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GB778667A - Improvements in or relating to compressor blade root fixings - Google Patents

Improvements in or relating to compressor blade root fixings

Info

Publication number
GB778667A
GB778667A GB919454A GB919454A GB778667A GB 778667 A GB778667 A GB 778667A GB 919454 A GB919454 A GB 919454A GB 919454 A GB919454 A GB 919454A GB 778667 A GB778667 A GB 778667A
Authority
GB
United Kingdom
Prior art keywords
blade
curved
root portion
dovetail
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
GB919454A
Inventor
Norman Battle
John Shaw Hollings
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 GB919454A priority Critical patent/GB778667A/en
Publication of GB778667A publication Critical patent/GB778667A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings

Landscapes

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

Abstract

778,667. Compressor blades. ROLLSROYCE, Ltd. March 29, 1955 [March 29, 1954], No. 9194/54. Class 110 (3). A blade of an axial-flow compressor is made of plastics material and has an enlarged root portion of dovetail shape which is curved chordwise of the blade in a circular arc and which engages in a correspondingly-curved slot in the rotor or stator in which the blade is to be mounted, the curvature being in the same sense as that of the camber line of the blade, the dovetail root being faired smoothly into the aerofoil section of the blade. The root portion 13 of the blade 12 is of dovetail cross-section and is curved as shown clearly in Fig. 2 and the slot 11 in the rotor disc 10 is correspondingly shaped and curved. The camber line of each aerofoil section of the blade may be a circular arc, the cylindrical surface through which forms a continuation of the cylindrical surface through the centre of the root portion. The Provisional Specification refers also to turbine blades and to blades having roots of bulb shape.
GB919454A 1954-03-29 1954-03-29 Improvements in or relating to compressor blade root fixings Expired GB778667A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB919454A GB778667A (en) 1954-03-29 1954-03-29 Improvements in or relating to compressor blade root fixings

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB919454A GB778667A (en) 1954-03-29 1954-03-29 Improvements in or relating to compressor blade root fixings

Publications (1)

Publication Number Publication Date
GB778667A true GB778667A (en) 1957-07-10

Family

ID=9867213

Family Applications (1)

Application Number Title Priority Date Filing Date
GB919454A Expired GB778667A (en) 1954-03-29 1954-03-29 Improvements in or relating to compressor blade root fixings

Country Status (1)

Country Link
GB (1) GB778667A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3178101A (en) * 1961-04-27 1965-04-13 Rolls Royce Axial flow compressors
DE3045224A1 (en) * 1979-11-30 1981-06-19 United Technologies Corp., 06101 Hartford, Conn. BLADE FOR TURBINE ENGINES
GB2243413A (en) * 1990-03-29 1991-10-30 Gen Electric Rotor blade mounting for gas turbine engine.
EP1855011A1 (en) * 2006-05-12 2007-11-14 Snecma Moteurs Assembly for the engine compressor of an aircraft comprising tilted-head hammer attachment vanes
US10364873B1 (en) * 2017-10-05 2019-07-30 Ronald Wayne Wolverton Torque converter stator having interchangeable blades

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3178101A (en) * 1961-04-27 1965-04-13 Rolls Royce Axial flow compressors
DE3045224A1 (en) * 1979-11-30 1981-06-19 United Technologies Corp., 06101 Hartford, Conn. BLADE FOR TURBINE ENGINES
JPS57400A (en) * 1979-11-30 1982-01-05 United Technologies Corp Fan blade
JPH0141839B2 (en) * 1979-11-30 1989-09-07 Yunaitetsudo Tekunorojiizu Corp
DE3045224C2 (en) * 1979-11-30 1992-07-09 United Technologies Corp., Hartford, Conn., Us
GB2243413A (en) * 1990-03-29 1991-10-30 Gen Electric Rotor blade mounting for gas turbine engine.
GB2243413B (en) * 1990-03-29 1993-12-22 Gen Electric Gas turbine bladed disk.
EP1855011A1 (en) * 2006-05-12 2007-11-14 Snecma Moteurs Assembly for the engine compressor of an aircraft comprising tilted-head hammer attachment vanes
FR2900989A1 (en) * 2006-05-12 2007-11-16 Snecma Sa AIRCRAFT ENGINE COMPRESSOR ASSEMBLY COMPRISING AUBES WITH FOOT HAMMER ATTACHMENT
US7959410B2 (en) 2006-05-12 2011-06-14 Snecma Assembly for an aircraft engine compressor comprising blades with hammer attachment with inclined root
US10364873B1 (en) * 2017-10-05 2019-07-30 Ronald Wayne Wolverton Torque converter stator having interchangeable blades

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