US1544318A - Turbine-blade lashing - Google Patents
Turbine-blade lashing Download PDFInfo
- Publication number
- US1544318A US1544318A US662323A US66232323A US1544318A US 1544318 A US1544318 A US 1544318A US 662323 A US662323 A US 662323A US 66232323 A US66232323 A US 66232323A US 1544318 A US1544318 A US 1544318A
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- United States
- Prior art keywords
- lashing
- blade
- turbine
- partition
- blading
- 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
Definitions
- My invention relates toturbine blading of the type having intermediate partition or wall 'eleinentsand it has for an object to provide lashing for blading of this character which shall servethepurposes of strengthening the blade structure and of minimizing blade vibration.
- Another object of my invention isto provide lashing for the .1 character of blading' indicated which-is effective both to strengthen the blade structure and ,to form a packing means between the inner and outer tiers of adjacentrowsoi' moving and stationary blades.
- Fig. 1 is a detail view of multiple exhaust blades with my improved lashing means applied thereto;
- Fig. 2 is a sectional view taken along the line 11-11 of Fig. 1;
- Fig-. 3- is a sectional detail View showing a modified typeot lashing. forzbladingot this character;
- Fig; 4 is a sectional detail view alongthe line- IVIV of F ig.-11, showing my improved lashing c'onstruction applied .to the blading shroud elements;
- Fig. 5 is'a sectional View showing a'mo dified form ofmy improved lashingand
- Fig. 6- is a sectional view showing a further modified forinwherein the lashing forms a labyrinth packing to preventleakage between the inner and outertiersofblading.
- Outer portions 1-4 are separated by partition or wall elements l5-and' .16 carried, .respectively, at the front and atthe back of each blade.
- the blades are shown provided, at the tips,-,with shroud or wall elements-17 and 18 projecting, respectively, ;iorwa'rdly' and rearwardly of each blade.
- wall element'sl't'fand 18 are preferably made integral with the blades, and such elements areofsuch angextent that the partition or wall'element 15 engages with theelement l6oifathe adjacent bladeand the shroud or wall element 17 engages with the element 181015- the; adjacentbladeywhen the bladi'ng I is assembled, in order to form division ⁇ walls for the blading and shroudin-g therefor, as shown-in Fig.1.
- FIG. 2 I show a groove 20 at one side to receive a lashing strip 21, which is secured 1n the groove in the manner,re-,.
- FIG. 8 I show partition or wall elements'having grooves 20 at each side Y which is strong and in order tominimize vibration thereof.
- my-i-mproved lashing may be formed in any desired shape.
- Fig. 5 I show a strip 22 triangular. in cross-section fitting into a similar shaped recess in the partition or shroud element of the blade.
- FIG. 1 show a moving blade 11 Se-1 cured tothe rotor 10 and a stationary'bl'ade secured to the stator of the turbine.
- the moving blade 11 is shown'with a partition or wall'25 similar in construction to those shown in Fig. '1 dividing the .blade into inner and outer tiers 13 and 14.
- the moving blade 11 is shown'with a partition or wall'25 similar in construction to those shown in Fig. '1 dividing the .blade into inner and outer tiers 13 and 14.
- stationary bladeSO is divided by thepartiftion26into inner and outer tiers 23 and .24.
- each side of the partitions 254and 26 are grooves 27 and 28 in which my improved lashing is secured in themanner already outlined.
- 'The'lashing strip-applied to the moving blade ll-has a base 29,- fitting into the groove 27 of'the partition '25 and a flange portion 32 ext'ending beyond the partion- 25.
- The'lashing applied to the stationary blade is similarin construction, having a base 31 fitting into the groove 28 of the partition 26, and a. flange portion 33 extending beyond the partition-26.
- the lashing applied to the moving blade is inserted in an inverted relation with respect to that applied to the stationary-blade so that the flange portions 32 and 33 overlap each other 'with only sufiicient clearance between to prevent rubbing.
- I form by means of my improved lashinga labyrinth packing preventing leakage of steam between the inner and outer tiers of blading.
- a turbine bladelashing having a flange.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
June 30, 1925. 1,544,318
F. HODGKINSON TURBINE BLADE LASHING Filed Sept. 12, 1923 ffiada/rinsan WITNESSES: no I, ENTQR Patented June 30, '1925.
,jumr-Eo S TE? r'nano s nonexinsoiv, or" svfaa'rntionn, r'nn tsftnvnnih, Assienb'a, 'ro Whs'riiifd HOUSE ELECTRIC AND MANUFACTURING GGMPANY, A oonro-nai'r'ibn'ior rhiviv- TURBINE-BLADE tin-shine.
To all whom'z'tm'ay concern:
Be'it known that I, FRANCIS HonoKINsoN, a'subject of the King of Great Britain, and a resident of Swarthmore, in the county of Delaware and State-of Pennsylvania, have invented a new and useful Improvement in Turbine-Blade Lashing, of which the following is 'a specification;
My invention relates toturbine blading of the type having intermediate partition or wall 'eleinentsand it has for an object to provide lashing for blading of this character which shall servethepurposes of strengthening the blade structure and of minimizing blade vibration.
Another object of my invention isto provide lashing for the .1 character of blading' indicated which-is effective both to strengthen the blade structure and ,to form a packing means between the inner and outer tiers of adjacentrowsoi' moving and stationary blades. V
luyv improved lashingis particularly applicable to turbine blading ofthe multipleexhaust type, such asshown, described and claimed in thepatent to- Baumann, reissued April26, 1921, No. 15,092, andassigned to the Westinghouse Electric and Manufacturing'Company: I provide the partition or wall elements of b'lading .ofthis type with lateral grooves toreceive lashing members for-the purposes'aforesaid. H
As is well-known'in} the art, in applying blade lashing, a suitable number of blades in a row are grouped together and e lashed, leaving a joint between such grouping or segment and the adjacent group or-segment to allow for expansion due to the' different rate of heating of the rotor and the blading ofthe turbine..- In applying myT improved lashing I group a certain number of blades in themanner'aforesaid', the number depend ing on their length. I make the lashing strip, say, one and one-half times the length of a blade. Different groupings would be made, however, according to the blade design.
Apparatus made in accordance with my invention is illustrated in the accompanying drawings, forming a part of this application, in which Fig. 1 is a detail view of multiple exhaust blades with my improved lashing means applied thereto; Fig. 2 is a sectional view taken along the line 11-11 of Fig. 1; Fig-. 3- is a sectional detail View showing a modified typeot lashing. forzbladingot this character; Fig; 4: is a sectional detail view alongthe line- IVIV of F ig.-11, showing my improved lashing c'onstruction applied .to the blading shroud elements; Fig. 5 is'a sectional View showing a'mo dified form ofmy improved lashingand Fig. 6- is a sectional view showing a further modified forinwherein the lashing forms a labyrinth packing to preventleakage between the inner and outertiersofblading.
Referring now to theldrawingfora better 7 understanding of my'lnvention, i, show 111 J F ig. 1 a rotor 10 towhich'blades 11 of the multiple-exhaust type are secured by any suitable root co'n11ection,12. i v
In the drawing the blades 11 areshown provided with inner portions13 and .with
Outer portions 1-4:, separated by partition or wall elements l5-and' .16 carried, .respectively, at the front and atthe back of each blade. The blades are shown provided, at the tips,-,with shroud or wall elements-17 and 18 projecting, respectively, ;iorwa'rdly' and rearwardly of each blade. The partition or wall elements-15 and 16; and the shroud or. wall element'sl't'fand 18 are preferably made integral with the blades, andsuch elements areofsuch angextent that the partition or wall'element 15 engages with theelement l6oifathe adjacent bladeand the shroud or wall element 17 engages with the element 181015- the; adjacentbladeywhen the bladi'ng I is assembled, in order to form division {walls for the blading and shroudin-g therefor, as shown-in Fig.1. a
. Itmust be understood, however, that the location-of the partition or wall elements 15 and lG-Jand thejsl roud elements 17 and 18 as shown in. the-drawings, is for the purposes of illustration only. The enveloping which lashing strips are brazed, welded, or
soldered. In Fig. 2, I show a groove 20 at one side to receive a lashing strip 21, which is secured 1n the groove in the manner,re-,.
ferred to. In Fig. 8, I show partition or wall elements'having grooves 20 at each side Y which is strong and in order tominimize vibration thereof. V I
For ease-of insertion, my-i-mproved lashing may be formed in any desired shape. For instance, in Fig. 5 I show a strip 22 triangular. in cross-section fitting into a similar shaped recess in the partition or shroud element of the blade.
" In Fig 6 I show a moving blade 11 Se-1 cured tothe rotor 10 and a stationary'bl'ade secured to the stator of the turbine. The moving blade 11 is shown'with a partition or wall'25 similar in construction to those shown in Fig. '1 dividing the .blade into inner and outer tiers 13 and 14. The
stationary bladeSO is divided by thepartiftion26into inner and outer tiers 23 and .24.
