GB1263435A - Turbomachines - Google Patents

Turbomachines

Info

Publication number
GB1263435A
GB1263435A GB06967/70A GB1696770A GB1263435A GB 1263435 A GB1263435 A GB 1263435A GB 06967/70 A GB06967/70 A GB 06967/70A GB 1696770 A GB1696770 A GB 1696770A GB 1263435 A GB1263435 A GB 1263435A
Authority
GB
United Kingdom
Prior art keywords
ring
interior
plugs
vane
porous
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
GB06967/70A
Inventor
Leo Arthur Corrigan
Earle Rutledge Wall Jr
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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 Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB1263435A publication Critical patent/GB1263435A/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
    • 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

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)

Abstract

1,263,435. Turbines; axial-flow compressors. GENERAL MOTORS CORP. April 9, 1970 [July 25, 1969], No. 16967/70. Headings F1C and F1T. The throat area of an assembly of fixed guide vanes 10 for a turbine or compressor can be varied by generally axially movable aerofoil section plugs 40 disposed between adjacent vanes with their span extending generally circumferentially of the assembly. Each plug 40 is supported by a faired strut 51 from an actuating ring 54 which is axially slidable in a chamber defined between a structural ring 11 and a shroud facing ring 15. Cranked brackets 56 connect the actuating ring 54 to arms 60 which at one end 61 are pivotally mounted on a flange on ring 11 and at the other end 65 are connected to a unison ring 64. Thus circumferential movement of the latter causes movement of the plugs 40 in the direction 'B' so as to vary the throat area. Cooling air supplied through holes 36 in ring 11 flows through holes 68 into the interior of actuating ring 54 and thence through struts 51 to the interior of plugs 40, the walls of the latter being porous. Shroud facing rings 15, 20, 22 are also porous to assist cooling. Cooling air can flow to the interior of each vane 10 through its ends and through a hollow supporting spine 26. In a modification, Fig. 3 (not shown), the plug 40 is formed as a 360 degree one piece or segmental ring having a notch (49) at the position of each vane 10.
GB06967/70A 1969-07-25 1970-04-09 Turbomachines Expired GB1263435A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US84488569A 1969-07-25 1969-07-25

Publications (1)

Publication Number Publication Date
GB1263435A true GB1263435A (en) 1972-02-09

Family

ID=25293869

Family Applications (1)

Application Number Title Priority Date Filing Date
GB06967/70A Expired GB1263435A (en) 1969-07-25 1970-04-09 Turbomachines

Country Status (3)

Country Link
US (1) US3567331A (en)
CA (1) CA918077A (en)
GB (1) GB1263435A (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4497171A (en) * 1981-12-22 1985-02-05 The Garrett Corporation Combustion turbine engine
FR2685033B1 (en) * 1991-12-11 1994-02-11 Snecma STATOR DIRECTING THE AIR INLET INSIDE A TURBOMACHINE AND METHOD FOR MOUNTING A VANE OF THIS STATOR.
FR2775731B1 (en) * 1998-03-05 2000-04-07 Snecma CIRCULAR STAGE OF BLADES AT INTERIOR ENDS JOINED BY A CONNECTING RING
EP2623717A1 (en) * 2012-02-02 2013-08-07 Siemens Aktiengesellschaft Blade ring for an axial turbo engine and method for adjusting the absorption characteristics of the blade ring
US10711632B2 (en) * 2018-08-29 2020-07-14 General Electric Company Variable nozzles in turbine engines and methods related thereto
US10746057B2 (en) 2018-08-29 2020-08-18 General Electric Company Variable nozzles in turbine engines and methods related thereto

Also Published As

Publication number Publication date
CA918077A (en) 1973-01-02
US3567331A (en) 1971-03-02

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