US3813185A - Support structure for rotor blades of turbo-machines - Google Patents

Support structure for rotor blades of turbo-machines Download PDF

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Publication number
US3813185A
US3813185A US00267183A US26718372A US3813185A US 3813185 A US3813185 A US 3813185A US 00267183 A US00267183 A US 00267183A US 26718372 A US26718372 A US 26718372A US 3813185 A US3813185 A US 3813185A
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US
United States
Prior art keywords
drum
fibrous material
bars
structure according
projections
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
Application number
US00267183A
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English (en)
Inventor
M Bauger
J Olivier
Croix A La
L Bauger
J Bouiller
M Gobin
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication date
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Publication of US3813185A publication Critical patent/US3813185A/en
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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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • a support structure for rotor blades of a turbomachine comprises a substantially cylindrical or conical hollow drum of fibrous material and a plurality of blade-carrier bars of metal attached side by side on the outer surface of the blades.
  • the present invention relates to support structures for the rotor blades of turbo-machines and relates more particularly, but not exclusively, to the compressor rotors of turbo-jet engines.
  • ln rotors comprising a drum made of a conventional material, frequently a rabbet type attachment technique is resorted to to satisfy these requirements.
  • the drum is provided with a series of grooves, of dove-tail section for example,. .used toreceive the blade roots which latter are profiledin a corresponding manner.
  • the object of the present invention is'to resolve the aforestated difficulties in order to make it possible, under satisfactory technical and economic conditions, to use fibrous materials to produce a rotor blade support structure for use in turbo-machine's.
  • a support structure in accordance with the invention accordingly comprises, in combination, a hollow'drum of fibrous material, a plurality of blade-carrier bars of metal arranged side by side on the external surface of the drum of fibrous material and extending each in the axial direction thereof, and at least one ring of fibrous 2 material circumferentially arranged in hoop fashion around the metal bars to retain the bars on the drum.
  • each metal bar viewed in section in a plane containing the drum axis, exhibits a crenellated configuration comprising one or more projections alternating with one or more depressions which latter open in the radially outer direction of the drum and each extend in the circumferential direction thereof, the homologous depressions'formed in the successive bars being disposed in circumferential extension of one another in order to constitute one or more annular grooves in which said ring or rings can be received.
  • each metal bar is formed on its external face, with at least one profiled axial groove (for example of dovetail section) shallower than said depression or depressions and constituting, in at least one of the projections of said crenellated configuration, a location for a correspondingly profiled blade root.
  • profiled axial groove for example of dovetail section
  • the radial thickness of a ring of fibrous material measured from the bottom of the depression in which said ring is located, is at most equal to the radial height of the contiguous projection, measured between the base thereof and the bottom of the groove formed therein.
  • the length, measured in a direction parallel with the axis of the drum, of a projection is greater than that of the blade root fitted in the groove formed in said projection.
  • the rotor can thus be equipped with a plurality of spacers each of which has a root whose profile is identical with that of the blade roots, said spacer root having two axially spaced end portions which respectively penetrate into the grooves in two successive projections in one and the same bar and abut against the roots of the blades respectively fitted in said grooves, in such a fashion that said spacer, in the region of a ring of fibrous material, straddles the depression defined between said projections.
  • the aforesaid spacers will be provided, on their radially outerface, with labyrinth partitions designed to cooperate, in a sealing relationship, with a structure fixed to the stator of the turbomachine.
  • the projections in the aforesaid metal bars are partially recessed in order to lighten the bars.
  • the metal bars are attached to the drum of fibrous material, by gluing.
  • the design of a blade support structure in accordance with the invention does not require any machining of the drum of fibrous material.
  • the attachmentof the blades is effected without any particular difficulty and by a conventional method, the profiled blade roots being fitted in profiled grooves formed in the metal bars.
  • the strength of these latter vis-a-vis. the tear-out stresses produced. by the centrifugal force;'is ensured by the'provision of the rings of fibrous material which act as hoops.
  • the aforesaid bars do not produce more than a limited increase in the weight of the structure. It can be pointed out in this context that these bars are drastically lightened by the depressions, grooves and recesses formed in them. Their mechanical strength is nevertheless considerable bearing in mind the way in which they are hooped by the rings of fibrous material.
  • the assembly constituted by the drum, the bars and the rings is, ultimately, lighter than a metal drum of the same strength as used in the building of the rotor in a conventional turbo machine.
  • FIG. 1 is an axial half-section along the line ll of FIG. 2, through part of a turbo machine equipped with a support structure in accordance with the invention.
  • FIGS. 2 and 3 are partial transverse sectional views respectively on the lines ll-ll and lll-lll of FIG. 1, of said turbo machine.
  • FIGS. 1 to 3 the rotor blade support structure of a turbo machine such as a low-pressure compressor designed for fitting to a turbo-jet engine is indicated generally at l.
