manchon cylindrique (70) est prévu, ayant une surface de manchon intérieure (72) positionné en prise avec une surface extérieure (74) de l'épaulement (62s) de boulon et ayant une surface de manchon extérieure (76) en prise sur le disque d'étanchéité (36) dans le trou (58) pour boulon. Le manchon (70) comprend des extrémités de manchon axiales opposées (82, 84) qui sont alignées axialement sur les extrémités d'épaulement de boulon axiales (64, 66).
PCT/US2014/061134 2014-10-17 2014-10-17 Boulon de broche de turbine à gaz doté d'un manchon ajusté par contraction WO2016060686A1 (fr)

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Application Number Priority Date Filing Date Title
PCT/US2014/061134 WO2016060686A1 (fr) 2014-10-17 2014-10-17 Boulon de broche de turbine à gaz doté d'un manchon ajusté par contraction

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Application Number Priority Date Filing Date Title
PCT/US2014/061134 WO2016060686A1 (fr) 2014-10-17 2014-10-17 Boulon de broche de turbine à gaz doté d'un manchon ajusté par contraction

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT202100010781A1 (it) * 2021-04-28 2022-10-28 Nuovo Pignone Tecnologie Srl Rotore di turbomacchina con giranti impilate e turbomacchina

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB599809A (en) * 1945-01-15 1948-03-22 Bristol Aeroplane Co Ltd Improvements in axial flow compressors, turbines and the like
GB723882A (en) * 1951-09-05 1955-02-16 Vickers Electrical Co Ltd Improvements in the construction of rotors for steam- and gas-turbines
FR2111096A5 (fr) * 1970-10-07 1972-06-02 Carrier Corp
FR2329882A1 (fr) * 1975-10-28 1977-05-27 Europ Turb Vapeur Disposition de centrage de tirants assemblant des pieces tournantes
JPS57210103A (en) * 1981-06-17 1982-12-23 Hitachi Ltd Stacked rotor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB599809A (en) * 1945-01-15 1948-03-22 Bristol Aeroplane Co Ltd Improvements in axial flow compressors, turbines and the like
GB723882A (en) * 1951-09-05 1955-02-16 Vickers Electrical Co Ltd Improvements in the construction of rotors for steam- and gas-turbines
FR2111096A5 (fr) * 1970-10-07 1972-06-02 Carrier Corp
FR2329882A1 (fr) * 1975-10-28 1977-05-27 Europ Turb Vapeur Disposition de centrage de tirants assemblant des pieces tournantes
JPS57210103A (en) * 1981-06-17 1982-12-23 Hitachi Ltd Stacked rotor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT202100010781A1 (it) * 2021-04-28 2022-10-28 Nuovo Pignone Tecnologie Srl Rotore di turbomacchina con giranti impilate e turbomacchina
WO2022228727A1 (fr) * 2021-04-28 2022-11-03 Nuovo Pignone Tecnologie - S.R.L. Rotor de turbomachine avec rouets empilés, et turbomachine
AU2022266952B2 (en) * 2021-04-28 2023-12-21 Nuovo Pignone Tecnologie - S.R.L. Turbomachine rotor with stacked impellers and turbomachine

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