US3625634A - Turbomachine rotor - Google Patents

Turbomachine rotor Download PDF

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Publication number
US3625634A
US3625634A US883920A US3625634DA US3625634A US 3625634 A US3625634 A US 3625634A US 883920 A US883920 A US 883920A US 3625634D A US3625634D A US 3625634DA US 3625634 A US3625634 A US 3625634A
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United States
Prior art keywords
rotor
blades
mounting portion
ring
rings
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Expired - Lifetime
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US883920A
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Rowland L Stedfeld
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Motors Liquidation Co
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Motors Liquidation Co
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    • 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
    • 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

Definitions

  • a turbomachine rotor comprises a number of rings forming a drum with end bells at the ends of the drum. Each ring mounts a row of blades with roots which extend through openings in the ring and which are brazed or welded to retain them on the ring. Rings of fibrous composite wrap extend around the blade mounting rings between the rows of eqeflh r me be We e e bqrv v PATENTEU DEC H971 I 3525 534 INVIiN'IUR.
  • QW HTTORNEY TURBOMACHINE ROTOR My invention is directed to turbomachine rotors and particularly to provide a strong, lightweight rotor for turbomachines such as axial-flow compressors and turbines.
  • my invention is applied to a multistage axial-flow compressor having a lightweight composite fiber-reinforced drum rotor, but other adaptations of the invention are readily perceived.
  • the principal virtue of the invention lies in the felicitous use of very high tensile strength fibrous composite wrap to reinforce the metal rotor drum against the very high centrifugal forces exerted upon it, principally by the blades, but also by the structure of the drum itself.
  • Another feature of my invention is an arrangement by which the blade roots, which are extensions of the blade profile, are inserted through mating openings in the drum and are welded or brazed in place.
  • the principal objects of my invention are to improve the strength and reliability of turbomachine rotors and to provide an improved rotor structure having light weight and adapted to exploit the advantages of lightweight materials such as titanium and fibrous composite wraps.
  • FIG. 1 is a sectional view of a drum rotor taken in a plane containing the axis thereof.
  • FIG. 2 is an enlarged view of a portion of FIG. 1.
  • FIG. 3 is a view taken on the plane indicated by the line 3 3 in FIG. 2.
  • FIG. 4 is a fragmentary axonometric view of a rotor ring.
  • FIG. I shows a rotor for a four-stage axial-flow compressor.
  • the rotor comprises a drum 9 made up of four rings 10 and two end bells 11 and 13. As illustrated, the end bells are integral with stub shafts by which the drum may be mounted for rotation in suitable bearings, one stub shaft having a driving flange 14.
  • the parts 10, 11, and 13 as shown are held together by a tie bolt 15 and nut 17.
  • the end bells may have any suitable shape and the tie bolt may or may not be present, depending upon the particular design. In many cases, it is preferred to weld the rings 10 together, in which case the tie bolt is ordinarily omitted.
  • the rings l0 progressively increase in diameter, although they may not and, in general, they are as nearly alike as feasible, although they may differ in width and, ordinarily, in the number of blades mounted on the rings.
  • each ring 10 includes a blade mounting portion 18 and a flange portion 19.
  • the blade mounting portion includes a pilot 20 which extends into an annular recess 22 at the edge of the flange portion of the adjacent ring 10.
  • Adjacent rings thus are piloted together and centered and, in the form illustrated, they are welded together as indicated at 23 by a suitable process such as electron beam welding.
  • Each ring 10 bears on the interior of its blade mounting portion 18 a ring of bosses 24 each providing a mount for one of the ring of blades 26 mounted on the particular rotor ring.
  • the blades are of suitable airfoil shape, ordinarily a cambered airfoil with a concave and a convex face, as most clearly apparent in FIGS. 3 and 4.
  • Each blade includes a root portion 27, of the same overall airfoil contour as the blade 26, which is mounted in its respective one of the bosses 24.
  • each boss is machined to provide a blade mounting hole 28 extending through the boss.
  • the mounting holes are of the same airfoil configuration as the blade root 27 and closely fit the root.
  • the bosses 24 and holes 28 may be formed on the ring 10 by electrochemical machining or electric discharge machining, or by any other available process capable of producing the desired shape to a fair de ree of precision.
  • he blades 26 are fixed to the rotor by welding or brazing the root 27 in the holes 28.
  • the flange portion 19 defines a shallow annular trough 32 which receives a reinforcing wrap 34.
  • This wrap is a fibrous wrap of suitable high tensile strength fibers such as glass fibers, boron fibers, or other material, plus an epoxy resin which binds the fibers together.
  • the reinforcing rings thus provide a very substantial addition to the hoop strength of the ring 10. Since the flange portion 19 overlies the adjacent blade mounting portion 18, it accepts centrifugal stresses from both adjacent rows of blades.
  • my invention provides a lightweight rotor structure which is readily fabricated and which is particularly adapted to withstand the stresses of operation in high speed turbomachinery.
  • An axial-flow turbomachine rotor drum comprising, in combination, a plural number of open-centered metal rotor rings arranged coaxially in successive abutting relationship to define a rotor drum, each rotor ring including a blade mounting portion and a flange portion extending axially from the blade mounting portion, a ring of blades mounted on and fixed to each blade mounting portion, the blades having airfoil-contoured roots and the mounting portion defining airfoil-contoured holes receiving the blade roots, a fiber-reinforced tensile wrap disposed on the outer surface of each flange portion, the flange portion overlapping the exterior of the blade mounting portion of an adjacent rotor ring, the roots of the blades having spanwise-extending flutes thereon defining shallow recesses between the flutes, and braze metal within the recesses fixing the blades to the rotor rings.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A turbomachine rotor comprises a number of rings forming a drum with end bells at the ends of the drum. Each ring mounts a row of blades with roots which extend through openings in the ring and which are brazed or welded to retain them on the ring. Rings of fibrous composite wrap extend around the blade mounting rings between the rows of blades. The rings may be welded together.

