US20130309087A1 - Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft - Google Patents

Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft Download PDF

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Publication number
US20130309087A1
US20130309087A1 US13/979,145 US201213979145A US2013309087A1 US 20130309087 A1 US20130309087 A1 US 20130309087A1 US 201213979145 A US201213979145 A US 201213979145A US 2013309087 A1 US2013309087 A1 US 2013309087A1
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US
United States
Prior art keywords
shaft
stub
drum
stub shafts
shaft drum
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.)
Abandoned
Application number
US13/979,145
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English (en)
Inventor
Andrew Paul Watson
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.)
Elliott Co
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Elliott Co
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Filing date
Publication date
Application filed by Elliott Co filed Critical Elliott Co
Priority to US13/979,145 priority Critical patent/US20130309087A1/en
Assigned to ELLIOTT COMPANY reassignment ELLIOTT COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WATSON, ANDREW PAUL
Assigned to ELLIOTT COMPANY reassignment ELLIOTT COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WATSON, ANDREW PAUL
Publication of US20130309087A1 publication Critical patent/US20130309087A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
    • F25B3/00—Self-contained rotary compression machines, i.e. with compressor, condenser and evaporator rotating as a single unit
    • 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
    • F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49236—Fluid pump or compressor making

Definitions

  • This invention relates, in general, to axial compressors and, more particularly, to a method of attaching a stub shaft to a drum of an axial flow compressor rotor shaft.
  • Turbo machines such as centrifugal flow compressors, axial flow compressors, and turbines are utilized in various industries.
  • Axial flow compressors in particular, have a widespread use in power stations, jet engine applications, gas turbines, and automotive applications.
  • Axial flow compressors are also commonly used in large scale industrial applications, such as air separation plants and hot gas expanders used in the oil refinery industry.
  • Axial flow compressors generally include a rotating shaft coupled to a central drum having a number of airfoil blades circumferentially arranged and spaced apart in multiple rows along the axial length of the drum.
  • the airfoil blades rotate between a corresponding number of stationary blades attached to a stationary tubular casing.
  • the working fluid such as air, enters and exits the axial compressor in the axial direction of the rotating shaft. Energy from the working fluid causes a relative motion of the rotating airfoil blades with respect to stationary blades.
  • the cross-sectional area between the central drum and the casing decreases from an inlet end to a discharge end, such that the working fluid is compressed as it passes through the axial flow compressor.
  • one or more solid stub shafts are operatively coupled to a hollow shaft drum by way of an interference connection, such as a rabbet fit. Due to the design of the stub shaft and the hollow drum, the two components tend to grow apart both radially and axially during compressor operation. The major change in dimension occurs in the radial direction. The magnitude of radial expansion of the stub shaft is usually smaller than the magnitude of radial expansion of the hollow drum, which reduces the effectiveness of the interference fit. In order to overcome this problem, prior art systems utilize long through-bolts that extend between the inlet and discharge ends of the stub shaft. The through-bolts extend in an axial direction within an annular clearance space between the stub shaft and the hollow shaft drum and prevent the shaft drum from radially growing apart from the stub shaft.
  • U.S. Pat. No. 1,142,069 to Westinghouse discloses a marine turbine including a rotor element having a drum to which an impulse wheel is bolted by means of a plurality of bolts.
  • the first shaft end is formed integrally with the impulse wheel while the second shaft end is formed integrally with the drum.
  • FIGS. 1 and 3 of the Westinghouse patent illustrate that the bolts are circumferentially arranged about the impulse wheel.
