GB1394739A - Compressor or turbine rotor - Google Patents

Compressor or turbine rotor

Info

Publication number
GB1394739A
GB1394739A GB2456872A GB2456872A GB1394739A GB 1394739 A GB1394739 A GB 1394739A GB 2456872 A GB2456872 A GB 2456872A GB 2456872 A GB2456872 A GB 2456872A GB 1394739 A GB1394739 A GB 1394739A
Authority
GB
United Kingdom
Prior art keywords
apertures
rotor
web
flanges
blades
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
GB2456872A
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 GB2456872A priority Critical patent/GB1394739A/en
Publication of GB1394739A publication Critical patent/GB1394739A/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
    • 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
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins

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

1394739 Turbine and compressor bladed rotors ROLLS-ROYCE (1971) Ltd 17 May 1973 [25 May 1972] 24568/72 Heading FIT A turbine or compressor rotor comprises a filament wound drum having at least one row of apertures therein adapted to receive the root portions of a row of rotor blades. By the term "filament wound" is meant formed from a length or plurality of lengths of a fibrous material which is wound to form the desired shape and simultaneously or subsequently embedded in a matrix material. The rotor shown is a compressor rotor of a gas turbine engine and comprises a cylindrical web portion 29 with four flanges 30 between which are formed apertures 31 for reception of blade root portions 40. The web 29 is connected integrally by means of a frusto-conical portion 32 with a further web 33 similarly formed with flanges 34 and apertures 35, and the web 33 is in turn connected integrally by a frusto-conical portion 36 with a further web 37 similarly formed with flanges 38 and apertures 39. The blades are also formed of fibre material and the roots 40 are in the form of loops which are inserted through the apertures 31 and are retained by pins 41 passed through the loops below the web 29, a spreader member 42 having an arcuate outer surface and a recess to receive the pin being provided. Filler pieces 44 are provided between adjacent blades of a blade row, the filler pieces engaging against projections 45 formed at both sides of the blades. In a second embodiment the rotor drum is formed with inwardly-directed flanges 55, 56, 57 the blade roots 58, 59 being again in the form of loops which extend through apertures between the flanges and are retained by pins 61, 62, annular rings 63 being incorporated in the rotor drum during the winding phase of manufacture. The rotor may be formed of carbon fibres embedded in an epoxy resin matrix.
GB2456872A 1972-05-25 1972-05-25 Compressor or turbine rotor Expired GB1394739A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2456872A GB1394739A (en) 1972-05-25 1972-05-25 Compressor or turbine rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2456872A GB1394739A (en) 1972-05-25 1972-05-25 Compressor or turbine rotor

Publications (1)

Publication Number Publication Date
GB1394739A true GB1394739A (en) 1975-05-21

Family

ID=10213694

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2456872A Expired GB1394739A (en) 1972-05-25 1972-05-25 Compressor or turbine rotor

Country Status (1)

Country Link
GB (1) GB1394739A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
FR2453971A1 (en) * 1979-04-14 1980-11-07 Mtu Muenchen Gmbh WHEEL FOR AXIAL FLOW TURBOMACHINES
US4541778A (en) * 1984-05-18 1985-09-17 The United States Of America As Represented By The Secretary Of The Navy Pin rooted blade biaxial air seal
FR2601069A1 (en) * 1986-07-02 1988-01-08 Rolls Royce Plc TURBINE.
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
US5601404A (en) * 1994-11-05 1997-02-11 Rolls-Royce Plc Integral disc seal
EP3726006A1 (en) * 2019-04-15 2020-10-21 Safran Aero Boosters SA Hybrid rotor with inserts

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
FR2453971A1 (en) * 1979-04-14 1980-11-07 Mtu Muenchen Gmbh WHEEL FOR AXIAL FLOW TURBOMACHINES
US4541778A (en) * 1984-05-18 1985-09-17 The United States Of America As Represented By The Secretary Of The Navy Pin rooted blade biaxial air seal
FR2601069A1 (en) * 1986-07-02 1988-01-08 Rolls Royce Plc TURBINE.
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
US5601404A (en) * 1994-11-05 1997-02-11 Rolls-Royce Plc Integral disc seal
EP3726006A1 (en) * 2019-04-15 2020-10-21 Safran Aero Boosters SA Hybrid rotor with inserts
BE1027190B1 (en) * 2019-04-15 2020-11-16 Safran Aero Boosters Sa HYBRID ROTOR WITH INSERTS

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Legal Events

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