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US3505717A - Method of making a bladed rotor member for a fluid flow machine - Google Patents

Method of making a bladed rotor member for a fluid flow machine Download PDF

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Publication number
US3505717A
US3505717A US602931A US3505717DA US3505717A US 3505717 A US3505717 A US 3505717A US 602931 A US602931 A US 602931A US 3505717D A US3505717D A US 3505717DA US 3505717 A US3505717 A US 3505717A
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United States
Prior art keywords
hub portion
rotor member
fibres
making
blades
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
US602931A
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Jack Palfreyman
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Rolls Royce PLC
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Rolls Royce PLC
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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
    • F01D5/12—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
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49801—Shaping fiber or fibered material

Definitions

  • This invention concerns a method of making a bladed rotor member of a gas turbine engine, and, although it is not so restricted, it is more particularly concerned with a method of making a rotor member of a gas turbine engine compressor.
  • the invention relates to an improvement in or modification of the invention set forth in the commonly assigned co-pending US. application of Jack Palfreyman and Norman Willie Shepherd, Ser. No. 424,658, filed Jan. 11, 1965, and now U.S. Patent No. 3,456,917, issued July 22, 1969.
  • a method of making a bladed rotor member of a gas turbine engine comprising coating a plurality of fibres, employing said coated fibres in the formation of both the blades and a hub portion of the rotor member, the blades and hub portion together forming an integral structure, and sandwiching the hub portion between axially spaced metal discs which are secured to the hub portion.
  • the metal discs are bonded to the rotor member by synthetic resin material. Additionally, the metal discs may be secured to the hub portion by bolts, rivets or the like.
  • the rotor member may be formed of a plurality of 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 bundle may extend from a common blade to two dilferent blades.
  • the spaced portions of the various bundles are interwoven with each other.
  • the fibres may be of inorganic material. Each fibre may be individually coated with a metal or alloy. Alternatively, each fibre may be individually coated with a synthetic resin material.
  • the rotor member may be a rotor disc.
  • a plurality of said rotor discs may be produced, the metal discs of each said rotor disc being welded to casing members which form part of a gas turbine engine rotor drum.
  • the invention also comprises a bladed rotor member of a gas turbine engine e.g. that of a compressor thereof, when made by the method set forth above.
  • FIGURE 1 is a diagrammatic view, partly in section, of a gas turbine engine having a compressor made by the method of the present invention
  • FIGURE 2 is a broken away sectional view of the compressor shown in FIGURE 1, and
  • FIGURE 3 is a diagrammatic view showing the manner in which metal coated fibres are employed to form the blades and discs of the rotor of the said compressor.
  • FIGURE 1 there. is shown a gas turbine engine 10 having an engine casing 11 in which there are mounted in fiow series a compressor 12, combustion equipment 13, and a turbine 14, the turbine exhaust equipment 13, to atmosphere through an exhaust duct 15.
  • the compressor 12 and turbine 14 are mounted on common shafting 16 (FIGURE 2) one portion of which forms part of a rotor drum 17 of the compressor 12.
  • the shafting 16 is mounted in a bearing 20 which is supported from the engine casing 11 by a plurality of angularly spaced apart struts 21.
  • the compressor 12 has two axially spaced rotor discs 22 each of which is provided with a plurality of angularly spaced apart blades 23.
  • the rotor discs 22, together withtheir blades 23, are formed of individually coated fibres 24, eg silica fibres which have been coated with aluminum or with an epoxy, or polymide or polyimidazole, or polyquinoxaline or polythiazole resin.
  • the fibres may be formed from a ceramic constituted by an oxide, nitride or carbide.
  • the fibres may, moreover, be formed of silicon nitride or silicon carbide, or from sapphire or silica.
  • the fibres may be 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 colurnbium.
  • the rotor discs 22 and their blades 23 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 rotor discs 22, together with its blades 23, are formed of a plurality of bundles of the said fibres 24. Opposite ends of each said bundle are used in the formation of different blades 23, the central part of each bundle being divided into two spaced portions 26, 27 which are used in the formation of the hub portions 30 of the rotor discs 22.
  • each said bundle are flattened and extend from a common blade 23a to two different blades 23b, 230.
  • Each of the portions 26, 27 is interwoven with other such portions.
  • the fibres After the fibres have been arranged as shown in FIG- URE 3, they are hot pressed together to form, in the case of aluminum coated silica fibres, an aluminum mass reinforced by silicon fibres, the said mass having blades 23 formed integrally with the hub portion 30.
  • each of the rotor discs 22 is then sandwiched between axially spaced metal discs 31, 32 to which it is secured by a high temperature epoxy or polyimide resin and also, if desired, by rivets (not shown).
  • the metal discs 31, 32 are welded to casing members 33, 34, 35 which are secured to the shafting 16 and form part of the rotor drum 17.
  • a method of making a bladed rotor member for a gas turbine engine said rotor member being an integral structural unit comprising a hub portion, a plurality of blades integral with said hub portion and a plurality of bundles of individually coated fibers embedded both in said hub portion and in said respective blades, said hub portion being sandwiched between axially spaced metal discs, said method comprising the steps of: individually coating a plurality of fibers, forming said fibers into a plurality of bundles, forming said bundles into an integral rotor having said plurality of blades integral with said hub portion, sandwiching said hub portion of said integral structural unit between axially spaced metal disQS, an 12,857,094" 1Q/1.9.. 8 W n..

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

April 14, 1970 J. PALFREYMAN 3,505,717
METHOD OF MAKING A BLADED ROTOR MEMBER FOR A FLUID FLOW MACHINE Filed Dec. 19, 1966 I It Z United States Patent Ofice 3,505,717 Patented Apr. 14, 1970 US. Cl. 29-1563 3 Claims ABSTRACT OF THE DISCLOSURE A method of making a bladed rotor member of a gas turbine engine in which coated fibres are employed in the formation of both the blades and the hub portion of the rotor member. The blades and hub portion together form an integral structure, the hub portion being sandwiched between axially spaced metal discs which are secured to the hub portion.
This invention concerns a method of making a bladed rotor member of a gas turbine engine, and, although it is not so restricted, it is more particularly concerned with a method of making a rotor member of a gas turbine engine compressor.
The invention relates to an improvement in or modification of the invention set forth in the commonly assigned co-pending US. application of Jack Palfreyman and Norman Willie Shepherd, Ser. No. 424,658, filed Jan. 11, 1965, and now U.S. Patent No. 3,456,917, issued July 22, 1969.
According to the present invention, there is provided a method of making a bladed rotor member of a gas turbine engine, comprising coating a plurality of fibres, employing said coated fibres in the formation of both the blades and a hub portion of the rotor member, the blades and hub portion together forming an integral structure, and sandwiching the hub portion between axially spaced metal discs which are secured to the hub portion.
Preferably, the metal discs are bonded to the rotor member by synthetic resin material. Additionally, the metal discs may be secured to the hub portion by bolts, rivets or the like.
The rotor member may be formed of a plurality of 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. Thus, the central part of each bundle may be divided into two spaced portions.
The spaced portions of each bundle may extend from a common blade to two dilferent blades.
Preferably the spaced portions of the various bundles are interwoven with each other.
The fibres may be of inorganic material. Each fibre may be individually coated with a metal or alloy. Alternatively, each fibre may be individually coated with a synthetic resin material.
The rotor member may be a rotor disc. Thus a plurality of said rotor discs may be produced, the metal discs of each said rotor disc being welded to casing members which form part of a gas turbine engine rotor drum.
The invention also comprises a bladed rotor member of a gas turbine engine e.g. that of a compressor thereof, when made by the method set forth above.
The invention is illustrated, merely by way of example, in the accompanying drawings, in which:
FIGURE 1 is a diagrammatic view, partly in section, of a gas turbine engine having a compressor made by the method of the present invention,
FIGURE 2 is a broken away sectional view of the compressor shown in FIGURE 1, and
FIGURE 3 is a diagrammatic view showing the manner in which metal coated fibres are employed to form the blades and discs of the rotor of the said compressor.
In FIGURE 1 there. is shown a gas turbine engine 10 having an engine casing 11 in which there are mounted in fiow series a compressor 12, combustion equipment 13, and a turbine 14, the turbine exhaust equipment 13, to atmosphere through an exhaust duct 15.
The compressor 12 and turbine 14 are mounted on common shafting 16 (FIGURE 2) one portion of which forms part of a rotor drum 17 of the compressor 12. The shafting 16 is mounted in a bearing 20 which is supported from the engine casing 11 by a plurality of angularly spaced apart struts 21.
The compressor 12 has two axially spaced rotor discs 22 each of which is provided with a plurality of angularly spaced apart blades 23. The rotor discs 22, together withtheir blades 23, are formed of individually coated fibres 24, eg silica fibres which have been coated with aluminum or with an epoxy, or polymide or polyimidazole, or polyquinoxaline or polythiazole resin.
Alternatively, the fibres may be formed from a ceramic constituted by an oxide, nitride or carbide. The fibres may, moreover, be formed of silicon nitride or silicon carbide, or from sapphire or silica. The fibres may be coated with silver, or nickel, or iron or an alloy, thereof. Moreover, 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 colurnbium.