  • U.S. Pat. No. 3,749,516 to Samurin et al. discloses a rotor structure for turbo machines having stub shafts fixedly secured to the ends of a through-bolt.
  • a plurality of impellers is attached to the stub shafts.
  • the stub shafts are threaded onto the through-bolt and compressed axially to form a rigid structure.
  • a plurality of driving means in the form of pins is positioned intermediate to the impellers and between the impellers and the stub shafts.
  • Radially disposed keys are inserted between the impellers and the stub shafts to engage the pins and provide a driving connection to the impeller assembly from the stub shafts.
  • U.S. Pat. No. 7,335,108 to Lin et al. discloses a composite drive shaft with captured end adapters.
  • the drive shaft assembly includes a composite tube captured by end adapters.
  • the end adapters are captured at the end portions of the composite tube.
  • Each end adapter includes an adapter tube interface configured to engage the composite tube.
  • a plurality of lugs protrudes radially outward from the adapter tube interface to engage the composite tube at its interior surface. The lugs function to transmit the torque from the end adapters to the composite tube and vice versa.
  • a shaft assembly for an axial compressor includes a first stub shaft, a second stub shaft, and a hollow shaft drum having a longitudinal axis.
  • the first stub shaft and the second stub shaft may be coupled to opposing ends of the shaft drum along its longitudinal axis.
  • a plurality of keys may be disposed in a radial arrangement near the outer circumference of the first and second stub shafts and the shaft drum.
  • a plurality of pins may engage the plurality of keys, wherein the pins prevent the shaft drum from rotating axially relative to the first stub shaft and the second stub shaft and prevent the shaft drum from axially and radially separating from the stub shafts.
  • the shaft assembly may further include a plurality of shoulder structures provided on the first stub shaft and the second stub shaft and a plurality of shoulder recesses provided at opposing ends of the shaft drum along its longitudinal axis.
  • the plurality of shoulder structures may be operative for engaging the plurality of shoulder recesses to form a rabbet fit between the first and second stub shafts and the shaft drum for maintaining coaxial arrangement.
  • each pin of the axial shaft assembly may be dimensioned to be larger than the corresponding key to allow for an interference fit between the pin and the key.
  • each key may include a slot formed on the first and second stub shafts and a corresponding slot formed on the shaft drum.
  • the shaft drum may further include a plurality of recesses provided on its outer surface in axially-offset rows, each of the plurality of recesses operative for receiving a rotor blade.
  • one or more through-bolts may extend axially between the first and second stub shafts through the shaft drum.
  • the one or more through-bolts desirably provides a closing force to prevent relative movement between the first and second stub shafts and the shaft drum.
  • Each through-bolt may include threaded ends and a nut may be provided at each threaded end to tighten the through-bolt and couple the first and second stub shafts to the shaft drum.
  • an axial compressor may be provided to include a housing having an inlet casing provided at one end and a discharge casing provided at an opposing end and an axial shaft assembly provided inside the housing.
  • the axial shaft assembly may extend between the inlet casing and the discharge casing along the longitudinal length of the housing.
  • a plurality of stator blades may extend radially inward from an inner surface of the housing and a plurality of rotor blades may extend radially outward from the outer surface of the axial shaft assembly.
  • the axial shaft assembly may further include a first stub shaft, a second stub shaft, and a hollow shaft drum having a longitudinal axis.
  • the first stub shaft and the second stub shaft may be coupled to opposing ends of the shaft drum along its longitudinal axis.
  • a plurality of keys may be disposed in a radial arrangement near the outer circumference of the first and second stub shafts and the shaft drum.
  • a plurality of pins may engage the plurality of keys, wherein the pins prevent the shaft drum from rotating axially relative to the first stub shaft and the second stub shaft and prevent the shaft drum from axially and radially separating from the stub shafts.
