GB702549A - Improvements in or relating to blade structures for axial flow compressors, turbinesor the like - Google Patents

Improvements in or relating to blade structures for axial flow compressors, turbinesor the like

Info

Publication number
GB702549A
GB702549A GB9315/51A GB931551A GB702549A GB 702549 A GB702549 A GB 702549A GB 9315/51 A GB9315/51 A GB 9315/51A GB 931551 A GB931551 A GB 931551A GB 702549 A GB702549 A GB 702549A
Authority
GB
United Kingdom
Prior art keywords
sides
blade
root portion
blades
divergent
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
GB9315/51A
Inventor
John Ernest Bell
Gordon Manns Lewis
Bertram Anthony Peaster
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.)
Bristol Aeroplane Co Ltd
Original Assignee
Bristol Aeroplane Co Ltd
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 Bristol Aeroplane Co Ltd filed Critical Bristol Aeroplane Co Ltd
Priority to GB9315/51A priority Critical patent/GB702549A/en
Publication of GB702549A publication Critical patent/GB702549A/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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/3076—Sheet metal discs
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

702,549. Turbine and compressor blades. BRISTOL AEROPLANE CO., Ltd. April 21 1952 [April 20, 1951], No. 9315/51. Class 110 (3) An axial-flow turbine or compressor blade comprises a blade working portion and a hollow sheet metal root portion extending therefrom, the root portion having a pair of opposite divergent sides with one or more stiffening members extending therebetween to prevent lateral movement of the sides. The blade working portion may be hollow and of sheet metal, the divergent sides of the root portion being made integral therewith. In Figs. I and II, the blade root portion comprises a platform 4 having divergent sides 7, 8 which are connected by a stiffening member 9, the flanges 10, 11 of which are connected to the inner faces of the sides 7, 8. The blade working portion extends through the platform 4 and stiffener 9 and the remaining sides 5, 6 and blade are cut away at 13, 12 for lightening purposes or to allow the passage of cooling or heating fluid. The blade root portions may be accommodated in axial, circumferential or oblique slots. In Fig. III, the rotor blades 24 pass through a. ring 18 comprising a frustoconical surface 19, having divergent sides 20, 21 which are connected by a sheet metal stiffening ring 23 having upward-turned flanges 26, 27. Down-turned lugs 31, 32 also extend from the ring 25 and correspond to lugs extending from the sides 20, 21, and U-shaped stiffeners 33 extend therebetween. Bolts 30 secure the blades between the rotor discs 28, 29 In Fig. VI the root portion comprising the divergent sides 35, 36 is formed integral with the blades and the ends of the roots are closed either by integrally pressed-out parts or by additional parts brazed in position, these parts constituting the stiffening members. Tray-like distance pieces 37 having sides 38, 39 contiguous with the sides of the roots 36, 35 ate disposed between the blade roots. A platform ring member 18 with downward-turned side flanges surrounds the root portions and distance pieces.
GB9315/51A 1951-04-20 1951-04-20 Improvements in or relating to blade structures for axial flow compressors, turbinesor the like Expired GB702549A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB9315/51A GB702549A (en) 1951-04-20 1951-04-20 Improvements in or relating to blade structures for axial flow compressors, turbinesor the like

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9315/51A GB702549A (en) 1951-04-20 1951-04-20 Improvements in or relating to blade structures for axial flow compressors, turbinesor the like

Publications (1)

Publication Number Publication Date
GB702549A true GB702549A (en) 1954-01-20

Family

ID=9869608

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9315/51A Expired GB702549A (en) 1951-04-20 1951-04-20 Improvements in or relating to blade structures for axial flow compressors, turbinesor the like

Country Status (1)

Country Link
GB (1) GB702549A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2857093A (en) * 1954-12-02 1958-10-21 Cincinnati Testing & Res Lab Stator casing and blade assembly
US6543995B1 (en) * 1999-08-09 2003-04-08 United Technologies Corporation Stator vane and stator assembly for a rotary machine
EP1219783A3 (en) * 2000-12-28 2004-02-11 ALSTOM (Switzerland) Ltd Stator vane for an axial flow turbine
EP1746252A3 (en) * 2005-07-20 2010-03-17 United Technologies Corporation Structural strut and shroud element

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2857093A (en) * 1954-12-02 1958-10-21 Cincinnati Testing & Res Lab Stator casing and blade assembly
US6543995B1 (en) * 1999-08-09 2003-04-08 United Technologies Corporation Stator vane and stator assembly for a rotary machine
EP1219783A3 (en) * 2000-12-28 2004-02-11 ALSTOM (Switzerland) Ltd Stator vane for an axial flow turbine
EP1746252A3 (en) * 2005-07-20 2010-03-17 United Technologies Corporation Structural strut and shroud element

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