Description

United States Patent [72] Inventor Rowland L. Stedfeld Indianapolis, Ind. 2: Appl. No. 883,920 [22] Filed Dec. 10, 1969 [45] Patented Dec. 7, 1971 [73] Assignee General Motors Corporation Detroit, Mich.
[541 TURBOMACHINE ROTOR 1 Claim, 4 Drawing Figs.
[52] 0.8. CI 416/198, 416/218, 416/230 [51] Int. Cl. F0111 5/06, FOld 5/06 [50] Field of Search 416/230, 201,244,245,198,200,196,218
[56] References Cited UNlT ED STATES PATENTS 2,803,397 8ll9 5 7 qardiner v 9 /Z7 M Primary Examiner Everette A. Powell, Jr. Attorneys-Paul Fitzpatrick and Jean L. Carpenter ABSTRACT: A turbomachine rotor comprises a number of rings forming a drum with end bells at the ends of the drum. Each ring mounts a row of blades with roots which extend through openings in the ring and which are brazed or welded to retain them on the ring. Rings of fibrous composite wrap extend around the blade mounting rings between the rows of eqeflh r me be We e e bqrv v PATENTEU DEC H971 I 3525 534 INVIiN'IUR.
241a! QW HTTORNEY TURBOMACHINE ROTOR My invention is directed to turbomachine rotors and particularly to provide a strong, lightweight rotor for turbomachines such as axial-flow compressors and turbines. In the preferred embodiment, my invention is applied to a multistage axial-flow compressor having a lightweight composite fiber-reinforced drum rotor, but other adaptations of the invention are readily perceived.
The principal virtue of the invention lies in the felicitous use of very high tensile strength fibrous composite wrap to reinforce the metal rotor drum against the very high centrifugal forces exerted upon it, principally by the blades, but also by the structure of the drum itself.
Another feature of my invention is an arrangement by which the blade roots, which are extensions of the blade profile, are inserted through mating openings in the drum and are welded or brazed in place.
The principal objects of my invention are to improve the strength and reliability of turbomachine rotors and to provide an improved rotor structure having light weight and adapted to exploit the advantages of lightweight materials such as titanium and fibrous composite wraps.
The nature of my invention and the advantages thereof will be clear to those skilled in the art from the succeeding detailed disclosure of the preferred embodiment of the invention, which is presented to explain the principles of the invention and is not to be construed in a limiting sense.
FIG. 1 is a sectional view of a drum rotor taken in a plane containing the axis thereof.
FIG. 2 is an enlarged view of a portion of FIG. 1.
FIG. 3 is a view taken on the plane indicated by the line 3 3 in FIG. 2.
FIG. 4 is a fragmentary axonometric view of a rotor ring.
FIG. I shows a rotor for a four-stage axial-flow compressor. The rotor comprises a drum 9 made up of four rings 10 and two end bells 11 and 13. As illustrated, the end bells are integral with stub shafts by which the drum may be mounted for rotation in suitable bearings, one stub shaft having a driving flange 14. The parts 10, 11, and 13 as shown are held together by a tie bolt 15 and nut 17. The end bells may have any suitable shape and the tie bolt may or may not be present, depending upon the particular design. In many cases, it is preferred to weld the rings 10 together, in which case the tie bolt is ordinarily omitted.
As shown, the rings l0 progressively increase in diameter, although they may not and, in general, they are as nearly alike as feasible, although they may differ in width and, ordinarily, in the number of blades mounted on the rings.
My invention lies primarily in the structure of the blade mounting rings and the mounting of the blades to the rings, which are shown more clearly in FIGS. 2, 3, and 4. Referring to these figures which illustrate a welded rotor structure, each ring 10 includes a blade mounting portion 18 and a flange portion 19. The blade mounting portion includes a pilot 20 which extends into an annular recess 22 at the edge of the flange portion of the adjacent ring 10. Adjacent rings thus are piloted together and centered and, in the form illustrated, they are welded together as indicated at 23 by a suitable process such as electron beam welding.
Each ring 10 bears on the interior of its blade mounting portion 18 a ring of bosses 24 each providing a mount for one of the ring of blades 26 mounted on the particular rotor ring. The blades are of suitable airfoil shape, ordinarily a cambered airfoil with a concave and a convex face, as most clearly apparent in FIGS. 3 and 4. Each blade includes a root portion 27, of the same overall airfoil contour as the blade 26, which is mounted in its respective one of the bosses 24. As shown most clearly in FIGS. 3 and 4, each boss is machined to provide a blade mounting hole 28 extending through the boss. The mounting holes are of the same airfoil configuration as the blade root 27 and closely fit the root. The bosses 24 and holes 28 may be formed on the ring 10 by electrochemical machining or electric discharge machining, or by any other available process capable of producing the desired shape to a fair de ree of precision.
he blades 26 are fixed to the rotor by welding or brazing the root 27 in the holes 28. To improve the braze joint in the case of a brazed airfoil, it is preferred to provide flutes 30 (FIG. 2) on the roots 27 between which are defined shallow recesses 31 to receive the braze metal.
The flange portion 19 defines a shallow annular trough 32 which receives a reinforcing wrap 34. This wrap is a fibrous wrap of suitable high tensile strength fibers such as glass fibers, boron fibers, or other material, plus an epoxy resin which binds the fibers together. The reinforcing rings thus provide a very substantial addition to the hoop strength of the ring 10. Since the flange portion 19 overlies the adjacent blade mounting portion 18, it accepts centrifugal stresses from both adjacent rows of blades.
It will be apparent to those skilled in the art from the foregoing description that my invention provides a lightweight rotor structure which is readily fabricated and which is particularly adapted to withstand the stresses of operation in high speed turbomachinery.
The detailed description of the preferred embodiment of the invention for the purpose of explaining the principles thereof is not to be considered as limiting or restricting the invention, as many modifications may be made by the exercise of skill in the art.
Iclaim:
1. An axial-flow turbomachine rotor drum comprising, in combination, a plural number of open-centered metal rotor rings arranged coaxially in successive abutting relationship to define a rotor drum, each rotor ring including a blade mounting portion and a flange portion extending axially from the blade mounting portion, a ring of blades mounted on and fixed to each blade mounting portion, the blades having airfoil-contoured roots and the mounting portion defining airfoil-contoured holes receiving the blade roots, a fiber-reinforced tensile wrap disposed on the outer surface of each flange portion, the flange portion overlapping the exterior of the blade mounting portion of an adjacent rotor ring, the roots of the blades having spanwise-extending flutes thereon defining shallow recesses between the flutes, and braze metal within the recesses fixing the blades to the rotor rings.

Claims (1)

1. An axial-flow turbomachine rotor drum comprising, in combination, a plural number of open-centered metal rotor rings arranged coaxially in successive abutting relationship to define a rotor drum, each rotor ring including a blade mounting portion and a flange portion extending axially from the blade mounting portion, a ring of blades mounted on and fixed to each blade mounting portion, the blades having airfoil-contoured roots and the mounting portion defining airfoil-contoured holes receiving the blade roots, a fiber-reinforced tensile wrap disposed on the outer surface of each flange portion, the flange portion overlapping the exterior of the blade mounting portion of an adjacent rotor ring, the roots of the blades having spanwiseextending flutes thereon defining shallow recesses between the flutes, and braze metal within the recesses fixing the blades to the rotor rings.
US883920A 1969-12-10 1969-12-10 Turbomachine rotor Expired - Lifetime US3625634A (en)

