GB827264A - Improvements in compressor rotor - Google Patents

Improvements in compressor rotor

Info

Publication number
GB827264A
GB827264A GB36997/57A GB3699757A GB827264A GB 827264 A GB827264 A GB 827264A GB 36997/57 A GB36997/57 A GB 36997/57A GB 3699757 A GB3699757 A GB 3699757A GB 827264 A GB827264 A GB 827264A
Authority
GB
United Kingdom
Prior art keywords
blade
blades
slot
recess
roots
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
GB36997/57A
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 GB827264A publication Critical patent/GB827264A/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
    • F01D5/3023—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
    • 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
    • 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

Landscapes

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

Abstract

827,264. Axial-flow compressor bladed rotors. GENERAL ELECTRIC CO. Nov. 27, 1957 [Dec. 17, 1956], No. 36997/57. Class 110 (3). A rotor for an axial flow compressor comprises a blade-supporting member having at least one circumferentially extending blademounting slot, an entry slot being provided for insertion and removal of the blades. Each blade has a platform and a root, and upon assembly, the blades are arranged so that portions of the roots of two of the blades extend into the entry slot and other portions of the two roots extend into the blade-mounting slot, the two blades being locked on to the blade-supporting member whereby all the blades of the blade row are secured against circumferential movement. The rotor drum 1 is formed with thickened ribs 8, 9 in which circumferential blade-mounting slots 10 are formed, each slot 10 being formed with slot 24 whereby the blade roots may be entered. The rotor drum is also formed with a shallow groove to receive the blade platform portions 16, this groove being widened adjacent the entry slot 24 to provide a recess 28. The dovetail-shaped blade roots 14 are entered in the slot 24 and moved circumferentially around the slot 10. The last two blades 12a, 12b are similar to the other blades except that their platforms 16a, 16b are axially extended at 30a, the extensions being received in the recess 28. A screwed pin 35 having a shank portion 34 is screwed into a hole provided near one end of the recess 28, and after the last two blades have been inserted, the platform extension 30a of one of them abuts against the end 32 of the recess 28, and the screw 35 is then screwed outwardly until the shoulder 44 abuts against the under-side of the platform extension 30a of the blade 12b and the pin 34 bears against the end of that platform extension.
GB36997/57A 1956-12-17 1957-11-27 Improvements in compressor rotor Expired GB827264A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US628682A US2931625A (en) 1956-12-17 1956-12-17 Compressor rotor

Publications (1)

Publication Number Publication Date
GB827264A true GB827264A (en) 1960-02-03

Family

ID=24519874

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36997/57A Expired GB827264A (en) 1956-12-17 1957-11-27 Improvements in compressor rotor

Country Status (4)

Country Link
US (1) US2931625A (en)
DE (1) DE1134472B (en)
FR (1) FR1192330A (en)
GB (1) GB827264A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3252687A (en) * 1965-02-01 1966-05-24 Gen Motors Corp Rotor blade locking
US3263962A (en) * 1965-04-22 1966-08-02 Gen Motors Corp Rotor blade lock
US3742706A (en) * 1971-12-20 1973-07-03 Gen Electric Dual flow cooled turbine arrangement for gas turbine engines
FR2508542A1 (en) * 1981-06-29 1982-12-31 Gen Electric PERFECTED TURBINE ENGINEERING BEAN AND ROTOR ASSEMBLY COMPRISING SUCH AUBES
FR2535389A1 (en) * 1981-03-25 1984-05-04 Rolls Royce DEVICE FOR MOUNTING, ON THEIR CARRIER DISC, PROFILED BLADES FOR COMPRESSOR OR TURBINE
CN102979763A (en) * 2012-12-29 2013-03-20 成都成发科能动力工程有限公司 Moving blade mounting structure for axial compressor rotor and moving blade mounting way

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US3165294A (en) * 1962-12-28 1965-01-12 Gen Electric Rotor assembly
US3981623A (en) * 1975-05-02 1976-09-21 General Motors Corporation Turbomachine rotor stage
US4310286A (en) * 1979-05-17 1982-01-12 United Technologies Corporation Rotor assembly having a multistage disk
GB2097480B (en) * 1981-04-29 1984-06-06 Rolls Royce Rotor blade fixing in circumferential slot
GB2406144A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Gas turbine engine blade retention system using a key
US7513102B2 (en) * 2005-06-06 2009-04-07 General Electric Company Integrated counterrotating turbofan
US7510371B2 (en) * 2005-06-06 2009-03-31 General Electric Company Forward tilted turbine nozzle
US7594388B2 (en) * 2005-06-06 2009-09-29 General Electric Company Counterrotating turbofan engine
US9097131B2 (en) * 2012-05-31 2015-08-04 United Technologies Corporation Airfoil and disk interface system for gas turbine engines
US20140182293A1 (en) * 2012-12-31 2014-07-03 United Technologies Corporation Compressor Rotor for Gas Turbine Engine With Deep Blade Groove

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US672838A (en) * 1900-03-01 1901-04-23 Westinghouse Machine Co Fluid-pressure turbine.
US1010630A (en) * 1908-05-26 1911-12-05 Colonial Trust Co Blade-holding means for turbines.
US1705585A (en) * 1924-09-08 1929-03-19 Westinghouse Electric & Mfg Co Turbine-blade fastening
US1687891A (en) * 1924-09-08 1928-10-16 Westinghouse Electric & Mfg Co Blade fastening
FR741284A (en) * 1931-09-01 1933-02-08
US2315631A (en) * 1942-02-14 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade locking apparatus
CH240276A (en) * 1942-08-13 1945-12-15 Sulzer Ag Axial turbo-machine and process for its manufacture.
US2393447A (en) * 1944-05-20 1946-01-22 Allis Chalmers Mfg Co Turbine blade locking apparatus
US2434935A (en) * 1946-02-08 1948-01-27 Westinghouse Electric Corp Turbine apparatus
DE838191C (en) * 1946-06-07 1952-03-27 Gebrüder Sulzer Aktiengesellschaft, Winterthur (Schweiz) Axial turbo-machine blades and methods of making the same
BE490366A (en) * 1948-09-17
DE803181C (en) * 1948-10-02 1951-03-01 Maschf Augsburg Nuernberg Ag Bucket lock for axial rotor machines
US2667327A (en) * 1950-06-14 1954-01-26 Westinghouse Electric Corp Rotor construction

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3252687A (en) * 1965-02-01 1966-05-24 Gen Motors Corp Rotor blade locking
US3263962A (en) * 1965-04-22 1966-08-02 Gen Motors Corp Rotor blade lock
US3742706A (en) * 1971-12-20 1973-07-03 Gen Electric Dual flow cooled turbine arrangement for gas turbine engines
FR2535389A1 (en) * 1981-03-25 1984-05-04 Rolls Royce DEVICE FOR MOUNTING, ON THEIR CARRIER DISC, PROFILED BLADES FOR COMPRESSOR OR TURBINE
FR2508542A1 (en) * 1981-06-29 1982-12-31 Gen Electric PERFECTED TURBINE ENGINEERING BEAN AND ROTOR ASSEMBLY COMPRISING SUCH AUBES
CN102979763A (en) * 2012-12-29 2013-03-20 成都成发科能动力工程有限公司 Moving blade mounting structure for axial compressor rotor and moving blade mounting way

Also Published As

Publication number Publication date
DE1134472B (en) 1962-08-09
FR1192330A (en) 1959-10-26
US2931625A (en) 1960-04-05

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