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US10385874B2 - Pin to reduce relative rotational movement of disk and spacer of turbine engine - Google Patents

Pin to reduce relative rotational movement of disk and spacer of turbine engine Download PDF

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Publication number
US10385874B2
US10385874B2 US15/588,871 US201715588871A US10385874B2 US 10385874 B2 US10385874 B2 US 10385874B2 US 201715588871 A US201715588871 A US 201715588871A US 10385874 B2 US10385874 B2 US 10385874B2
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US
United States
Prior art keywords
spacer
disk
pin
recessed area
turbine engine
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.)
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Application number
US15/588,871
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English (en)
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US20180320708A1 (en
Inventor
Kenneth Gregory Thomas
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.)
Solar Turbines Inc
Original Assignee
Solar Turbines 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 Solar Turbines Inc filed Critical Solar Turbines Inc
Priority to US15/588,871 priority Critical patent/US10385874B2/en
Assigned to SOLAR TURBINES INCORPORATED reassignment SOLAR TURBINES INCORPORATED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: THOMAS, KENNETH GREGORY
Priority to MX2019013305A priority patent/MX2019013305A/es
Priority to AU2018264866A priority patent/AU2018264866B2/en
Priority to PCT/US2018/030938 priority patent/WO2018208577A1/fr
Priority to CN201880030216.9A priority patent/CN110603372B/zh
Publication of US20180320708A1 publication Critical patent/US20180320708A1/en
Application granted granted Critical
Publication of US10385874B2 publication Critical patent/US10385874B2/en
Active legal-status Critical Current
Adjusted expiration legal-status Critical

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Classifications

    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • 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
    • 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
    • F05D2250/13—Two-dimensional trapezoidal
    • F05D2250/132—Two-dimensional trapezoidal hexagonal
    • 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

