GB836920A - Rotors for multi-stage axial flow compressors or turbines - Google Patents

Rotors for multi-stage axial flow compressors or turbines

Info

Publication number
GB836920A
GB836920A GB15470/57A GB1547057A GB836920A GB 836920 A GB836920 A GB 836920A GB 15470/57 A GB15470/57 A GB 15470/57A GB 1547057 A GB1547057 A GB 1547057A GB 836920 A GB836920 A GB 836920A
Authority
GB
United Kingdom
Prior art keywords
sections
cylindrical
dowels
recesses
rotor
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.)
Expired
Application number
GB15470/57A
Inventor
Michael Joseph French
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Publication of GB836920A publication Critical patent/GB836920A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

836,920. Turbine and compressor rotors. NAPIER & SON Ltd., D. May 15, 1958 [May 15, 1957], No. 15470/57. Class 110 (3). A rotor for a multi-stage axial-flow compressor or turbine comprises several sections having hollow cylindrical or frusto-conical portions with flat faces at the extreme ends thereof which lie in parallel planes perpendicular to the axis of rotation and which abut against the adjacent end faces of the adjacent sections, dowels being provided which extend radially across the abutting end faces and fit tightly in recesses in adjacent sections. The compressor rotor shown comprises a series of abutting cylindrical sections 14 each having an annular flange at the periphery of which rotor blades 11 are mounted. The rotor also comprises two end sections 16, 17, which abut against the end sections 14 and have cylindrical portions 20, 21 respectively which carry the inner races of support bearings. The cylindrical sections abut in planes lying normal to the axis of rotation and radially-extending semicylindrical recesses are formed in the edges of the sections, the recesses in adjoining sections co-operating to form cylindrical openings in which cylindrical dowels 25 are engaged. The dowels have heads 26 to prevent radial outward movement, the heads being formed with diametrical grooves 27 in which circlips 28 are engaged so as to prevent radial inward movement of the dowels. A tube member 23 extends through the centre of the rotor assembly being tightened by a nut 29 so as to draw the end sections 16, 17 towards one another, thereby holding the cylindrical sections 14 in axial compression. The semi-cylindrical recesses are formed by assembling the cylindrical sections together and then drilling radial holes, the diameter of the holes being slightly less than that of the dowels. The tube 23 is inserted hot so that in cooling, the dowels and adjacent parts of the sections are somewhat distorted so as to ensure a tight fit of the dowels in the recesses. Sealing rings 32 may be provided between the platforms 33 of adjacent rows of rotor blades.
GB15470/57A 1957-05-15 1957-05-15 Rotors for multi-stage axial flow compressors or turbines Expired GB836920A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB344873X 1957-05-15

Publications (1)

Publication Number Publication Date
GB836920A true GB836920A (en) 1960-06-09

Family

ID=10366246

Family Applications (1)

Application Number Title Priority Date Filing Date
GB15470/57A Expired GB836920A (en) 1957-05-15 1957-05-15 Rotors for multi-stage axial flow compressors or turbines

Country Status (3)

Country Link
CH (1) CH344873A (en)
FR (1) FR1195912A (en)
GB (1) GB836920A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0028217A1 (en) * 1979-10-25 1981-05-06 ELIN-UNION Aktiengesellschaft für elektrische Industrie Rotor for a thermic turbomachine
EP1061233A2 (en) * 1999-06-16 2000-12-20 Mitsubishi Heavy Industries, Ltd. A gas-turbine rotor connection
WO2001040631A1 (en) * 1999-12-03 2001-06-07 Siemens Westinghouse Power Corporation Shear pin with locking cam
EP1577493A1 (en) * 2004-03-17 2005-09-21 Siemens Aktiengesellschaft Turbomachine and rotor for a turbomachine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3070348A (en) * 1960-07-25 1962-12-25 Gen Motors Corp Composite rotor
US5031400A (en) * 1988-12-09 1991-07-16 Allied-Signal Inc. High temperature turbine engine structure

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0028217A1 (en) * 1979-10-25 1981-05-06 ELIN-UNION Aktiengesellschaft für elektrische Industrie Rotor for a thermic turbomachine
EP1061233A2 (en) * 1999-06-16 2000-12-20 Mitsubishi Heavy Industries, Ltd. A gas-turbine rotor connection
EP1061233A3 (en) * 1999-06-16 2002-05-29 Mitsubishi Heavy Industries, Ltd. A gas-turbine rotor connection
WO2001040631A1 (en) * 1999-12-03 2001-06-07 Siemens Westinghouse Power Corporation Shear pin with locking cam
EP1577493A1 (en) * 2004-03-17 2005-09-21 Siemens Aktiengesellschaft Turbomachine and rotor for a turbomachine
WO2005093219A1 (en) * 2004-03-17 2005-10-06 Siemens Aktiengesellschaft Non-positive-displacement machine and rotor for a non-positive-displacement machine
JP2007529668A (en) * 2004-03-17 2007-10-25 シーメンス　アクチエンゲゼルシヤフト Fluid machinery and its rotor
US7585148B2 (en) 2004-03-17 2009-09-08 Siemens Aktiengesellschaft Non-positive-displacement machine and rotor for a non-positive-displacement machine
CN101010486B (en) * 2004-03-17 2011-06-01 西门子公司 Turbine and rotor
JP4722120B2 (en) * 2004-03-17 2011-07-13 シーメンス アクチエンゲゼルシヤフト Fluid machinery and its rotor
EP2787168A2 (en) 2004-03-17 2014-10-08 Siemens Aktiengesellschaft Turbomachine and rotor for a turbomachine
EP2787168A3 (en) * 2004-03-17 2015-04-15 Siemens Aktiengesellschaft Turbomachine and rotor for a turbomachine

Also Published As

Publication number Publication date
CH344873A (en) 1960-02-29
FR1195912A (en) 1959-11-20

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