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GB1012899A - Air cooled gas turbine blades - Google Patents

Air cooled gas turbine blades

Info

Publication number
GB1012899A
GB1012899A GB43187/64A GB4318764A GB1012899A GB 1012899 A GB1012899 A GB 1012899A GB 43187/64 A GB43187/64 A GB 43187/64A GB 4318764 A GB4318764 A GB 4318764A GB 1012899 A GB1012899 A GB 1012899A
Authority
GB
United Kingdom
Prior art keywords
blade
parts
gas turbine
air
root
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
GB43187/64A
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.)
Sulzer AG
Original Assignee
Sulzer AG
Gebrueder Sulzer AG
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 Sulzer AG, Gebrueder Sulzer AG filed Critical Sulzer AG
Publication of GB1012899A publication Critical patent/GB1012899A/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
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Landscapes

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

Abstract

1,012,899. Gas turbine blades. SULZER BROS. Ltd. Oct. 22, 1964 [Oct. 29, 1963], No. 43187/64. Heading FIT. A hollow, air cooled, gas turbine blade having a fir tree root 2, Fig. 4, is formed from two parts a and b, Fig. 2, joined along at least part of a joint face extending through the leading and trailing edges of the blade and through the end faces of the root, the two parts defining between them an opening through which a member 12 can be introduced into and removed from the blade interior 11. Each blade root receiving groove 3 in the turbine rotor 4 has a cylindrical base portion 15 receiving the radially inner end of the member 12 formed with projections 14 and 16. The portion of the member 12 contained within the blade is formed with projections 13 which may have deformable edges for reliable engagement with the blade. Air is introduced into the groove 3 through a conduit (not shown) in the rotor, and flows into the blade interior, where the member 12 ensures that the cooling air effectively sweeps the blade walls. A continuous weld seam m extends between the two parts a and b along the leading edge of the blade, whereas the weld n along the trailing edge is interrupted to leave gaps (not shown) through which air may leave the blade interior. A gap 24 is also left between the parts a and b at the outer tip of the blade.
GB43187/64A 1963-10-29 1964-10-22 Air cooled gas turbine blades Expired GB1012899A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1328963A CH407654A (en) 1963-10-29 1963-10-29 Air-cooled blade of a gas turbine

Publications (1)

Publication Number Publication Date
GB1012899A true GB1012899A (en) 1965-12-08

Family

ID=4391104

Family Applications (1)

Application Number Title Priority Date Filing Date
GB43187/64A Expired GB1012899A (en) 1963-10-29 1964-10-22 Air cooled gas turbine blades

Country Status (4)

Country Link
BE (1) BE654935A (en)
CH (1) CH407654A (en)
GB (1) GB1012899A (en)
NL (2) NL124984C (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2224082A (en) * 1988-10-19 1990-04-25 Rolls Royce Plc Turbine disc having cooling and sealing arrangements
WO2015134005A1 (en) * 2014-03-05 2015-09-11 Siemens Aktiengesellschaft Turbine airfoil
US9777575B2 (en) 2014-01-20 2017-10-03 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities
CN117307254A (en) * 2023-11-28 2023-12-29 成都中科翼能科技有限公司 Turbine rotor structure of gas turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1947295A1 (en) * 2007-01-18 2008-07-23 Siemens Aktiengesellschaft Vane plug of an axial turbine vane

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2224082A (en) * 1988-10-19 1990-04-25 Rolls Royce Plc Turbine disc having cooling and sealing arrangements
US9777575B2 (en) 2014-01-20 2017-10-03 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities
WO2015134005A1 (en) * 2014-03-05 2015-09-11 Siemens Aktiengesellschaft Turbine airfoil
US9631499B2 (en) 2014-03-05 2017-04-25 Siemens Aktiengesellschaft Turbine airfoil cooling system for bow vane
JP2017518451A (en) * 2014-03-05 2017-07-06 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ Turbine blade cooling system for arcuate vanes
CN117307254A (en) * 2023-11-28 2023-12-29 成都中科翼能科技有限公司 Turbine rotor structure of gas turbine
CN117307254B (en) * 2023-11-28 2024-01-23 成都中科翼能科技有限公司 Turbine rotor structure of gas turbine

Also Published As

Publication number Publication date
CH407654A (en) 1966-02-15
NL300988A (en)
BE654935A (en) 1965-04-28
NL124984C (en)

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