US3112915A - Rotor assembly air baffle - Google Patents

Rotor assembly air baffle Download PDF

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US3112915A
US3112915A US161519A US16151961A US3112915A US 3112915 A US3112915 A US 3112915A US 161519 A US161519 A US 161519A US 16151961 A US16151961 A US 16151961A US 3112915 A US3112915 A US 3112915A
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blades
rotor
baille
blade
rotor assembly
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US161519A
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Morris Drew
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General Electric Co
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General Electric Co
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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
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005Sealing means between non relatively rotating elements
    • F01D11/006Sealing the gap between rotor blades or blades and rotor
    • 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
    • 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
    • F01D5/30Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • This invention relates to a rotor assembly and a rotor assembly air baille for use with a turbomachine rotor wheel and blade assembly.
  • an air baille comprising end plates, one lltting on each side of the blade Shanks and facing in an axial direction, with a connecting member extending between adjacent Shanks to maintain the end plates in position.
  • These plates are of configuration such that one baille may extend past at least two of the blade Shanks and abut the adjacent baille plates so as to present a substantially continuous annular Wall facing the gas stream which limits gas leakage and substantially decreases the aerodynamic drag on the rotor assembly while still allowing ease of assembly of the bailles and blades.
  • the particular Wedging contact between adjacent blade platforms serves to damp vibration between adjacent blade assemblies and in this manner adds to the overall structural integrity of the rotor assembly.
  • FIG. l is a side view of the turbomachine rotor wheel assembly
  • FIG. 2 is an enlarged perspective view of the air baille
  • FIG. 3 is a side plan view of the air baille positioned in the phantom rotor assembly
  • FIG. 4 is a cross-sectional view of the air baille along the lines 4-4 of FIG. 3.
  • FIG. l therein is illustrated a turbomachine rotor assembly comprising a rotor wheel 11 with blades 12 attached thereto extending in a radial direction. These blades are attached in a Siamese twin fashion with two blades having bases extending into an opening 13 in the turbine wheel and forming a structure having corrugated sides corresponding to that opening so that the blades are retained from being thrown out in a radial direction.
  • a locking strip 14 extends through the rotor wheel beneath the blades and is bent radially outward so that the end tab 15 overlies a portion of the rotor Wheel and the blades to maintain the blades in position on the rotor wheel.
  • the blades consist of a shank portion 18 and a vane portion 19 with a platform 20 therebetween.
  • the blades iit together and are supported in the siamese twin manner illustrated to simplify the assembly on the rotor wheel and also to provide a self-damping effect to limit blade vibration during operation of the turbomachine. Vibration between the blades of a pair is damped by centrifugal force causing the blades to tend to move together due to the centers of support and centers of mass of the blades being oilset from a radial line so that a torque is applied on the blades of a pair to move the blades toward one another. This torque force causes the blades to move together and the platforms to contact thereby limiting vibration therebetween.
  • This blade mounting assembly is more fully disclosed in U.S. Patent 2,990,156, Marshall et al., Blade Damping Means. It may be seen that by individually assembling the blades around the rotor in this manner a complete rotor assembly may be built up.
  • an air baffle 27 is provided as illustrated in FIGS. 2 and 4 with the phantom outline of the rotor assembly illustrated in FIG. 3.
  • This air baille consists of end plates 29 and 30 with connecting members 31 and 32 extending therebetween.
  • the special configuration allows the end plates to overlap at least two adjacent blade shank portions and extend between the rotor wheel and blade platform to provide a sealing Wall and prevent the axial passage of gas therethrough.
  • the use of ilat end plates to form a substantially continuous wall to seal against gas passage substantially reduces the aerodynamic drag on the rotor structure when compared to structures having uneven surfaces facing the gas stream.
  • the end wall 29 is shaped so as to abut the adjacent identical baille and wall so that the walls cooperate to form an annular wall substantially sealing against axial gas flow past the blade shanks.
  • all of the end plates 30 cooperate to provide a downstream sealing wall.
  • the end Wall 29 has a cut out portion 33 to allow for the axial insertion of the final two blades on the rotor Wheel by allowing the baille to be assembled between the blades and the cornplete assembly of two blades of different pairs and the baille to be moved axially into position with the cut out portion 33 clearing the turbine wheel to allow for this insertion.
  • the connecting members 31 and 32 are iltted adjacent the platform and rotor wheels respectively to maintain the baille in the desired position illustrated.
  • the connecting member 31 is of a cross section to fit between the adjacent platforms 20 of blades of separate Siamese twin assemblies and be forced further in rubbing contact with these adjacent platforms by centrifugal force acting on the baille.
