GB1340937A - Turbomachinery rotors - Google Patents

Turbomachinery rotors

Info

Publication number
GB1340937A
GB1340937A GB1222971A GB1222971A GB1340937A GB 1340937 A GB1340937 A GB 1340937A GB 1222971 A GB1222971 A GB 1222971A GB 1222971 A GB1222971 A GB 1222971A GB 1340937 A GB1340937 A GB 1340937A
Authority
GB
United Kingdom
Prior art keywords
axial
rim
webs
april
disc
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
GB1222971A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1340937A publication Critical patent/GB1340937A/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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)
  • Applications Or Details Of Rotary Compressors (AREA)

Abstract

1340937 Turbomachine rotors GENERAL ELECTRIC CO 29 April 1971 [30 April 1970] 12229/71 Heading F1T An axial flow compressor or turbine rotor comprises a disc 34 having a rim 36 with blade mounting slots 38 extending thereacross, thin platforms 40 being provided between adjacent slots and angled outwardly from the inlet to the discharge side of the rim, circumferential and axial webs 42, 44 extending between the latter and the platforms. In a modification Fig.4 (not shown) circumferential webs 42 are not provided and each axial web 44 is replaced by two axial webs (48) disposed at the sides of platform 40, adjacent slots 38. In both arrangements rim 36 is lightened by axial cavities 46. Disc 34 is connected to an adjacent rotor stage by a frusto-conical member 30 and bolts.
GB1222971A 1970-04-30 1971-04-29 Turbomachinery rotors Expired GB1340937A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US3322070A 1970-04-30 1970-04-30

Publications (1)

Publication Number Publication Date
GB1340937A true GB1340937A (en) 1973-12-19

Family

ID=21869177

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1222971A Expired GB1340937A (en) 1970-04-30 1971-04-29 Turbomachinery rotors

Country Status (6)

Country Link
US (1) US3661475A (en)
BE (1) BE766401A (en)
CA (1) CA943467A (en)
DE (1) DE2120470A1 (en)
FR (1) FR2092118B1 (en)
GB (1) GB1340937A (en)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE791162A (en) * 1971-11-10 1973-03-01 Penny Robert N TURBINE ROTOR
US4310286A (en) * 1979-05-17 1982-01-12 United Technologies Corporation Rotor assembly having a multistage disk
US4536129A (en) * 1984-06-15 1985-08-20 United Technologies Corporation Turbine blade with disk rim shield
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
FR2679296B1 (en) * 1991-07-17 1993-10-15 Snecma SEPARATE INTER-BLADE PLATFORM FOR TURBOMACHINE ROTOR WING DISC.
US5271718A (en) * 1992-08-11 1993-12-21 General Electric Company Lightweight platform blade
FR2697051B1 (en) * 1992-10-21 1994-12-02 Snecma Turbomachine rotor comprising a disk whose periphery is occupied by oblique cells which alternate with teeth of variable cross section.
US5310318A (en) * 1993-07-21 1994-05-10 General Electric Company Asymmetric axial dovetail and rotor disk
GB9405473D0 (en) * 1994-03-19 1994-05-04 Rolls Royce Plc A gas turbine engine fan blade assembly
US6511294B1 (en) 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US6524070B1 (en) 2000-08-21 2003-02-25 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US6471474B1 (en) 2000-10-20 2002-10-29 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
JP2003120209A (en) * 2001-10-10 2003-04-23 Mitsubishi Heavy Ind Ltd Sealing structure of spindle bolt and gas turbine
US6764282B2 (en) * 2001-11-14 2004-07-20 United Technologies Corporation Blade for turbine engine
FR2868814B1 (en) * 2004-04-09 2009-12-18 Snecma Moteurs DEVICE FOR ASSEMBLING ANNULAR FLANGES, PARTICULARLY IN A TURBOMACHINE
US7179049B2 (en) * 2004-12-10 2007-02-20 Pratt & Whitney Canada Corp. Gas turbine gas path contour
US7360437B2 (en) * 2005-06-28 2008-04-22 General Electric Company Devices for evaluating material properties, and related processes
US20140174098A1 (en) * 2012-12-20 2014-06-26 United Technologies Corporation Turbine disc with reduced neck stress concentration

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA590294A (en) * 1960-01-05 Rolls-Royce Limited Axial-flow compressors and turbines
US2452782A (en) * 1945-01-16 1948-11-02 Power Jets Res & Dev Ltd Construction of rotors for compressors and like machines
US3291446A (en) * 1965-04-13 1966-12-13 Chrysler Corp Turbine wheel
GB1093568A (en) * 1965-11-23 1967-12-06 Rolls Royce Improvements in or relating to bladed rotors such as compressor rotors
US3383095A (en) * 1967-09-12 1968-05-14 Gen Electric Lock for turbomachinery blades
US3556675A (en) * 1969-01-29 1971-01-19 Gen Electric Turbomachinery rotor with integral shroud

Also Published As

Publication number Publication date
CA943467A (en) 1974-03-12
FR2092118A1 (en) 1972-01-21
FR2092118B1 (en) 1974-10-11
DE2120470A1 (en) 1971-11-11
US3661475A (en) 1972-05-09
BE766401A (en) 1971-09-16

Similar Documents

Publication Publication Date Title
GB1340937A (en) Turbomachinery rotors
GB1376966A (en) Porous abradable seal structures
GB1306575A (en) Segmented seal assembly for axial flow turbines
US3999883A (en) Variable turbomachine stator
GB1470322A (en) Rotor vane
GB1327317A (en) Gas turbines
GB1491556A (en) Rotor blades for turbomachines
GB1088360A (en) Improvements in gas turbine ducted fan engine sealing means
GB1460714A (en) Bladed rotor for a gas turbine engine
GB1265464A (en)
GB1217275A (en) Gas turbine engine axial flow multi-stage compressor
GB1484703A (en) Turbine with internally cooled rim and predetermined rupture regions
GB1195973A (en) Air Intakes.
GB1458524A (en) Turbine rotor discs
GB1211188A (en) Gas turbine engines
GB902064A (en) Blade damping means for compressors and turbines
GB1468470A (en) Turbines
GB1148339A (en) Compressors or turbines for gas turbine engines
GB1282142A (en) Improvements in or relating to gas turbine engines
GB742476A (en) Improvements in or relating to bladed stator and rotor constructions for fluid machines such as axial-flow turbines or compressors
GB1081943A (en) Improvements in stator assembly for turbines and compressors
US2543923A (en) Radial air compressor
GB848465A (en) Rotors of multi-stage axial flow compressors or turbines
GB1527074A (en) Bladed rotors
GB929103A (en) Improvements in turbines

Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees