US1347003A - Blade for fluid-pressure turbines - Google Patents
Blade for fluid-pressure turbines Download PDFInfo
- Publication number
- US1347003A US1347003A US283641A US28364119A US1347003A US 1347003 A US1347003 A US 1347003A US 283641 A US283641 A US 283641A US 28364119 A US28364119 A US 28364119A US 1347003 A US1347003 A US 1347003A
- Authority
- US
- United States
- Prior art keywords
- blade
- fluid
- blades
- pressure turbines
- metal
- 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 - Lifetime
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
Definitions
- This invention relates to stationary guide blades employed in the diaphragms of axial flow fluid pressure turbines of the impulse t pe.
- the stationary guide blades of such turbines when mounted in the diaphragms are subjected to considerable bending stresses due to the pressure of the motive fluid on the diaphragm.
- the latter are made of greater cross-section near their inlet edges than near their outlet edges.
- the blades are, according to this invention, made of a single thickness of sheet metal, sheet steel for example, the
- the free edge 8 of the bent portion 6 is pressed into close contact with the surface of the blade and is preferably chamfered or reduced in thickness so that the inner surface of the finished blade will present a sub stantially continuous curve. If desired the free edge 8 may be welded to the main portion of the blade as shown in Fig. 2.
- the bent-over portion 6 of the blade is either closed at the ends of the blades by welding, or the space within the bent-over portion is filled either completely or at the ends only of the blade with a strip or strips of metal 9.
- Figs. 1 and 5 show constructions in which the desired increase in the thickness of the blades 7 at their inlet edges is obtained by securing a strip of metal 11 thereto.
- the strip 11 is attached to the blade by welding at the parts 12, 13 and in Fig. 5 by meansvof rivets 14:.
- a turbine blade having its major portion formed of a single thickness of sheet metal and its inlet edge formed of two thicknesses of metal.
- a turbine blade having its major portion formed of a single thickness of sheet metal and being doubled at its inlet edge to form two thicknesses of metal.
- a turbine blade having its major portion formed of a single thickness of sheet metal and at its inlet edge being doubled over a metal filler to form a thickened inlet edge.
Description
'K. BAUMANN, H. L. GUY AND J. F. F. WINNING.
BLADE FORFLUID PRESSURE TURBINES.
APPLICATION FILED MAR.19,1919.
1,347,003. P ten edJuly 20,1920.
vi 9 fii 6 aiS 8 6 F192 3 Fig.3 9
- M 6 9 ii; 10 8 Q 8 INVENTOR 3, 4M0
UNITED STATES PATENT OFFICE KARL BAUMANN, OF URMSTON, AND HE NRY LEWIS GUY AND JOHN FREDERICK BRITISH WESTINGHOUSE ELECTRIC ITED, A CORPORATION OF GREAT BRI AND MANUFACTURING COMPANY, LIM- TAIN.
BLADE FOR FLUID-PRESSURE TURBINES.
Application filed March 19 To all whom it may concern:
Be it known that we, KARL BAUMANN, a citizen of the Confederation of Switzerland, and a resident of Urmston, in the county of Lancaster, England; HENRY LEWIS GUY, a subject of the King of Great Britain, and a resident of Victoria Park, Manchester, in the county of Lancaster, England, and JOHN F REDERICK FRANKLAND WINNING, a subject of the King of Great Britain, and a resident of Stretford, Manchester, in the county of Lancaster, England, have invented a new and useful Improvement in Blades for Fluid-Pressure Turbines, of which the following is a specification.
This invention relates to stationary guide blades employed in the diaphragms of axial flow fluid pressure turbines of the impulse t pe.
The stationary guide blades of such turbines when mounted in the diaphragms are subjected to considerable bending stresses due to the pressure of the motive fluid on the diaphragm. In order to obtain suflicient strength to resist such bending stresses without unduly obstructing the flow of motive fluid between the blades the latter are made of greater cross-section near their inlet edges than near their outlet edges.
In order to reduce the cost of blades of this character the blades are, according to this invention, made of a single thickness of sheet metal, sheet steel for example, the
increase in thickness at their inlet edges necessary to enable them to withstand the bending stresses being secured by turning or bending over the sheet metal at these edges, or alternatively by welding or otherwise securing a strip of metal to said edges.
Various forms of blades constructed in accordance with the invention are illustrated in the several figures of the accompanying drawing, in which Figures 1 to 5, inclusive, are cross-sections.
In carrying out the invention in the manner illustrated in Figs. 1 to 3 the bent-over portion 6 at the inlet edge of the blade 7 is Specification of Letters Patent.