  • a method of attaching stub shafts to a shaft drum of an axial compressor may include the steps of providing an axial shaft assembly having a first stub shaft, a second stub shaft, and a hollow shaft drum having a longitudinal axis.
  • the first stub shaft and the second stub shaft are desirably coupled to opposing ends of the shaft drum along its longitudinal axis.
  • the method may additionally include the step of providing a plurality of keys disposed in a radial arrangement near the outer circumference of the first and second stub shafts and the shaft drum.
  • the method may include the step of providing a plurality of pins engaging the plurality of keys, wherein the pins prevent the shaft drum from rotating axially relative to the first stub shaft and the second stub shaft and prevent the shaft drum from axially and radially separating from the stub shafts.
  • the method may further include the steps of providing a plurality of shoulder structures provided on the first stub shaft and the second stub shaft and providing a plurality of shoulder recesses provided at opposing ends of the shaft drum along its longitudinal axis.
  • the plurality of shoulder structures are operative for engaging the plurality of shoulder recesses to form a rabbet fit between the first and second stub shafts and the shaft drum for maintaining coaxial arrangement.
  • Each pin may be dimensioned to be larger than the corresponding key to allow for an interference fit between the pin and the key.
  • each key may include a slot formed on the first and second stub shafts and a corresponding slot formed on the shaft drum.
  • the method of assembling stub shafts to a shaft drum of an axial compressor may include the step of providing one or more through-bolts extending axially between the first and second stub shafts through the shaft drum.
  • the one or more through-bolts may be operative for providing a closing force to prevent relative movement between the first and second stub shafts and the shaft drum.
  • Each through-bolt may include threaded ends and a nut is provided at each threaded end to tighten the through-bolt and couple the first and second stub shafts to the shaft drum.
  • FIG. 1 is a cross-sectional view of an axial flow compressor showing the through-bolt arrangement according to the prior art
  • FIG. 2 is a cross-sectional view of internal components of an axial flow compressor according to one embodiment of the present invention
  • FIG. 3 is a detailed cross-sectional view of another embodiment of a pin in use with an axial shaft assembly in accordance with the embodiment of FIG. 2 ;
  • FIG. 4 is a detailed cross-sectional view of a pin in use with an axial shaft assembly shown in FIG. 2 ;
  • FIG. 5 is an exploded view of internal components of an axial flow compressor in accordance with another embodiment of the present invention.
  • Axial compressor 10 in accordance with a prior art embodiment is shown.
  • Axial compressor 10 includes an inlet end 20 provided opposite a discharge end 30 along the axial direction of axial compressor 10 .
  • Inlet end 20 includes an inlet casing 40 for directing the working fluid into axial compressor 10 .
  • inlet casing 40 is secured to a first end of housing 50 of axial compressor 10 by a plurality of mechanical fasteners 55 .
  • a discharge casing 60 is provided at discharge end 30 for expelling the working fluid once it is passed through axial compressor 10 .
  • Discharge casing 60 is secured to the second end of housing 50 by a plurality of mechanical fasteners 55 .
  • an axial shaft assembly 70 is provided inside housing 50 .
  • Axial shaft assembly 70 is rotatable about a longitudinal axis 80 of housing 50 to drive the working fluid from inlet end 20 to discharge end 30 .
  • Axial shaft assembly 70 includes a plurality of rotor vanes 90 extending radially outward from its outer peripheral edge.
  • a plurality of stator blades 100 extend radially inward from an inner peripheral edge of housing 50 .
  • Rotor vanes 90 and stator blades 100 are arranged in one or more alternating rows along longitudinal axis 80 .
  • Working fluid is redirected between the alternating rows of rotor vanes 90 and stator blades 100 as it is passed from inlet end 20 toward discharge end 30 .
