US3612719A - Means for supporting an impeller of a centrifugal compressor - Google Patents

Means for supporting an impeller of a centrifugal compressor Download PDF

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Publication number
US3612719A
US3612719A US844796A US3612719DA US3612719A US 3612719 A US3612719 A US 3612719A US 844796 A US844796 A US 844796A US 3612719D A US3612719D A US 3612719DA US 3612719 A US3612719 A US 3612719A
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United States
Prior art keywords
impeller
shaft
vane assembly
front vane
centrifugal compressor
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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.)
Expired - Lifetime
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US844796A
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English (en)
Inventor
Jiro Nomura
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Filing date
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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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/285—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together
    • 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
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/045—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type the wheel comprising two adjacent bladed wheel portions, e.g. with interengaging blades for damping vibrations
    • 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
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
    • F16D1/06—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end
    • F16D1/08—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end with clamping hub; with hub and longitudinal key
    • F16D1/09—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end with clamping hub; with hub and longitudinal key with radial clamping due to axial loading of at least one pair of conical surfaces
    • F16D1/092—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end with clamping hub; with hub and longitudinal key with radial clamping due to axial loading of at least one pair of conical surfaces the pair of conical mating surfaces being provided on the coupled hub and shaft

Definitions

  • the eccentric arm S in the case of a high-speed rotating body, the eccentric arm S must not be large, because of the deformations due to its centrifugal force and the heat, not only in the stationary state but in the rotating state.
  • the conventional centrifugal compressor in which the front vane and the impeller are formed integrally with each other, the production of a larger eccentric arm S in the supporting device may be avoided, but only small centrifugal compressors have such an integrally formed front vane and impeller.
  • the vane and the impeller comprise separate components and it may be impossible to avoid occurrence of a larger eccentric arm S with the conventional means for supporting the impeller on the shaft.
  • FIGS. 1, 2 and 3 illustrate a conventional means for supporting the impeller of a centrifugal compressor on the shaft and as a component which is separate from the vane which is also supported on the shaft.
  • a shaft 01 is rotated by suitable driving means which have not been shown.
  • An impeller 02 is secured on a tapered portion of shaft 01 by means of a key 03.
  • Front vanes are also engaged with the tapered portion of shaft 01, in a manner similar to the engagement of impeller 02 therewith, and are connected, by means of knock pin 05 to rotate with impeller 02.
  • These vanes receive gaseous fluid from an inlet, as shown by an arrow, and radially accelerate the gaseous fluid to pressurize the latter while delivering it to an outlet.
  • Such pressurizing is effected by rotation of front vane 04 and impeller 02 as a unit with shaft 01.
  • a nut 06 is screwed on to a threaded portion of shaft 01 and, through a spring 07, urges front vane 04 and impeller 02 axially along the tapered portions of shaft 01.
  • An inner vortex chamber 08 is provided adjacent front vane 04 and impeller 02.
  • FIG. 2 illustrates the case in which the front vane 04 is maintained in contact with the tapered portion of shaft 01 by the resultant force OF of spring 07.
  • the force OF of spring 07 does not act on impeller 02, which elongates, in the amount 08, in a radial direction because of deformation due to centrifugal force and heat.
  • Impeller 02 thus has a vibrating state in relation to shaft 01 so that the maximum radial gap on one side becomes 2-08.
  • the maximum eccentricity arm of the center of gravity of impeller 02 is 08.
  • impeller 02 in such case, moves axially in the amount of 08as the maximum displacement resulting from the production of a radial gap.
  • the tapered portion has a ratio of ml for the length n, in the radial direction
  • FIG. 3 illustrates the case in which, during rotation, impeller 02 is firmly in contact with the tapered portion of shaft 01 by means of the force OF of spring 07.
