US3765796A - Filament reinforced rotor assembly - Google Patents

Filament reinforced rotor assembly Download PDF

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Publication number
US3765796A
US3765796A US00249283A US3765796DA US3765796A US 3765796 A US3765796 A US 3765796A US 00249283 A US00249283 A US 00249283A US 3765796D A US3765796D A US 3765796DA US 3765796 A US3765796 A US 3765796A
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US
United States
Prior art keywords
annular
rotor assembly
ring
cavity
rotatable member
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
US00249283A
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English (en)
Inventor
W Pilpel
H Stargardter
S Sattar
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Application granted granted Critical
Publication of US3765796A publication Critical patent/US3765796A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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

  • the rotor assembly comprises a rotatable member having an annular cavity concentric to the members axis.
  • the composite ring is positioned within the cavity and has an inner diameter somewhat larger than the diameter of the rotor surface about which the ring is disposed.
  • the rotor surface diameter increases and comes into centrifugal load bearing relationship to the composite ring, whereupon the ring carries a portion of the centrifugal loads 'thus reducing the strength requirement of 'the rotatable member.
  • An object of the present invention is a'lightweight rotor assembly having high strength.
  • Another object of the present invention is a rotor assembly with the ability to withstand a contaminating environment such as a high temperature oxygen environment.
  • the present invention contemplates a rotor assembly comprising a rotatable member having an annular cavity therein and an annular filament wound composite ring located within said cavity'and radially spaced from a radially outwardly facing annular surface of said cavity and adapted to carry a portion of the centrifugal loads of said rotor assembly during operation. Having the filaments located within the annular cavity protects them from direct exposure to whatever environment happens to surround the rotatable member. When the rotor assembly reaches operating temperatures and speeds, the ring carries a portion of the assembly centrifugal loads.
  • FIG. 1 is a sectional view of a portion of a turbine rotor assembly.
  • FIG. 2 is a sectional view of the rotor assembly of FIG. 1 with the blades and blade locks removed, taken along the line 2-2 of FIG. 1.
  • the turbine rotor assembly 10 is suitably mounted within the turbine section (not shown) of a gas turbine engine by means (not shown) well known to one skilled in the art.
  • the present invention is particularly suited to use in a turbine rotor assembly due to the extremely high temperatures and corrosive environment to which a turbine rotor assembly is exposed; however, it should be obvious that this invention may be useful in a compressor rotor assembly, or for that matter in any rotor assembly subjected to any combination of high temperatures, a corrosive environment and high centrifugal loads.
  • the rotor assembly 10 comprises a rotatable member or disc 12 and a plurality of radially extending circumferentially spaced blades 14 attached by suitable means to the periphery 16 of said disc 12 such as by the use of a fir tree root 18 and corresponding fir tree slots 20 shown in drawing and well known in the art.
  • Blade locks 22 or other suitable blade retention means are also generally required.
  • the blade attachment means is simply a matter of choice and is not a part of the present invention.
  • the disc 12 includes an annular cavity 24 formed therein. Positioned within the annular cavity 24 is an annular filament reinforced composite ring 26.
  • the composite ring 26 comprises one or more circumferentially wound filaments embedded in a matrix material; in this embodiment it is contemplated that the filaments be made from carbon and that the matrix material be made from carbon.
  • the filaments and matrix materials are a matter of choice and depend on several factors such as maximum strength requirements, maximum temperature requirements, and filament/matrix thermal and stiffness compatibility. Examples of other possible filament-matrix combinations are saphirenickel, boron-titanium, and graphite-graphite; the present invention, however, is not limited to any particular filament-matrix combination.
  • the annular cavity 24 has a radially outwardly facing surface 32 which in this exemplary embodiment is interrupted by a plurality of circumferentially spaced slots 34 whose function will hereinafter be made clear; however, for the purpose of this invention the annular surface 32 may be continuous.
  • the composite ring 26 includes an inner annular surface 36 having a diameter slightly larger than the diameter of the annular surface 32. This difference in diameters is necessary to account for the differences in thermal and centrifugal growth rates between the disc 12 and the composite ring 26; the composite ring 26 expands considerably less than the disc 12 during operation, and the difference in diameters is chosen such that the ring 26 will come into centrifugal load bearing relationship to the disc 12 at operating speeds and temperatures.
  • the surface 36 will come into direct contact with the surface 32; however, it is possible that some other hardware may be located between the two surfaces.
  • flexible positioning means such as a plurality of circumferentially spaced springs 38 locates the ring 26 concentric to the annular surface 32.
  • the springs 38 are of the well known Bellville type, and at least three of said springs, equally spaced about the inner annular surface 36 of said ring 26 are required to assure concentric positioning of the ring 26.
  • the flexible positioning means permits essentially unhampered growth between the disc 12 and the ring 26 until the ring comes into centrifugal load bearing relationship to said disc 12; another requirement is that the flexible positioning means does not operate to create unacceptable stress concentrations within the composite ring.
  • the springs 38 are positioned within the slots 34 and are sized such that when fully compressed by the composite ring 26 the ends 40, 42 of the spring 38 abut the sides 44, 46, respectively, of the slot 34; if there were a gap between these surfaces the composite material would tend to enter that gap and the filaments might be damaged to the point of failure of the composite ring.
  • the thickness of the spring 38 is the same as the depth of the slot 34.
  • the disc 12 comprises left and right annular rings 50, 52, respectively.
  • Each of said annular rings 50, 52 has an annular groove 54, 56, respectively.
  • the annular rings 50, 52 are joined together by suitable means such as diffusion bonding at 58 and 60; it is also contemplated that the rings may be mechanically joined.
  • the grooves 44, 46 cooperate to form the annular cavity 24.
  • the cavity 24 it may be necessary or desirable to fill the cavity 24 with an inert gas to assure that the filaments and matrix material are not exposed to any contaminating substances inside the cavity; in that case it is mandatory that the cavity be airtight. Additionally, some filament and matrix materials may react chemically with the disc material, damaging the filaments and reducing the effective hoop strength of the composite ring. if that is the case, it is desirable to insulate the composite ring from the disc material. This might be accomplished in serveral ways,
  • a filament reinforced rotor assembly comprising:
  • annular rotatable member including a plurality of blade receiving slots circumferentially spaced about its periphery and having an axis and having an annular cavity therein concentric with said axis,
  • said cavity including a radially outwardly facing annular surface concentric with said axis, said annular surface being interrupted by a plurality of circumferentially spaced slots;
  • annular filament reinforced composite ring located within said cavity and having an inner diameter slightly larger than the diameter of said annular surface when said rotor is at rest, the difference in diameters being adapted to assure that said ring comes into centrifugal load bearing relationship to said rotatable member at rotor assembly operational speeds and temperatures due to the different centrifugal and thermal growth rates of said rotatable member and said composite ring;
  • each of said springs having a radially outwardly facing surface, said springs being compressed by said composite ring during rotor assembly operation, and when compressed said outwardly facing surface being flush with said annular surface and defining a substantially smooth continuous annular surface therewith with substantially no gaps and no sharp edges to damage the composite ring.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00249283A 1972-05-01 1972-05-01 Filament reinforced rotor assembly Expired - Lifetime US3765796A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US24928372A 1972-05-01 1972-05-01

