GB1262182A - Improvements in or relating to turbine rotor blades - Google Patents
Improvements in or relating to turbine rotor bladesInfo
- Publication number
- GB1262182A GB1262182A GB2304869A GB2304869A GB1262182A GB 1262182 A GB1262182 A GB 1262182A GB 2304869 A GB2304869 A GB 2304869A GB 2304869 A GB2304869 A GB 2304869A GB 1262182 A GB1262182 A GB 1262182A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- peak
- bulge
- turbine rotor
- given
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C2003/142—Aerofoil profile with variable camber along the airfoil chord
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/301—Cross-sectional characteristics
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Hydraulic Turbines (AREA)
Abstract
1,262,182. Turbine blades. MOSKOVSKY ORDENA LENINA ENERGETICHESKY INSTITUT. May 6, 1969 [May 12, 1968], No.23048/69. Heading F1T. A steam or gas turbine rotor blade which is twisted and of varying cross-section from root to tip has a wave-shaped bulge 2 in the mainly concave pressure face, the peak m of the bulge being situated between the blade leading edge a and the mid-point of the concave face. At the blade cross section being considered, the distance I of the bulge peak m from the leading edge a is given by the formula: - where B is the chord length and # is the angle between the chord and the plane of rotor rotation. The blade thickness y at the peak m is given by: -
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU1239940A SU411214A1 (en) | 1968-05-12 | 1968-05-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1262182A true GB1262182A (en) | 1972-02-02 |
Family
ID=20442451
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2304869A Expired GB1262182A (en) | 1968-05-12 | 1969-05-06 | Improvements in or relating to turbine rotor blades |
Country Status (5)
Country | Link |
---|---|
CH (1) | CH489696A (en) |
DE (1) | DE1923535C3 (en) |
FR (1) | FR2014127A1 (en) |
GB (1) | GB1262182A (en) |
SU (1) | SU411214A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2151310A (en) * | 1983-12-12 | 1985-07-17 | Gen Electric | Gas turbine engine blade |
EP1225303A2 (en) * | 2001-01-12 | 2002-07-24 | Mitsubishi Heavy Industries, Ltd. | Blade structure in a gas turbine |
GB2373548A (en) * | 2001-03-21 | 2002-09-25 | Rolls Royce Plc | Gas trubine engine aerofoils |
EP1211382A3 (en) * | 2000-11-30 | 2004-01-02 | United Technologies Corporation | Turbomachine rotor with blades of different frequency |
EP1564374A1 (en) * | 2004-02-12 | 2005-08-17 | Siemens Aktiengesellschaft | Turbine blade for a turbomachine |
WO2005106207A1 (en) * | 2004-04-27 | 2005-11-10 | Siemens Aktiengesellschaft | Compressor blade and compressor |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL7909125A (en) * | 1979-12-19 | 1981-07-16 | Philips Nv | PLAY-FREE HOOK JOINT. |
US4641796A (en) * | 1983-09-30 | 1987-02-10 | The Boeing Company | Airfoil |
CA1262409A (en) * | 1985-05-01 | 1989-10-24 | Kenneth Odell Johnson | Counter rotation power turbine |
US5197854A (en) * | 1991-09-05 | 1993-03-30 | Industrial Design Laboratories, Inc. | Axial flow fan |
FR2907157A1 (en) * | 2006-10-13 | 2008-04-18 | Snecma Sa | MOBILE AUB OF TURBOMACHINE |
DE102009036406A1 (en) * | 2009-08-06 | 2011-02-10 | Mtu Aero Engines Gmbh | airfoil |
US8393872B2 (en) * | 2009-10-23 | 2013-03-12 | General Electric Company | Turbine airfoil |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR776676A (en) * | 1933-10-23 | 1935-01-31 | Helical turbine | |
BE639412A (en) * | 1962-11-30 |
-
1968
- 1968-05-12 SU SU1239940A patent/SU411214A1/ru active
-
1969
- 1969-05-06 GB GB2304869A patent/GB1262182A/en not_active Expired
- 1969-05-08 DE DE19691923535 patent/DE1923535C3/en not_active Expired
- 1969-05-08 FR FR6914820A patent/FR2014127A1/fr not_active Withdrawn
- 1969-05-29 CH CH817469A patent/CH489696A/en not_active IP Right Cessation
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2151310A (en) * | 1983-12-12 | 1985-07-17 | Gen Electric | Gas turbine engine blade |
EP1211382A3 (en) * | 2000-11-30 | 2004-01-02 | United Technologies Corporation | Turbomachine rotor with blades of different frequency |
EP1225303A2 (en) * | 2001-01-12 | 2002-07-24 | Mitsubishi Heavy Industries, Ltd. | Blade structure in a gas turbine |
EP1225303A3 (en) * | 2001-01-12 | 2004-07-28 | Mitsubishi Heavy Industries, Ltd. | Blade structure in a gas turbine |
US6887042B2 (en) | 2001-01-12 | 2005-05-03 | Mitsubishi Heavy Industries, Ltd. | Blade structure in a gas turbine |
US7229248B2 (en) | 2001-01-12 | 2007-06-12 | Mitsubishi Heavy Industries, Ltd. | Blade structure in a gas turbine |
GB2373548A (en) * | 2001-03-21 | 2002-09-25 | Rolls Royce Plc | Gas trubine engine aerofoils |
US6572332B2 (en) | 2001-03-21 | 2003-06-03 | Rolls-Royce Plc | Gas turbine engine aerofoils |
GB2373548B (en) * | 2001-03-21 | 2004-06-09 | Rolls Royce Plc | Gas turbine engine aerofoils |
EP1564374A1 (en) * | 2004-02-12 | 2005-08-17 | Siemens Aktiengesellschaft | Turbine blade for a turbomachine |
WO2005106207A1 (en) * | 2004-04-27 | 2005-11-10 | Siemens Aktiengesellschaft | Compressor blade and compressor |
Also Published As
Publication number | Publication date |
---|---|
CH489696A (en) | 1970-04-30 |
FR2014127A1 (en) | 1970-04-17 |
DE1923535B2 (en) | 1971-12-16 |
DE1923535A1 (en) | 1970-01-29 |
SU411214A1 (en) | 1974-01-15 |
DE1923535C3 (en) | 1973-07-19 |
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