Definitions

  • the present disclosure relates generally to turbine engines and, more particularly, to a pin for reducing relative rotational movement of a disk and a spacer of an axial compressor of the turbine engine.
  • Some axial compressors of turbine engines use spacers to provide an inner flowpath for working fluid.
  • the spacers are typically thin rings, installed onto each of a plurality of disks of the axial compressor.
  • An interference engagement or, more particularly, a thermal interference engagement and a small cylindrical anti-rotation pin are used to couple each spacer to a corresponding disk.
  • the disk and spacer pairs are oriented along a common rotational axis of the axial compressor.
  • the spacers typically cool and shrink at a higher rate than the corresponding disks, thereby relieving the thermal interference engagement.
  • the rotational inertia of the spacers often breaks the pins, allowing the spacers to rotationally shift relative to the corresponding disks from the factory set positions.
  • the turbine engine may require removal from service and disassembly.
  • U.S. Pat. No. 8,840,375 to Virkler discloses a lock assembly for a gas turbine engine.
  • the lock assembly includes a lock body with an undercut slot that receives a retaining wire of a polygon shape.
  • a rotor disk has a circumferentially intermittent slot structure extending radially outward relative to an axis of rotation.
  • a component defined about the axis of rotation has multiple radial tabs extending radially inward relative to the axis of rotation. The radial tabs are engageable with the intermittent slot structure.
  • a lock assembly, which includes the retaining wire, is engaged with at least one opening formed by the intermittent slot structure to provide an anti-rotation interface for the component.
  • an axial compressor of a turbine engine includes a plurality of disk and spacer pairs oriented along a common axis of rotation.
  • Each of a disk of the disk and spacer pairs and a spacer of the disk and spacer pairs have a contacting face defining an engagement between the disk and the spacer.
  • the contacting face of each of the disk and the spacer includes a recessed area.
  • a pin has a stem received within the recessed area of the disk and a head received within the recessed area of the spacer.
  • the head of the pin includes at least two flats corresponding to complementary surfaces of the recessed area of the spacer.
  • a method of operating a turbine engine includes steps of rotating a disk and spacer pair of a plurality of disk and spacer pairs about a common axis of rotation, and engaging a contacting face of a disk of the disk and spacer pair with a contacting face of a spacer of the disk and spacer pair during rotation.
  • the method also includes a step of restricting relative rotation of the disk and the spacer using a pin having a stem received within a recessed area of the disk and a head received within a recessed area of the spacer.
  • the restricting step includes contacting at least two flats of the head of the pin with complementary surfaces of the recessed area of the spacer.
  • a turbine engine in yet another aspect, includes an axial compressor.
  • the axial compressor includes a plurality of disk and spacer pairs oriented along a common axis of rotation, with each of a disk of the disk and spacer pairs and a spacer of the disk and spacer pairs having a contacting face defining an engagement between the disk and the spacer.
  • the contacting face of each of the disk and the spacer includes a recessed area.
  • a pin has a stem received within the recessed area of the disk and a hexagonally shaped head received within the recessed area of the spacer.
  • FIG. 1 is a partial cross section of an axial compressor of a turbine engine, according to an exemplary embodiment of the present disclosure
  • FIG. 2 is a perspective view of an exemplary pin that may be used with the axial compressor of FIG. 1 , according to the present disclosure
  • FIG. 3 is a first side view of the exemplary pin of FIG. 2 ;
  • FIG. 4 is a second side view of the exemplary pin of FIG. 2 ;
  • FIG. 5 is a top view of the exemplary pin of FIG. 2 ;
  • FIG. 6 is a partial cross section of the exemplary pin of the previous FIGS., assembled with a disk and a spacer of a turbine engine;
  • FIG. 7 is a section view taken along lines 7 - 7 of FIG. 6 ;
  • FIG. 8 is a perspective view of the spacer of the present disclosure.
  • FIG. 9 is an enlargement of a portion of the spacer of FIG. 8 ;
  • FIG. 10 is a section view taken along lines 10 - 10 of FIG. 9 ;
  • FIG. 11 is a flow diagram of an exemplary method of operating a turbine engine, according to the present disclosure.
  • FIG. 1 A portion of an exemplary turbine engine 10 is shown generally in FIG. 1 .
  • a section view of an axial compressor 12 of the turbine engine 10 is shown.
  • the turbine engine 10 may also include a combustor and a power turbine and/or a variety of additional or alternative components for compressing gas.
  • the axial compressor 12 may include a plurality of disk and spacer pairs 14 oriented along a common axis of rotation A 1 .
  • the disk and spacer pairs 14 may all have similar configurations and, as such, only a single disk and spacer pair 14 will be described.
  • Each of a disk 16 and a spacer 18 of the disk and spacer pairs 14 may have a respective contacting face 20 , 22 defining an engagement between the disk 16 and the spacer 18 . That is, at least some portion of the contacting face 20 of the disk 16 and at least some portion of the contacting face 22 of the spacer 18 may interface or connect to define the engagement. As used herein, the contacting faces 20 , 22 of the disk 16 and the spacer 18 may include surfaces of the respective components that face one another.
  • the disk 16 may have a generally cylindrical body, which may or may not be hollow, including or supporting a plurality of static blades.
  • the spacer 18 may have a thin ring-shaped body for providing space, along the common axis of rotation A 1 , between the disks 16 and, thus, providing an inner flowpath for working fluid.
  • Each spacer 18 of the disk and spacer pairs 14 may be the same material as the corresponding disk 16 , which may, for example, include stainless steel.
  • the present disclosure may be applicable to disks and spacers having various shapes, size, materials, and configurations.
  • the contacting face 20 , 22 of each of the disk 16 and the spacer 18 may include a respective recessed area 24 , 26 .
  • the recessed areas 24 , 26 which may be recessed relative to the respective contacting face 20 , 22 , may be aligned such that a pin 28 may be positioned as shown.
  • the recessed areas 24 , 26 may be aligned along an axis parallel to the common axis of rotation A 1 .
  • the pin 28 may generally include a stem 30 and a head 32 and, as will be discussed below, the stem 30 may be received at least partly within the recessed area 24 of the disk 16 and the head 32 may be received at least partly within the recessed area 26 of the spacer 18 .
  • a thermal interference engagement between the disk 16 and the spacer 18 may secure the engagement of the disk 16 , spacer 18 , and pin 28 .
  • the exemplary pin 28 including the stem 30 and the head 32 , is shown generally in FIGS. 2-5 .
  • the head 32 of the pin 28 may include a plurality of flats, or planar surfaces, 40 .
  • the head 32 may have a hexagonal shape, including six straight sides and angles.
  • the recessed area 26 , or portions thereof, of the spacer 18 may have a shape corresponding to the hexagonal shape of the head 32 , or a portion of the head 32 , of the pin 28 .
  • the stem 30 of the pin 28 may have a cylindrical shape, with the recessed area 24 , or portions thereof, of the disk 16 having a shape corresponding to the cylindrical shape of the stem 30 , or a portion of the stem 30 , of the pin 28 .
  • the pin 28 may be made from a variety of different materials, including, for example, the same material as one or both of the disk 16 and the spacer 18 .
  • the pin 28 may have a passage 42 therethrough oriented along a longitudinal axis A 2 of the pin 28 . The passage 42 may provide an escape of air when the pin 28 is pressed into a blind hole.
  • the stem 30 of the pin 28 is shown received within the recessed area 24 of the disk 16 , and the head 32 of the pin 28 is shown received within the recessed area 26 of the spacer 18 .
  • the stem 30 of the pin 28 may have a substantially cylindrical body, which may be received within a substantially cylindrical opening or cavity of the recessed area 24 .
  • the recessed area 24 may be shaped, sized, and/or configured to receive the stem 30 , such as with a frictional fit.
  • the head 32 of the pin 28 may include at least two flats 40 corresponding to complementary surfaces of the recessed area 26 of the spacer 18 . That is, the recessed area 26 may include planar surfaces having similar angles as corresponding surfaces of the head 32 of the pin 28 . Thus, the recessed area 26 may be shaped, sized, and/or configured such that at least one of the flats 40 contacts or engages a corresponding surface of the recessed area 26 during operation and/or shutdown of the turbine engine 10 .
  • a predetermined clearance 50 may be provided between a top surface 52 of the head 32 of the pin 28 and an inner surface 54 of the recessed area 26 of the spacer 18 .
  • the predetermined clearance 50 may be reduced, such as during a hot shutdown of the turbine engine 10 , as the spacer 18 cools and shrinks more quickly than the corresponding disk 16 .
  • the predetermined clearance 50 may be as small as, for example, 0.005 inch; however, the predetermined clearance 50 may vary, depending on the particular application.
  • the spacer 18 is shown in FIGS. 8, 9 and 10 and may include a thin ring-shaped body.
  • the spacer 18 may be sized, shaped, and/or configured to interact with the corresponding disk 16 in the manner described herein.
  • the spacer 18 may include at least one recessed area 26 .
  • the spacer 18 may include a plurality of recessed areas 26 , such as, for example, four recessed areas 26 , spaced about the spacer 18 .
  • the disk 16 may have a corresponding number of recessed areas 24 , with a corresponding number of pins 28 , such as four pins 28 , configured for receipt within the plurality of recessed areas 24 , 26 .
  • the head 32 of the pin 28 may include a plurality of flats 40 .
  • the recessed area 26 of the spacer 18 may have a shape corresponding to the shape of the head 32 of the pin 28 .
  • the spacer 18 may cool more quickly than the corresponding disk 16 , thus reducing the predetermined clearance 50 and causing one or more of the flats 40 to engage one or more corresponding surface of the recessed area 26 .
  • the present disclosure relates generally to turbine engines and, more particularly, to an axial compressor of a turbine engine. Further, the present disclosure relates to an axial compressor having a plurality of disk and spacer pairs. Yet further, the present disclosure is applicable to a pin for reducing relative rotational movement of a disk and a spacer of the disk and spacer pairs.
  • an exemplary turbine engine 10 includes an axial compressor 12 .
  • the axial compressor 12 includes a plurality of disk and spacer pairs 14 oriented along a common axis of rotation A 1 .
  • Each of a disk 16 and a spacer 18 of the disk and spacer pairs 14 have a contacting face 20 , 22 defining an engagement between the disk 16 and the spacer 18 .
  • the contacting face 20 , 22 of each of the disk 16 and the spacer 18 includes at least one recessed area 24 , 26 for receiving a pin 28 .
  • the pin 28 has a stem 30 received within the recessed area 24 of the disk 16 , and a head 32 , including a plurality of flats 40 , received within the recessed area 26 of the spacer 18 .
  • a flow diagram 60 representing primary steps of a method of operating the turbine engine 10 or, more particularly, the axial compressor 12 , according to the present disclosure, is shown.
  • the method includes a step of rotating the disk and spacer pair 14 about a common axis of rotation A 1 .
  • a contacting face 20 of the disk 16 may engage a contacting face 22 of the spacer 18 , at box 64 .
  • a thermal interference engagement between the disk 16 and the spacer 18 of the disk and spacer pair 14 may form. That is, the disk 16 , spacer 18 , and pin 28 may be configured to rotate together using a frictional fit or engagement.
  • a predetermined clearance 50 between a top surface 52 of the head 32 of the pin 28 , and an inner surface 54 of the recessed area 26 of the spacer 18 may be reduced.
  • relative rotation of the disk 16 and the spacer 18 may be reduced or restricted using the pin 28 , which has the stem 30 received within the recessed area 24 of the disk 16 , and the head 32 received within the recessed area 26 of the spacer 18 , at box 66 .
  • the restricting step includes contacting at least two flats 40 of the head 32 of the pin 28 with complementary surfaces of the recessed area 26 of the spacer 18 , at box 68 .
  • the restricting step may include engaging four pins 28 with four recessed areas 24 , 26 spaced about each of the disk 16 and the spacer 18 .
  • Some conventional axial compressors utilize small cylindrical pins having an interference fit with one or both of a disk and spacer.
  • the spacer may cool and shrink at a higher rate than the corresponding disk. This may relieve the designed interference fit and cause the spacer to become loose on the disk.
  • the small cylindrical pin is often insufficient to restrain the spacer in the circumferential direction. The force exerted on the pin by the rotational inertia of the spacer may cause the pin to break, thereby freeing the spacer to rotate relative to the disk from the factory setting.
  • the pin of the present disclosure reduces clocking and provides a more durable and robust engagement of the disk and spacer in the context of an axial compressor, or other similar context.
  • the spacer may cool more quickly than the corresponding disk, thus reducing the predetermined clearance and causing one or more of the flats to engage one or more corresponding surface of the recessed area.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US15/588,871 2017-05-08 2017-05-08 Pin to reduce relative rotational movement of disk and spacer of turbine engine Active 2038-02-16 US10385874B2 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US15/588,871 US10385874B2 (en) 2017-05-08 2017-05-08 Pin to reduce relative rotational movement of disk and spacer of turbine engine
MX2019013305A MX2019013305A (es) 2017-05-08 2018-05-03 Perno para reducir el movimiento rotatorio relativo de un disco y un espaciador de un motor de turbina.
AU2018264866A AU2018264866B2 (en) 2017-05-08 2018-05-03 Pin to reduce relative rotational movement of disk and spacer of turbine engine
PCT/US2018/030938 WO2018208577A1 (fr) 2017-05-08 2018-05-03 Broche pour réduire le mouvement rotatif relatif d'un disque et d'un élément d'espacement d'un moteur à turbine
CN201880030216.9A CN110603372B (zh) 2017-05-08 2018-05-03 用于减小涡轮发动机的盘和间隔件的相对旋转运动的销

