GB647143A - Improvements in or relating to turbine blades - Google Patents

Improvements in or relating to turbine blades

Info

Publication number
GB647143A
GB647143A GB19010/47A GB1901047A GB647143A GB 647143 A GB647143 A GB 647143A GB 19010/47 A GB19010/47 A GB 19010/47A GB 1901047 A GB1901047 A GB 1901047A GB 647143 A GB647143 A GB 647143A
Authority
GB
United Kingdom
Prior art keywords
elements
ring
tongues
pair
assembly
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
GB19010/47A
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.)
EDWARD ALBERT STALKER
Original Assignee
EDWARD ALBERT STALKER
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 EDWARD ALBERT STALKER filed Critical EDWARD ALBERT STALKER
Publication of GB647143A publication Critical patent/GB647143A/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
    • F01D5/186—Film cooling
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F01D5/12—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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

647,143. Turbine blades. STALKER, E. A. July 16, 1947, No. 19010. Convention date, Oct. 22, 1945. [Class 110(iii)] A gas turbine blade comprises an assembly of axially nested elements including at least a pair which are separated at their longitudinal edges to form discharge slots for cooling fluid. One element of the pair has a partition 8 engaging a recess 6 in the other element to provide a structural and heat exchange separator, and between the elements cooling channels 10 communicating with the discharge slots. The elements may be of forged material and have end flanges 2 which are welded together to form the assembly into a blade of aerofoil shape. The nose element, Fig. 3, is made of a superior alloy and has perforations 23 for discharging cooling fluid. In a modification, Fig. 6, the elements are made of sheet metal with flanges 12 at one end only which are welded to a ring 16. The ring 16 and a retaining ring 18'in two segments are clamped between hub sections 20 of the rotor. A shroud ring 22 is shrunk on over tongues 14 on the elements, the tongues being then riveted over.
GB19010/47A 1945-10-22 1947-07-16 Improvements in or relating to turbine blades Expired GB647143A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US647143XA 1945-10-22 1945-10-22

Publications (1)

Publication Number Publication Date
GB647143A true GB647143A (en) 1950-12-06

Family

ID=22057801

Family Applications (1)

Application Number Title Priority Date Filing Date
GB19010/47A Expired GB647143A (en) 1945-10-22 1947-07-16 Improvements in or relating to turbine blades

Country Status (2)

Country Link
FR (1) FR963825A (en)
GB (1) GB647143A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2823893A (en) * 1952-06-09 1958-02-18 Gen Motors Corp Laminated turbine buckets
DE1110469B (en) * 1956-03-28 1961-07-06 Robert Pouit Gas turbine with reaction blades
US4026659A (en) * 1975-10-16 1977-05-31 Avco Corporation Cooled composite vanes for turbine nozzles

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH584833A5 (en) * 1975-05-16 1977-02-15 Bbc Brown Boveri & Cie

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2823893A (en) * 1952-06-09 1958-02-18 Gen Motors Corp Laminated turbine buckets
DE1110469B (en) * 1956-03-28 1961-07-06 Robert Pouit Gas turbine with reaction blades
US4026659A (en) * 1975-10-16 1977-05-31 Avco Corporation Cooled composite vanes for turbine nozzles

Also Published As

Publication number Publication date
FR963825A (en) 1950-07-21

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