  • a shaft seal 110 is provided at an interface with the inlet and discharge casings, 40 and 60 , respectively, to seal axial shaft assembly 70 and prevent leakage of the working fluid from axial compressor 10 .
  • Axial shaft assembly 70 further includes an inlet end stub shaft 120 and a discharge end stub shaft 130 connected to a hollow shaft drum 140 .
  • Inlet end stub shaft 120 and discharge end stub shaft 130 are connected to opposing ends of shaft drum 140 along its longitudinal axis.
  • Shoulder structures 150 are provided at inlet end stub shaft 120 and discharge end stub shaft 130 .
  • Complementary shoulder recesses 160 are provided at each end of shaft drum 140 at the interface of shaft drum 140 with each of inlet end stub shaft 120 and discharge end stub shaft 130 . Shoulder structures 150 and shoulder recesses 160 form a rabbet fit between stub shafts 120 , 130 and shaft drum 140 to maintain the coaxial arrangement of these components.
  • Stub shafts 120 , 130 are further secured to shaft drum 140 via a plurality of through-bolts 170 extending from inlet end stub shaft 120 to discharge end stub shaft 130 through shaft drum 140 .
  • a plurality of holes 180 are formed in a radial pattern around the circumference of inlet end stub shaft 120 and discharge end stub shaft 130 .
  • Through-bolt 170 is inserted through each of the plurality of holes 180 to securely connect the stub shafts to shaft drum 140 .
  • Each through-bolt 170 must be pre-stretched in order to provide a large closing force in the rabbet fit between the stub shafts 120 , 130 and shaft drum 140 . This arrangement keeps shaft drum 140 from slipping relative to each of the stub shafts 120 , 130 and prevents shaft drum 140 from axially and radially growing apart from the stub shafts 120 , 130 during operation of axial compressor 10 .
  • shaft assembly 200 is utilized with axial compressor 10 ; however, it is to be understood that this described embodiment is exemplary only, and that shaft assembly 200 may be utilized with a plurality of other turbine devices.
  • shaft assembly 200 includes an inlet end stub shaft 210 and a discharge end stub shaft 220 connected to a hollow shaft drum 230 .
  • Inlet end stub shaft 210 and discharge end stub shaft 220 are connected to opposing ends of shaft drum 230 along its longitudinal axis 240 .
  • Shaft drum 230 may be manufactured from the same material as the stub shafts 210 and 220 .
  • shaft drum 230 may be manufactured from a different material compared to stub shafts 210 and 220 .
  • Shaft drum 230 desirably, has a plurality of recesses 250 for receiving rotor blades 260 (shown in FIGS. 4-5 ).
  • Each recess 250 is provided on the outer surface of shaft drum 230 .
  • FIGS. 4 and 5 illustrate a dove-tail recess 250 ; however, other embodiments are possible without departing from the scope and spirit of the structure of shaft drum 230 .
  • each rotor blade 260 is slidingly received inside recess 250 , such that a plurality of rotor blades 260 is arranged in rows extending axially along the longitudinal length of shaft drum 230 .
  • shoulder structures 270 are provided at inlet end stub shaft 210 and discharge end stub shaft 220 .
  • Complementary shoulder recesses 280 are provided at each end of shaft drum 230 at the interface of shaft drum 230 with each of inlet end stub shaft 210 and discharge end stub shaft 220 .
  • Shoulder structures 270 and shoulder recesses 280 form a rabbet fit between stub shafts 210 and 220 and shaft drum 230 to maintain the coaxial arrangement of these components.
  • Shoulder structures 270 desirably extend over shoulder recesses 280 in a radial direction of shaft drum 230 . This arrangement keeps shaft drum 230 from slipping relative to each of the stub shafts 210 and 220 and prevents shaft drum 230 from axially and radially growing apart from the stub shafts 210 and 220 during operation of axial compressor 10 .
  • stub shafts 210 and 220 are further secured to shaft drum 230 via a plurality of pins 290 secured inside a plurality of keys 300 provided on the stub shafts 210 , 220 , and shaft drum 230 .
  • Keys 300 are disposed in a radial arrangement near the outer circumference of the stub shafts 210 , 220 and shaft drum 230 .
  • Each key 300 includes a stub shaft slot 310 and a corresponding shaft drum slot 320 provided on the respective components.
  • Each key 300 may be rounded in cross-section; however, one of ordinary skill in the art will recognize that other shapes, such as square or rectangular, may also be possible.
  • Each pin 290 is shaped such that it may be disposed inside a corresponding key 300 .
  • each pin 290 may have an elongated cylinder shape that corresponds to key 300 .
  • each pin 290 is dimensioned slightly larger than a corresponding key 300 to allow for an interference fit between pin 290 and key 300 . This arrangement keeps shaft drum 230 from slipping relative to each of the stub shafts 210 and 220 and prevents shaft drum 230 from axially and radially growing apart from the stub shafts 210 and 220 during operation of axial compressor 10 .
  • pin 290 includes a recess 370 extending axially inward from one end of pin 290 .
  • Recess 370 is desirably coaxial with a longitudinal axis of pin 290 and extends through a portion of the body of pin 290 .
  • Recess 370 is shaped to accommodate a pin insertion tool (not shown) for inserting pin 290 into corresponding key 300 .
  • a pin insertion tool (not shown) for inserting pin 290 into corresponding key 300 .
  • Recess 370 is provided to facilitate handling of pin 290 as it is moved from a cooling station, such as a container with liquid nitrogen, and positioned for insertion into key 300 .
  • the pin insertion tool is inserted into recess 370 such that pin 290 may be cooled and inserted into key 300 .
  • the pin insertion tool is then retracted from recess 370 .
  • Recess 370 has a chamfered edge 380 to facilitate insertion of the pin insertion tool.
  • a plurality of through-bolts 330 may be provided between inlet end stub shaft 210 and discharge end stub shaft (not shown in FIG. 5 ).
  • Through-bolt 330 desirably extends through shaft drum 230 and includes threaded ends 335 .
  • a plurality of holes 340 are formed in a radial pattern around the circumference of inlet end stub shaft 210 and discharge end stub shaft 220 .
  • Through-bolt 330 is inserted through each of the plurality of holes 340 to securely connect the stub shafts 210 and 220 to shaft drum 230 .
  • a nut 350 is threaded onto each threaded end 335 of through-bolt 330 and tightened to couple the stub shafts 210 and 220 to shaft drum 230 .
  • a washer 360 may be provided at the interface between nut 350 and hole 340 .
  • the method of attaching stub shafts 210 and 220 to shaft drum 230 begins at a step where inlet end stub shaft 210 and discharge end stub shaft 220 are provided on opposing ends of shaft drum 230 .
  • shoulder structures 270 are provided at inlet end stub shaft 210 and discharge end stub shaft 220 .
  • complementary shoulder recesses 280 are provided at each end of shaft drum 230 at the interface of shaft drum 230 with each of inlet end stub shaft 210 and discharge end stub shaft 220 .
  • Shoulder structures 270 and shoulder recesses 280 form a rabbet fit between stub shafts 210 and 220 and shaft drum 230 to maintain the coaxial arrangement of these components.
  • a plurality of keys 300 are provided on the stub shafts 210 , 220 , and shaft drum 230 . Keys 300 are disposed in a radial arrangement near the outer circumference of the stub shafts 210 , 220 , and shaft drum 230 .
  • a plurality of pins 290 are inserted into one of the slots 310 or 320 formed on inlet end stub shaft 210 or shaft drum 230 , respectively.
  • each pin 290 is dimensioned slightly larger than a corresponding key 300 to allow for an interference fit between pin 290 and key 300 .
  • inlet end stub shaft 210 and discharge end stub shaft 220 are secured to shaft drum 230 by inserting and securing each pin 290 inside key 300 .
  • the interference fit between each pin 290 and key 300 is sufficient to prevent relative movement of the stub shafts 210 and 220 with respect to shaft drum 230 .
  • a plurality of through-bolts 330 may be inserted through the corresponding plurality of holes 340 provided on the stub shafts 210 and 220 to further secure the shaft assembly 200 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Applications Or Details Of Rotary Compressors (AREA)
  • Rotary Pumps (AREA)
  • Compressor (AREA)
US13/979,145 2011-07-19 2012-07-17 Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft Abandoned US20130309087A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US13/979,145 US20130309087A1 (en) 2011-07-19 2012-07-17 Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US201161509262P 2011-07-19 2011-07-19
PCT/US2012/047005 WO2013012836A2 (en) 2011-07-19 2012-07-17 Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft
US13/979,145 US20130309087A1 (en) 2011-07-19 2012-07-17 Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft

Publications (1)

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US20130309087A1 true US20130309087A1 (en) 2013-11-21

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US13/979,145 Abandoned US20130309087A1 (en) 2011-07-19 2012-07-17 Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft

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US (1) US20130309087A1 (ja)
EP (1) EP2734793A4 (ja)
JP (1) JP2014521018A (ja)
KR (1) KR20140079337A (ja)
CN (1) CN103930681A (ja)
AU (1) AU2012284172A1 (ja)
BR (1) BR112013018028A2 (ja)
CA (1) CA2823409A1 (ja)
MX (1) MX2013008014A (ja)
RU (1) RU2013146686A (ja)
UA (1) UA111842C2 (ja)
WO (1) WO2013012836A2 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11073019B2 (en) 2019-02-05 2021-07-27 Rolls-Royce Plc Metallic shaft

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104613005A (zh) * 2015-01-30 2015-05-13 哈尔滨汽轮机厂有限责任公司 一种高转速红套压气机转子

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US2949278A (en) * 1956-07-05 1960-08-16 Gen Motors Corp Turbine blade retention
US3059901A (en) * 1958-04-01 1962-10-23 Carrier Corp Rotor construction
US3625634A (en) * 1969-12-10 1971-12-07 Gen Motors Corp Turbomachine rotor
US20060222537A1 (en) * 2005-02-23 2006-10-05 Kilty William T Shaft coupling

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GB599809A (en) * 1945-01-15 1948-03-22 Bristol Aeroplane Co Ltd Improvements in axial flow compressors, turbines and the like
US2548886A (en) * 1947-10-25 1951-04-17 Gen Electric Gas turbine power plant with axial flow compressor
US2685405A (en) * 1948-05-03 1954-08-03 Edward A Stalker Axial flow compressor
US3749516A (en) * 1971-10-06 1973-07-31 Carrier Corp Rotor structure for turbo machines
US3901622A (en) * 1973-05-31 1975-08-26 Gen Motors Corp Yieldable shroud support
US5366359A (en) * 1993-08-20 1994-11-22 General Motors Corporation Scroll compressor orbital scroll drive and anti-rotation assembly
JP3346277B2 (ja) * 1998-05-13 2002-11-18 株式会社日立製作所 圧縮機ロータ
US6918713B2 (en) * 2002-04-12 2005-07-19 Kramski Gmbh Cylindrical pin
CN100535625C (zh) * 2007-09-30 2009-09-02 沈阳黎明航空发动机(集团)有限责任公司 一种压气机-透平转子组件动平衡夹具
JP5689607B2 (ja) * 2010-03-17 2015-03-25 東京電力株式会社 軸流圧縮機

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Publication number Priority date Publication date Assignee Title
US2949278A (en) * 1956-07-05 1960-08-16 Gen Motors Corp Turbine blade retention
US3059901A (en) * 1958-04-01 1962-10-23 Carrier Corp Rotor construction
US3625634A (en) * 1969-12-10 1971-12-07 Gen Motors Corp Turbomachine rotor
US20060222537A1 (en) * 2005-02-23 2006-10-05 Kilty William T Shaft coupling

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11073019B2 (en) 2019-02-05 2021-07-27 Rolls-Royce Plc Metallic shaft

Also Published As

Publication number Publication date
CA2823409A1 (en) 2013-01-24
AU2012284172A1 (en) 2013-07-18
WO2013012836A2 (en) 2013-01-24
KR20140079337A (ko) 2014-06-26
CN103930681A (zh) 2014-07-16
WO2013012836A3 (en) 2014-05-01
EP2734793A2 (en) 2014-05-28
UA111842C2 (uk) 2016-06-24
RU2013146686A (ru) 2015-08-27
MX2013008014A (es) 2013-08-21
BR112013018028A2 (pt) 2019-09-24
EP2734793A4 (en) 2015-10-28
JP2014521018A (ja) 2014-08-25

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Owner name: ELLIOTT COMPANY, PENNSYLVANIA

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Effective date: 20130603

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Owner name: ELLIOTT COMPANY, PENNSYLVANIA

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Effective date: 20130619

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