Publications (1)

Publication Number Publication Date
US3765796A true US3765796A (en) 1973-10-16

Family

ID=22942805

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Application Number Title Priority Date Filing Date
US00249283A Expired - Lifetime US3765796A (en) 1972-05-01 1972-05-01 Filament reinforced rotor assembly

Country Status (9)

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US (1) US3765796A (US20080293856A1-20081127-C00139.png)
JP (1) JPS4954710A (US20080293856A1-20081127-C00139.png)
AU (1) AU463947B2 (US20080293856A1-20081127-C00139.png)
CA (1) CA971111A (US20080293856A1-20081127-C00139.png)
DE (1) DE2318089A1 (US20080293856A1-20081127-C00139.png)
FR (1) FR2182960B1 (US20080293856A1-20081127-C00139.png)
GB (1) GB1420816A (US20080293856A1-20081127-C00139.png)
IT (1) IT984127B (US20080293856A1-20081127-C00139.png)
SE (1) SE385138B (US20080293856A1-20081127-C00139.png)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4232996A (en) * 1978-10-06 1980-11-11 The United States Of America As Represented By The Secretary Of The Air Force Light weight fan assembly
US4464096A (en) * 1979-11-01 1984-08-07 United Technologies Corporation Self-actuating rotor seal
US4787821A (en) * 1987-04-10 1988-11-29 Allied Signal Inc. Dual alloy rotor
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
US6213720B1 (en) * 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
WO2005065002A2 (de) * 2004-01-08 2005-07-21 Mtu Aero Engines Gmbh Rotor für eine turbomaschine und verfahren zur herstellung eines solchen rotors
EP2189624A2 (en) 2008-11-24 2010-05-26 General Electric Company Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
US20110005061A1 (en) * 2007-12-28 2011-01-13 Messier-Dowty Sa Process for manufacturing a metal part reinforced with ceramic fibres
EP3085889A1 (en) * 2015-02-23 2016-10-26 General Electric Company Hybrid metal and composite spool for rotating machinery
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
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
US9976429B2 (en) 2015-06-09 2018-05-22 General Electric Company Composite disk