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Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3813185A (en) * 1971-06-29 1974-05-28 Snecma Support structure for rotor blades of turbo-machines
US3824037A (en) * 1971-10-12 1974-07-16 Messerschmitt Boelkow Blohm Suspension of rotor blades on the rotor head of a rotorcraft without the use of flapping or drag hinges
US3904316A (en) * 1974-08-16 1975-09-09 Gen Motors Corp Turbine rotor with slot loaded blades and composite bands
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
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
US4516908A (en) * 1981-04-17 1985-05-14 Nuovo Pignone S.P.A. Power stage of a gas turbine
US4536127A (en) * 1983-05-06 1985-08-20 Motoren-Und Turbinen-Union Turbocompressor provided with an abradable coating
US4566700A (en) * 1982-08-09 1986-01-28 United Technologies Corporation Abrasive/abradable gas path seal system
US4648802A (en) * 1984-09-06 1987-03-10 Pda Engineering Radial flow rotor with inserts and turbine utilizing the same
US4867644A (en) * 1987-05-15 1989-09-19 Allied-Signal Inc. Composite member, unitary rotor member including same, and method of making
US4919594A (en) * 1987-05-15 1990-04-24 Allied-Signal Inc. Composite member, unitary rotor member including same, and method of making
US5632600A (en) * 1995-12-22 1997-05-27 General Electric Company Reinforced rotor disk assembly
EP0846844A1 (en) * 1996-12-04 1998-06-10 Asea Brown Boveri AG Rotor assembly with rotor discs connected by both non-positive interlocking and interpenetrating or positive interlocking means
US6213720B1 (en) 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
WO2005056983A1 (en) * 2003-12-13 2005-06-23 Mtu Aero Engines Gmbh Fibre-reinforced rotor for a turbo generator
US20060125331A1 (en) * 2002-12-19 2006-06-15 Michael Frank Electric machine comprising a wrapped coil that is to be deep-frozen
DE102006015838A1 (en) * 2006-04-03 2007-10-04 Rolls-Royce Deutschland Ltd & Co Kg Axial compressor e.g. high pressure compressor, for gas turbine engine, has rotor drum that is formed from rotor rings with fiber belts and is made from high temperature resistant fibers that are bedded with polymer e.g. polyamide
EP2189624A2 (en) 2008-11-24 2010-05-26 General Electric Company Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
US20100158690A1 (en) * 2008-12-24 2010-06-24 Cortequisse Jean-Francois One-Piece Bladed Drum of an Axial Turbomachine Compressor
US7811062B1 (en) * 1997-06-03 2010-10-12 Rolls-Royce Plc Fiber reinforced metal rotor
US20130309087A1 (en) * 2011-07-19 2013-11-21 Elliott Company Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft
US8677622B2 (en) 2006-03-10 2014-03-25 Rolls-Royce Deutschland Ltd & Co Kg Intake cone in a fiber compound material for a gas turbine engine and method for its manufacture
US8777576B2 (en) 2011-08-22 2014-07-15 General Electric Company Metallic fan blade platform
US20180010479A1 (en) * 2016-07-05 2018-01-11 Rolls-Royce Plc Turbine arrangement
CN111550435A (en) * 2020-05-25 2020-08-18 中国航发沈阳发动机研究所 Multistage rotor disk connection structure

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2453294A1 (en) * 1979-04-04 1980-10-31 Snecma DEVICE FOR FIXING BLADES ON A COMPRESSOR ROTOR FOR A TURBO-REACTOR
EP2287445A1 (en) 2009-07-16 2011-02-23 Techspace Aero S.A. Axial compressor rotor drum with composite web

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2143466A (en) * 1937-12-31 1939-01-10 Westinghouse Electric & Mfg Co Turbine apparatus
FR980131A (en) * 1951-05-08
FR55020E (en) * 1946-09-20 1951-06-05 High temperature gas turbine
US2803397A (en) * 1952-05-20 1957-08-20 Gen Motors Corp Compressor wheel
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US3519368A (en) * 1968-09-03 1970-07-07 Gen Electric Composite turbomachinery rotors
US3532438A (en) * 1966-11-29 1970-10-06 Rolls Royce Aerofoil-shaped blades,and blade assemblies,for use in a fluid flow machine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR980131A (en) * 1951-05-08
US2143466A (en) * 1937-12-31 1939-01-10 Westinghouse Electric & Mfg Co Turbine apparatus
FR55020E (en) * 1946-09-20 1951-06-05 High temperature gas turbine
US2803397A (en) * 1952-05-20 1957-08-20 Gen Motors Corp Compressor wheel
US3532438A (en) * 1966-11-29 1970-10-06 Rolls Royce Aerofoil-shaped blades,and blade assemblies,for use in a fluid flow machine
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US3519368A (en) * 1968-09-03 1970-07-07 Gen Electric Composite turbomachinery rotors