  • axial movement of front vane 04 along the tapered portion of shaft (ll is prevented, so that front vane 04 elongates radially in the amount 08due to heat deformation and other defects, and vibrates to the extent that it reaches a maximum radial gap 208with respect to one side and shaft 01.
  • the maximum eccentric arm of the center of gravity of front vane 04 is 05. It follows, of course, that front vane 04 does not fluctuate axially inasmuch as this vane is urged in the axial direction of impeller 02 by means of the force OF of spring 07.
  • This invention relates to means for supporting an impeller of a centrifugal compressor on a shaft and, more particularly, to an improved supporting means supporting an impeller and an associated front vane, formed as separate components, on tapered portions of a shaft.
  • the present invention eliminates the above-mentioned disadvantages of conventional supporting means for an impeller of the type in which the front vane and the impeller form separate components of a centrifugal compressor.
  • the invention furthermore provides a supporting means by means of which the center of gravity of the front vane and the impeller are prevented from increasing eccentricity not only in the stationary state but also in the rotating statel
  • a first buffer member or spring is provided at the inlet side of the front vane.
  • a second buffer member is provided between the front vane and the impeller.
  • the two bufier members are so related that the first buffer member is stronger than the second buffer member.
  • the two buffer members act in the same axial direction so that they urge the front vane and the impeller along the conically tapered portions of the shaft, thereby preventing production of a gap between the front vane and the impeller and the contacting portions of the shaft.
  • the front vane and the impeller are always urged by the buffer members, irrespective of whether the parts are stationary or rotating, so that they are maintained in contact with the tapered portions of the shaft to prevent excessive eccentricity of the center of gravity and to provide a smooth rotary motion.
  • An object of the present invention is to provide an improved 'means for mounting an impeller and a front vane or vanes, the
  • impeller and the front vane or vanes comprising separate components, on tapered portions of a shaft of a centrifugal compressor.
  • Another object of the invention is to provide such a mounting means by means of which both the front vane and the impeller are maintained in firm contact with the respective tapered portions of shaft.
  • a further object of the invention is to provide such a mounting means including a first buffer engaged between a retaining member and the inlet end of the front vane, and a second buffer engaged between the front vane and the impeller.
  • Another object of the invention is to provide such a mounting means in which the first b'ufier or buffer member is stronger than the second buffer or buffer member.
  • FIG. 1 is a diametric sectional view through a centrifugal compressor illustrating prior art mounting means
  • FIGS. 2 and 3 are partial radial sectional views through the centrifugal compressor shown in FIG. 1 and illustrating certain effects occurring during operation;
  • FIG. 4 is a diametric sectional view through a centrifugal compressor embodying the mounting means of the present invention.
  • FIGS. 5 and 6 are partial radial sectional views illustrating certain effects occurring during operation of the compressor.
  • a shaft 1 of a centrifugal compressor has an impeller 2 mounted thereon and secured to rotate therewith through the medium of a key member 3. Impeller 2 is engaged with a cylindrical portion la of shaft 1 and also with a conically tapered portion lb of shaft 1.
  • a front vane or vanes 4 are also mounted on shaft 1 and secured to rotate therewith through the medium of a key member 5.
  • the vane 4 or vane assembly is mounted on a conically tapered portion lc of shaft 1.
  • both impeller 2 and vane assembly 4 rotate, as a unit with shaft 1, within an inner vortex chamber 6 so that gaseous fluid is drawn in at an inlet of vortex chamber 6 and delivered radially outwardly from an outlet, the gaseous fluid being thereby pressurized.
  • a nut 7 is screwed on to a threaded portion 1d of shaft 1, and a first spring 8 is provided between nut 7 and front vane assembly 4 to bias vane assembly 4 and impeller 2 axially to the right.
  • a second spring 9 is provided between front vane assembly 4 and impeller 2, which are engaged, respectively, with conically tapered portions 1c and lb of shaft 1.
  • a gap c which is somewhat larger than that of a conventional compressor of this type, including separate impeller 2 and vane assembly, 4 is provided between the adjacent surfaces of vane assembly 4 and impeller 2.
  • the buffer action of the second spring 9, which means the amount of the action during compression and tension, is weaker than that of the spring 8.
  • impeller 2 is illustrated as engaged with a cylindrical portion la and a conically tapered portion lb of shaft 1, it may be engaged solely with a conically tapered portion.
