GB1270156A - Improvements in transonic blades for axial flow turbines - Google Patents
Improvements in transonic blades for axial flow turbinesInfo
- Publication number
- GB1270156A GB1270156A GB60427/69A GB6042769A GB1270156A GB 1270156 A GB1270156 A GB 1270156A GB 60427/69 A GB60427/69 A GB 60427/69A GB 6042769 A GB6042769 A GB 6042769A GB 1270156 A GB1270156 A GB 1270156A
- Authority
- GB
- United Kingdom
- Prior art keywords
- thickness
- blades
- axial flow
- blade
- transonic
- 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
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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1,270,156. Turbine blades. GENERAL ELECTRIC CO. Dec. 11, 1969 [Jan. 24, 1969], No.60427/69. Heading F1T. An axial flow elastic-fluid turbine has the tips of the rotor blades designed for transonic flow of the working fluid therepast, each blade having a rounded nose portion 3 which increases and then decreases in thickness, a mid-portion 4 of gradually increasing thickness and a tail portion 5 of decreasing thickness, the portions defining two points of substantially equal maximum thickness at d and t. The portions 3, 5 of adjacent blades overlap to define a convergent-divergent flow passage, the surfaces 10, 12 of which are gently concave. The pressure and suction sides 6, 7 respectively of each blade are substantially flat over the midportion 4. The nose portion 3 is generally elliptical and satisfies the condition 1/d # 1À8.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US79383169A | 1969-01-24 | 1969-01-24 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1270156A true GB1270156A (en) | 1972-04-12 |
Family
ID=25160924
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB60427/69A Expired GB1270156A (en) | 1969-01-24 | 1969-12-11 | Improvements in transonic blades for axial flow turbines |
Country Status (7)
Country | Link |
---|---|
US (1) | US3565548A (en) |
JP (1) | JPS5612681B1 (en) |
CH (1) | CH515412A (en) |
DE (1) | DE2002348C3 (en) |
FR (1) | FR2029035A1 (en) |
GB (1) | GB1270156A (en) |
SE (1) | SE358438B (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9046111B2 (en) | 2010-02-24 | 2015-06-02 | Rolls-Royce Plc | Compressor aerofoil |
Families Citing this family (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3697193A (en) * | 1970-12-10 | 1972-10-10 | Adrian Phillips | Fluidfoil section |
DE2524250A1 (en) * | 1975-05-31 | 1976-12-02 | Maschf Augsburg Nuernberg Ag | LARGE CIRCLING SPEED FOR THERMAL, AXIAL-FLOW TURBO MACHINES |
US4240952A (en) * | 1979-01-15 | 1980-12-23 | Clarence E. Hulbert, Jr. | Method of making concrete from fly ash |
US4333088A (en) * | 1980-11-03 | 1982-06-01 | Exxon Research & Engineering Co. | Disposable peristaltic pump assembly for facsimile printer |
US4616975A (en) * | 1984-07-30 | 1986-10-14 | General Electric Company | Diaphragm for a steam turbine |
US4643645A (en) * | 1984-07-30 | 1987-02-17 | General Electric Company | Stage for a steam turbine |
US4900230A (en) * | 1989-04-27 | 1990-02-13 | Westinghouse Electric Corp. | Low pressure end blade for a low pressure steam turbine |
US5197854A (en) * | 1991-09-05 | 1993-03-30 | Industrial Design Laboratories, Inc. | Axial flow fan |
US5588804A (en) * | 1994-11-18 | 1996-12-31 | Itt Automotive Electrical Systems, Inc. | High-lift airfoil with bulbous leading edge |
