US3456917A - Bladed rotor,particularly for a compressor - Google Patents

Bladed rotor,particularly for a compressor Download PDF

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Publication number
US3456917A
US3456917A US424658A US42465865A US3456917A US 3456917 A US3456917 A US 3456917A US 424658 A US424658 A US 424658A US 42465865 A US42465865 A US 42465865A US 3456917 A US3456917 A US 3456917A
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US
United States
Prior art keywords
blades
bladed rotor
fibres
fibers
rotor
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
US424658A
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English (en)
Inventor
Jack Palfreyman
Norman Willie Shepherd
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.)
Rolls Royce PLC
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Rolls Royce PLC
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Filing date
Publication date
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Publication of US3456917A publication Critical patent/US3456917A/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2307/00—Use of elements other than metals as reinforcement

Definitions

  • a bladed rotor of fiber-reinforced construction has respective pairs of blades which are interconnected by continuously curved and interwoven bundles of fibers. Each bundle of fibers, which is preferably of catenary form, is held in tension on rotation of the rotor.
  • This invention concerns a bladed rotor and, although it is not so restricted, it is more particularly concerned with a rotor of a gas turbine engine compressor.
  • a bladed rotor comprising a hub portion, a plurality of blades united with said hub portion, at least part of each blade comprising fibers, and at least part of the hub portion comprising respective continuously curved and interwoven groups of fibers connecting each respective blade to another blade, whereby the fibers of each said group are in tension along their axes on rotation of the rotor.
  • the rotor may be formed of a plurality of groups, or bundles, of said fibres, opposite ends of each said bundle being used in the formation of different blades, and the central part of each bundle being used in the formation of the hub portion.
  • the central part of each bundle may be divided into two spaced portions.
  • each blade of a diametrically opposite pair of blades may come from the same bundle or bundles, and in this case the spaced portions may be of catenary shape.
  • each bundle may extend from a common blade to two different blades.
  • the spaced portions of the various bundles are interwoven with each other.
  • the hub portion may comprise at least two discs each of which carries a plurality of blades, the blades of each disc being connected to those of the adjacent disc by a group of said fibres.
  • the rotor may be made up of a plurality of laminae which have been united together, each lamina consisting of a part of both the hub portion and the blades.
  • the fibres may be of inorganic material; e.g. they may be formed of a ceramic oxide, nitride or carbide. Thus they may be formed of sapphire, or silica or silicon nitride, or silicon carbide.
  • the fibres may be formed from carbonaceous material such, for example, as graphite.
  • the fibres are formed of boron.
  • Each fibre may be individually coated with a metal or alley.
  • it may be coated with silver, or nickel or iron or titanium or platinum or columbium, or aluminium or any alloy thereof.
  • each fibre may be individually coated witth a synthetic resin material such for example, as an epoxy or polyimide, or polyimidazole, or polyquinoxaline, or polythiazole resin.
  • a synthetic resin material such for example, as an epoxy or polyimide, or polyimidazole, or polyquinoxaline, or polythiazole resin.
  • the bladed rotor may, if desired, be formed of synthetic resin material reinforced by the said individually coated fibres.
  • FIGURE 1 is a diagrammatic perspective view of a rotor of a gas turbine engine compressor
  • FIGURE 2 is a diagrammatic view showing the manner in which metal coated fibres are employed to form the blades and discs of the rotor of FIGURE 1,
  • FIGURE 3 diagrammatically illustrates the manner in which the said fibres are used to interconnect the blades of two discs of the rotor
  • FIGURE 4 is a developed plan view looking in the direction of the arrow 4 of FIGURE 1, but with the blades removed, and
  • FIGURE 5 is a view similar to FIGURE 4 but illustrating a modification.
  • a gas turbine engine compressor rotor 10 has a tub portion consisting of a cylindrical casing 11 and discs 12, 13. Each of the discs 12, 13 is provided with a plurality of angularly spaced apart blades 14.
  • the blades 14, casing 11, and discs 12, 13 are formed, at least in part, of individually coated fibres 15, e.g. silica fibres which have been coated with aluminium or with an epoxy, or polyimide or polyimidezole, or polyquinoxaline or polythiazole resin.
  • the fibres may be formed from a ceramic constituted by an oxide, nitride or carbide.
  • the fibres may also be formed of sapphire, silica, silicon nitride or silicon carbide, coated with silver, or nickel, or iron, or an alloy thereof.
  • the fibres may be graphite or boron fibres coated with a synthetic resin (e.g. an epoxy or polyimide resin) or with a metal such, for example, as silver, nickel, platinum or columbium.
  • the blades 14, casing 11 and discs 12, 13 may be formed of a synthetic resin material, such for example as an epoxy or a high temperature polyimide resin, reinforced by any of the said coated fibres.