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/588,871 US10385874B2 (en) 2017-05-08 2017-05-08 Pin to reduce relative rotational movement of disk and spacer of turbine engine

Publications (2)

Publication Number Publication Date
US20180320708A1 US20180320708A1 (en) 2018-11-08
US10385874B2 true US10385874B2 (en) 2019-08-20

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Family Applications (1)

Application Number Title Priority Date Filing Date
US15/588,871 Active 2038-02-16 US10385874B2 (en) 2017-05-08 2017-05-08 Pin to reduce relative rotational movement of disk and spacer of turbine engine

Country Status (5)

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US (1) US10385874B2 (fr)
CN (1) CN110603372B (fr)
AU (1) AU2018264866B2 (fr)
MX (1) MX2019013305A (fr)
WO (1) WO2018208577A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114909381B (zh) * 2021-02-07 2023-11-03 中国航发商用航空发动机有限责任公司 一种螺栓防转装配结构及采用该装配结构的航空发动机

Citations (18)

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Publication number Priority date Publication date Assignee Title
US5320488A (en) 1993-01-21 1994-06-14 General Electric Company Turbine disk interstage seal anti-rotation system
US6158102A (en) 1999-03-24 2000-12-12 General Electric Co. Apparatus and methods for aligning holes through wheels and spacers and stacking the wheels and spacers to form a turbine rotor
US20020009367A1 (en) * 2000-07-07 2002-01-24 Liheng Chen Propeller assembly incorporating improved locking structure
US6494684B1 (en) 1999-10-27 2002-12-17 Rolls-Royce Plc Locking devices
US20070177973A1 (en) 2006-01-27 2007-08-02 Mitsubishi Heavy Industries, Ltd Stationary blade ring of axial compressor
US20090148279A1 (en) 2006-10-13 2009-06-11 Siemens Power Generation, Inc. Gas turbine belly band seal anti-rotation structure
US20120244004A1 (en) 2011-03-21 2012-09-27 Virkler Scott D Component lock for a gas turbine engine
EP2546461A1 (fr) 2011-07-11 2013-01-16 General Electric Company Ensemble de rotor et moteur à turbine à gaz associé
US20140037452A1 (en) * 2012-08-06 2014-02-06 Mitsubishi Heavy Industries, Ltd. Fixture for connecting rotors of rotary machine and method of connecting rotors
US20140255192A1 (en) * 2013-03-07 2014-09-11 Alstom Technology Ltd Turbine rotor for a thermoelectric power station
US8932022B2 (en) * 2012-02-03 2015-01-13 Pratt & Whitney Canada Corp. Fastening system for fan and shaft interconnection
US20150023796A1 (en) * 2013-07-19 2015-01-22 Ralph R. Barber Expanding lock pin for turbine side entry blade
US8956122B2 (en) * 2009-09-17 2015-02-17 Siemens Aktiengesellschaft Blade fastening having safety device for turbine blades
US20160237855A1 (en) * 2015-02-16 2016-08-18 MTU Aero Engines AG Axially divided inner ring for a turbomachine and guide vane ring
US20170167522A1 (en) * 2015-12-15 2017-06-15 MTU Aero Engines AG Fastening assembly
US20180257189A1 (en) * 2017-03-13 2018-09-13 General Electric Company Machining system for turbomachine dovetail
US20180266260A1 (en) * 2017-03-16 2018-09-20 Doosan Heavy Industries & Construction Co., Ltd Apparatus for axial locking of bucket and bucket assembly and gas turbine having the same
US20180320533A1 (en) * 2017-05-04 2018-11-08 Rolls-Royce Corporation Turbine assembly with auxiliary wheel

