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US3640640A - Fluid flow machine - Google Patents

Fluid flow machine Download PDF

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Publication number
US3640640A
US3640640A US95993A US3640640DA US3640640A US 3640640 A US3640640 A US 3640640A US 95993 A US95993 A US 95993A US 3640640D A US3640640D A US 3640640DA US 3640640 A US3640640 A US 3640640A
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United States
Prior art keywords
force
fluid flow
flow machine
blades
transmitting
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Expired - Lifetime
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US95993A
Inventor
Jack Palfreyman
Henry Edward Middleton
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Rolls Royce PLC
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Rolls Royce PLC
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Publication date
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Publication of US3640640A publication Critical patent/US3640640A/en
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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

Definitions

  • ABSTRACT The invention concerns a fluid flow machine having a support member, a plurality of angularly spaced-apart blades each of which is mounted in the support member for limited pivotal movement, and frangible force-transmitting means which interconnect adjacent blades so as normally to restrain the blades against such pivotal movement, the frangible forcetransmitting means breaking when subjected to a force exceeding a predetermined value.
  • This invention concerns a fluid flow machine such, for example, as a gas turbine engine compressor.
  • a fluid flow machine having a support member provided with a plurality of angularly spaced-apart blades each of which is mounted in the support member for limited pivotal movement, adjacent blades being interconnected by frangible force-transmitting means which normally restrain the blades against such pivotal movement and which break when subjected to a force exceeding a predetermined value.
  • Each adjacent pair of blades are preferably interconnected by force-transmitting members which extend from the respective blades and which are connected together in shear.
  • each force-transmitting member may be provided with fingers which are intercalated with those of the adjacent force transmitting member and are connected thereto in shear.
  • the force-transmitting member may extend between the tips of the blades but preferably extend between the roots of the blades.
  • each blade preferably has part-cylindrical members disposed on opposite sides thereof, the curved surfaces of the part-cylindrical members engaging corresponding surfaces of an aperture within the support member within which the root is mounted t permit the said limited pivotal movement of the blade.
  • each force-transmitting member may have a portion which is trapped between the respective root partcylindrical member.
  • each force-transmitting member is a fiber-reinforced synthetic resin strip.
  • the support member is preferably a rotor member, although the invention is also applicable to a stator construction.
  • blades as used in this specification, is intended to cover bladelike members such as stator vanes.
  • the fluid flow machine is preferably a gas turbine engine compressor.
  • FIG. 1 is a diagrammatic view of part of a rotor of a gas turbine engine compressor according to the present invention.
  • FIG. 2 is a broken-away view taken on the line 2-2 of FIG. 1.
  • a gas turbine engine compressor has a rotor member 11 provided with a plurality of angularly spaced-apart aerofoil-shaped rotor blades 12.
  • Each of the blades 12 has a dovetail shaped root 13 mounted in an aperture 14 within the rotor member 11.
  • Each root 13 has part-cylindrical members 15 disposed on opposite sides thereon, the part-cylindrical members 15 being mounted within the respective aperture 14 and having curved surfaces which engage corresponding surfaces of the aperture 14.
  • each root is so mounted as to permit limited pivotal movement of the respective blade 12 in the rotor member 11.
  • Each pair of adjacent blades 12 are interconnected by force-transmitting members 16, 17 which extend from the roots 13 of the blades.
  • the end portion of each member 16 is provided with fingers 20 which are intercalated with fingers 21 of the adjacent force-transmitting member 17 and are connected to the latter in shear.
  • Each of the force-transmitting members 16, 17 has an end portion 22 which is trapped between the res ective root 13 and the respective part-cyhndncal member 5.
  • Each of the force-transmitting members 16, 17 may be a fiber-reinforces synthetic resin strip, e.g., a nylon strip reinforced with carbon fibers formed from polyacrylonitrile, the fingers 20, 21 being resin bonded together.
  • the force-transmitting members 16, 17 normally restrain the blades 12 against pivotal movement.
  • any such pivotal movement will cause a force to be transmitted through one of the force-transmitting members 16, 17 and this force will tend to be dissipated by causing pivotal movement of an adjacent blade or blades 12 and, if he force exceeds a predetermined value by causing the connection between the fingers 20, 21 to break.
  • a fluid flow machine having a support member, a plurality of angularly spaced-apart blades each of which is mounted in the support member for limited pivotal movement, and frangible force-transmitting means which interconnect adjacent blades so as normally to restrain the blades against such pivotal movement, the frangible force-transmitting means breaking when subjected to a force exceeding a predetermined value.
  • a fluid flow machine as claimed in claim 1 in which each adjacent pair of blades re interconnected by force-transmitting members which extend from the respective blades and which are connected together in shear.
  • a fluid flow machine as claimed in claim 2 in which an end portion of each force-transmitting member is provided with fingers which are intercalated with those of the adjacent force-transmitting member and are connected thereto in shear.
  • a fluid flow machine as claimed in claim 2 in which the force-transmitting members extend between the roots of the blades.
  • a fluid flow machine as claimed in claim 2 in which the root of each blade has part-cylindrical members disposed on opposite sides thereof, the curved surfaces of the part-cylindrical members engaging corresponding surfaces of an aperture within the support member within which the root is mounted to permit the said limited pivotal movement of the blade.
  • each force-transmitting member has a portion which is trapped between the respective root and part-cylindrical member.
  • each force-transmitting member is a fiber-reinforced synthetic resin strip.

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

Abstract

The invention concerns a fluid flow machine having a support member, a plurality of angularly spaced-apart blades each of which is mounted in the support member for limited pivotal movement, and frangible force-transmitting means which interconnect adjacent blades so as normally to restrain the blades against such pivotal movement, the frangible forcetransmitting means breaking when subjected to a force exceeding a predetermined value.

Description

United States Patent Palfreyman et al.
[ Feb. 8, 1972 [54] FLUID FLOW MACHINE [72] Inventors: Jack Palfreyman, Tansley, near Matlock; Henry Edward Middleton, Derby, both of England [73] Assignee: Rolls-Royce Limited, Derby, England [22] Filed: Dec. 4, 1970 [21] Appl. No.: 95,993
[52] US. Cl ..4l6/2,416/l35,416/140, 416/194, 416/212, 416/219 [51] Int. Cl ..F0ld 5/32 [58] Field of Search ..416/2,134,131,140,135, 416/194, 196, 212, 219, 221
[56] References Cited UNITED STATES PATENTS 2,772,854 12/1956 Anxionnaz ..416/196 2,819,869 l/l958 Meyer ..4l6/l31 2,997,274 8/1961 Hanson ..416/l40 Primary ExaminerEdgar W. Geoghegan Attorney-Cushman, Darby & Cushman [57] ABSTRACT The invention concerns a fluid flow machine having a support member, a plurality of angularly spaced-apart blades each of which is mounted in the support member for limited pivotal movement, and frangible force-transmitting means which interconnect adjacent blades so as normally to restrain the blades against such pivotal movement, the frangible forcetransmitting means breaking when subjected to a force exceeding a predetermined value.
9 Claims, 2 Drawing Figures PAIENIEDFEB 81972 FIG. 7.
F IG. 2.
rum) 11.0w MACHINE This invention concerns a fluid flow machine such, for example, as a gas turbine engine compressor.
According to the invention there is provided a fluid flow machine having a support member provided with a plurality of angularly spaced-apart blades each of which is mounted in the support member for limited pivotal movement, adjacent blades being interconnected by frangible force-transmitting means which normally restrain the blades against such pivotal movement and which break when subjected to a force exceeding a predetermined value.
Accordingly, if a blade is struck by a bird, or other foreign object, limited pivotal movement of he blade, under the force imposed thereon, is permitted, with the result that damage to the blade is limited. Moreover, the said force will be dissipated, at least in part, by virtue of being transmitted to the adjacent blades by the force-transmitting means, while if the force is sufi'rciently great it will be at least partially dissipated (without causing damage elsewhere) by its causing the forcetransmitting means to break.
Each adjacent pair of blades are preferably interconnected by force-transmitting members which extend from the respective blades and which are connected together in shear.
Thus an end portion of each force-transmitting member may be provided with fingers which are intercalated with those of the adjacent force transmitting member and are connected thereto in shear.
The force-transmitting member may extend between the tips of the blades but preferably extend between the roots of the blades.
The root of each blade preferably has part-cylindrical members disposed on opposite sides thereof, the curved surfaces of the part-cylindrical members engaging corresponding surfaces of an aperture within the support member within which the root is mounted t permit the said limited pivotal movement of the blade. Thus each force-transmitting member may have a portion which is trapped between the respective root partcylindrical member.
Preferably each force-transmitting member is a fiber-reinforced synthetic resin strip.
The support member is preferably a rotor member, although the invention is also applicable to a stator construction. In this connection it should be noted that the term blades, as used in this specification, is intended to cover bladelike members such as stator vanes.
The fluid flow machine is preferably a gas turbine engine compressor.
The invention is illustrated, merely by way of example, in the accompanying drawings, in which:
FIG. 1 is a diagrammatic view of part of a rotor of a gas turbine engine compressor according to the present invention, and
FIG. 2 is a broken-away view taken on the line 2-2 of FIG. 1.