  • each of the discs 12, 13, together with its blades 14, are formed, at least in part, of a plurality of bundles of the said fibres 15. Opposite ends of each said bundle are used in the formation of diametrically oppositely disposed blades 14, the central part of each bundle being divided into two spaced portions continuously curved groups or bundles of fibers 16, 17 which are used in the formation of the discs 12, 13.
  • each blade 14 is connected to another blade 14 by way of the respective two groups of fibers 16, 17 which extend through a respective one of the discs 12, 13.
  • each of the groups 16, 17 may have a catenary shape the various groups 16, 17 being interwoven with each other.
  • the formation of the groups 16, 17 in a catenary shape ensures that, during rotation of the rotor, all parts of these groups are in tension along their axes and this is desirable since, for example, aluminium coated silica fibres are strong in tension but weak in compression.
  • the blades 14 of the discs 12, 13 are interconnected by coated fibres 20 which may form part of the fibres employed in the formation of the blades 14 or may be constituted by wholly separate fibres. As shown best in FIGURE 4, the fibres 20 are arranged in a lazy-tong pattern embracing the roots of the blades 14 of the discs 12, 13. The angle a between adjacent limbs of the lazytong pattern is such that as the discs 12, 13 twist relatively to each other about the rotational axis the fibres will lie substantially along the line of the resultant tensile stress.
  • FIGURE illustrates a modification of the invention in which the roots of the blades 14 of the discs 12, 13, instead of being interconnected :by the lazy-tong pattern of fibres as shown in FIGURE 4, are interconnected by fibres 21 which extend from the root of a blade 14 of one of the discs to an obliquely disposed blade 14 of the other disc.
  • the fibres 21 extend to an angle of substantially 13, to the planes of the discs 12, 13, the angle 6 being such as to make the fibers 21 lie substantially along the line of resultant tensile stress when the two discs are made to twist relatively to each other.
  • the blades 14 and hub portion 11-13, or parts thereof, instead of being united together simultaneously with their formation, as described above, may initially be formed separately and subsequently united.
  • a bladed rotor comprising a hub portion, a plurality of blades united with said hub portion, at least part of each blade comprising embedded fibers, and at least part of the hub portion comprising respective continuously uniformly curved and interwoven groups of fibers connecting each respective blade to another blade, whereby the fibers of each said group are in tension along their axes on rotation of the rotor, respective pairs of said groups of fibers interconnecting respective pairs of blades and being oppositely curved, the central part of each group of a said pair of groups being spaced from the other group of said pair, and at least some of the said fibers comprising respective blades being integral with the fibers of respective groups interconnecting said pair of blades.
  • a bladed rotor as claimed in claim 1 in which all the said fibers comprising respective blades of each diametrically opposite pair of blades on the rotor are integral with the fibers of respective groups interconnecting said pair of blades.
  • a bladed rotor as claimed in claim 1 in which each continuously curved interwoven group of fibers is of catenary shape.
  • a bladed rotor as claimed in claim 1 in which the hub portion comprises at least two discs each of which carriesa plurality of blades, and a plurality of fibers interconnect the blades of each disc with those of the adjacent disc.
  • a bladed rotor as claimed in claim 1 in which the fibers are of inorganic material.
  • a bladed rotor as claimed in claim 6 in which the fibers are formed of a ceramic material.
  • a bladed rotor as claimed in claim 6 in which the fibers are formed of a material selected from the group consisting of silica, silicon nitride and silicon carbide.
  • a bladed rotor as claimed in claim 6 in which the fibers are formed of sapphire.
  • a bladed rotor as claimed in claim 1 in which the fibers are of carbonaceous material.
  • each fiber has an individual coating of material selected from the group consisting of silver and any alloy thereof.
  • a bladed rotor as claimed in claim 13 in which each fiber has an individual coating of material selected from the group consisting of nickel and any alloy thereof.
  • each fiber has an individual coating of material selected from the group consisting of iron and any alloy thereof.
  • each fiber has an individual coating of material selected from the group consisting of titanium and any alloy thereof.
  • each fiber has an individual coating of material selected from the group consisting of platinum and any alloy thereof.
  • each fiber has an individual coating of material selected from the group consisting of columbium and any alloy thereof.
  • each fiber has an individual coating of material selected from the group consisting of aluminium and any alloy thereof.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Moulding By Coating Moulds (AREA)
  • Reinforced Plastic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US424658A 1964-01-15 1965-01-11 Bladed rotor,particularly for a compressor Expired - Lifetime US3456917A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB15221/67A GB1090722A (en) 1964-01-15 1964-01-15 Method of making a bladed rotor for a fluid flow machine, e.g. a gas turbine engine
GB1887/64A GB1090721A (en) 1964-01-15 1964-01-15 Method of making a bladed rotor for a fluid flow machine, e.g. a gas turbine engine