  • the wedging action of the connecting member 31 acting against and between the adjacent blade platforms 2i) provides a more rigid and unified blade and rotor assembly. This Wedging action is aided by the centrifugal force acting on the baille which tends to force the connecting member 31 between the adjacent blade platforms.
  • member 32 is of a general inverted V configuration to provide maximum support in two planes against forces acting normal to the baille end plates. @ne primary cause for such forces is the axial pressure caused by the primary gas flow acting on the end plate. Another cause for such a force is the interaction of the connecting member 31 and the blade platforms 20, as illustrated in FIG. 3, the platform 20 slants and is not normal to the blade axis, therefore centrifugal forces acting on the baille in forcing the connecting member against the blade platforms intersections results in an axially directed force on the baille toward the end plate 29.
  • the end plate 30 is also made thicker to further resist this axial directed force.
  • the air baille when the air baille is positioned as illustrated in the drawings, it eilectively seals against the axial passage of gas past the blade Shanks.
  • Another very important function served by the air baille is that while the Siamese twin blade assembly damps vibration between the blades of the assembly, the baille serves to damp vibration between adjacent assemblies by establishing a rubbing contact with blades of at least two assemblies and being forced into even greater contact by centrifugal forces acting on the baille. In this manner, the overall structural integrity of the rotor assembly is greatly enhanced in addition to sealing the rotor assembly against undesirable passage of gas therethrough.
  • a rotor assembly for turbomachinery comprising the combination of a rotor
  • each of said blades having a shank portion adjacent said rotor and a vane portion with a platform therebetween, bailles to prevent axial ilow of gas between the shank portions of the blades having end plates fitting on the upstream and downstream sides of adjacent shank portions covering the opening between said shank portions, the adjacent blade platforms and said rotor, the end plates of adjacent bailles abutting each other to form substantially continuous annular walls, said plate members joined and maintained in said position by a pair of connecting members extending between said blade Shanks, with one of said connecting members wedging between said adjacent blade platforms to damp vibrations therebetween and said other member being of a two planed configuration to provide maximum support between said plate members.

Description

Dec. 3, 1963 D. MoRRls 3,112,915
ROTOR ASSEMBLY AIR BAFFLE Filed Dec. 22, 1961 INVENTOR DEE/'V 1026/5 2r-5 4 MM United States Patent O 3,112,915 ROTOR ASSEMBLY AIR BAFFLE Drew Morris, Cincinnati, Ohio, assiguor to General Electric Company, a corporation of New York Filed Dec. 22, 1961, Ser. No. 161,519 1 Claim. (Cl. 253-77) This invention relates to a rotor assembly and a rotor assembly air baille for use with a turbomachine rotor wheel and blade assembly.
In various turbomachinery designs utilizing arfoils or blades mounted around the periphery of a rotor wheel, it is important that the primary gas ilow pass only through the annular passage in which the vane portion of the blades are located, since any primary ilow leakage outside this annular passage severely affects the eillciency of the engine with resulting loss in thrust or power output. One primary area of diillculty in which gas leakage is a problem is around the shank portions of the blades lying between the blade platforms and the turbine wheel.
In addition to gas leakage, another diiliculty encountered in rotor assemblies of the. type mentioned is vibration between the rotor and blades and between the individual blades mounted on the periphery of the rotor. Various methods have been employed to prevent or damp this vibration, however these have generally involved the use of a heavy or complicated structure and costly components.
Previous attempts to add individual air bailles to the rotor and blade assembly have frequently resulted in unsatisfactory sealing, or the bailles which have been utilized are subject to failure or have not accomplished such other functions which may be performed by such a baille. The baille should present little aerodynamic drag on the rotor and in addition, if designed correctly can serve the useful function of damping vibrations between adjacent blades.
It is therefore one object of this invention to provide an easily assembled improved type air baille and blade assembly for a turbomachine rotor assembly.
It is another object of this invention to provide an improved air baille which effectively seals against gas passage, presents a minimum aerodynamic drag on the rotor assembly and serves to damp vibrations between adjacent blade assemblies.
Briefly stated, in accordance with one aspect of the invention, there is provided an air baille comprising end plates, one lltting on each side of the blade Shanks and facing in an axial direction, with a connecting member extending between adjacent Shanks to maintain the end plates in position. These plates are of configuration such that one baille may extend past at least two of the blade Shanks and abut the adjacent baille plates so as to present a substantially continuous annular Wall facing the gas stream which limits gas leakage and substantially decreases the aerodynamic drag on the rotor assembly while still allowing ease of assembly of the bailles and blades. In addition, the particular Wedging contact between adjacent blade platforms serves to damp vibration between adjacent blade assemblies and in this manner adds to the overall structural integrity of the rotor assembly.
