US1516607A - Hollow turbine bucket and method of manufacturing same - Google Patents
Hollow turbine bucket and method of manufacturing same Download PDFInfo
- Publication number
- US1516607A US1516607A US654523A US65452323A US1516607A US 1516607 A US1516607 A US 1516607A US 654523 A US654523 A US 654523A US 65452323 A US65452323 A US 65452323A US 1516607 A US1516607 A US 1516607A
- Authority
- US
- United States
- Prior art keywords
- bucket
- base
- wall
- turbine bucket
- manufacturing same
- 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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
Definitions
- Fig. 1 is a. view of a partially completed tur ine bucket embodying my invention
- Fig. 2 is a vertical sectional view thereof
- Fig. 3 is a sectional lan view through the base of the bucket
- Fig. 5 is a view s owing a completed bucket mounted on a rotor.
- the front and back Walls of the bucket may be formed of two curved pieces of sheet metal suitably united along their edges, 6 being the front wall and 7 the back wall.
- walls 6 and 7 from Monel metal and they ma lie-united rspective along their edges in any suita 1e manner such as by sol ering, brazing, welding or the like.
- the back wall 7 extends throughout the length of the bucket while the front wall terminates at the top of the base.
- base is made up primarily of two main pieces, a front piece 8 and a back piece 9.
- the front piece 8 has a curved surface 10 which fits the inner surface of back wall 7 and the back piece 9 has a curved surface 11 which fits around the outer surface of wall 7.
- the lower end of wall 7 is thus held between'the two base pieces 8 and 9.
- the front base piece 8 has a which projects up between wal s 6 and 7 and thls projecting portion is preferably tapered in accordance with the falling off of the centrifugal stresses. This may be done by cutting a V-shaped notch in the projection as indicated at 13.
- the projection 12 forms a reinforcing member for giving strength to the inner end of the bucket.
- the base may be finished to any suitable contour for attachmg it to a rotor or bucket-carrying member.
- Fig. 5 I have shown it provided with slots 18 to form a dove-tail for engagement with a groove 19 in the rotor this being a well-known form of bucket fastening means.
- the rotor or bucket carrying member is indicated at 19.
- pins 14 are so located that when the bucket bases are finished, the pins are removed with the waste material.
- the holes 15 and pins 14 do not therefore serve in any way to weaken the structure.
- the 'plate' 16 serves to grip and hold the lower end of inner wall 6.
- the base member 9 preferabl extends up along the back of wall 7 as indicated at 20 to brace the back of the bucket.
- lhe bucket may be provided with a suitable tenon 21 for fastening in place a bucket cover 22, the tenon being fixed to the'bucket by welding or. in any other desired manner.
- a turbine bucket comprising curved front and back walls united along their longitudinal edges, the back wall projecting below the front wall at one end, and a plurality of base pieces between which the projecting end of the back wall is held.
- a turbine bucket comprising curved front and back walls united along their longitudinal edges, the back wall projecting below the front wall at one end, a front and back base piece between which the projecting end is clamped, and a reinforcing projection on'the front base piece which extends up between said front andback walls.
- a turbine bucket comprising curved front and back walls united along their longitudinal edges, the back wall projecting below the front wall at one end, a front and back base piece between which the projecting end is clamped, and a tapered reinforcing member which projects from the base piece up between said front and back walls.
- a turbine bucket comprising curved front and back walls united along their longitudinal edges, and base pieces between which the lower ends of said walls are held, said wallsv and base pieces being united by fused metal.
- a turbine bucket comprising curved 7 front and back walls united along their longitudinal edges, and a plurality of base pieces between which the lower end of the back wall is held, said wall and back piece being united by fused metal.
- a turbine bucket comprising curved JOHN JOHANSON.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Nov.'25, 1,516,607
J.JOHANSON HOLLOW TURBINE BUCKET AND METHOD OF MANUFACTURING SAME Filed July 30, 1925 Inventor: John Johanson,
- Hisw t' or eg- 20 with such buckets has been to provide a Patented Nov. 25, 1924. V
'NITED STATES r 1,516,607 PATENT OFFICE.
JOHN JOHANSON, OT SGHENEOTADY, NEW YORK, ASSIGN OR TO GENERAL ELECTRIC I COMPANY, A CORPORATION OF NEW YORK.
' nor-now rumamn BUcxE'r Arm marnon or MANUFACTURING sum.
Application filed Iuly 80, 1928. Serial No. 654,528.
To all whom it may concern:
Be it known that 1, JOHN JOHANSON, a citizen of the United States, residing at Schenectad in the county of Schenectady, State of Nie w York, have invented certain new and useful Improvements in Hollow Turbine Buckets and Methods of Manufacturing Same, of which the following is a specification.
It has heretofore been proposed to make turbine buckets hollow in order to reduce their weight and thereby decrease the centrifugal stresses but even with hollow buckets of light wei ht the centrifugalstresses become of consi erable value asthe buckets increase in length. The stresses" are-highest of course, at the roots of the buckets and gradually decrease toward the tips, the greatest stress being in the basesof the buckets. One of the problems in connection practical structure having su'fiicient strength at its base or inner end to withstand the centrifugal stresses met with in modern turbine practice and the object of my invention is to provide an improved hollow turbine bucket structure which will meet this condition and an improved method of manufacturing thesame.