  • Nut 7 is screwed on to shaft 1 sufiiciently tightly so as to resist the buffered action in any state of the first and second springs 8 and 9. If the buffer force 4F of the first spring 8 is twice that 2F, of the second spring 9, front vane assembly 4 and impeller 2 are urged, by means of the first and second springs 8 and 9, to the right along the conically tapered portions 10 and lb in contact with shaft 1, so as to be firmly engaged therewith not only in the stationary state but also in the rotary state.
  • FIG. 5 denotes the case that, notwithstanding front vane assembly 4 is engaged in contact with conically tapered portion lc of shaft 1, during rotation a gap 8 is produced in the radial direction, by means of centrifugal force, this gap appearing between the impeller 2 and shaft 1. Furthermore, there is an axial displacement of impeller 2 through a distance n6 due to the occurrence of gap 8, where n is a length in the axial direction and when the taper of the conically tapered portion lb has a ratio of ml.
  • the second spring 9 will act at the starting point of the spring contacting position of front vane assembly 4 first engaged in in contact therewith, and impeller 2 is positively engaged in contact with shaft 1 so that it is firmly supported thereby.
  • impeller 2 is-biased by means of a bufi'er force 2F in the direction of the arrow and at the conically tapered portion lb of shaft 1.
  • FIG. 6 illustrates a case which is the contrary of that shown in FIG. 5 in that, notwithstanding that impeller 2 is firmly in contact with shaft 1, during rotation a gap 6 caused by heat deformation and the like, in the radial direction, and a displacement of n6' in the axial direction, are produced, where n is a length in the axial direction and when the taper of the conically tapered portion 10 has a ratio of n'zl.
  • the buffer force 4F of the first spring 8 is twice the buffer force 2F of the second spring 9
  • the first spring 8 will act on front vane assembly 4 so that the latter is firmly engaged in contact with the conically tapered portion 10 of shaft 1, with the second spring 9 being compressed.
  • both the first and second springs 8 and 9 are effective in the direction of the arrow to maintain the first engagement of the impeller and the front vane assembly with the respective conically tapered portions of shaft 1.
  • front vane assembly 4 and impeller 2 are divided into two separate components, the unbalanced force, during rotation, is eliminated, inasmuch as the center of gravity of front vane assembly 4 and impeller 2 coincides with the axis of shaft 1 as the vane assembly and the impeller are always firmly engaged in contact with the respective tapered portions of shaft 1, not only in the stationary state but also in the rotating state. Consequently, the centrifugal compressor rotates with smooth operation of front vane assembly 4 and impeller 2, so that there is no deleterious effect on the bearings or burning of the bearings or other components, resulting in long life for the parts.
  • the mounting arrangement of the present invention positively supports a body of revolution without any eccentric movement of the center of gravity, even during rotation of a rotor of a centrifugal compressor in which the impeller and a front vane assembly form separate components.
  • the mounting arrangement comprises a first buffer member or spring at the inlet side of the front vane assembly, and a second buffer member or spring between the front vane assembly and the impeller.
  • the first buffer member is substantially stronger than the second buffer member, with respect to its biasing force, and both buffer members act in the same axial direction to urge the front vane assembly and the impeller into firm engagement with the respective conically tapered portions of the centrifugal compressor shaft.
  • these buffer members prevent the production of a gap between the shaft, on the one hand, and the front vane assembly and the impeller. on the other hand.
  • an impeller and vane assembly mounting arrangement comprising, in combination, a retaining member secured to said shaft adjacent the inlet end of said front vane assembly; a first buffer member embracing said shaft between said retaining member and said front vane assembly; and a second buffer member embracing said shaft between said front vane assembly and said impeller; said buffer members acting in the same axial direction to bias a front vane assembly and said impeller, onto the respective tapered portions of the shaft, to prevent radial gaps between said front vane assembly and said shaft and between said impeller and said shaft during rotation of said shaft.
  • an impeller and vane assembly mounting arrangement as claimed in claim 4, in which said impeller and said vane assembly are mounted on said shaft with an initial small axial gap therebetween.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US844796A 1968-08-20 1969-07-25 Means for supporting an impeller of a centrifugal compressor Expired - Lifetime US3612719A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP43059426A JPS4815164B1 (de) 1968-08-20 1968-08-20