The invention will be better understood from the following description taken in connection with the accompanying drawings and its scope will be pointed out in the appended claim.
In the drawing:
FIG. l is a side view of the turbomachine rotor wheel assembly,
FIG. 2 is an enlarged perspective view of the air baille,
FIG. 3 is a side plan view of the air baille positioned in the phantom rotor assembly,
"ice
FIG. 4 is a cross-sectional view of the air baille along the lines 4-4 of FIG. 3.
eferring now to FIG. l, therein is illustrated a turbomachine rotor assembly comprising a rotor wheel 11 with blades 12 attached thereto extending in a radial direction. These blades are attached in a Siamese twin fashion with two blades having bases extending into an opening 13 in the turbine wheel and forming a structure having corrugated sides corresponding to that opening so that the blades are retained from being thrown out in a radial direction. A locking strip 14 extends through the rotor wheel beneath the blades and is bent radially outward so that the end tab 15 overlies a portion of the rotor Wheel and the blades to maintain the blades in position on the rotor wheel. The blades consist of a shank portion 18 and a vane portion 19 with a platform 20 therebetween.
The blades iit together and are supported in the siamese twin manner illustrated to simplify the assembly on the rotor wheel and also to provide a self-damping effect to limit blade vibration during operation of the turbomachine. Vibration between the blades of a pair is damped by centrifugal force causing the blades to tend to move together due to the centers of support and centers of mass of the blades being oilset from a radial line so that a torque is applied on the blades of a pair to move the blades toward one another. This torque force causes the blades to move together and the platforms to contact thereby limiting vibration therebetween. This blade mounting assembly is more fully disclosed in U.S. Patent 2,990,156, Marshall et al., Blade Damping Means. It may be seen that by individually assembling the blades around the rotor in this manner a complete rotor assembly may be built up.
Viewing this rotor assembly as a whole, the normal primary gas ow would be normal and into the drawing in passing between the blade vane portions 12, however, it can be seen that some of this ow could leak or pass through the openings 26 between adjacent blades if this opening were not closed. To accomplish this, an air baffle 27 is provided as illustrated in FIGS. 2 and 4 with the phantom outline of the rotor assembly illustrated in FIG. 3. This air baille consists of end plates 29 and 30 with connecting members 31 and 32 extending therebetween. The special configuration allows the end plates to overlap at least two adjacent blade shank portions and extend between the rotor wheel and blade platform to provide a sealing Wall and prevent the axial passage of gas therethrough. The use of ilat end plates to form a substantially continuous wall to seal against gas passage substantially reduces the aerodynamic drag on the rotor structure when compared to structures having uneven surfaces facing the gas stream.
Referring back to FIG. l, the end wall 29 is shaped so as to abut the adjacent identical baille and wall so that the walls cooperate to form an annular wall substantially sealing against axial gas flow past the blade shanks. In a similar fashion, all of the end plates 30 cooperate to provide a downstream sealing wall. Also, the end Wall 29 has a cut out portion 33 to allow for the axial insertion of the final two blades on the rotor Wheel by allowing the baille to be assembled between the blades and the cornplete assembly of two blades of different pairs and the baille to be moved axially into position with the cut out portion 33 clearing the turbine wheel to allow for this insertion. As illustrated in FIG. 3, the connecting members 31 and 32 are iltted adjacent the platform and rotor wheels respectively to maintain the baille in the desired position illustrated.
The connecting member 31 is of a cross section to fit between the adjacent platforms 20 of blades of separate Siamese twin assemblies and be forced further in rubbing contact with these adjacent platforms by centrifugal force acting on the baille. The wedging action of the connecting member 31 acting against and between the adjacent blade platforms 2i) provides a more rigid and unified blade and rotor assembly. This Wedging action is aided by the centrifugal force acting on the baille which tends to force the connecting member 31 between the adjacent blade platforms.
Further, member 32 is of a general inverted V configuration to provide maximum support in two planes against forces acting normal to the baille end plates. @ne primary cause for such forces is the axial pressure caused by the primary gas flow acting on the end plate. Another cause for such a force is the interaction of the connecting member 31 and the blade platforms 20, as illustrated in FIG. 3, the platform 20 slants and is not normal to the blade axis, therefore centrifugal forces acting on the baille in forcing the connecting member against the blade platforms intersections results in an axially directed force on the baille toward the end plate 29. The end plate 30 is also made thicker to further resist this axial directed force.