  • the structure comprises a hollow drum 2, with its axis XX, and a plurality of bars 3 extending in each case in the axial direction of said drum and attached side by side in a contiguous manner (see FIG. 2) to the external surface thereof.
  • the drum 2 is made of a fibrous material and can be produced by winding a fibre, for example a glass fibre or carbon fibre, onto a cylindrical or slightly conical mandrel which functions as a mould.
  • the operation is carried out in the conventional way by rotating the mandrel about its own axis and simultaneously causing the fibre to execute an alternating rectilinear motion parallel to the mandrel axis. In this fashion, a crossed helical winding is obtained which ensures that the drum is flexionally and torsionally rigid.
  • the fibres are covered, during the winding operation, with an appropriate binder such as synthetic resin material. After the binder has hardened, the mandrel is withdrawn from the thusformed drum.
  • the bars 3 are made of metal, advantageously titanium. Each of them has a smooth internal face by which it is attached, advantageously by gluing (for example by means of a resin-based adhesive), to the external surface of the drum, and an external face shaped in the manner shown.
  • each of the metal bars 3 viewed in section in a plane containing the axis of the drum, exhibits a crenellated configuration comprising projections 4a, 4b 4p alternating with depressions 5a, 5b 5p
  • each of said projections is partially recessed as indicated at 16.
  • Each of the depressions 5a, 5b 5p opens in the radially outer direction of the drum and extends in the circumferential direction thereof.
  • the homologous depressions such as those 5p formed in successive bars are disposed in circumferential extension of one another, in order to constitute annular grooves 6a, 6b 6p.
  • each metal bar 3 further presents on its external face at least one axial profiled groove such as those 7a, 7b, 7c shallower than the depressions 5a, 5b 5p.
  • the groove 70 will advantageously have a dove-tail section whilst the grooves 7b and 70 each form a half dove-tail section. Two half dove-tail sections belonging to two adjacent bars together form a complete dove-tail. This arrangement, however, is by no means mandatory and the connection between two adjacent bars could equally well be effected in a joint plane located between two grooves such as 70, 7b.
  • the grooves 7a, 7b, 7c each extend over the axial length of the projections 4a, 4b 4p between two axially consecutive depressions such as 5a, 5b.
  • reference numerals 8 and 9 have been used to indicate a rotor blade and its root, respectively, and reference numeral 15 to indicate a stator blade. These blades are advantageously made of titanium.
  • each of the annular grooves 60, 6b 6p there is located a ring 10a, 10b 10p of fibrous material wound circumferentially, ater the manner of a hoop, around the metal bars 3.
  • the radial thickness e of a ring such as that 10p, measured from the bottom of the groove 5p, will advantageously be less than or equal to the radial height h of the contiguous projections 4p measured between the base of said projection and the base of a groove such as that 7a formed therein.
  • each of the projections 40, 4b 4p is greater than that of the blade root 9 fitted in the groove (such as 70) formed in said projection.
  • This particular feature, associated with the earlier one, makes it possible to fit spacers 11 each of which has a root 12 with an identical profile with that of the roots 9 of the blade 8.
  • Each spacer root 12 has two axially spaced end portions which can be fitted in the grooves (for example the grooves 7a) of two successive projections (such as those 4a, 4b) in one and the same bar and abut against the roots 9 of the blades 8 respectively fitted in said grooves.
  • each spacer 11, in the region of a ring such as that 10b, of fibrous material straddles the depression comprised between said projections.
  • Each spacer at its radially outer face, exhibits labyrinth partitions 13 designed to co-operate in sealing fashion with a stator ring 14 which, at their internal radius, links together the stator blades 15.
  • the turbo machine is assembled in a conventional manner. If the stator is made up of a series of one-piece rings which already carry a ring of stator blades 15, then the assembly operation is carried out in sections. For example, one starts by fitting the rotor blades 8 of a stage, then the spacers l1 separating this stage from the next, then a ring of stator blades 15, then the rotor blades 8 of the next stage, and so on. In the case where the stator is split into two parts or half-shells, at an axial split plane, the rotor can be completely equipped with all its blades 8 before assembling in the stator.
  • a support structure for turbo-machine rotor blades comprising, in combination, a hollow drum of fibrous material, a plurality of blade-carrier bars of metal arranged side by side on the external surface of said drum of fibrous material and extending each in the axial direction thereof, and at least one ring of fibrous material circumferentially arranged in hoop fashion around said metal bars to retain said bars on said drum.
  • each metal bar is formed, on its external face, with at least one axially profiled groove shallower than said depres- 6 sion and constituting, in at least one of the projections of said crenellated configuration, a location designed to receive a blade root profiled in a corresponding manner.
  • a structure according to claim 4 in which the length of a projection, measured in a direction parallel with the drum axis, is greater than that of the blade root fitted in the groove formed in said projection; and in which said structure further comprises a plurality of spacers each with a root having a profile identical with said blade roots, said spacer root presenting two axially spaced end portions which respectively penetrate into the grooves in two successive projections in one and the same bar and abut against the roots of the blades respectively fitted in said grooves, in such a fashion that said spacer, in the region of said ring of fibrous material, straddles the depression defined between said projections.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00267183A 1971-06-29 1972-06-28 Support structure for rotor blades of turbo-machines Expired - Lifetime US3813185A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7123689A FR2143561B1 (de) 1971-06-29 1971-06-29

Publications (1)

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US3813185A true US3813185A (en) 1974-05-28

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US00267183A Expired - Lifetime US3813185A (en) 1971-06-29 1972-06-28 Support structure for rotor blades of turbo-machines

Country Status (4)

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US (1) US3813185A (de)
DE (1) DE2231175C3 (de)
FR (1) FR2143561B1 (de)
GB (1) GB1385968A (de)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3904316A (en) * 1974-08-16 1975-09-09 Gen Motors Corp Turbine rotor with slot loaded blades and composite bands
US3966523A (en) * 1975-08-11 1976-06-29 United Technologies Corporation Method of making filament reinforced composite rings from plural flat filamentary spiral layers
US4063847A (en) * 1974-08-23 1977-12-20 Rolls-Royce (1971) Limited Gas turbine engine casing
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
US4191510A (en) * 1977-04-28 1980-03-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Axial flow compressor rotor drum
US4220055A (en) * 1977-09-23 1980-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Device to balance a rotor
US4397609A (en) * 1980-10-03 1983-08-09 Richard Kochendorfer Bandage for radially stressing the segments of a compressor rotor for a turbine
US4460311A (en) * 1980-05-24 1984-07-17 MTU Motogren-Und Turbinen-Union Apparatus for minimizing and maintaining constant the blade tip clearance of axial-flow turbines in gas turbine engines
US4468148A (en) * 1981-10-28 1984-08-28 Rolls-Royce Limited Means for reducing stress or fretting in clamped assemblies
US4536129A (en) * 1984-06-15 1985-08-20 United Technologies Corporation Turbine blade with disk rim shield
US4659282A (en) * 1984-03-03 1987-04-21 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Apparatus for preventing the spreading of titanium fires in gas turbine engines
US4867644A (en) * 1987-05-15 1989-09-19 Allied-Signal Inc. Composite member, unitary rotor member including same, and method of making
US5927692A (en) * 1996-11-18 1999-07-27 Lewmar Marine Limited Winch with epicyclic final reduction gear drive
US5941688A (en) * 1996-11-07 1999-08-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Fibre-reinforced rotor stage for a turbomachine
US6213720B1 (en) 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
US20050129522A1 (en) * 2003-12-11 2005-06-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US20050254958A1 (en) * 2004-05-14 2005-11-17 Paul Stone Natural frequency tuning of gas turbine engine blades
US20050271505A1 (en) * 2004-06-08 2005-12-08 Alford Mary E Turbine engine shroud segment, hanger and assembly
US20100129227A1 (en) * 2008-11-24 2010-05-27 Jan Christopher Schilling Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
US7811062B1 (en) * 1997-06-03 2010-10-12 Rolls-Royce Plc Fiber reinforced metal rotor
US7918644B2 (en) 2006-04-03 2011-04-05 Rolls-Royce Deutschland Ltd & Co Kg Axial-flow compressor for a gas turbine engine
US20150044049A1 (en) * 2013-03-13 2015-02-12 Rolls-Royce North American Technologies, Inc. Dovetail retention system for blade tracks
US20160245086A1 (en) * 2015-02-23 2016-08-25 General Electric Company Hybrid metal and composite spool for rotating machinery
US20180100402A1 (en) * 2016-10-12 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Rotor blade assembly comprising a ring segment shaped or disc segment shaped blade carrier and a radially inner reinforcement structure
US20180100398A1 (en) * 2016-10-12 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Rotor blade assembly comprising a ring-shaped or disc-shaped blade carrier and a radially inner reinforcement structure
US10047763B2 (en) 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2404134A1 (fr) * 1977-09-23 1979-04-20 Snecma Rotor pour turbomachines
US4717610A (en) * 1987-02-02 1988-01-05 United Technologies Corporation Composite disk for supporting fan blades
DE3711764A1 (de) * 1987-04-07 1988-10-27 Mtu Muenchen Gmbh Axialleitgitter fuer verdichter
DE102008051933A1 (de) * 2008-10-09 2010-04-15 Mtu Aero Engines Gmbh Haltevorrichtung zum Halten wenigstens einer Rotorschaufel und Verfahren zum Montieren eines Schaufelkranzes
EP2287445A1 (de) * 2009-07-16 2011-02-23 Techspace Aero S.A. Rotortrommel eines Axialkompressors mit Verbundgewebe
RU172776U1 (ru) * 2016-10-31 2017-07-24 Публичное акционерное общество "Научно-производственное объединение "Сатурн" Статор турбины
BE1027150B1 (fr) 2019-03-29 2020-10-26 Safran Aero Boosters Sa Rotor hybride à coquille externe rapportée contre la paroi annulaire composite
BE1027343B1 (fr) 2019-06-07 2021-01-14 Safran Aero Boosters Sa Rotor hybride avec des pions de plateforme penetrant dans le tambour
BE1027359B1 (fr) 2019-06-11 2021-01-21 Safran Aero Boosters Sa Rotor hybride à coquille externe rapportée contre la paroi annulaire composite

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3515501A (en) * 1967-04-12 1970-06-02 Rolls Royce Rotor blade assembly
US3532438A (en) * 1966-11-29 1970-10-06 Rolls Royce Aerofoil-shaped blades,and blade assemblies,for use in a fluid flow machine
US3554667A (en) * 1969-08-25 1971-01-12 Gen Motors Corp Turbomachine rotor
US3554668A (en) * 1969-05-12 1971-01-12 Gen Motors Corp Turbomachine rotor
US3625634A (en) * 1969-12-10 1971-12-07 Gen Motors Corp Turbomachine rotor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3532438A (en) * 1966-11-29 1970-10-06 Rolls Royce Aerofoil-shaped blades,and blade assemblies,for use in a fluid flow machine
US3515501A (en) * 1967-04-12 1970-06-02 Rolls Royce Rotor blade assembly
US3554668A (en) * 1969-05-12 1971-01-12 Gen Motors Corp Turbomachine rotor
US3554667A (en) * 1969-08-25 1971-01-12 Gen Motors Corp Turbomachine rotor
US3625634A (en) * 1969-12-10 1971-12-07 Gen Motors Corp Turbomachine rotor

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3904316A (en) * 1974-08-16 1975-09-09 Gen Motors Corp Turbine rotor with slot loaded blades and composite bands
US4063847A (en) * 1974-08-23 1977-12-20 Rolls-Royce (1971) Limited Gas turbine engine casing
US3966523A (en) * 1975-08-11 1976-06-29 United Technologies Corporation Method of making filament reinforced composite rings from plural flat filamentary spiral layers
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
US4191510A (en) * 1977-04-28 1980-03-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Axial flow compressor rotor drum
US4220055A (en) * 1977-09-23 1980-09-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Device to balance a rotor
US4460311A (en) * 1980-05-24 1984-07-17 MTU Motogren-Und Turbinen-Union Apparatus for minimizing and maintaining constant the blade tip clearance of axial-flow turbines in gas turbine engines
US4397609A (en) * 1980-10-03 1983-08-09 Richard Kochendorfer Bandage for radially stressing the segments of a compressor rotor for a turbine
US4468148A (en) * 1981-10-28 1984-08-28 Rolls-Royce Limited Means for reducing stress or fretting in clamped assemblies
US4659282A (en) * 1984-03-03 1987-04-21 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Apparatus for preventing the spreading of titanium fires in gas turbine engines
US4536129A (en) * 1984-06-15 1985-08-20 United Technologies Corporation Turbine blade with disk rim shield
US4867644A (en) * 1987-05-15 1989-09-19 Allied-Signal Inc. Composite member, unitary rotor member including same, and method of making
US5941688A (en) * 1996-11-07 1999-08-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Fibre-reinforced rotor stage for a turbomachine
US5927692A (en) * 1996-11-18 1999-07-27 Lewmar Marine Limited Winch with epicyclic final reduction gear drive
US7811062B1 (en) * 1997-06-03 2010-10-12 Rolls-Royce Plc Fiber reinforced metal rotor
US6213720B1 (en) 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
US20050129522A1 (en) * 2003-12-11 2005-06-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US6929453B2 (en) 2003-12-11 2005-08-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
US20050254958A1 (en) * 2004-05-14 2005-11-17 Paul Stone Natural frequency tuning of gas turbine engine blades
US20050271505A1 (en) * 2004-06-08 2005-12-08 Alford Mary E Turbine engine shroud segment, hanger and assembly
US7052235B2 (en) * 2004-06-08 2006-05-30 General Electric Company Turbine engine shroud segment, hanger and assembly
US7918644B2 (en) 2006-04-03 2011-04-05 Rolls-Royce Deutschland Ltd & Co Kg Axial-flow compressor for a gas turbine engine
US20100129227A1 (en) * 2008-11-24 2010-05-27 Jan Christopher Schilling Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
US8011877B2 (en) * 2008-11-24 2011-09-06 General Electric Company Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
US9458726B2 (en) * 2013-03-13 2016-10-04 Rolls-Royce Corporation Dovetail retention system for blade tracks
US20150044049A1 (en) * 2013-03-13 2015-02-12 Rolls-Royce North American Technologies, Inc. Dovetail retention system for blade tracks
US20160245086A1 (en) * 2015-02-23 2016-08-25 General Electric Company Hybrid metal and composite spool for rotating machinery
CN105909553A (zh) * 2015-02-23 2016-08-31 通用电气公司 用于旋转机械的混合金属和复合物线轴
JP2016166603A (ja) * 2015-02-23 2016-09-15 ゼネラル・エレクトリック・カンパニイ 回転機械のための混成金属及び複合材スプール
US9777593B2 (en) * 2015-02-23 2017-10-03 General Electric Company Hybrid metal and composite spool for rotating machinery
CN105909553B (zh) * 2015-02-23 2019-07-09 通用电气公司 用于旋转机械的混合金属和复合物线轴
US10047763B2 (en) 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US20180100402A1 (en) * 2016-10-12 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Rotor blade assembly comprising a ring segment shaped or disc segment shaped blade carrier and a radially inner reinforcement structure
US20180100398A1 (en) * 2016-10-12 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Rotor blade assembly comprising a ring-shaped or disc-shaped blade carrier and a radially inner reinforcement structure
US10794199B2 (en) * 2016-10-12 2020-10-06 Rolls-Royce Deutschland Ltd & Co Kg Rotor blade assembly comprising a ring segment shaped or disc segment shaped blade carrier and a radially inner reinforcement structure
US10794188B2 (en) * 2016-10-12 2020-10-06 Rolls-Royce Deutschland Ltd & Co Kg Rotor blade assembly comprising a ring-shaped or disc-shaped blade carrier and a radially inner reinforcement structure

Also Published As

Publication number Publication date
DE2231175A1 (de) 1973-01-18
GB1385968A (en) 1975-03-05
DE2231175C3 (de) 1979-05-03
FR2143561A1 (de) 1973-02-09
FR2143561B1 (de) 1974-03-08
DE2231175B2 (de) 1978-09-14

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