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US3612719A true US3612719A (en) 1971-10-12

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US844796A Expired - Lifetime US3612719A (en) 1968-08-20 1969-07-25 Means for supporting an impeller of a centrifugal compressor

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US (1) US3612719A (de)
JP (1) JPS4815164B1 (de)
CH (1) CH496173A (de)
DE (1) DE1942397B2 (de)
DK (1) DK126517B (de)
FR (1) FR2015947A1 (de)
GB (1) GB1228678A (de)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4125344A (en) * 1975-06-20 1978-11-14 Daimler-Benz Aktiengesellschaft Radial turbine wheel for a gas turbine
US4245957A (en) * 1978-11-17 1981-01-20 General Motors Corporation Bladed fan assembly and compression loaded connector
US4353685A (en) * 1978-06-19 1982-10-12 Wrr Industries, Inc. Turbocharger compressor rotor retainer
FR2583827A1 (fr) * 1985-06-19 1986-12-26 Mitsubishi Heavy Ind Ltd Machine tournante a plusieurs roues coaxiales, notamment compresseur centrifuge
US5882178A (en) * 1997-03-24 1999-03-16 Delaware Capital Formation, Inc. Impeller and shaft coupling
US6012901A (en) * 1997-09-19 2000-01-11 Asea Brown Boveri Ag Compressor impeller fastening for high speed turboengines
US6290467B1 (en) * 1999-12-03 2001-09-18 American Standard International Inc. Centrifugal impeller assembly
US6481917B1 (en) * 2000-05-02 2002-11-19 Honeywell International Inc. Tie-boltless shaft lock-up mechanism
US20040131469A1 (en) * 2002-10-24 2004-07-08 Anthony Billington Compressor wheel assembly
US20050249565A1 (en) * 2002-08-02 2005-11-10 Abb Turbo Systems Ag Method and device for chucking rotationally symmetrical bodies and configuration of the body to be chucked
US20070095969A1 (en) * 2005-11-02 2007-05-03 The Boeing Company Rotor wing aircraft having a bypassable radial inflow turbine
US20100215508A1 (en) * 2009-02-25 2010-08-26 Behzad Hagshenas Axially Segmented Impeller
US20150247409A1 (en) * 2012-04-11 2015-09-03 Honeywell International Inc. Axially-split radial turbines
US10119551B2 (en) 2015-08-07 2018-11-06 Hamilton Sundstrand Corporation Anti-icing impeller spinner
US10197065B2 (en) * 2014-02-26 2019-02-05 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Centrifugal compressor, turbocharger provided with the centrifugal compressor, and method for producing the centrifugal compressor
US10443604B2 (en) 2014-10-31 2019-10-15 Trane International Inc. Systems and methods to clamp an impeller to a compressor shaft
EP3760851A4 (de) * 2018-08-07 2021-01-06 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbinenwelle, auflader und verfahren zur herstellung eines aufladers
US11365630B1 (en) * 2020-12-28 2022-06-21 Rolls-Royce North American Technologies Inc. Fan rotor with tapered drive joint

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3805899A1 (de) * 1988-02-25 1989-09-07 Klein Schanzlin & Becker Ag Welle
CN100582489C (zh) * 2004-06-29 2010-01-20 英格索尔-兰德公司 将叶轮可拆卸地连接到轴的装置和方法
MX2020002299A (es) 2017-08-29 2020-09-10 Armstrong World Ind Inc Recubrimientos con alto contenido de sólidos para paneles de construcción.