Publications (1)

Publication Number Publication Date
US3456917A true US3456917A (en) 1969-07-22

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Family Applications (2)

Application Number Title Priority Date Filing Date
US424658A Expired - Lifetime US3456917A (en) 1964-01-15 1965-01-11 Bladed rotor,particularly for a compressor
US667168A Expired - Lifetime US3424434A (en) 1964-01-15 1967-09-12 Bladed rotor for a fluid flow machine,e.g. a gas turbine engine

Family Applications After (1)

Application Number Title Priority Date Filing Date
US667168A Expired - Lifetime US3424434A (en) 1964-01-15 1967-09-12 Bladed rotor for a fluid flow machine,e.g. a gas turbine engine

Country Status (4)

Country Link
US (2) US3456917A (fr)
DE (1) DE1426846B2 (fr)
FR (2) FR1424045A (fr)
GB (2) GB1090721A (fr)

Cited By (13)

* 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
US3572969A (en) * 1969-05-13 1971-03-30 Gen Motors Corp Turbomachine rotor
US3628890A (en) * 1969-09-04 1971-12-21 Gen Electric Compressor blades
US3685919A (en) * 1970-09-11 1972-08-22 Speck Pumpen Circulating pump
US3834832A (en) * 1971-12-21 1974-09-10 Rolls Royce 1971 Ltd Fibre reinforced composite structures
US3931445A (en) * 1970-10-12 1976-01-06 Minnesota Mining And Manufacturing Company Precoated large-diameter monofilaments for prepreg tape
US4354804A (en) * 1979-11-30 1982-10-19 Williams Research Corporation Composite turbine wheel, method of manufacture and fixture therefor
US4659325A (en) * 1984-12-21 1987-04-21 E. I. Du Pont De Nemours And Company Centrifuge rotor having a flexible carrier
US4747900A (en) * 1984-07-07 1988-05-31 Rolls-Royce Plc Method of manufacture of compressor rotor assembly
US4826645A (en) * 1984-07-07 1989-05-02 Rolls-Royce Limited Method of making an integral bladed member
DE3910674C1 (fr) * 1989-04-03 1990-09-20 Schmetz Gmbh & Co Kg Unternehmensverwaltung, 5750 Menden, De
US5273401A (en) * 1992-07-01 1993-12-28 The United States Of America As Represented By The Secretary Of The Air Force Wrapped paired blade rotor
US20040042902A1 (en) * 2002-09-03 2004-03-04 Hornick David Charles Organic matrix composite integrally bladed rotor

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3905723A (en) * 1972-10-27 1975-09-16 Norton Co Composite ceramic turbine rotor
US3876327A (en) * 1973-02-26 1975-04-08 Goulds Pumps Non-metallic pump
US4464097A (en) * 1982-04-01 1984-08-07 General Electric Company Turbomachinery rotor and method of manufacture
US4465434A (en) * 1982-04-29 1984-08-14 Williams International Corporation Composite turbine wheel
US4611972A (en) * 1984-05-31 1986-09-16 Ralph Andrae Aeroplane propeller
FR2605586B1 (fr) * 1986-10-22 1990-11-30 Snecma Anneau porte-pales pour aubage d'helice de grande dimension
FR2637319B1 (fr) * 1988-09-30 1994-02-25 Propulsion Ste Europeenne Roue de turbine grande vitesse en materiau composite
US5222866A (en) * 1988-09-30 1993-06-29 Societe Europeenne De Propulsion High speed composite turbine wheel
FR2692255B1 (fr) * 1992-06-11 1994-11-04 Snecma Procédé d'assemblage d'au moins deux pièces réalisées dans un matériau composite comprenant une matrice céramique ou vitrocéramique renforcée par des fibres céramiques.
US5735673A (en) * 1996-12-04 1998-04-07 United Technologies Corporation Turbine engine rotor blade pair
WO2006019942A2 (fr) * 2004-07-22 2006-02-23 Integral Technologies, Inc. Pompes exemptes de decharges electrostatiques economiques faites de resines chargees de materiaux conducteurs
US9291060B2 (en) 2013-03-14 2016-03-22 Rolls-Royce Corporation High strength joints in ceramic matrix composite preforms
US10393134B2 (en) * 2017-08-04 2019-08-27 Borgwarner Inc. Polymeric compressor wheel with metal sleeve