For a consideration of what believe to be novel and my invention, attention is dirooted to the accompanying description and the claims appended thereto.
In the drawing, Fig. 1 is a. view of a partially completed tur ine bucket embodying my invention; Fig. 2 is a vertical sectional view thereof; Fig. 3 is a sectional lan view through the base of the bucket; ig. 41s an exploded view of the parts used in manufacturmglmy improved bucket, and Fig. 5 is a view s owing a completed bucket mounted on a rotor. Y
The front and back Walls of the bucket may be formed of two curved pieces of sheet metal suitably united along their edges, 6 being the front wall and 7 the back wall. I may with advantage form. walls 6 and 7 from Monel metal and they ma lie-united rspective along their edges in any suita 1e manner such as by sol ering, brazing, welding or the like. The back wall 7 extends throughout the length of the bucket while the front wall terminates at the top of the base. The
base is made up primarily of two main pieces, a front piece 8 and a back piece 9.
The front piece 8 has a curved surface 10 which fits the inner surface of back wall 7 and the back piece 9 has a curved surface 11 which fits around the outer surface of wall 7. The lower end of wall 7 is thus held between'the two base pieces 8 and 9. The front base piece 8 has a which projects up between wal s 6 and 7 and thls projecting portion is preferably tapered in accordance with the falling off of the centrifugal stresses. This may be done by cutting a V-shaped notch in the projection as indicated at 13. The projection 12 forms a reinforcing member for giving strength to the inner end of the bucket.
After the parts have been this assembled- I then unite themto form-a unitary struc ,parts and eflect a. union of them, forming" in substance a unitary structure.
' After the assembled parts have been thus united into a unitary structure, the base may be finished to any suitable contour for attachmg it to a rotor or bucket-carrying member. In Fig. 5 I have shown it provided with slots 18 to form a dove-tail for engagement with a groove 19 in the rotor this being a well-known form of bucket fastening means. In Fig. 5, the rotor or bucket carrying member is indicated at 19. Preferably, pins 14 are so located that when the bucket bases are finished, the pins are removed with the waste material. The holes 15 and pins 14 do not therefore serve in any way to weaken the structure. The 'plate' 16 serves to grip and hold the lower end of inner wall 6. The base member 9 preferabl extends up along the back of wall 7 as indicated at 20 to brace the back of the bucket.
lhe bucket may be provided with a suitable tenon 21 for fastening in place a bucket cover 22, the tenon being fixed to the'bucket by welding or. in any other desired manner.
By the above described arrangement 'I provide a structure wherein the bucket proper comprisin walls 6 and 7 is firmly anchored to the ase and also a structure wherein the base and the portion of the bucket next to the base are amply strong to withstand the centrifugal stresses met with. At the same time by following m method of construction the bucket may". e manufactured at a reasonable cost. The reinforcing projection 12 may be made as long as found desirable in any particular case and may be given a crosssection such as to provide the desired strength. By its use I provide in substance the equivalent of a tapered bucket. I 1
What I claim as new and desire to secure by Letters Patent of the United States, is
1. A turbine bucket comprising curved front and back walls united along their longitudinal edges, the back wall projecting below the front wall at one end, and a plurality of base pieces between which the projecting end of the back wall is held.
2. A turbine bucket comprising curved front and back walls united along their longitudinal edges, the back wall projecting below the front wall at one end, a front and back base piece between which the projecting end is clamped, and a reinforcing projection on'the front base piece which extends up between said front andback walls.
3. A turbine bucket comprising curved front and back walls united along their longitudinal edges, the back wall projecting below the front wall at one end, a front and back base piece between which the projecting end is clamped, and a tapered reinforcing member which projects from the base piece up between said front and back walls.
4. A turbine bucket comprising curved front and back walls united along their longitudinal edges, and base pieces between which the lower ends of said walls are held, said wallsv and base pieces being united by fused metal.
5. A turbine bucket comprising curved 7 front and back walls united along their longitudinal edges, and a plurality of base pieces between which the lower end of the back wall is held, said wall and back piece being united by fused metal.