Referring to the drawings, a gas turbine engine compressor has a rotor member 11 provided with a plurality of angularly spaced-apart aerofoil-shaped rotor blades 12.
Each of the blades 12 has a dovetail shaped root 13 mounted in an aperture 14 within the rotor member 11. Each root 13 has part-cylindrical members 15 disposed on opposite sides thereon, the part-cylindrical members 15 being mounted within the respective aperture 14 and having curved surfaces which engage corresponding surfaces of the aperture 14. Thus each root is so mounted as to permit limited pivotal movement of the respective blade 12 in the rotor member 11.
Each pair of adjacent blades 12 are interconnected by force-transmitting members 16, 17 which extend from the roots 13 of the blades. The end portion of each member 16 is provided with fingers 20 which are intercalated with fingers 21 of the adjacent force-transmitting member 17 and are connected to the latter in shear.
Each of the force-transmitting members 16, 17 has an end portion 22 which is trapped between the res ective root 13 and the respective part-cyhndncal member 5. Each of the force-transmitting members 16, 17 may be a fiber-reinforces synthetic resin strip, e.g., a nylon strip reinforced with carbon fibers formed from polyacrylonitrile, the fingers 20, 21 being resin bonded together.
The force-transmitting members 16, 17 normally restrain the blades 12 against pivotal movement.
Accordingly, if a blade 12 is struck by a bird or other foreign object, it is unlikely to break since the part-cylindrical members 15 will allow the blade a limited degree of pivotal movement. Moreover, any such pivotal movement will cause a force to be transmitted through one of the force-transmitting members 16, 17 and this force will tend to be dissipated by causing pivotal movement of an adjacent blade or blades 12 and, if he force exceeds a predetermined value by causing the connection between the fingers 20, 21 to break.
We claim:
1. A fluid flow machine having a support member, a plurality of angularly spaced-apart blades each of which is mounted in the support member for limited pivotal movement, and frangible force-transmitting means which interconnect adjacent blades so as normally to restrain the blades against such pivotal movement, the frangible force-transmitting means breaking when subjected to a force exceeding a predetermined value.
2. A fluid flow machine as claimed in claim 1 in which each adjacent pair of blades re interconnected by force-transmitting members which extend from the respective blades and which are connected together in shear.
3. A fluid flow machine as claimed in claim 2 in which an end portion of each force-transmitting member is provided with fingers which are intercalated with those of the adjacent force-transmitting member and are connected thereto in shear.
4. A fluid flow machine as claimed in claim 2 in which the force-transmitting members extend between the roots of the blades.
5. A fluid flow machine as claimed in claim 2 in which the root of each blade has part-cylindrical members disposed on opposite sides thereof, the curved surfaces of the part-cylindrical members engaging corresponding surfaces of an aperture within the support member within which the root is mounted to permit the said limited pivotal movement of the blade.
6. A fluid flow machine as claimed in claim 5 in which each force-transmitting member has a portion which is trapped between the respective root and part-cylindrical member.
7. A fluid flow machine as claimed in claim 2 in which each force-transmitting member is a fiber-reinforced synthetic resin strip.
8. A fluid flow machine as claimed in claim 1 in which the support member is a rotor member.
9. A fluid flow machine as claimed in claim 1 in which the machine is a gas turbine engine compressor.
UNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION entofls) Jack Palfreyman and Henry Edward Middleton Inv It is certified that error appears in the above-identified patent and that said Letters Patent are hereby corrected as shown below:
In the above-identified patent, please add the following to the front page format after "[21] Appl. No. 95,993" [30] Foreign Application Priority Data, December 19, 1969 Great Britain 620 I2/69.
In the Claims Claim 2, line 2, delete "re and insert --are--.
Signed and sealed this 13th day of June 1972.
(SEAL) Attest:
EDWARD MQFLEI'CHERJR. ROBERT GOT'ISCHALK Commissioner of Patents Attesting Officer USCOMM-DC GONG-P69 h 0.5. sovzaunzur rmm'ms OFFICE n09 o-ass-su F ORM PO-IOSO (10-69)

