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GB1326122A - Blade securing arrangement for compressors and or turbines - Google Patents

Blade securing arrangement for compressors and or turbines

Info

Publication number
GB1326122A
GB1326122A GB2003971A GB2003971A GB1326122A GB 1326122 A GB1326122 A GB 1326122A GB 2003971 A GB2003971 A GB 2003971A GB 2003971 A GB2003971 A GB 2003971A GB 1326122 A GB1326122 A GB 1326122A
Authority
GB
United Kingdom
Prior art keywords
blades
blade
platforms
root
circumferentially
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
GB2003971A
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.)
Daimler Benz AG
Original Assignee
Daimler Benz AG
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 Daimler Benz AG filed Critical Daimler Benz AG
Publication of GB1326122A publication Critical patent/GB1326122A/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides

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

1326122 Turbomachine rotor blade fixing DAIMLER-BENZ AG 19 April 1971 [21 Jan 1970] 20039/71 Heading FIT Turbine or compressor blades 4 are assembled in an annular groove 3 on the rotor 2 by inserting the root 5 of each blade radially through a recess 9 into the groove 3 and then turning the blade through 60-90 degrees so that root 5 engages under groove flanges 6, the blade then being moved circumferentially. To permit assembly of the last few blades, the platforms 12 of the latter have one or both of their circumferentially extending sides of reduced length, as shown in Fig.8. When all the blades have been inserted recess 9 is closed by a locking member 10 having similar shape to a blade root 5. The blades are then moved circumferentially so that platforms 7 overlie member 10 and two-part spacing members 14 are inserted between some of the blades having circumferentially shortened platforms 12. A sheet metal locking member 16 is finally inserted and retained in position by bending over tabs 18. Imbalance can be avoided by providing several members 10, 14 and 16 symmetrically about the periphery of the rotor.
GB2003971A 1970-01-21 1971-04-19 Blade securing arrangement for compressors and or turbines Expired GB1326122A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2002469A DE2002469C3 (en) 1970-01-21 1970-01-21 Blade fastening in a dovetail-shaped circumferential groove of a rotor of flow machines with axial flow, in particular gas turbine jet engines

Publications (1)

Publication Number Publication Date
GB1326122A true GB1326122A (en) 1973-08-08

Family

ID=5760103

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2003971A Expired GB1326122A (en) 1970-01-21 1971-04-19 Blade securing arrangement for compressors and or turbines

Country Status (4)

Country Link
US (1) US3778191A (en)
DE (1) DE2002469C3 (en)
FR (1) FR2075804A5 (en)
GB (1) GB1326122A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119026A (en) * 1981-03-25 1983-11-09 Rolls Royce Aerofoil blade mounting
GB2156908A (en) * 1984-03-30 1985-10-16 Rolls Royce Bladed rotor assembly for gas turbine engine
GB2165313A (en) * 1984-10-01 1986-04-09 Gen Electric Turbomachinery inner and outer casing and blade mounting arrangement

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3902824A (en) * 1974-07-29 1975-09-02 Gen Motors Corp Blade lock
JPS57168005A (en) * 1981-04-10 1982-10-16 Hitachi Ltd Rotor structue for axial machines
US4684326A (en) * 1982-08-16 1987-08-04 Terry Corporation Bladed rotor assembly, and method of forming same
JPH0658168A (en) * 1992-08-06 1994-03-01 Hitachi Ltd Compressor for gas turbine and gas turbine
DE10351092B4 (en) * 2003-10-31 2013-11-21 MTU Aero Engines AG Turbomachine and bladed rotor for a compressor stage of a turbomachine
DE102004011508A1 (en) 2004-03-08 2005-09-29 Alstom Technology Ltd Rotor end
DE102004051116A1 (en) * 2004-10-20 2006-04-27 Mtu Aero Engines Gmbh Rotor of a turbomachine, in particular gas turbine rotor
EP1698759B1 (en) * 2005-02-23 2015-06-03 Alstom Technology Ltd Rotor end piece
FR2900989B1 (en) * 2006-05-12 2008-07-11 Snecma Sa AIRCRAFT ENGINE COMPRESSOR ASSEMBLY COMPRISING AUBES WITH FOOT HAMMER ATTACHMENT
US8899933B2 (en) * 2012-01-03 2014-12-02 General Electric Company Rotor blade mounting
US9828865B2 (en) 2012-09-26 2017-11-28 United Technologies Corporation Turbomachine rotor groove
US9404367B2 (en) * 2012-11-21 2016-08-02 Solar Turbines Incorporated Gas turbine engine compressor rotor assembly and balancing system
US11242761B2 (en) * 2020-02-18 2022-02-08 Raytheon Technologies Corporation Tangential rotor blade slot spacer for a gas turbine engine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US995367A (en) * 1909-03-01 1911-06-13 Allis Chalmers Steam-turbine.
US1539574A (en) * 1922-04-18 1925-05-26 Westinghouse Electric & Mfg Co Turbine-blade fastening
US2857134A (en) * 1954-03-17 1958-10-21 Parsons C A & Co Ltd Assembly of blades for turbines and the like
GB903176A (en) * 1960-01-18 1962-08-15 Rolls Royce Method of mounting a multi-blade set on a support member, for example to form a gas turbine compressor rotor
GB916001A (en) * 1961-02-09 1963-01-16 Prvni Brnenska Strojirna Improvements in or relating to rotors for turbines and compressors
US3216700A (en) * 1963-10-24 1965-11-09 Gen Electric Rotor blade locking means

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119026A (en) * 1981-03-25 1983-11-09 Rolls Royce Aerofoil blade mounting
US4451204A (en) * 1981-03-25 1984-05-29 Rolls-Royce Limited Aerofoil blade mounting
GB2156908A (en) * 1984-03-30 1985-10-16 Rolls Royce Bladed rotor assembly for gas turbine engine
GB2165313A (en) * 1984-10-01 1986-04-09 Gen Electric Turbomachinery inner and outer casing and blade mounting arrangement
US4907944A (en) * 1984-10-01 1990-03-13 General Electric Company Turbomachinery blade mounting arrangement

Also Published As

Publication number Publication date
US3778191A (en) 1973-12-11
DE2002469A1 (en) 1971-07-29
FR2075804A5 (en) 1971-10-08
DE2002469B2 (en) 1977-08-11
DE2002469C3 (en) 1978-03-30

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees