GB1306891A – Method and blade arrangement to reduce the serpentine motion of a mass particle flowing through a turbomachine
– Google Patents
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
1970-05-27
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.)
1970-05-27
Filing date
1971-05-25
Publication date
1973-02-14
1971-05-25
Application filed by BBC Brown Boveri AG Switzerland, BBC Brown Boveri France SA
filed
Critical
BBC Brown Boveri AG Switzerland
1973-02-14
Publication of GB1306891A
publication
Critical
patent/GB1306891A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
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
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
US3270953A
(en)
*
1963-05-21
1966-09-06
Jerie Jan
Axial flow compressor, blower or ventilator with reduced noise production
1970
1970-05-27
CH
CH784170A
patent/CH516747A/en
not_active
IP Right Cessation
1970-08-31
DE
DE2043083A
patent/DE2043083C3/en
not_active
Expired
1971
1971-04-30
US
US00139037A
patent/US3764225A/en
not_active
Expired – Lifetime
1971-05-24
FR
FR7118577A
patent/FR2093626A5/fr
not_active
Expired
1971-05-25
GB
GB1699271A
patent/GB1306891A/en
not_active
Expired
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
DE2043083B2
(en)
1975-10-09
CH516747A
(en)
1971-12-15
DE2043083A1
(en)
1971-12-09
US3764225A
(en)
1973-10-09
FR2093626A5
(en)
1972-01-28
DE2043083C3
(en)
1979-07-26
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Legal Events
Date
Code
Title
Description
1973-06-27
PS
Patent sealed [section 19, patents act 1949]
1977-12-21
PLNP
Patent lapsed through nonpayment of renewal fees