Patented. July 20, 1920. 1919. Serial No. 283,641.
preferably not pressed fiat against the rest of the blade as this may tend to damage the metal but is so turned over as to leave a space between the adjacent surfaces, onabling an easier bend to be employed. The free edge 8 of the bent portion 6 is pressed into close contact with the surface of the blade and is preferably chamfered or reduced in thickness so that the inner surface of the finished blade will present a sub stantially continuous curve. If desired the free edge 8 may be welded to the main portion of the blade as shown in Fig. 2. The bent-over portion 6 of the blade is either closed at the ends of the blades by welding, or the space within the bent-over portion is filled either completely or at the ends only of the blade with a strip or strips of metal 9. This is desirable as otherwise when the blades are secured to the diaphragm by casting, the hollow spaces left within the turnedover portions of the blade might be partly filled with cast metal, particles of which might become detached and cause serious damage to the turbine. It has also been found that blow holes are liable to be formed near the embedded ends of the blades when the diaphragm is cast around them unless the ends ofthe blades are either closed by welding or filled up as described. In the construction illustrated in Fig. 3 the free edge 8 of the bent-over portion of the blade as well as the filling piece 9 is held in position by means of rivets 10.
Figs. 1 and 5 show constructions in which the desired increase in the thickness of the blades 7 at their inlet edges is obtained by securing a strip of metal 11 thereto. As shown in Fig. 4: the strip 11 is attached to the blade by welding at the parts 12, 13 and in Fig. 5 by meansvof rivets 14:.
IVe claim as our invention 1. A turbine blade having its major portion formed of a single thickness of sheet metal and its inlet edge formed of two thicknesses of metal.
2. A turbine blade having its major portion formed of a single thickness of sheet metal and being doubled at its inlet edge to form two thicknesses of metal.
3. A turbine blade having its major portion formed of a single thickness of sheet metal and at its inlet edge being doubled over a metal filler to form a thickened inlet edge.
In testimony whereof We have hereunto subscribed our names this third day of Janu- 10 my, 1919.
KARL BAUMANN.
HENRY LEWIS GUY.
In testimony whereof I' have hereunto subscribed my name this eleventh day of January, 1919. r V a I g H JOHN FREDERI'GK FRANKLAND WINNI'N
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US283641A US1347003A (en) | 1919-03-19 | 1919-03-19 | Blade for fluid-pressure turbines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US283641A US1347003A (en) | 1919-03-19 | 1919-03-19 | Blade for fluid-pressure turbines |
Publications (1)
Publication Number | Publication Date |
---|---|
US1347003A true US1347003A (en) | 1920-07-20 |
Family
ID=23086954
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US283641A Expired - Lifetime US1347003A (en) | 1919-03-19 | 1919-03-19 | Blade for fluid-pressure turbines |
Country Status (1)
Country | Link |
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US (1) | US1347003A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3406760A (en) * | 1967-09-18 | 1968-10-22 | Wallace Murray Corp | Flexible blade fan |
US3850545A (en) * | 1972-09-07 | 1974-11-26 | Hayes Albion Corp | Flex fan |
US4619580A (en) * | 1983-09-08 | 1986-10-28 | The Boeing Company | Variable camber vane and method therefor |
US20050186075A1 (en) * | 2004-02-24 | 2005-08-25 | Rolls-Royce Plc | Gas turbine nozzle guide vane |
US20110081238A1 (en) * | 2009-10-01 | 2011-04-07 | Eric Durocher | Gas turbine engine sheet metal vane |
US10760587B2 (en) | 2017-06-06 | 2020-09-01 | Elliott Company | Extended sculpted twisted return channel vane arrangement |
-
1919
- 1919-03-19 US US283641A patent/US1347003A/en not_active Expired - Lifetime
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3406760A (en) * | 1967-09-18 | 1968-10-22 | Wallace Murray Corp | Flexible blade fan |
US3850545A (en) * | 1972-09-07 | 1974-11-26 | Hayes Albion Corp | Flex fan |
US4619580A (en) * | 1983-09-08 | 1986-10-28 | The Boeing Company | Variable camber vane and method therefor |
US20050186075A1 (en) * | 2004-02-24 | 2005-08-25 | Rolls-Royce Plc | Gas turbine nozzle guide vane |
US7438518B2 (en) * | 2004-02-24 | 2008-10-21 | Rolls-Royce Plc | Gas turbine nozzle guide vane |
US20110081238A1 (en) * | 2009-10-01 | 2011-04-07 | Eric Durocher | Gas turbine engine sheet metal vane |
US10760587B2 (en) | 2017-06-06 | 2020-09-01 | Elliott Company | Extended sculpted twisted return channel vane arrangement |
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