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1605356A (en) * 1925-06-29 1926-11-02 Int Motor Co Method of making universal joints
US2405283A (en) * 1941-08-19 1946-08-06 Fed Reserve Bank Elastic fluid mechanism
US2844354A (en) * 1954-04-08 1958-07-22 Cincinnati Testing & Res Lab Rotor blade and method of making same
US2857094A (en) * 1955-07-19 1958-10-21 John R Erwin Integral plastic rotors
US2859936A (en) * 1954-03-03 1958-11-11 Cincinnati Testing & Res Lab Compressor blade and method of forming same
US3038248A (en) * 1954-11-04 1962-06-12 Kremer Henry Strengthening of metal
US3187422A (en) * 1956-08-27 1965-06-08 Owens Corning Fiberglass Corp Reinforcement of metal

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3098723A (en) * 1960-01-18 1963-07-23 Rand Corp Novel structural composite material
GB901075A (en) * 1960-05-12 1962-07-11 Rolls Royce Improvements relating to compressor blades
US3248082A (en) * 1965-08-19 1966-04-26 Whitfield Lab Inc Reinforced gas-turbine blade or vane

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1605356A (en) * 1925-06-29 1926-11-02 Int Motor Co Method of making universal joints
US2405283A (en) * 1941-08-19 1946-08-06 Fed Reserve Bank Elastic fluid mechanism
US2859936A (en) * 1954-03-03 1958-11-11 Cincinnati Testing & Res Lab Compressor blade and method of forming same
US2844354A (en) * 1954-04-08 1958-07-22 Cincinnati Testing & Res Lab Rotor blade and method of making same
US3038248A (en) * 1954-11-04 1962-06-12 Kremer Henry Strengthening of metal
US2857094A (en) * 1955-07-19 1958-10-21 John R Erwin Integral plastic rotors
US3187422A (en) * 1956-08-27 1965-06-08 Owens Corning Fiberglass Corp Reinforcement of metal

Cited By (18)

* 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
US3572969A (en) * 1969-05-13 1971-03-30 Gen Motors Corp Turbomachine rotor
US3628890A (en) * 1969-09-04 1971-12-21 Gen Electric Compressor blades
US3685919A (en) * 1970-09-11 1972-08-22 Speck Pumpen Circulating pump
US3931445A (en) * 1970-10-12 1976-01-06 Minnesota Mining And Manufacturing Company Precoated large-diameter monofilaments for prepreg tape
US3834832A (en) * 1971-12-21 1974-09-10 Rolls Royce 1971 Ltd Fibre reinforced composite structures
US4354804A (en) * 1979-11-30 1982-10-19 Williams Research Corporation Composite turbine wheel, method of manufacture and fixture therefor
US4747900A (en) * 1984-07-07 1988-05-31 Rolls-Royce Plc Method of manufacture of compressor rotor assembly
US4826645A (en) * 1984-07-07 1989-05-02 Rolls-Royce Limited Method of making an integral bladed member
US4659325A (en) * 1984-12-21 1987-04-21 E. I. Du Pont De Nemours And Company Centrifuge rotor having a flexible carrier
DE3910674C1 (fr) * 1989-04-03 1990-09-20 Schmetz Gmbh & Co Kg Unternehmensverwaltung, 5750 Menden, De
US5273401A (en) * 1992-07-01 1993-12-28 The United States Of America As Represented By The Secretary Of The Air Force Wrapped paired blade rotor
US20040042902A1 (en) * 2002-09-03 2004-03-04 Hornick David Charles Organic matrix composite integrally bladed rotor
EP1396608A2 (fr) * 2002-09-03 2004-03-10 United Technologies Corporation Rotor à aubage intégré
US6881036B2 (en) * 2002-09-03 2005-04-19 United Technologies Corporation Composite integrally bladed rotor
US20050220621A1 (en) * 2002-09-03 2005-10-06 United Technologies Corporation Composite integrally bladed rotor
EP1396608A3 (fr) * 2002-09-03 2005-11-16 United Technologies Corporation Rotor à aubage intégré
US7284957B2 (en) * 2002-09-03 2007-10-23 United Technologies Corporation Composite integrally bladed rotor

Also Published As

Publication number Publication date
FR1424045A (fr) 1966-01-07
GB1090721A (en) 1967-11-15
DE1426846B2 (de) 1970-09-10
GB1090722A (en) 1967-11-15
DE1426846A1 (de) 1969-04-24
US3424434A (en) 1969-01-28
FR91585E (fr) 1968-07-05

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