Alternatively the rotor discs 22 and their blades 23 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.
As shown in FIGURE 3 each of the rotor discs 22, together with its blades 23, are formed of a plurality of bundles of the said fibres 24. Opposite ends of each said bundle are used in the formation of different blades 23, the central part of each bundle being divided into two spaced portions 26, 27 which are used in the formation of the hub portions 30 of the rotor discs 22.
The spaced portions 26, 27 of each said bundle are flattened and extend from a common blade 23a to two different blades 23b, 230. Each of the portions 26, 27 is interwoven with other such portions.
After the fibres have been arranged as shown in FIG- URE 3, they are hot pressed together to form, in the case of aluminum coated silica fibres, an aluminum mass reinforced by silicon fibres, the said mass having blades 23 formed integrally with the hub portion 30.
The hub portion 30 of each of the rotor discs 22 is then sandwiched between axially spaced metal discs 31, 32 to which it is secured by a high temperature epoxy or polyimide resin and also, if desired, by rivets (not shown). The metal discs 31, 32 are welded to casing members 33, 34, 35 which are secured to the shafting 16 and form part of the rotor drum 17.
I claim:
1. A method of making a bladed rotor member for a gas turbine engine, said rotor member being an integral structural unit comprising a hub portion, a plurality of blades integral with said hub portion and a plurality of bundles of individually coated fibers embedded both in said hub portion and in said respective blades, said hub portion being sandwiched between axially spaced metal discs, said method comprising the steps of: individually coating a plurality of fibers, forming said fibers into a plurality of bundles, forming said bundles into an integral rotor having said plurality of blades integral with said hub portion, sandwiching said hub portion of said integral structural unit between axially spaced metal disQS, an 12,857,094" 1Q/1.9.. 8 W n.. 230-134 fixedly securing said metal discs to said hub portion of 2,868,439 1/1959 Hampshire 230134 X said integral structural unit. 2,916,256 12/ 1959 Wel'ch 25 3-39 2. A method as claimed in claim 1 in which the secur- 2,918,252 12/ 1959 Haworth. ing of the metal discs to the hub portion is accomplished 5 2,950,083 8/1960 Compton ct a1. 156180 X by bonding the hub portion to the metal discs with a syn- 2,958,505 11/ 1960 Frank 29l56.8 X thetic resin material. 3,011,760 12/1961 Eckert 29l56.8 X 3. A method as claimed in claim 1 in which the secur- 3,021,246 2/1962 Hlllltel 6t 8 6296 X ing of the metal disc to the hub portion is accomplished 3,051,437 8/1962 Morley et a1. 253'39 by fixedly attaching the metal discs to the hub portion 10 3,403,844 10/1968 Stolfer 230-134 with at least one securing member.
CHARLIE T. MOON, Primary Examiner References C'ted H D. C. REILEY, Assistant Examiner UNITED STATES PATENTS 2,618,462 11/1952 Kane 253 77 x 15 2,844,354 7/1958 Warnken. 29419; 156l80, 296; 170l59; 230-134; 253-77
US602931A 1966-01-10 1966-12-19 Method of making a bladed rotor member for a fluid flow machine Expired - Lifetime US3505717A (en)

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GB1135/66A GB1089162A (en) 1966-01-10 1966-01-10 Method of making a bladed rotor member for a fluid flow machine

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3675294A (en) * 1968-03-20 1972-07-11 Secr Defence Method of making a bladed rotor
US3719875A (en) * 1972-01-26 1973-03-06 Sperry Rand Corp Brushless d.c. motor using magneto resistor sensing means
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
US4850090A (en) * 1987-07-22 1989-07-25 Rolls-Royce Plc Method of manufacture of an axial flow compressor stator assembly
US5440806A (en) * 1992-03-13 1995-08-15 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Method of making blank for the manufacturing of fiber-reinforced coatings or metal components
US5758549A (en) * 1996-05-17 1998-06-02 Regents Of The University Of California Interface structure for hub and mass attachment in flywheel rotors
US5778735A (en) * 1996-05-17 1998-07-14 Regents Of The University Of California Interlayer toughening of fiber composite flywheel rotors
EP1396608A2 (en) * 2002-09-03 2004-03-10 United Technologies Corporation Integrally bladed rotor

