US1229490A - Turbine. - Google Patents
Turbine. Download PDFInfo
- Publication number
- US1229490A US1229490A US72112612A US1912721126A US1229490A US 1229490 A US1229490 A US 1229490A US 72112612 A US72112612 A US 72112612A US 1912721126 A US1912721126 A US 1912721126A US 1229490 A US1229490 A US 1229490A
- Authority
- US
- United States
- Prior art keywords
- blade
- root
- rotor
- slots
- filler
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
Definitions
- This invention relates particularly to the fastening of the blades or vanes in the rotor and has for its object to provide a simple, inexpensive and secure means for accomplishing this purpose.
- Figure 1 is a perspective view of the rotor made in accordance with our invention.
- Fig. 2 is a cross sectional View of the blade.
- Fig. 3 is a cross sectional view of the root of the blade.
- Fig. 4 is a cross sectional view of the pack ing filler.
- Fig. 5 is a view looking on the end of a blade positioned in the rotor.
- a denotes the body of the rotor the periphery of which is transversally slotted at regular intervals, as indicated at 6, holes being drilled as inclicated at c to form an enlargement at the bottom of each slot.
- 10 denotes the blade or vane. 11, the root of the blade; and 12, a filler one side of which is shaped to fit the root of the blade, the other side being flat to fit against one wall of the slot in the rotor.
- the filler is placed against the root of the blade and then both are inserted in a slot in the rotor and driven down until the overhanging portion of the blade is set firmly against the edge of the rotor.
- the length of the root is slightly greater than the depth of the slotwith the result that when the blade is driven down into position the lower end of the root is bent at an angle to its main portion, forming a secured lock.
- a blade fastening device the combination with a rotor having transverse slots in its periphery, of a blade having a root of irregular cross section adapted to fit into said slot, and a filler adapted in shape to fit in said slot at one side of the root.
- the vcombination with a rotor having transverse slots in its periphery, of a blade and means for fastening said blade to said rotor comprising a blade root and a filler having correspondingly shaped contacting faces and adapted to fit snugly in the slots.
- a rotor having its periphery transversely slotted, blades overlying said slots and seated against the face of the rotor, each blade provided with a root fitting said slot, and means for bending the end of said root when the blade is driven into position, to lock the blade in place.
- a rotor having transverse peripheral slots the walls of which are inclined at the bottom, blades overlying said slots and seated against the face of the rotor, each blade being provided with a root adapted to fit within the slots and be deflected by the said incline when the blade is seated, and v blades overlying said slots and seated blade is properly seated, to lock the blade in against the face of therotoi', a'root formed position.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
W. J. A. LONDON & B, C. ALLEN.
TURBINE.
APPLICATION HLED SEPT. 19, I912.
1 229 490 v Patented June 12, 1917.-
WITNESSES M I WNVENTOR JA. London: 49 MM BY 7-2261 Azzmwax A ATTORNEY aria v,rric.
WILLIAM J. A. LONDON AND ROBERT C. ALLEN, 0F HARTFORD, CONNECTICUT, ASSIGN- ORS TO THE TERRY STEAM TURBINE COMPANY, OF HARTFORD, CONNECTICUT, A
CORPORATION OF CONNECTICUT.
Application filed September 19, 1912.
Z 0 all whom it may concern:
Be it known that we, W. J. A. LONDON, a subject of the King of England, and resident of Hartford and State of Connecticut, and whose post-oflice address is Hartford, Con necticut, and ROBERT C. ALLEN, a citizen of the United States, and resident of Hartford and State of Connecticut, and whose postofiice address is Hartford, Connecticut, have invented new and useful Improvements in Turbines, of which the following is a specification.
This invention relates particularly to the fastening of the blades or vanes in the rotor and has for its object to provide a simple, inexpensive and secure means for accomplishing this purpose.
Referring to the drawings:
Figure 1 is a perspective view of the rotor made in accordance with our invention.
Fig. 2 is a cross sectional View of the blade.
Fig. 3 is a cross sectional view of the root of the blade.
Fig. 4: is a cross sectional view of the pack ing filler.
Fig. 5 is a view looking on the end of a blade positioned in the rotor.
Referring to the drawings a denotes the body of the rotor the periphery of which is transversally slotted at regular intervals, as indicated at 6, holes being drilled as inclicated at c to form an enlargement at the bottom of each slot. 10 denotes the blade or vane. 11, the root of the blade; and 12, a filler one side of which is shaped to fit the root of the blade, the other side being flat to fit against one wall of the slot in the rotor. The filler is placed against the root of the blade and then both are inserted in a slot in the rotor and driven down until the overhanging portion of the blade is set firmly against the edge of the rotor. The length of the root is slightly greater than the depth of the slotwith the result that when the blade is driven down into position the lower end of the root is bent at an angle to its main portion, forming a secured lock. The outer Specification of Letters Patent.
TURBINE.
Iatented June 12, 1917.
Serial No. 721,126.
or upper ends of the several blades are fitted into a shroud in any usual or convenient manner. The construction here described is extremely simple and provides a very secure and rigid fastening for the blade.
IVe claim as our invention:
1. In a blade fastening device the combination with a rotor having transverse slots in its periphery, of a blade having a root of irregular cross section adapted to fit into said slot, and a filler adapted in shape to fit in said slot at one side of the root.
2. In a device of the character described, the combination with a rotorhaving transverse slots in its periphery, of a blade provided with a root of reduced size and of irregular cross section, a filler adapted in shape to fit the irregular side of said root and with the root to closely fill the slots in the rotor, said blade overlying said filler.
3. In a device of the character described, the vcombination with a rotor having transverse slots in its periphery, of a blade and means for fastening said blade to said rotor comprising a blade root and a filler having correspondingly shaped contacting faces and adapted to fit snugly in the slots.
4. In a turbine a rotor having its periphery transversely slotted, blades overlying said slots and seated against the face of the rotor, each blade provided with a root fitting said slot, and means for bending the end of said root when the blade is driven into position, to lock the blade in place.
5. In a turbine a rotor having transverse peripheral slots the walls of which are inclined at the bottom, blades overlying said slots and seated against the face of the rotor, each blade being provided with a root adapted to fit within the slots and be deflected by the said incline when the blade is seated, and v blades overlying said slots and seated blade is properly seated, to lock the blade in against the face of therotoi', a'root formed position.
integrally with the blade, a filler block fitting against said root, said filler block and i g root filling said slots and said root being rel atively longer than said filler block and Witnesses:
adapted to contact with and be deflected by I GEORGE R. TRIPP,
the inclined Wall of said slots when said 1 G. H. PLAINE.
Copies of this patent may be obtained for five cents each, by addressing the Commissioner of Patents;
Washington, D. G.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US72112612A US1229490A (en) | 1912-09-19 | 1912-09-19 | Turbine. |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US72112612A US1229490A (en) | 1912-09-19 | 1912-09-19 | Turbine. |
Publications (1)
Publication Number | Publication Date |
---|---|
US1229490A true US1229490A (en) | 1917-06-12 |
Family
ID=3297336
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US72112612A Expired - Lifetime US1229490A (en) | 1912-09-19 | 1912-09-19 | Turbine. |
Country Status (1)
Country | Link |
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US (1) | US1229490A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2657902A (en) * | 1947-12-17 | 1953-11-03 | Packard Motor Car Co | Turbine rotor for turbojet engines |
US4480957A (en) * | 1983-04-14 | 1984-11-06 | General Electric Company | Dynamic response modification and stress reduction in dovetail and blade assembly |
-
1912
- 1912-09-19 US US72112612A patent/US1229490A/en not_active Expired - Lifetime
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2657902A (en) * | 1947-12-17 | 1953-11-03 | Packard Motor Car Co | Turbine rotor for turbojet engines |
US4480957A (en) * | 1983-04-14 | 1984-11-06 | General Electric Company | Dynamic response modification and stress reduction in dovetail and blade assembly |
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