GB822172A - Improvements in or relating to the blade rotors for gas turbine engines - Google Patents

Improvements in or relating to the blade rotors for gas turbine engines

Info

Publication number
GB822172A
GB822172A GB20062/55A GB2006255A GB822172A GB 822172 A GB822172 A GB 822172A GB 20062/55 A GB20062/55 A GB 20062/55A GB 2006255 A GB2006255 A GB 2006255A GB 822172 A GB822172 A GB 822172A
Authority
GB
United Kingdom
Prior art keywords
flanges
screwed
adjacent
gas turbine
compressor
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
GB20062/55A
Inventor
Nigel Edward Payne
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB20062/55A priority Critical patent/GB822172A/en
Publication of GB822172A publication Critical patent/GB822172A/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
    • F01D5/063—Welded rotors
    • 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
    • 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)

Abstract

822,172. Turbine and compressor rotors. ROLLS-ROYCE Ltd. July 11, 1956 [July 11, 1955], No. 20062/55. Class 110 (3). A multi-stage, axial-flow compressor or turbine rotor for an aircraft gas turbine engine comprises a number of axially-spaced bladecarrying members such as discs or rings which have cylindrical flanges extending on either side thereof, the flanges being screwed and adjacent flanges being in screwed engagement one within the other and also abutting one another adjacent the screwed portions and being welded together adjacent the abutment. The gas turbine engine compressor rotor shown comprises discs 16, 17, 18 which carry rotor blades 15 and which are formed with cylindrical flanges 19, 20 on their upstream and downstream surfaces respectively. The flanges 20 are stepped inwardly so as to fit within the adjacent flanges 19 and the inter-engaging surfaces are screwed at 19a, 20b. The flanges 19, 20 are also formed with flanges 19c, 20c which abut and are welded together and with portions 19b, 20a which form a spigot and socket connection to locate the flanges radially. The flanges 19 are formed on their outer surfaces with ribs 19d which in the assembly cooperate with shroud members 13a mounted at the inner ends of the stator blades 13. The end disc 18 is formed with a conical portion 22 which is connected to the driving shaft 21. The flange 20 on the downstream face of the end disc 18 is formed with ribs 24 which co-operate with a flange 25 on the stator structure so as to form a labyrinth seal. The screw-threads are handed so that in operation the torque tends to tighten the connection.
GB20062/55A 1955-07-11 1955-07-11 Improvements in or relating to the blade rotors for gas turbine engines Expired GB822172A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB20062/55A GB822172A (en) 1955-07-11 1955-07-11 Improvements in or relating to the blade rotors for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB20062/55A GB822172A (en) 1955-07-11 1955-07-11 Improvements in or relating to the blade rotors for gas turbine engines

Publications (1)

Publication Number Publication Date
GB822172A true GB822172A (en) 1959-10-21

Family

ID=10139743

Family Applications (1)

Application Number Title Priority Date Filing Date
GB20062/55A Expired GB822172A (en) 1955-07-11 1955-07-11 Improvements in or relating to the blade rotors for gas turbine engines

Country Status (1)

Country Link
GB (1) GB822172A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2456835A1 (en) * 1979-05-17 1980-12-12 United Technologies Corp ROTOR ASSEMBLY HAVING MULTI-STAGE DISC
EP0604754A1 (en) * 1992-11-26 1994-07-06 ABBPATENT GmbH Turbine rotor
US5833244A (en) * 1995-11-14 1998-11-10 Rolls-Royce P L C Gas turbine engine sealing arrangement
FR3101106A1 (en) * 2019-09-25 2021-03-26 Safran Aircraft Engines Turbine rotor of a turbomachine and turbomachine turbine equipped with such a rotor.

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2456835A1 (en) * 1979-05-17 1980-12-12 United Technologies Corp ROTOR ASSEMBLY HAVING MULTI-STAGE DISC
EP0604754A1 (en) * 1992-11-26 1994-07-06 ABBPATENT GmbH Turbine rotor
US5833244A (en) * 1995-11-14 1998-11-10 Rolls-Royce P L C Gas turbine engine sealing arrangement
FR3101106A1 (en) * 2019-09-25 2021-03-26 Safran Aircraft Engines Turbine rotor of a turbomachine and turbomachine turbine equipped with such a rotor.

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