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4125344A (en) * 1975-06-20 1978-11-14 Daimler-Benz Aktiengesellschaft Radial turbine wheel for a gas turbine
US4353685A (en) * 1978-06-19 1982-10-12 Wrr Industries, Inc. Turbocharger compressor rotor retainer
US4245957A (en) * 1978-11-17 1981-01-20 General Motors Corporation Bladed fan assembly and compression loaded connector
FR2583827A1 (fr) * 1985-06-19 1986-12-26 Mitsubishi Heavy Ind Ltd Machine tournante a plusieurs roues coaxiales, notamment compresseur centrifuge
US4697987A (en) * 1985-06-19 1987-10-06 Mitsubishi Jukogyo Kabushiki Kaisha Rotary machine having an impeller with a sleeve fixedly mounted to a shaft
US5882178A (en) * 1997-03-24 1999-03-16 Delaware Capital Formation, Inc. Impeller and shaft coupling
US6012901A (en) * 1997-09-19 2000-01-11 Asea Brown Boveri Ag Compressor impeller fastening for high speed turboengines
US6290467B1 (en) * 1999-12-03 2001-09-18 American Standard International Inc. Centrifugal impeller assembly
US20020028142A1 (en) * 1999-12-03 2002-03-07 Dewhirst Randy E. Centrifugal impeller assembly
US6481917B1 (en) * 2000-05-02 2002-11-19 Honeywell International Inc. Tie-boltless shaft lock-up mechanism
US20050249565A1 (en) * 2002-08-02 2005-11-10 Abb Turbo Systems Ag Method and device for chucking rotationally symmetrical bodies and configuration of the body to be chucked
US20040131469A1 (en) * 2002-10-24 2004-07-08 Anthony Billington Compressor wheel assembly
US7008191B2 (en) 2002-10-24 2006-03-07 Holset Engineering Company, Limited Compressor wheel assembly
US7510139B2 (en) * 2005-11-02 2009-03-31 Walliser Eric W Rotor wing aircraft having a bypassable radial inflow turbine
US20070095969A1 (en) * 2005-11-02 2007-05-03 The Boeing Company Rotor wing aircraft having a bypassable radial inflow turbine
US20100215508A1 (en) * 2009-02-25 2010-08-26 Behzad Hagshenas Axially Segmented Impeller
US8147208B2 (en) * 2009-02-25 2012-04-03 Hamilton Sundstrand Corporation Axially segmented impeller
US20150247409A1 (en) * 2012-04-11 2015-09-03 Honeywell International Inc. Axially-split radial turbines
US9726022B2 (en) * 2012-04-11 2017-08-08 Honeywell International Inc. Axially-split radial turbines
US10197065B2 (en) * 2014-02-26 2019-02-05 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Centrifugal compressor, turbocharger provided with the centrifugal compressor, and method for producing the centrifugal compressor
US10443604B2 (en) 2014-10-31 2019-10-15 Trane International Inc. Systems and methods to clamp an impeller to a compressor shaft
US11225973B2 (en) 2014-10-31 2022-01-18 Trane International Inc. Systems and methods to clamp an impeller to a compressor shaft
US10119551B2 (en) 2015-08-07 2018-11-06 Hamilton Sundstrand Corporation Anti-icing impeller spinner
EP3760851A4 (de) * 2018-08-07 2021-01-06 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbinenwelle, auflader und verfahren zur herstellung eines aufladers
CN112272733A (zh) * 2018-08-07 2021-01-26 三菱重工发动机和增压器株式会社 涡轮轴组件、增压器及增压器的制造方法
US11525394B2 (en) * 2018-08-07 2022-12-13 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbine shaft, turbocharger, and manufacturing method of turbocharger
US11365630B1 (en) * 2020-12-28 2022-06-21 Rolls-Royce North American Technologies Inc. Fan rotor with tapered drive joint
US20220205362A1 (en) * 2020-12-28 2022-06-30 Rolls-Royce North American Technologies Inc. Fan rotor with tapered drive joint

Also Published As

Publication number Publication date
FR2015947A1 (de) 1970-04-30
JPS4815164B1 (de) 1973-05-12
DE1942397A1 (de) 1970-03-05
CH496173A (de) 1970-09-15
DE1942397B2 (de) 1971-12-16
DK126517B (da) 1973-07-23
GB1228678A (de) 1971-04-15

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