6. A turbine bucket comprising curved JOHN JOHANSON.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US654523A US1516607A (en) | 1923-07-30 | 1923-07-30 | Hollow turbine bucket and method of manufacturing same |
FR584517D FR584517A (en) | 1923-07-30 | 1924-07-22 | Hollow turbine blade and its manufacturing process |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US654523A US1516607A (en) | 1923-07-30 | 1923-07-30 | Hollow turbine bucket and method of manufacturing same |
Publications (1)
Publication Number | Publication Date |
---|---|
US1516607A true US1516607A (en) | 1924-11-25 |
Family
ID=24625214
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US654523A Expired - Lifetime US1516607A (en) | 1923-07-30 | 1923-07-30 | Hollow turbine bucket and method of manufacturing same |
Country Status (2)
Country | Link |
---|---|
US (1) | US1516607A (en) |
FR (1) | FR584517A (en) |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2601969A (en) * | 1946-01-25 | 1952-07-01 | United Specialties Co | Turbine wheel |
US2656146A (en) * | 1948-04-08 | 1953-10-20 | Curtiss Wright Corp | Turbine blade construction |
US2767460A (en) * | 1950-02-08 | 1956-10-23 | Robbins Engineering Company | Turbine blade and method of making same |
US2786646A (en) * | 1949-08-10 | 1957-03-26 | Power Jets Res & Dev Ltd | Bladed rotors for axial flow turbines and similarly bladed fluid flow machines |
US2819870A (en) * | 1955-04-18 | 1958-01-14 | Oleh A Wayne | Sheet metal blade base |
US2853272A (en) * | 1952-09-12 | 1958-09-23 | Napier & Son Ltd | Hollow blades for turbo machines |
US2856152A (en) * | 1953-04-23 | 1958-10-14 | American Motors Corp | Turbine wheel assembly |
US2976014A (en) * | 1952-01-19 | 1961-03-21 | Bbc Brown Boveri & Cie | Blading for use in axial flow machines |
US3012308A (en) * | 1957-08-12 | 1961-12-12 | Joy Mfg Co | Method of making blade structures |
US3063674A (en) * | 1961-02-08 | 1962-11-13 | Jr Clarence E Middlebrooks | Rotor construction and method |
DE976242C (en) * | 1943-05-28 | 1963-05-22 | Versuchsanstalt Fuer Luftfahrt | Method for producing hollow blades from sheet metal, in particular for gas turbines |
US20100006352A1 (en) * | 2008-07-11 | 2010-01-14 | Fabio Agostini | Cannon-shaped wind turbines for electric vehicles |
US20110142639A1 (en) * | 2009-12-15 | 2011-06-16 | Campbell Christian X | Modular turbine airfoil and platform assembly with independent root teeth |
US20160230568A1 (en) * | 2015-02-05 | 2016-08-11 | Rolls-Royce Corporation | Ceramic matrix composite gas turbine engine blade |
US10738628B2 (en) * | 2018-05-25 | 2020-08-11 | General Electric Company | Joint for band features on turbine nozzle and fabrication |
-
1923
- 1923-07-30 US US654523A patent/US1516607A/en not_active Expired - Lifetime
-
1924
- 1924-07-22 FR FR584517D patent/FR584517A/en not_active Expired
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE976242C (en) * | 1943-05-28 | 1963-05-22 | Versuchsanstalt Fuer Luftfahrt | Method for producing hollow blades from sheet metal, in particular for gas turbines |
US2601969A (en) * | 1946-01-25 | 1952-07-01 | United Specialties Co | Turbine wheel |
US2656146A (en) * | 1948-04-08 | 1953-10-20 | Curtiss Wright Corp | Turbine blade construction |
US2786646A (en) * | 1949-08-10 | 1957-03-26 | Power Jets Res & Dev Ltd | Bladed rotors for axial flow turbines and similarly bladed fluid flow machines |
US2767460A (en) * | 1950-02-08 | 1956-10-23 | Robbins Engineering Company | Turbine blade and method of making same |
US2976014A (en) * | 1952-01-19 | 1961-03-21 | Bbc Brown Boveri & Cie | Blading for use in axial flow machines |
US2853272A (en) * | 1952-09-12 | 1958-09-23 | Napier & Son Ltd | Hollow blades for turbo machines |
US2856152A (en) * | 1953-04-23 | 1958-10-14 | American Motors Corp | Turbine wheel assembly |
US2819870A (en) * | 1955-04-18 | 1958-01-14 | Oleh A Wayne | Sheet metal blade base |
US3012308A (en) * | 1957-08-12 | 1961-12-12 | Joy Mfg Co | Method of making blade structures |
US3063674A (en) * | 1961-02-08 | 1962-11-13 | Jr Clarence E Middlebrooks | Rotor construction and method |
US20100006352A1 (en) * | 2008-07-11 | 2010-01-14 | Fabio Agostini | Cannon-shaped wind turbines for electric vehicles |
US20110142639A1 (en) * | 2009-12-15 | 2011-06-16 | Campbell Christian X | Modular turbine airfoil and platform assembly with independent root teeth |
US8496443B2 (en) * | 2009-12-15 | 2013-07-30 | Siemens Energy, Inc. | Modular turbine airfoil and platform assembly with independent root teeth |
US20160230568A1 (en) * | 2015-02-05 | 2016-08-11 | Rolls-Royce Corporation | Ceramic matrix composite gas turbine engine blade |
US10253639B2 (en) * | 2015-02-05 | 2019-04-09 | Rolls-Royce North American Technologies, Inc. | Ceramic matrix composite gas turbine engine blade |
US10738628B2 (en) * | 2018-05-25 | 2020-08-11 | General Electric Company | Joint for band features on turbine nozzle and fabrication |
Also Published As
Publication number | Publication date |
---|---|
FR584517A (en) | 1925-02-09 |
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