GB1048340A - Nozzle blade assembly for turbines - Google Patents

Nozzle blade assembly for turbines

Info

Publication number
GB1048340A
GB1048340A GB39117/65A GB3911765A GB1048340A GB 1048340 A GB1048340 A GB 1048340A GB 39117/65 A GB39117/65 A GB 39117/65A GB 3911765 A GB3911765 A GB 3911765A GB 1048340 A GB1048340 A GB 1048340A
Authority
GB
United Kingdom
Prior art keywords
blade
blades
angular position
turbine
casing
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
GB39117/65A
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.)
Worthington Corp
Original Assignee
Worthington Corp
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 Worthington Corp filed Critical Worthington Corp
Publication of GB1048340A publication Critical patent/GB1048340A/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
    • 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
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • 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
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/912—Interchangeable parts to vary pumping capacity or size of pump

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Medicines Containing Material From Animals Or Micro-Organisms (AREA)

Abstract

1,048,340. Turbines. WORTHINGTON CORPORATION. Sept. 14, 1965 [Nov. 5, 1964], No. 39117/65. Heading F1T. A nozzle blade assembly preferably in two halves and suitable for use in a radial inlet, double flow gas turbine having first stage rotor blades 22, an outer sheet metal casing (not shown) and an inner casing 10 provided with a lining 14 positioned and sealed at 16, comprises independently removable blades 40 each consisting of an aerofoil member 42 anda member 44 for covering a preferably non- circular longitudinal groove 46, Fig. 3 (not shown), therein. The members 42, 44 may be of stainless steel. After assembly of the member 42 by its groove on to a support bolt 32, the cover member 44 is connected to the member 42 by screws 50 which thereafter are preferably welded over and ground flush with the blade surface. On initial assembly each blade 40 is adjusted by square end 74 of bolt 32 to the angular position for optimum turbine efficiency and locked therein by nuts 38. A hole 64 is then drilled and tapped in the casing 10 through one of a number of angularly spaced bores 62 in enlarged portion 34 of belt 32, and a screw 66 inserted therein to positively secure the blade against angular movement. A nut 70 locked by peening at 76 prevents disengagement of screw 66. The angular position of the blade may later be adjusted by engaging the screw 66 with the tapped hole 64 through a different bore 62. To facilitate determination of the blade angular position for turbine optimum efficiency, the inflow passage to one side of the turbine is covered by a blank 86, Fig. 4 (not shown), located over bolts 32 and secured to the casing 10 by plates (100) and bolts (102, 104), and the flow and length of the nozzle blades are reduced by one half. After the blade angular position has been established, the blank and half-length blades are replaced by the full-length blades 40.
GB39117/65A 1964-11-05 1965-09-14 Nozzle blade assembly for turbines Expired GB1048340A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US409229A US3263963A (en) 1964-11-05 1964-11-05 Nozzle blade assembly comprising replaceable and adjustable nozzle blades

Publications (1)

Publication Number Publication Date
GB1048340A true GB1048340A (en) 1966-11-16

Family

ID=23619597

Family Applications (1)

Application Number Title Priority Date Filing Date
GB39117/65A Expired GB1048340A (en) 1964-11-05 1965-09-14 Nozzle blade assembly for turbines

Country Status (5)

Country Link
US (1) US3263963A (en)
BE (1) BE670006A (en)
DE (1) DE1426886A1 (en)
GB (1) GB1048340A (en)
NL (1) NL6514267A (en)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3856434A (en) * 1973-10-18 1974-12-24 Westinghouse Electric Corp Centrifugal fan wheel
US4565495A (en) * 1983-08-11 1986-01-21 Electric Power Research Institute, Inc. Armoring system for an airfoil centrifugal fan
CH676735A5 (en) * 1988-08-03 1991-02-28 Asea Brown Boveri
JP2828587B2 (en) * 1993-12-28 1998-11-25 三菱電機株式会社 Cooling fan for vehicle alternator
WO1998031922A1 (en) * 1997-01-14 1998-07-23 Siemens Aktiengesellschaft Turbine blade for a turbine engine, specially a gas turbine engine
CN102444426B (en) 2010-09-30 2015-05-27 阿尔斯通技术有限公司 Method of modifying a steam turbine
US9303524B2 (en) * 2012-10-25 2016-04-05 Solar Turbines Incorporated Variable area turbine nozzle with a position selector
US20140119894A1 (en) * 2012-10-25 2014-05-01 Solar Turbines Incorporated Variable area turbine nozzle
GB201614803D0 (en) * 2016-09-01 2016-10-19 Rolls Royce Plc Variable stator vane rigging
CN109322709B (en) * 2018-09-13 2021-11-12 合肥通用机械研究院有限公司 Adjustable nozzle blade mechanism of turboexpander
CN113356933B (en) * 2021-07-05 2022-02-01 无锡发那特机械科技有限公司 Variable-section nozzle ring with quick-release type flow limiting sheet

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE148611C (en) *
US1248168A (en) * 1915-05-22 1917-11-27 Allis Chalmers Mfg Co Guide-vane.
US1656006A (en) * 1922-01-09 1928-01-10 Allis Chalmers Mfg Co Hydraulic machine
FR894567A (en) * 1942-02-02 1944-12-28 Vevey Atel Const Mec Guide vane for hydraulic turbine
US2945960A (en) * 1956-05-19 1960-07-19 Escher Wyss Ag Hydraulic turbine plant having a concrete spiral housing

Also Published As

Publication number Publication date
DE1426886A1 (en) 1969-03-06
US3263963A (en) 1966-08-02
BE670006A (en) 1966-03-23
NL6514267A (en) 1966-05-06

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