CA1001078A - Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades - Google Patents

Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades

Info

Publication number
CA1001078A
CA1001078A CA206,376A CA206376A CA1001078A CA 1001078 A CA1001078 A CA 1001078A CA 206376 A CA206376 A CA 206376A CA 1001078 A CA1001078 A CA 1001078A
Authority
CA
Canada
Prior art keywords
bearing
axial flow
mounting arrangement
variable pitch
stationary 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
CA206,376A
Other versions
CA206376S (en
Inventor
John J. Ciokajlo
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Application granted granted Critical
Publication of CA1001078A publication Critical patent/CA1001078A/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
CA206,376A 1973-11-02 1974-08-06 Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades Expired CA1001078A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00412321A US3850544A (en) 1973-11-02 1973-11-02 Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades

Publications (1)

Publication Number Publication Date
CA1001078A true CA1001078A (en) 1976-12-07

Family

ID=23632524

Family Applications (1)

Application Number Title Priority Date Filing Date
CA206,376A Expired CA1001078A (en) 1973-11-02 1974-08-06 Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades

Country Status (3)

Country Link
US (1) US3850544A (en)
CA (1) CA1001078A (en)
DE (1) DE2444478A1 (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214851A (en) * 1978-04-20 1980-07-29 General Electric Company Structural cooling air manifold for a gas turbine engine
US4808069A (en) * 1986-07-03 1989-02-28 The United States Of America As Represented By The Secretary Of The Air Force Anti-rotation guide vane bushing
FR2603340B1 (en) * 1986-09-03 1988-11-04 Snecma TURBOMACHINE COMPRISING A DEVICE FOR ADJUSTING THE GAMES OF A LABYRINTH JOINT BETWEEN ROTOR AND STATOR AND OF THE GAS VEIN ALIGNMENT AND METHOD OF APPLICATION
US4990056A (en) * 1989-11-16 1991-02-05 General Motors Corporation Stator vane stage in axial flow compressor
US5342167A (en) * 1992-10-09 1994-08-30 Airflow Research And Manufacturing Corporation Low noise fan
FR2777318B1 (en) * 1998-04-09 2000-05-12 Snecma PROCESS FOR REDUCING THE EXISTING CLEARANCE BETWEEN A SHIRT AND A TURBINE DISTRIBUTOR OF A TURBOREACTOR
ITTO20010444A1 (en) * 2001-05-11 2002-11-11 Fiatavio Spa AXIAL TURBINE FOR AERONAUTICAL APPLICATIONS.
US8202043B2 (en) * 2007-10-15 2012-06-19 United Technologies Corp. Gas turbine engines and related systems involving variable vanes
US8491257B2 (en) * 2007-12-12 2013-07-23 Honeywell International Inc. Nozzle vane and crank arm assembly and method
US20100275572A1 (en) * 2009-04-30 2010-11-04 Pratt & Whitney Canada Corp. Oil line insulation system for mid turbine frame
FR2977635B1 (en) * 2011-07-04 2017-03-24 Snecma DRIVE SHAFT DEVICE OF A TURBOMACHINE
EP3907374A1 (en) 2013-08-21 2021-11-10 Raytheon Technologies Corporation Variable area turbine arrangement with secondary flow modulation
US9790860B2 (en) * 2015-01-16 2017-10-17 United Technologies Corporation Cooling passages for a mid-turbine frame
CN109236474B (en) * 2018-11-15 2020-03-13 中国航发湖南动力机械研究所 Oil supply support plate, gas turbine starter and micro-combustion engine
US11274770B2 (en) * 2019-04-18 2022-03-15 Raytheon Technologies Corporation Monolithic fluid transfer tube
US11346241B2 (en) * 2020-05-28 2022-05-31 Pratt & Whitney Canada Corp. Variable guide vanes assembly

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2414788A (en) * 1942-11-23 1947-01-28 Allis Chalmers Mfg Co Turbine construction
US2680001A (en) * 1950-11-13 1954-06-01 United Aircraft Corp Arrangement for cooling turbine bearings
GB803137A (en) * 1955-08-05 1958-10-22 Rolls Royce Improvements in or relating to axial-flow fluid machines for example turbines and compressors of gas-turbine engines
US3084849A (en) * 1960-05-18 1963-04-09 United Aircraft Corp Inlet and bearing support for axial flow compressors
US3312448A (en) * 1965-03-01 1967-04-04 Gen Electric Seal arrangement for preventing leakage of lubricant in gas turbine engines
CH494895A (en) * 1968-07-26 1970-08-15 Sulzer Ag Guide vane ring for turbo machines

Also Published As

Publication number Publication date
US3850544A (en) 1974-11-26
DE2444478A1 (en) 1975-05-07

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