In each side of the partitions 254and 26 are grooves 27 and 28 in which my improved lashing is secured in themanner already outlined. 'The'lashing strip-applied to the moving blade ll-has a base 29,- fitting into the groove 27 of'the partition '25 and a flange portion 32 ext'ending beyond the partion- 25. The'lashing applied to the stationary blade is similarin construction, having a base 31 fitting into the groove 28 of the partition 26, and a. flange portion 33 extending beyond the partition-26. The lashing applied to the moving blade is inserted in an inverted relation with respect to that applied to the stationary-blade so that the flange portions 32 and 33 overlap each other 'with only sufiicient clearance between to prevent rubbing. In the mannerindicated I form by means of my improved lashinga labyrinth packing preventing leakage of steam between the inner and outer tiers of blading. I
means between the tiers. 1
7 While I have shown my invention in several forms, it will be obvious to those skilled in the art that it is notso limited,but is susceptible, of various other changes and modifications without departing 'from' the spiritthereof, and I desire, therefore, that only such limitations shall be'placedthereupon as are imposed by the'priorartor as .wall-forming flange elements carried-by each row of bladesdividing. it; into inner and outer t1ers,.grooves; 1n" the lateral faces of the wall forming'flange .elements and lashing strips fittinginto the .grooves,gsaid lashing strips having overlapping fiange portions forming packing means between the tiers. V 1
'2. A turbine bladelashing having a flange.
portion cooperating with the-flange portion the lashing of an adjacent row of blades to form a labyrinth packing.
In a turbine having a pluralityof rows of tiered blading, partition members between the tiers,.packing means betweenzthepartitionmembersofadjacent rows, said packing means being. effectivejo lash segmentsof a row of blading. i
4. In a turbine, the combination of a row of moving tiered blading, a-row of. station- 'ary tiered blading, partition. members between the tiers, lashing strips secu'redin grooves along the lateral faces of partition members, saidlashing stripshaving cooperating flange portions to form packing 5; In combination, a turbinewith rows of moving and of stationary blades, partition members dividing. the moving .and the sta tionary blades into tiers, lashing strips with laterally-extending flange portions secured in grooves along the sides of the partition members, the laterally extending flange port tions of the lashing'strips .of 'one row of blades overlapping similarzfiange portions of adjacent lashing strips. l
In testimony whereof, I have hereunto subscribed my name thisl0th day of Sept,
1923. Y FRANCIS HODGKINSON.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US662323A US1544318A (en) | 1923-09-12 | 1923-09-12 | Turbine-blade lashing |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US662323A US1544318A (en) | 1923-09-12 | 1923-09-12 | Turbine-blade lashing |
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US1544318A true US1544318A (en) | 1925-06-30 |
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US662323A Expired - Lifetime US1544318A (en) | 1923-09-12 | 1923-09-12 | Turbine-blade lashing |
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Cited By (70)
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US2603453A (en) * | 1946-09-11 | 1952-07-15 | Curtiss Wright Corp | Cooling means for turbines |
US2660400A (en) * | 1948-11-25 | 1953-11-24 | Rolls Royce | Blade for turbines or compressors |
US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
US2914296A (en) * | 1953-06-18 | 1959-11-24 | Gen Electric | Overspeed control for fuel system turbopump |
US2956774A (en) * | 1954-09-28 | 1960-10-18 | Stalker Corp | Vibration dampers for bladed wheels |
US3045969A (en) * | 1958-09-26 | 1962-07-24 | Escher Wyss Ag | Vibration damping device for turbo-machine |
US3377050A (en) * | 1966-06-21 | 1968-04-09 | Bristol Siddeley Engines Ltd | Shrouded rotor blades |
US3515501A (en) * | 1967-04-12 | 1970-06-02 | Rolls Royce | Rotor blade assembly |
US3524712A (en) * | 1966-05-17 | 1970-08-18 | Rolls Royce | Compressor blade for a gas turbine engine |
US3610776A (en) * | 1970-03-02 | 1971-10-05 | Rolls Royce | Compressor blade for a gas turbine engine |