It may be seen that when the air baille is positioned as illustrated in the drawings, it eilectively seals against the axial passage of gas past the blade Shanks. Another very important function served by the air baille is that while the Siamese twin blade assembly damps vibration between the blades of the assembly, the baille serves to damp vibration between adjacent assemblies by establishing a rubbing contact with blades of at least two assemblies and being forced into even greater contact by centrifugal forces acting on the baille. In this manner, the overall structural integrity of the rotor assembly is greatly enhanced in addition to sealing the rotor assembly against undesirable passage of gas therethrough.
While a particular embodiment has been illustrated and described, it will be obvious to those skilled in the art that various changes and modications may be made without departing from the spirit of the invention, and it is intended to cover in the appended claim all such changes and modiilcations that come within the true scope of the invention.
I claim: A rotor assembly for turbomachinery comprising the combination of a rotor,
a plurality of blades mounted around the periphery of said rotor, each of said blades having a shank portion adjacent said rotor and a vane portion with a platform therebetween, bailles to prevent axial ilow of gas between the shank portions of the blades having end plates fitting on the upstream and downstream sides of adjacent shank portions covering the opening between said shank portions, the adjacent blade platforms and said rotor, the end plates of adjacent bailles abutting each other to form substantially continuous annular walls, said plate members joined and maintained in said position by a pair of connecting members extending between said blade Shanks, with one of said connecting members wedging between said adjacent blade platforms to damp vibrations therebetween and said other member being of a two planed configuration to provide maximum support between said plate members.
References Cited in the ille of this patent UNITED STATES PATENTS 2,271,971 Doran Feb. 3, 1942 2,669,383 Purvis et al. Feb. 16, 1954 2,755,063 Wilkinson July 17, 1956 2,781,998 Barr Feb. 19, 1957 2,942,842 Hayes June 28, 1960 FOREIGN PATENTS 652,099 Great Britain Apr. 18, 1951 590,294 Canada Jan. 5, 1960
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Cited By (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1300734B (en) * 1963-12-16 1969-08-07 Rolls Royce Device for vibration damping on the blades of a gas turbine
US3610778A (en) * 1968-08-09 1971-10-05 Sulzer Ag Support for rotor blades in a rotor
US3709631A (en) * 1971-03-18 1973-01-09 Caterpillar Tractor Co Turbine blade seal arrangement
US3728041A (en) * 1971-10-04 1973-04-17 Gen Electric Fluidic seal for segmented nozzle diaphragm
US3751183A (en) * 1971-12-02 1973-08-07 Gen Electric Interblade baffle and damper
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
US3918842A (en) * 1973-06-26 1975-11-11 Rolls Royce 1971 Ltd Blade assembly for a fluid flow machine
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4343594A (en) * 1979-03-10 1982-08-10 Rolls-Royce Limited Bladed rotor for a gas turbine engine
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4516910A (en) * 1982-05-18 1985-05-14 S.N.E.C.M.A. Retractable damping device for blades of a turbojet
EP0169800A1 (en) * 1984-07-23 1986-01-29 United Technologies Corporation Turbine cover-seal assembly
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5313786A (en) * 1992-11-24 1994-05-24 United Technologies Corporation Gas turbine blade damper
US5338152A (en) * 1992-05-11 1994-08-16 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Arrangement for sealing structural members using a V-shaped insert, particularly in the case of turbo-engines
US5388962A (en) * 1993-10-15 1995-02-14 General Electric Company Turbine rotor disk post cooling system
EP0702131A1 (en) * 1994-09-19 1996-03-20 General Electric Company Stable blade vibration damper for gas turbine engine
EP0709549A1 (en) * 1994-10-26 1996-05-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Bladed rotor especially for a turbomachine
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US20100111700A1 (en) * 2008-10-31 2010-05-06 Hyun Dong Kim Turbine blade including a seal pocket
US20100158686A1 (en) * 2008-12-19 2010-06-24 Hyun Dong Kim Turbine blade assembly including a damper
DE102009011879A1 (en) * 2009-03-05 2010-09-16 Mtu Aero Engines Gmbh Integrally bladed rotor and method of making an integrally bladed rotor
US20110255958A1 (en) * 2010-04-16 2011-10-20 General Electric Company Seal member for hot gas path component
DE102011082493A1 (en) * 2011-09-12 2013-03-14 Rolls-Royce Deutschland Ltd & Co Kg Safety segment for vibration damping of turbine blades and rotor device
US20140119918A1 (en) * 2012-10-31 2014-05-01 Solar Turbines Incorporated Damper for a turbine rotor assembly
US20140119916A1 (en) * 2012-10-31 2014-05-01 Solar Turbines Incorporated Damper for a turbine rotor assembly
CN104334856A (en) * 2012-05-31 2015-02-04 索拉透平公司 Turbine damper
US9279332B2 (en) 2012-05-31 2016-03-08 Solar Turbines Incorporated Turbine damper
DE102015112144A1 (en) * 2015-07-24 2017-02-09 Rolls-Royce Deutschland Ltd & Co Kg Rotor device of an aircraft engine with a damping device between blades
US20180058236A1 (en) * 2016-08-23 2018-03-01 United Technologies Corporation Rim seal for gas turbine engine
US20180106153A1 (en) * 2014-03-27 2018-04-19 United Technologies Corporation Blades and blade dampers for gas turbine engines
RU2764565C1 (en) * 2021-03-05 2022-01-18 Акционерное общество "Силовые машины - ЗТЛ, ЛМЗ, Электросила, Энергомашэкспорт" (АО "Силовые машины") Damper seal of the gas turbine impeller

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US2781998A (en) * 1950-03-07 1957-02-19 Centrax Power Units Ltd Bladed rotors
CA590294A (en) * 1960-01-05 Rolls-Royce Limited Axial-flow compressors and turbines
US2942842A (en) * 1956-06-13 1960-06-28 Gen Motors Corp Turbine blade lock

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CA590294A (en) * 1960-01-05 Rolls-Royce Limited Axial-flow compressors and turbines
US2271971A (en) * 1941-02-03 1942-02-03 Gen Electric Turbine bucket wheel
GB652099A (en) * 1947-10-16 1951-04-18 Rolls Royce Improvements relating to axial flow turbines
US2781998A (en) * 1950-03-07 1957-02-19 Centrax Power Units Ltd Bladed rotors
US2755063A (en) * 1950-11-14 1956-07-17 Rolls Royce Rotor constructions for gas-turbine engines
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
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Cited By (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1300734B (en) * 1963-12-16 1969-08-07 Rolls Royce Device for vibration damping on the blades of a gas turbine
US3610778A (en) * 1968-08-09 1971-10-05 Sulzer Ag Support for rotor blades in a rotor
US3709631A (en) * 1971-03-18 1973-01-09 Caterpillar Tractor Co Turbine blade seal arrangement
US3728041A (en) * 1971-10-04 1973-04-17 Gen Electric Fluidic seal for segmented nozzle diaphragm
US3751183A (en) * 1971-12-02 1973-08-07 Gen Electric Interblade baffle and damper
US3918842A (en) * 1973-06-26 1975-11-11 Rolls Royce 1971 Ltd Blade assembly for a fluid flow machine
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4343594A (en) * 1979-03-10 1982-08-10 Rolls-Royce Limited Bladed rotor for a gas turbine engine
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4516910A (en) * 1982-05-18 1985-05-14 S.N.E.C.M.A. Retractable damping device for blades of a turbojet
EP0169800A1 (en) * 1984-07-23 1986-01-29 United Technologies Corporation Turbine cover-seal assembly
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
WO1988005121A1 (en) * 1986-12-29 1988-07-14 United Technologies Corporation Interblade seal for turbomachine rotor
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5338152A (en) * 1992-05-11 1994-08-16 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Arrangement for sealing structural members using a V-shaped insert, particularly in the case of turbo-engines
US5313786A (en) * 1992-11-24 1994-05-24 United Technologies Corporation Gas turbine blade damper
WO1994012773A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade damper
US5388962A (en) * 1993-10-15 1995-02-14 General Electric Company Turbine rotor disk post cooling system
EP0702131A1 (en) * 1994-09-19 1996-03-20 General Electric Company Stable blade vibration damper for gas turbine engine
EP0709549A1 (en) * 1994-10-26 1996-05-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Bladed rotor especially for a turbomachine
FR2726323A1 (en) * 1994-10-26 1996-05-03 Snecma ASSEMBLY OF A ROTARY DISK AND AUBES, ESPECIALLY USED IN A TURBOMACHINE
US5599170A (en) * 1994-10-26 1997-02-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Seal for gas turbine rotor blades
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US8137072B2 (en) 2008-10-31 2012-03-20 Solar Turbines Inc. Turbine blade including a seal pocket
US20100111700A1 (en) * 2008-10-31 2010-05-06 Hyun Dong Kim Turbine blade including a seal pocket
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