US1544318A - Turbine-blade lashing - Google Patents

Turbine-blade lashing Download PDF

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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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Prior art keywords
lashing
blade
turbine
partition
blading
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Expired - Lifetime
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US662323A
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Hodgkinson Francis
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CBS Corp
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Westinghouse Electric and Manufacturing Co
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Priority to US662323A priority Critical patent/US1544318A/en
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/22Blade-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.

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.
US662323A 1923-09-12 1923-09-12 Turbine-blade lashing Expired - Lifetime US1544318A (en)

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Cited By (70)

* Cited by examiner, † Cited by third party
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
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
US20080260518A1 (en) * 2005-02-25 2008-10-23 Roland Blumenthal Holweck Vacuum Pump
US20090071162A1 (en) * 2004-12-01 2009-03-19 Suciu Gabriel L Peripheral combustor for tip turbine engine
CN101403394A (en) * 2007-10-04 2009-04-08 通用电气公司 Disk rotor and method of manufacture
US20090142184A1 (en) * 2004-12-01 2009-06-04 Roberge Gary D Vectoring transition duct for turbine engine
US20090145136A1 (en) * 2004-12-01 2009-06-11 Norris James W Tip turbine engine with multiple fan and turbine stages
US20090148273A1 (en) * 2004-12-01 2009-06-11 Suciu Gabriel L Compressor inlet guide vane for tip turbine engine and corresponding control method
US20090155079A1 (en) * 2004-12-01 2009-06-18 Suciu Gabriel L Stacked annular components for turbine engines
US7578655B1 (en) * 2006-05-20 2009-08-25 Florida Turbine Technologies, Inc. Composite gas turbine fan blade
US20090232650A1 (en) * 2004-12-01 2009-09-17 Gabriel Suciu Tip turbine engine and corresponding operating method
US7631480B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
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US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
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US20110299989A1 (en) * 2009-02-17 2011-12-08 Christoph Hermann Richter Blade union of a turbo machine
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US20120020793A1 (en) * 2009-01-29 2012-01-26 Mccracken James Turbine blade system
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US20130052032A1 (en) * 2010-01-26 2013-02-28 Herakles Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel
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Cited By (95)

* Cited by examiner, † Cited by third party
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
EP0900920A3 (en) * 1997-09-08 2000-03-22 General Electric Company Sealing device between a blade platform and two stator shrouds
US6454535B1 (en) 2000-10-31 2002-09-24 General Electric Company Blisk
US8087885B2 (en) 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
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US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
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
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
US20090071162A1 (en) * 2004-12-01 2009-03-19 Suciu Gabriel L Peripheral combustor for tip turbine engine
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US20090142184A1 (en) * 2004-12-01 2009-06-04 Roberge Gary D Vectoring transition duct for turbine engine
US20090145136A1 (en) * 2004-12-01 2009-06-11 Norris James W Tip turbine engine with multiple fan and turbine stages
US20090148273A1 (en) * 2004-12-01 2009-06-11 Suciu Gabriel L Compressor inlet guide vane for tip turbine engine and corresponding control method
US20090155079A1 (en) * 2004-12-01 2009-06-18 Suciu Gabriel L Stacked annular components for turbine engines
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US20090232650A1 (en) * 2004-12-01 2009-09-17 Gabriel Suciu Tip turbine engine and corresponding operating method
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US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7887296B2 (en) 2004-12-01 2011-02-15 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7921636B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
US7927075B2 (en) 2004-12-01 2011-04-19 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US20110142601A1 (en) * 2004-12-01 2011-06-16 Suciu Gabriel L Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US20110200424A1 (en) * 2004-12-01 2011-08-18 Gabriel Suciu Counter-rotating gearbox for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8061968B2 (en) 2004-12-01 2011-11-22 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
US8672630B2 (en) 2004-12-01 2014-03-18 United Technologies Corporation Annular turbine ring rotor
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8104257B2 (en) 2004-12-01 2012-01-31 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US8276362B2 (en) 2004-12-01 2012-10-02 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8468795B2 (en) 2004-12-01 2013-06-25 United Technologies Corporation Diffuser aspiration for a tip turbine engine
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US20080260518A1 (en) * 2005-02-25 2008-10-23 Roland Blumenthal Holweck Vacuum Pump
WO2007015916A2 (en) * 2005-07-27 2007-02-08 United Technologies Corporation Reinforcement rings for a diffuser section of a tip turbine engine fan rotor assembly
WO2007015916A3 (en) * 2005-07-27 2007-04-05 United Technologies Corp Reinforcement rings for a diffuser section of a tip turbine engine fan rotor assembly
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
US7618232B2 (en) * 2005-08-22 2009-11-17 Snecma Compressor comprising a plurality of cells reconstituting an annular volume of separation of flows in a turbine engine
US7578655B1 (en) * 2006-05-20 2009-08-25 Florida Turbine Technologies, Inc. Composite gas turbine fan blade
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
CN101403394A (en) * 2007-10-04 2009-04-08 通用电气公司 Disk rotor and method of manufacture
US20090092494A1 (en) * 2007-10-04 2009-04-09 General Electric Company Disk rotor and method of manufacture
US8894353B2 (en) * 2009-01-29 2014-11-25 Siemens Aktiengesellschaft Turbine blade system
US20120020793A1 (en) * 2009-01-29 2012-01-26 Mccracken James Turbine blade system
US20110299989A1 (en) * 2009-02-17 2011-12-08 Christoph Hermann Richter Blade union of a turbo machine
US9188014B2 (en) * 2010-01-26 2015-11-17 Snecma Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel
US20130052032A1 (en) * 2010-01-26 2013-02-28 Herakles Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel
US8985955B2 (en) 2010-07-28 2015-03-24 General Electric Company Turbine nozzle segment and method of repairing same
US11149552B2 (en) 2019-12-13 2021-10-19 General Electric Company Shroud for splitter and rotor airfoils of a fan for a gas turbine engine

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