IT8521411A0 - STATOR BLADE ESPECIALLY FOR GAS TURBOENGINE. - Google Patents

STATOR BLADE ESPECIALLY FOR GAS TURBOENGINE.

Info

Publication number
IT8521411A0
IT8521411A0 IT8521411A IT2141185A IT8521411A0 IT 8521411 A0 IT8521411 A0 IT 8521411A0 IT 8521411 A IT8521411 A IT 8521411A IT 2141185 A IT2141185 A IT 2141185A IT 8521411 A0 IT8521411 A0 IT 8521411A0
Authority
IT
Italy
Prior art keywords
turboengine
gas
stator blade
blade especially
stator
Prior art date
Application number
IT8521411A
Other languages
Italian (it)
Other versions
IT1185174B (en
Inventor
David Glenn Cherry
Dean Thomas Lenahan
Harvey Michael Maclin
Mikio Suo
Original Assignee
Schenectady New York U S A A
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 Schenectady New York U S A A filed Critical Schenectady New York U S A A
Publication of IT8521411A0 publication Critical patent/IT8521411A0/en
Application granted granted Critical
Publication of IT1185174B publication Critical patent/IT1185174B/en

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
IT21411/85A 1984-07-02 1985-07-02 STATOR SHOVEL PARTICULARLY FOR GAS TURBOMOBORE IT1185174B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US62731484A 1984-07-02 1984-07-02

Publications (2)

Publication Number Publication Date
IT8521411A0 true IT8521411A0 (en) 1985-07-02
IT1185174B IT1185174B (en) 1987-11-04

Family

ID=24514152

Family Applications (1)

Application Number Title Priority Date Filing Date
IT21411/85A IT1185174B (en) 1984-07-02 1985-07-02 STATOR SHOVEL PARTICULARLY FOR GAS TURBOMOBORE

Country Status (5)

Country Link
JP (1) JPS6123803A (en)
DE (1) DE3523145A1 (en)
FR (1) FR2568938B1 (en)
GB (1) GB2161220B (en)
IT (1) IT1185174B (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2235253A (en) * 1989-08-16 1991-02-27 Rolls Royce Plc Ceramic guide vane for gas turbine engine
JPH03213602A (en) * 1990-01-08 1991-09-19 General Electric Co <Ge> Self cooling type joint connecting structure to connect contact segment of gas turbine engine
US7581924B2 (en) * 2006-07-27 2009-09-01 Siemens Energy, Inc. Turbine vanes with airfoil-proximate cooling seam
FR3048719B1 (en) * 2016-03-14 2018-03-02 Safran Aircraft Engines FLOW RECTIFIER FOR TURBOMACHINE WITH INTEGRATED AND REPORTED PLATFORMS
US11156116B2 (en) * 2019-04-08 2021-10-26 Honeywell International Inc. Turbine nozzle with reduced leakage feather seals

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH386451A (en) * 1960-10-07 1965-01-15 Licentia Gmbh Wet steam turbine
NL6616482A (en) * 1966-02-28 1967-08-29
US3617685A (en) * 1970-08-19 1971-11-02 Chromalloy American Corp Method of producing crack-free electron beam welds of jet engine components
GB1483532A (en) * 1974-09-13 1977-08-24 Rolls Royce Stator structure for a gas turbine engine

Also Published As

Publication number Publication date
GB2161220A (en) 1986-01-08
FR2568938B1 (en) 1989-04-21
IT1185174B (en) 1987-11-04
FR2568938A1 (en) 1986-02-14
DE3523145A1 (en) 1986-01-09
GB2161220B (en) 1988-09-01
JPS6123803A (en) 1986-02-01
GB8515742D0 (en) 1985-07-24

Similar Documents

Publication Publication Date Title
IT8221755A0 (en) BLADE FOR A GAS TURBINE.
IT8519864A0 (en) ROTARY SEAL ESPECIALLY FOR GAS TURBINE.
BR8506985A (en) A SHAVING BLADE SET
IT8521719A0 (en) GAS TURBINE.BLADE DISC COMPLEX FOR
IT8520834A0 (en) BLADE FOR GAS TURBINE.
GB2107641B (en) A saw blade
DE3580755D1 (en) RAZOR BLADE.
IT8522972A0 (en) PLATFORM SEAL FOR FAN BLADE
IT8621513A0 (en) GAS TURBINE.
DE3769714D1 (en) STATOR BLADE.
IT8722413A0 (en) GAS TIGHT ARRANGEMENT FOR A MAST.
ES289449Y (en) PERFECTED ROTOR BLADE.
IT8523205A0 (en) ENHANCER FOR GAS TURBO ENGINE.
IT8522785A0 (en) MULTI-CHAMBER AIRPROFILE COOLING INSERT FOR TURBINE BLADE.
DE3578941D1 (en) CUTTING INSERT.
DE3584712D1 (en) CIRCULAR SAW BLADE.
IT8521277A0 (en) BAND SAW.
NO160807C (en) Gas turbine.
IT8423829A0 (en) BLADE FOR GAS TURBO ENGINE.
ZA857664B (en) A hub for a concrete saw blade
IT8520553A0 (en) CUTTING MACHINE.
AR228676A1 (en) TURBINE ROTOR BLADE
IT8619181A0 (en) TURBINE BLADE PLATFORM.
DE3580336D1 (en) CUTTING TOOL.
GB8516708D0 (en) Rotor blade construction