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3813185A (en) * 1971-06-29 1974-05-28 Snecma Support structure for rotor blades of turbo-machines
US3824037A (en) * 1971-10-12 1974-07-16 Messerschmitt Boelkow Blohm Suspension of rotor blades on the rotor head of a rotorcraft without the use of flapping or drag hinges
US3904316A (en) * 1974-08-16 1975-09-09 Gen Motors Corp Turbine rotor with slot loaded blades and composite bands
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
US4516908A (en) * 1981-04-17 1985-05-14 Nuovo Pignone S.P.A. Power stage of a gas turbine
US4566700A (en) * 1982-08-09 1986-01-28 United Technologies Corporation Abrasive/abradable gas path seal system
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
US4536127A (en) * 1983-05-06 1985-08-20 Motoren-Und Turbinen-Union Turbocompressor provided with an abradable coating
US4648802A (en) * 1984-09-06 1987-03-10 Pda Engineering Radial flow rotor with inserts and turbine utilizing the same
US4919594A (en) * 1987-05-15 1990-04-24 Allied-Signal Inc. Composite member, unitary rotor member including same, and method of making
US4867644A (en) * 1987-05-15 1989-09-19 Allied-Signal Inc. Composite member, unitary rotor member including same, and method of making
US5632600A (en) * 1995-12-22 1997-05-27 General Electric Company Reinforced rotor disk assembly
EP0846844A1 (en) * 1996-12-04 1998-06-10 Asea Brown Boveri AG Rotor assembly with rotor discs connected by both non-positive interlocking and interpenetrating or positive interlocking means
US7811062B1 (en) * 1997-06-03 2010-10-12 Rolls-Royce Plc Fiber reinforced metal rotor
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
US6213720B1 (en) 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
US20060125331A1 (en) * 2002-12-19 2006-06-15 Michael Frank Electric machine comprising a wrapped coil that is to be deep-frozen
US7339293B2 (en) * 2002-12-19 2008-03-04 Siemens Aktiengesellschaft Electric machine with a wrapped winding cooled to a low temperature
WO2005056983A1 (en) * 2003-12-13 2005-06-23 Mtu Aero Engines Gmbh Fibre-reinforced rotor for a turbo generator
US20080025844A1 (en) * 2003-12-13 2008-01-31 Mtu Aero Engines Gmbh Rotor for a Turbo Engine
US8123487B2 (en) * 2003-12-13 2012-02-28 Mtu Aero Engines Gmbh Rotor for a turbo engine
US8677622B2 (en) 2006-03-10 2014-03-25 Rolls-Royce Deutschland Ltd & Co Kg Intake cone in a fiber compound material for a gas turbine engine and method for its manufacture
US20070231144A1 (en) * 2006-04-03 2007-10-04 Karl Schreiber Axial-flow compressor for a gas turbine engine
DE102006015838A1 (en) * 2006-04-03 2007-10-04 Rolls-Royce Deutschland Ltd & Co Kg Axial compressor e.g. high pressure compressor, for gas turbine engine, has rotor drum that is formed from rotor rings with fiber belts and is made from high temperature resistant fibers that are bedded with polymer e.g. polyamide
US7918644B2 (en) * 2006-04-03 2011-04-05 Rolls-Royce Deutschland Ltd & Co Kg Axial-flow compressor for a gas turbine engine
JP2010121624A (en) * 2008-11-24 2010-06-03 General Electric Co <Ge> Fiber composite reinforced aircraft gas turbine engine drum with radially inwardly extending blade
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
EP2189624A2 (en) 2008-11-24 2010-05-26 General Electric Company Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
US8414256B2 (en) * 2008-12-24 2013-04-09 Techspace Aero, S.A. One-piece bladed drum of an axial turbomachine compressor
US20100158690A1 (en) * 2008-12-24 2010-06-24 Cortequisse Jean-Francois One-Piece Bladed Drum of an Axial Turbomachine Compressor
US20130309087A1 (en) * 2011-07-19 2013-11-21 Elliott Company Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft
US8777576B2 (en) 2011-08-22 2014-07-15 General Electric Company Metallic fan blade platform
US20180010479A1 (en) * 2016-07-05 2018-01-11 Rolls-Royce Plc Turbine arrangement
US10641126B2 (en) * 2016-07-05 2020-05-05 Rolls-Royce Plc Turbine arrangement
CN111550435A (en) * 2020-05-25 2020-08-18 中国航发沈阳发动机研究所 Multistage rotor disk connection structure

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GB1272200A (en) 1972-04-26
CA927751A (en) 1973-06-05

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