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GB749279A (en) * 1953-12-05 1956-05-23 Power Jets Res & Dev Ltd Bladed rotors for multistage axial flow compressors, turbines and like fluid flow machines
GB897415A (en) * 1959-10-20 1962-05-30 Rolls Royce Improvements in or relating to bladed rotors
US3263962A (en) * 1965-04-22 1966-08-02 Gen Motors Corp Rotor blade lock
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FR2607866B1 (fr) * 1986-12-03 1991-04-12 Snecma Axes de fixation de rotors de turbomachine, procede de montage et rotors ainsi montes
US5388963A (en) * 1993-07-02 1995-02-14 United Technologies Corporation Flange for high speed rotors
JPH11132166A (ja) * 1997-10-28 1999-05-18 Mitsubishi Heavy Ind Ltd スクロール型流体機械
FR2869374B1 (fr) * 2004-04-23 2009-01-30 Snecma Moteurs Sa Systeme de fixation de pieces par des goujons a collerettes
WO2012141846A2 (fr) * 2011-04-11 2012-10-18 Borgwarner Inc. Boîtier de palier d'un turbocompresseur à gaz d'échappement

Patent Citations (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5320488A (en) 1993-01-21 1994-06-14 General Electric Company Turbine disk interstage seal anti-rotation system
US6158102A (en) 1999-03-24 2000-12-12 General Electric Co. Apparatus and methods for aligning holes through wheels and spacers and stacking the wheels and spacers to form a turbine rotor
US6494684B1 (en) 1999-10-27 2002-12-17 Rolls-Royce Plc Locking devices
US20020009367A1 (en) * 2000-07-07 2002-01-24 Liheng Chen Propeller assembly incorporating improved locking structure
US20070177973A1 (en) 2006-01-27 2007-08-02 Mitsubishi Heavy Industries, Ltd Stationary blade ring of axial compressor
US20090148279A1 (en) 2006-10-13 2009-06-11 Siemens Power Generation, Inc. Gas turbine belly band seal anti-rotation structure
US8956122B2 (en) * 2009-09-17 2015-02-17 Siemens Aktiengesellschaft Blade fastening having safety device for turbine blades
US20120244004A1 (en) 2011-03-21 2012-09-27 Virkler Scott D Component lock for a gas turbine engine
US8840375B2 (en) 2011-03-21 2014-09-23 United Technologies Corporation Component lock for a gas turbine engine
EP2546461A1 (fr) 2011-07-11 2013-01-16 General Electric Company Ensemble de rotor et moteur à turbine à gaz associé
US8932022B2 (en) * 2012-02-03 2015-01-13 Pratt & Whitney Canada Corp. Fastening system for fan and shaft interconnection
US20140037452A1 (en) * 2012-08-06 2014-02-06 Mitsubishi Heavy Industries, Ltd. Fixture for connecting rotors of rotary machine and method of connecting rotors
US20140255192A1 (en) * 2013-03-07 2014-09-11 Alstom Technology Ltd Turbine rotor for a thermoelectric power station
US20150023796A1 (en) * 2013-07-19 2015-01-22 Ralph R. Barber Expanding lock pin for turbine side entry blade
US20160237855A1 (en) * 2015-02-16 2016-08-18 MTU Aero Engines AG Axially divided inner ring for a turbomachine and guide vane ring
US20170167522A1 (en) * 2015-12-15 2017-06-15 MTU Aero Engines AG Fastening assembly
US20180257189A1 (en) * 2017-03-13 2018-09-13 General Electric Company Machining system for turbomachine dovetail
US20180266260A1 (en) * 2017-03-16 2018-09-20 Doosan Heavy Industries & Construction Co., Ltd Apparatus for axial locking of bucket and bucket assembly and gas turbine having the same
US20180320533A1 (en) * 2017-05-04 2018-11-08 Rolls-Royce Corporation Turbine assembly with auxiliary wheel

Also Published As

Publication number Publication date
MX2019013305A (es) 2020-02-07
US20180320708A1 (en) 2018-11-08
CN110603372A (zh) 2019-12-20
AU2018264866B2 (en) 2023-11-30
WO2018208577A1 (fr) 2018-11-15
AU2018264866A1 (en) 2019-12-05
CN110603372B (zh) 2022-04-29

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