US4022544A (en) * | 1975-01-10 | 1977-05-10 | Anatoly Viktorovich Garkusha | Turbomachine rotor wheel |
CH666326A5 (en) * | 1984-09-19 | 1988-07-15 | Bbc Brown Boveri & Cie | Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates |
FR2612249A1 (en) * | 1987-03-12 | 1988-09-16 | Alsthom | MOBILE AUBAGE FOR STEAM TURBINES |
US4840536A (en) * | 1987-04-07 | 1989-06-20 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Axial guide blade assembly for a compressor stator |
US4919593A (en) * | 1988-08-30 | 1990-04-24 | Westinghouse Electric Corp. | Retrofitted rotor blades for steam turbines and method of making the same |
US5988980A (en) * | 1997-09-08 | 1999-11-23 | General Electric Company | Blade assembly with splitter shroud |
US6454535B1 (en) | 2000-10-31 | 2002-09-24 | General Electric Company | Blisk |
US20070022738A1 (en) * | 2005-07-27 | 2007-02-01 | United Technologies Corporation | Reinforcement rings for a tip turbine engine fan-turbine rotor assembly |
US20070039310A1 (en) * | 2005-08-22 | 2007-02-22 | Snecma | Compressor comprising a plurality of cells reconstituting an annular volume of separation of flows in a turbine engine |
US20070295011A1 (en) * | 2004-12-01 | 2007-12-27 | United Technologies Corporation | Regenerative Turbine Blade and Vane Cooling for a Tip Turbine Engine |
US20080014078A1 (en) * | 2004-12-01 | 2008-01-17 | Suciu Gabriel L | Ejector Cooling of Outer Case for Tip Turbine Engine |
US20080093174A1 (en) * | 2004-12-01 | 2008-04-24 | Suciu Gabriel L | Tip Turbine Engine with a Heat Exchanger |
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Cited By (95)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2603453A (en) * | 1946-09-11 | 1952-07-15 | Curtiss Wright Corp | Cooling means for turbines |
US2660400A (en) * | 1948-11-25 | 1953-11-24 | Rolls Royce | Blade for turbines or compressors |
US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
US2914296A (en) * | 1953-06-18 | 1959-11-24 | Gen Electric | Overspeed control for fuel system turbopump |
US2956774A (en) * | 1954-09-28 | 1960-10-18 | Stalker Corp | Vibration dampers for bladed wheels |
US3045969A (en) * | 1958-09-26 | 1962-07-24 | Escher Wyss Ag | Vibration damping device for turbo-machine |
US3524712A (en) * | 1966-05-17 | 1970-08-18 | Rolls Royce | Compressor blade for a gas turbine engine |
US3377050A (en) * | 1966-06-21 | 1968-04-09 | Bristol Siddeley Engines Ltd | Shrouded rotor blades |
US3515501A (en) * | 1967-04-12 | 1970-06-02 | Rolls Royce | Rotor blade assembly |
US3610776A (en) * | 1970-03-02 | 1971-10-05 | Rolls Royce | Compressor blade for a gas turbine engine |
US4022544A (en) * | 1975-01-10 | 1977-05-10 | Anatoly Viktorovich Garkusha | Turbomachine rotor wheel |
CH666326A5 (en) * | 1984-09-19 | 1988-07-15 | Bbc Brown Boveri & Cie | Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates |
FR2612249A1 (en) * | 1987-03-12 | 1988-09-16 | Alsthom | MOBILE AUBAGE FOR STEAM TURBINES |
EP0284829A1 (en) * | 1987-03-12 | 1988-10-05 | Gec Alsthom Sa | Rotor blading for steam turbines |
US4840539A (en) * | 1987-03-12 | 1989-06-20 | Alsthom | Moving blading for steam turbines |
US4840536A (en) * | 1987-04-07 | 1989-06-20 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Axial guide blade assembly for a compressor stator |
US4919593A (en) * | 1988-08-30 | 1990-04-24 | Westinghouse Electric Corp. | Retrofitted rotor blades for steam turbines and method of making the same |
US5988980A (en) * | 1997-09-08 | 1999-11-23 | General Electric Company | Blade assembly with splitter shroud |
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US6454535B1 (en) | 2000-10-31 | 2002-09-24 | General Electric Company | Blisk |
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US20080093174A1 (en) * | 2004-12-01 | 2008-04-24 | Suciu Gabriel L | Tip Turbine Engine with a Heat Exchanger |
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US20090142184A1 (en) * | 2004-12-01 | 2009-06-04 | Roberge Gary D | Vectoring transition duct for turbine engine |
US20090148273A1 (en) * | 2004-12-01 | 2009-06-11 | Suciu Gabriel L | Compressor inlet guide vane for tip turbine engine and corresponding control method |
US20090145136A1 (en) * | 2004-12-01 | 2009-06-11 | Norris James W | Tip turbine engine with multiple fan and turbine stages |
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