GB1271822A - Stator blade rings - Google Patents

Stator blade rings

Info

Publication number
GB1271822A
GB1271822A GB37290/69A GB3729069A GB1271822A GB 1271822 A GB1271822 A GB 1271822A GB 37290/69 A GB37290/69 A GB 37290/69A GB 3729069 A GB3729069 A GB 3729069A GB 1271822 A GB1271822 A GB 1271822A
Authority
GB
United Kingdom
Prior art keywords
journal
blade
fins
chambers
region
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
GB37290/69A
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 GB1271822A publication Critical patent/GB1271822A/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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
  • Mounting Of Bearings Or Others (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,271,822. Gas turbines; axial-flow compressors and pumps. SULZER BROS Ltd. July 24, 1969 [July 26, 1968], No. 37290/69. Headings F1C, FIG and F1T. In a turbine, compressor or like machine having angularly adjustable stator blades 5, each blade is journalled in a respective housing 4 secured to the outer side of the machine casing 1 so that the bearing surfaces are remote from the working fluid-flowing through the machine. Each housing 4 has spaced tubular walls 9, 20 defining cooling air chambers 14, 15 surrounding plastics dry running bearings 10, 11 in which the blade journal 8 is mounted. The chambers 15 of circumferentially adjacent housings 4 are inter-connected by resilient bellows 16 so that cooling air supplied through two diametrically opposite pipes 19 can flow to all the chambers 15. The cooling air from the latter passes through ports 18 into the chambers 14, each of which contains a U-shaped sheet metal baffle 36 to direct the air along the walls of the chamber. The neck 6 of each blade has cooling fins 23 around which is tightly fitted a sleeve 30. Each of the fins 23 has a segment 35 milled away, the milled regions alternating from fin to fin by 180 degrees so that the cooling air leaving region 46 at the open lower end of chamber 14 follows a tortuous path in flowing over the fins 23 before exhausting through holes 39 in sleeve 30 and ducts (not shown), into the working fluid. Sleeve 30 is a loose fit within a plate 22 and is urged by spring 31 against a recess 32 in a ring 33. Plate 22 is clamped in position by housing 4, the latter being secured to casing 1 by screws passing through flange 21. A thrust bearing comprising a collar 24, two discs 25 and a retaining ring 26 is provided at the top of each journal 8, leakage past the ring 26 being prevented by an O-ring seal 55. A collar 27 carries the blade adjusting lever 28. The journal 8 is formed from a material having good dry running properties and is shrunk or force fitted over the blade stem 7. In a modification, Fig. 5 (not shown), the journal 8 is cast with the blade, the aero-foil portion 5 being of heatresistant steel and the journal 8 of dry running material. The junction between the two materials is in the region of the fins 23. In this modification additional cooling of bearing 10 is effected by diverting some air from region 46 to a chamber (44) in journal 8 in the region of bearing 10, the air exhausting to atmosphere through bores (47), 40 in the journal.
GB37290/69A 1968-07-26 1969-07-24 Stator blade rings Expired GB1271822A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1127668A CH494895A (en) 1968-07-26 1968-07-26 Guide vane ring for turbo machines

Publications (1)

Publication Number Publication Date
GB1271822A true GB1271822A (en) 1972-04-26

Family

ID=4371878

Family Applications (1)

Application Number Title Priority Date Filing Date
GB37290/69A Expired GB1271822A (en) 1968-07-26 1969-07-24 Stator blade rings

Country Status (7)

Country Link
US (1) US3582231A (en)
BE (1) BE731928A (en)
CH (1) CH494895A (en)
DE (1) DE1751812B2 (en)
FR (1) FR2013758A1 (en)
GB (1) GB1271822A (en)
NL (1) NL145635B (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3850544A (en) * 1973-11-02 1974-11-26 Gen Electric Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades
US3966352A (en) * 1975-06-30 1976-06-29 United Technologies Corporation Variable area turbine
US4025227A (en) * 1975-06-30 1977-05-24 United Technologies Corporation Variable area turbine
CA1052231A (en) * 1976-04-22 1979-04-10 Dominion Engineering Works Limited Water turbine bearing seal
DE19747555A1 (en) * 1997-10-28 1999-04-29 Voith Sulzer Papiertech Patent Heated and / or coolable cylinder
US6453556B1 (en) * 2000-10-11 2002-09-24 Hmy Ltd. Method of producing exhaust gas vane blade for superchargers of motor vehicles and vane blade
EP1895106A1 (en) * 2006-08-28 2008-03-05 ABB Turbo Systems AG Sealing of variable guide vanes
CN112388260A (en) * 2020-11-20 2021-02-23 无锡航亚科技股份有限公司 Machining method for journal of double-journal rectifying blade of aircraft engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE514728A (en) * 1951-10-10
GB755527A (en) * 1953-10-15 1956-08-22 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in axial flow elastic fluid turbines
US3013771A (en) * 1960-10-18 1961-12-19 Chrysler Corp Adjustable nozzles for gas turbine engine
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit

Also Published As

Publication number Publication date
DE1751812B2 (en) 1971-05-13
FR2013758A1 (en) 1970-04-10
BE731928A (en) 1969-10-23
NL6811394A (en) 1970-01-29
US3582231A (en) 1971-06-01
NL145635B (en) 1975-04-15
CH494895A (en) 1970-08-15
DE1751812A1 (en) 1970-10-01

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee