GB1306891A - Method and blade arrangement to reduce the serpentine motion of a mass particle flowing through a turbomachine - Google Patents

Method and blade arrangement to reduce the serpentine motion of a mass particle flowing through a turbomachine

Info

Publication number
GB1306891A
GB1306891A GB1699271A GB1699271A GB1306891A GB 1306891 A GB1306891 A GB 1306891A GB 1699271 A GB1699271 A GB 1699271A GB 1699271 A GB1699271 A GB 1699271A GB 1306891 A GB1306891 A GB 1306891A
Authority
GB
United Kingdom
Prior art keywords
blades
radial forces
leading
flow
trailing edges
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
GB1699271A
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.)
BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
Original Assignee
BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
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 BBC Brown Boveri AG Switzerland, BBC Brown Boveri France SA filed Critical BBC Brown Boveri AG Switzerland
Publication of GB1306891A publication Critical patent/GB1306891A/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1306891 Axial-flow turbines and compressors BROWN BOVERI & Co Ltd 25 May 1971 [27 May 1970] 16992/71 Headings F1C FIT To reduce serpentine motion of a flow particle the blades of an axial-flow turbine or compressor are shaped so as to induce radial forces in the working fluid which at least partly compensate the radial forces resulting from the peripheral component of flow velocity. This is achieved by the stator blades 1 having leading and trailing edges 3, 4 conforming substantially, when viewed axially of the machine, to radii through axis O to thus exert no compensating radial forces on the working fluid, whereas the leading and trailing edges 11, 12 of each rotor blade 8 are substantially parallel causing the blades to induce compensating radial forces. Compensation can be increased if the leading and trailing edges of each rotor blade converge from root to tip as shown at 15, or if the edges of each stator blade converge more sharply from root to tip than the corresponding radii, as shown at 16. A further increase in compensation can be achieved if the rotor blades are wider than the stator blades in the circumferential direction.
GB1699271A 1970-05-27 1971-05-25 Method and blade arrangement to reduce the serpentine motion of a mass particle flowing through a turbomachine Expired GB1306891A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH784170A CH516747A (en) 1970-05-27 1970-05-27 Method and blading to reduce the snaking movement of a mass particle when flowing through a turbo machine

Publications (1)

Publication Number Publication Date
GB1306891A true GB1306891A (en) 1973-02-14

Family

ID=4331214

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1699271A Expired GB1306891A (en) 1970-05-27 1971-05-25 Method and blade arrangement to reduce the serpentine motion of a mass particle flowing through a turbomachine

Country Status (5)

Country Link
US (1) US3764225A (en)
CH (1) CH516747A (en)
DE (1) DE2043083C3 (en)
FR (1) FR2093626A5 (en)
GB (1) GB1306891A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160123236A1 (en) * 2013-10-17 2016-05-05 Mitsubishi Heavy Industries, Ltd. Compressor and gas turbine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5525555A (en) * 1978-08-12 1980-02-23 Hitachi Ltd Impeller
US4474534A (en) * 1982-05-17 1984-10-02 General Dynamics Corp. Axial flow fan
US5000660A (en) * 1989-08-11 1991-03-19 Airflow Research And Manufacturing Corporation Variable skew fan
CN107965352A (en) * 2017-12-26 2018-04-27 北京全四维动力科技有限公司 The bent blades of water erosion danger, leaf grating and industrial steam turbine using it can be reduced

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE311606C (en) *
US2320733A (en) * 1938-01-07 1943-06-01 Macard Screws Ltd Screw type fluid propelling apparatus
US2224519A (en) * 1938-03-05 1940-12-10 Macard Screws Ltd Screw type fluid propelling apparatus
US2298576A (en) * 1941-07-17 1942-10-13 Internat Engineering Inc Air handling apparatus
GB631231A (en) * 1947-12-10 1949-10-28 Aerex Ltd Improvements relating to cased screw fans
GB722001A (en) * 1951-03-09 1955-01-19 Power Jets Res & Dev Ltd Turbines
US3045969A (en) * 1958-09-26 1962-07-24 Escher Wyss Ag Vibration damping device for turbo-machine
CH478994A (en) * 1963-05-21 1969-09-30 Jerie Jan Blade arrangement on axial compressor, blower or fan

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160123236A1 (en) * 2013-10-17 2016-05-05 Mitsubishi Heavy Industries, Ltd. Compressor and gas turbine
US10774750B2 (en) * 2013-10-17 2020-09-15 Mitsubishi Heavy Industries, Ltd. Compressor with stator vane configuration in vicinity of bleed structure, and gas turbine engine

Also Published As

Publication number Publication date
DE2043083A1 (en) 1971-12-09
DE2043083C3 (en) 1979-07-26
US3764225A (en) 1973-10-09
DE2043083B2 (en) 1975-10-09
FR2093626A5 (en) 1972-01-28
CH516747A (en) 1971-12-15

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees