GB701263A - Improvements in or relating to turbo-machines - Google Patents

Improvements in or relating to turbo-machines

Info

Publication number
GB701263A
GB701263A GB1947750A GB1947750A GB701263A GB 701263 A GB701263 A GB 701263A GB 1947750 A GB1947750 A GB 1947750A GB 1947750 A GB1947750 A GB 1947750A GB 701263 A GB701263 A GB 701263A
Authority
GB
United Kingdom
Prior art keywords
blades
disc
adjacent
tongues
slots
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
GB1947750A
Inventor
Nelson Hector Kent
Norman Robert Robinson
Cyril Armer
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 GB1947750A priority Critical patent/GB701263A/en
Publication of GB701263A publication Critical patent/GB701263A/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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Abstract

701,263. Making turbine blades; soldering and brazing. ROLLS-ROYCE, Ltd. Oct. 8 1951 [Aug. 3, 1950], No. 19477/50. Classes 83 (2, and 83 (4) [Also in Group XXVI] Hollow turbine blades 13 are secured to a supporting member 10 by cutting away the leading and trailing edges of each blade 13 at one end to form tongues 13a, providing the member 10 with peripherally spaced radial and axial slots 11 with arcuate section grooves 12 in the walls of the slots, placing each blade 13 so that its root straddles the portion between adjacent slots 11 with the tongues 13a in contact with a wall of one slot 11 and the adjacent wall of the adjacent slot 11, inserting wedge means 14 between adjacent tongues 13a to deform them into the grooves 12 and brazing the tongues 13a to the walls. The grooves 12 are preferably halfway along the radial length of the slots 11 and the wedges 14 are preferably circular section pins. The blades 13 may be formed from sheet metal folded at the leading edge and welded at the trailing edge or from aerofoil section tube. The blades 13 are cut away beyond the periphery of disc 10 to leave passages 15 for cooling air flow into the blades 13. To provide a manifold for cooling, two annular discs 17 are secured to flanges 16 on the disc 10 and plates 18 extending between adjacent pairs of blades 13 are welded to the discs 17 or pegged to the disc 10 and may be tack welded to the blades 13. The plates 18 are strengthened by ribs 18a. One disc 17 which has a flange 19 co-operating with a labyrinth seal 20 is spaced from the disc 10 and apertures 21 in the flange 16 allow air flow into and around the blades 13. Specification 650,424, [Group XXVI], is referred to.
GB1947750A 1950-08-03 1950-08-03 Improvements in or relating to turbo-machines Expired GB701263A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1947750A GB701263A (en) 1950-08-03 1950-08-03 Improvements in or relating to turbo-machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1947750A GB701263A (en) 1950-08-03 1950-08-03 Improvements in or relating to turbo-machines

Publications (1)

Publication Number Publication Date
GB701263A true GB701263A (en) 1953-12-23

Family

ID=10130014

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1947750A Expired GB701263A (en) 1950-08-03 1950-08-03 Improvements in or relating to turbo-machines

Country Status (1)

Country Link
GB (1) GB701263A (en)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2948505A (en) * 1956-12-26 1960-08-09 Gen Electric Gas turbine rotor
US2967043A (en) * 1956-11-30 1961-01-03 Napier & Sons Ltd D Blades and blade mounting assemblies for turbines and axial flow compressors
US2974924A (en) * 1956-12-05 1961-03-14 Gen Electric Turbine bucket retaining means and sealing assembly
US2985426A (en) * 1954-07-15 1961-05-23 Rolls Royce Bladed rotor construction for axialflow fluid machine
US3006605A (en) * 1958-06-04 1961-10-31 Edward A Stalker Bladed rotor and the like for axial flow fluid machines
US3010696A (en) * 1955-09-26 1961-11-28 Rolls Royce Bladed rotor with means to supply fluid to passages in the blades
US3023998A (en) * 1959-03-13 1962-03-06 Jr Walter H Sanderson Rotor blade retaining device
US3042369A (en) * 1959-02-11 1962-07-03 Gen Motors Corp Pinned blade sealing means
DE1253956B (en) * 1962-04-13 1967-11-09 Gen Electric Impeller of a blower with an edge turbine
US3393862A (en) * 1965-11-23 1968-07-23 Rolls Royce Bladed rotors
EP0043300A2 (en) * 1980-06-30 1982-01-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Cooling system for turbine blades and discs
EP0441424A1 (en) * 1990-02-08 1991-08-14 General Motors Corporation Turbomachine rotor
US6991428B2 (en) * 2003-06-12 2006-01-31 Pratt & Whitney Canada Corp. Fan blade platform feature for improved blade-off performance
US7503748B2 (en) 2004-03-13 2009-03-17 Rolls-Royce, Plc Mounting arrangement for turbine blades
FR2960589A1 (en) * 2010-05-28 2011-12-02 Snecma Paddle wheel i.e. low pressure turbine wheel, for turboshaft engine e.g. turbopropeller, of airplane, has sealing units arranged between piece and upstream ends of platforms of paddles

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2985426A (en) * 1954-07-15 1961-05-23 Rolls Royce Bladed rotor construction for axialflow fluid machine
US3010696A (en) * 1955-09-26 1961-11-28 Rolls Royce Bladed rotor with means to supply fluid to passages in the blades
US2967043A (en) * 1956-11-30 1961-01-03 Napier & Sons Ltd D Blades and blade mounting assemblies for turbines and axial flow compressors
US2974924A (en) * 1956-12-05 1961-03-14 Gen Electric Turbine bucket retaining means and sealing assembly
US2948505A (en) * 1956-12-26 1960-08-09 Gen Electric Gas turbine rotor
US3006605A (en) * 1958-06-04 1961-10-31 Edward A Stalker Bladed rotor and the like for axial flow fluid machines
US3042369A (en) * 1959-02-11 1962-07-03 Gen Motors Corp Pinned blade sealing means
US3023998A (en) * 1959-03-13 1962-03-06 Jr Walter H Sanderson Rotor blade retaining device
DE1253956B (en) * 1962-04-13 1967-11-09 Gen Electric Impeller of a blower with an edge turbine
US3393862A (en) * 1965-11-23 1968-07-23 Rolls Royce Bladed rotors
EP0043300A2 (en) * 1980-06-30 1982-01-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Cooling system for turbine blades and discs
EP0043300A3 (en) * 1980-06-30 1982-01-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Cooling system for turbine blades and discs
EP0441424A1 (en) * 1990-02-08 1991-08-14 General Motors Corporation Turbomachine rotor
US6991428B2 (en) * 2003-06-12 2006-01-31 Pratt & Whitney Canada Corp. Fan blade platform feature for improved blade-off performance
US7503748B2 (en) 2004-03-13 2009-03-17 Rolls-Royce, Plc Mounting arrangement for turbine blades
FR2960589A1 (en) * 2010-05-28 2011-12-02 Snecma Paddle wheel i.e. low pressure turbine wheel, for turboshaft engine e.g. turbopropeller, of airplane, has sealing units arranged between piece and upstream ends of platforms of paddles

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