FR2728618B1 (en) * | 1994-12-27 | 1997-03-14 | Europ Propulsion | SUPERSONIC DISTRIBUTOR OF TURBOMACHINE INPUT STAGE |
DE19614420C2 (en) * | 1996-04-12 | 2003-05-22 | Aloys Wobben | Rotor blade and wind turbine with a rotor blade |
US6068454A (en) * | 1998-04-06 | 2000-05-30 | Ford Motor Company | Fuel pump with helical impeller |
US6358012B1 (en) * | 2000-05-01 | 2002-03-19 | United Technologies Corporation | High efficiency turbomachinery blade |
US7179058B2 (en) * | 2004-03-21 | 2007-02-20 | Bharat Heavy Electricals Limited | Aerodynamically wide range applicable cylindrical blade profiles |
US7175393B2 (en) * | 2004-03-31 | 2007-02-13 | Bharat Heavy Electricals Limited | Transonic blade profiles |
US8393872B2 (en) * | 2009-10-23 | 2013-03-12 | General Electric Company | Turbine airfoil |
JP6110544B2 (en) * | 2011-06-29 | 2017-04-05 | 三菱日立パワーシステムズ株式会社 | Supersonic turbine blade and axial turbine |
JP6030853B2 (en) * | 2011-06-29 | 2016-11-24 | 三菱日立パワーシステムズ株式会社 | Turbine blade and axial turbine |
US9340277B2 (en) * | 2012-02-29 | 2016-05-17 | General Electric Company | Airfoils for use in rotary machines |
DE102014200644B4 (en) | 2014-01-16 | 2017-03-02 | MTU Aero Engines AG | Extruded profile and method for producing a blade of a Nachleitrads, blade of a Nachleitrads, Nachleitrad and turbomachinery with such a Nachleitrad |
JP6081398B2 (en) * | 2014-03-12 | 2017-02-15 | 株式会社東芝 | Turbine blade cascade, turbine stage and steam turbine |
US10358926B2 (en) | 2017-08-11 | 2019-07-23 | General Electric Company | Low-noise airfoil for an open rotor |
GB201719538D0 (en) | 2017-11-24 | 2018-01-10 | Rolls Royce Plc | Gas turbine engine |
GB201719539D0 (en) * | 2017-11-24 | 2018-01-10 | Rolls Royce Plc | Gas Turbine Engine |
US20240052746A1 (en) * | 2022-08-09 | 2024-02-15 | Rtx Corporation | Fan blade or vane with improved bird impact capability |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE446861A (en) * | 1941-08-29 | |||
US2935246A (en) * | 1949-06-02 | 1960-05-03 | Onera (Off Nat Aerospatiale) | Shock wave compressors, especially for use in connection with continuous flow engines for aircraft |
US3333817A (en) * | 1965-04-01 | 1967-08-01 | Bbc Brown Boveri & Cie | Blading structure for axial flow turbo-machines |
FR1473721A (en) * | 1965-04-01 | 1967-03-17 | Brown | Movable fins for transonic flow |
CH427851A (en) * | 1965-04-01 | 1967-01-15 | Bbc Brown Boveri & Cie | Blade ring for transonic flow |
-
1969
- 1969-01-24 US US793831*A patent/US3565548A/en not_active Expired - Lifetime
- 1969-12-11 GB GB60427/69A patent/GB1270156A/en not_active Expired
- 1969-12-29 SE SE18019/69A patent/SE358438B/xx unknown
-
1970
- 1970-01-20 DE DE2002348A patent/DE2002348C3/en not_active Expired
- 1970-01-21 FR FR7002119A patent/FR2029035A1/fr active Pending
- 1970-01-23 CH CH97270A patent/CH515412A/en not_active IP Right Cessation
- 1970-01-23 JP JP575270A patent/JPS5612681B1/ja active Pending
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9046111B2 (en) | 2010-02-24 | 2015-06-02 | Rolls-Royce Plc | Compressor aerofoil |
Also Published As
Publication number | Publication date |
---|---|
DE2002348B2 (en) | 1979-06-13 |
US3565548A (en) | 1971-02-23 |
JPS5612681B1 (en) | 1981-03-24 |
DE2002348C3 (en) | 1984-09-06 |
CH515412A (en) | 1971-11-15 |
FR2029035A1 (en) | 1970-10-16 |
SE358438B (en) | 1973-07-30 |
DE2002348A1 (en) | 1970-07-30 |
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