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2448626A1 (fr) * 1979-02-08 1980-09-05 Snecma Perfectionnement aux rotors de machines tournantes

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1884252A (en) * 1931-05-19 1932-10-25 Gen Electric Rotary disk, turbine bucket wheel, or the like
US3519368A (en) * 1968-09-03 1970-07-07 Gen Electric Composite turbomachinery rotors
US3554668A (en) * 1969-05-12 1971-01-12 Gen Motors Corp Turbomachine rotor
US3610772A (en) * 1970-05-04 1971-10-05 Gen Motors Corp Bladed rotor
US3610777A (en) * 1970-05-15 1971-10-05 Gen Motors Corp Composite drum rotor
US3656864A (en) * 1970-11-09 1972-04-18 Gen Motors Corp Turbomachine rotor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1884252A (en) * 1931-05-19 1932-10-25 Gen Electric Rotary disk, turbine bucket wheel, or the like
US3519368A (en) * 1968-09-03 1970-07-07 Gen Electric Composite turbomachinery rotors
US3554668A (en) * 1969-05-12 1971-01-12 Gen Motors Corp Turbomachine rotor
US3610772A (en) * 1970-05-04 1971-10-05 Gen Motors Corp Bladed rotor
US3610777A (en) * 1970-05-15 1971-10-05 Gen Motors Corp Composite drum rotor
US3656864A (en) * 1970-11-09 1972-04-18 Gen Motors Corp Turbomachine rotor

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4232996A (en) * 1978-10-06 1980-11-11 The United States Of America As Represented By The Secretary Of The Air Force Light weight fan assembly
US4464096A (en) * 1979-11-01 1984-08-07 United Technologies Corporation Self-actuating rotor seal
US4787821A (en) * 1987-04-10 1988-11-29 Allied Signal Inc. Dual alloy rotor
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
US6213720B1 (en) * 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
WO2005065002A2 (de) * 2004-01-08 2005-07-21 Mtu Aero Engines Gmbh Rotor für eine turbomaschine und verfahren zur herstellung eines solchen rotors
WO2005065002A3 (de) * 2004-01-08 2007-03-22 Mtu Aero Engines Gmbh Rotor für eine turbomaschine und verfahren zur herstellung eines solchen rotors
US20110005061A1 (en) * 2007-12-28 2011-01-13 Messier-Dowty Sa Process for manufacturing a metal part reinforced with ceramic fibres
US8458886B2 (en) * 2007-12-28 2013-06-11 Messier-Bugatti-Dowty Process for manufacturing a metal part reinforced with ceramic fibres
US20100129227A1 (en) * 2008-11-24 2010-05-27 Jan Christopher Schilling 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
US8011877B2 (en) 2008-11-24 2011-09-06 General Electric Company Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
EP3085889A1 (en) * 2015-02-23 2016-10-26 General Electric Company Hybrid metal and composite spool for rotating machinery
US9777593B2 (en) 2015-02-23 2017-10-03 General Electric Company Hybrid metal and composite spool for rotating machinery
US9976429B2 (en) 2015-06-09 2018-05-22 General Electric Company Composite disk
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
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
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
DE2318089A1 (de) 1973-11-22
IT984127B (it) 1974-11-20
JPS4954710A (US20080293856A1-20081127-C00139.png) 1974-05-28
FR2182960A1 (US20080293856A1-20081127-C00139.png) 1973-12-14
GB1420816A (en) 1976-01-14
SE385138B (sv) 1976-06-08
CA971111A (en) 1975-07-15
AU463947B2 (en) 1975-08-07
FR2182960B1 (US20080293856A1-20081127-C00139.png) 1974-05-17
AU5409473A (en) 1974-10-10

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