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2618462A (en) * 1948-12-30 1952-11-18 Kane Saul Allan Turbine rotor formed of laminated plates with aperture overlap
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
US2868439A (en) * 1954-05-07 1959-01-13 Goodyear Aircraft Corp Plastic axial-flow compressor for gas turbines
US2916256A (en) * 1955-09-21 1959-12-08 United Aircraft Corp Rotor construction for compressors and turbines
US2918252A (en) * 1954-12-24 1959-12-22 Rolls Royce Turbine rotor disc structure
US2950083A (en) * 1954-07-23 1960-08-23 Thompson Ramo Wooldridge Inc Blade assembly
US2958505A (en) * 1958-11-20 1960-11-01 Robert G Frank Turbine bucket blades
US3011760A (en) * 1953-10-20 1961-12-05 Ernst R G Eckert Transpiration cooled turbine blade manufactured from wires
US3021246A (en) * 1957-05-17 1962-02-13 Hutter Ulrich Process for producing a structure of fiber reinforced plastic material
US3051437A (en) * 1956-01-25 1962-08-28 Rolls Royce Rotors, for example rotor discs for axial-flow turbines
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2618462A (en) * 1948-12-30 1952-11-18 Kane Saul Allan Turbine rotor formed of laminated plates with aperture overlap
US3011760A (en) * 1953-10-20 1961-12-05 Ernst R G Eckert Transpiration cooled turbine blade manufactured from wires
US2844354A (en) * 1954-04-08 1958-07-22 Cincinnati Testing & Res Lab Rotor blade and method of making same
US2868439A (en) * 1954-05-07 1959-01-13 Goodyear Aircraft Corp Plastic axial-flow compressor for gas turbines
US2950083A (en) * 1954-07-23 1960-08-23 Thompson Ramo Wooldridge Inc Blade assembly
US2918252A (en) * 1954-12-24 1959-12-22 Rolls Royce Turbine rotor disc structure
US2857094A (en) * 1955-07-19 1958-10-21 John R Erwin Integral plastic rotors
US2916256A (en) * 1955-09-21 1959-12-08 United Aircraft Corp Rotor construction for compressors and turbines
US3051437A (en) * 1956-01-25 1962-08-28 Rolls Royce Rotors, for example rotor discs for axial-flow turbines
US3021246A (en) * 1957-05-17 1962-02-13 Hutter Ulrich Process for producing a structure of fiber reinforced plastic material
US2958505A (en) * 1958-11-20 1960-11-01 Robert G Frank Turbine bucket blades
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3675294A (en) * 1968-03-20 1972-07-11 Secr Defence Method of making a bladed rotor
US3719875A (en) * 1972-01-26 1973-03-06 Sperry Rand Corp Brushless d.c. motor using magneto resistor sensing means
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
US4850090A (en) * 1987-07-22 1989-07-25 Rolls-Royce Plc Method of manufacture of an axial flow compressor stator assembly
US5440806A (en) * 1992-03-13 1995-08-15 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Method of making blank for the manufacturing of fiber-reinforced coatings or metal components
US5557846A (en) * 1992-03-13 1996-09-24 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Blank for the manufacturing of fiber reinforced coatings or metal components
US5758549A (en) * 1996-05-17 1998-06-02 Regents Of The University Of California Interface structure for hub and mass attachment in flywheel rotors
US5778735A (en) * 1996-05-17 1998-07-14 Regents Of The University Of California Interlayer toughening of fiber composite flywheel rotors
EP1396608A2 (en) * 2002-09-03 2004-03-10 United Technologies Corporation Integrally bladed rotor
US20050220621A1 (en) * 2002-09-03 2005-10-06 United Technologies Corporation Composite integrally bladed rotor
EP1396608A3 (en) * 2002-09-03 2005-11-16 United Technologies Corporation Integrally bladed rotor
US7284957B2 (en) 2002-09-03 2007-10-23 United Technologies Corporation Composite integrally bladed rotor

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Publication number Publication date
GB1089162A (en) 1967-11-01
DE1476893B1 (en) 1971-04-22

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