Claims (9)

1. A fluid flow machine having a support member, a plurality of angularly spaced-apart blades each of which is mounted in the support member for limited pivotal movement, and frangible forcetransmitting means which interconnect adjacent blades so as normally to restrain the blades against such pivotal movement, the frangible force-transmitting means breaking when subjected to a force exceeding a predetermined value.
2. A fluid flow machine as claimed in claim 1 in which each adjacent pair of blades are interconnected by force-transmitting members which extend from the respective blades and which are connected together in shear.
3. A fluid flow machine as claimed in claim 2 in which an end portion of each force-transmitting member is provided with fingers which are intercalated with those of the adjacent force-transmitting member and are connected thereto in shear.
4. A fluid flow machine as claimed in claim 2 in which the force-transmitting members extend between the roots of the blades.
5. A fluid flow machine as claimed in claim 2 in which the root of each blade has part-cylindrical members disposed on opposite sides thereof, the curved surfaces of the part-cylindrical members engaging corresponding surfaces of an aperture within the support member within which the root is mounted to permit the said limited pivotal movement of the blade.
6. A fluid flow machine as claimed in claim 5 in which each force-transmitting member has a portion which is trapped between the respective root and part-cylindrical member.
7. A fluid flow machine as claimed in claim 2 in which each force-transmitting member is a fiber-reinforced synthetic resin strip.
8. A fluid flow machine as claimed in claim 1 in which the support member is a rotor member.
9. A fluid flow machine as claimed in claim 1 in which the machine is a gas turbine engine compressor.
US95993A 1970-12-04 1970-12-04 Fluid flow machine Expired - Lifetime US3640640A (en)

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4452564A (en) * 1981-11-09 1984-06-05 The Garrett Corporation Stator vane assembly and associated methods
US5193982A (en) * 1991-07-17 1993-03-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Separate inter-blade platform for a bladed rotor disk
US5222865A (en) * 1991-03-04 1993-06-29 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
FR2715695A1 (en) * 1994-02-01 1995-08-04 Rolls Royce Plc Thrust reverser for a gas turbine engine with ducted fan.
US5791877A (en) * 1995-09-21 1998-08-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Damping disposition for rotor vanes
JP2001132407A (en) * 1999-09-17 2001-05-15 General Electric Co <Ge> Composite blade root mounting device
US6832896B1 (en) * 2001-10-24 2004-12-21 Snecma Moteurs Blade platforms for a rotor assembly
US20050084379A1 (en) * 2003-06-06 2005-04-21 Karl Schreiber Compressor blade root for engine blades of aircraft engines
EP1312756A3 (en) * 2001-11-14 2006-02-01 United Technologies Corporation Blade for turbine engine
EP1970538A1 (en) * 2007-03-16 2008-09-17 Snecma Turbomachine rotor disc
US20110103960A1 (en) * 2009-11-03 2011-05-05 General Electric Company Apparatus and method for reducing wear in disk lugs
US20120263595A1 (en) * 2011-04-14 2012-10-18 Rolls-Royce Plc Annulus filler system
US20130052020A1 (en) * 2011-08-23 2013-02-28 General Electric Company Coupled blade platforms and methods of sealing
US20130330196A1 (en) * 2012-06-07 2013-12-12 United Technologies Corporation Fan blade platform
US20140286781A1 (en) * 2013-01-11 2014-09-25 United Technologies Corporation Integral fan blade wear pad and platform seal
US20150118055A1 (en) * 2013-10-31 2015-04-30 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
EP3913190A1 (en) * 2020-05-21 2021-11-24 Raytheon Technologies Corporation Airfoil attachment for gas turbine engines

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2772854A (en) * 1951-02-27 1956-12-04 Rateau Soc Vibration damping means for bladings of turbo-machines
US2819869A (en) * 1950-05-02 1958-01-14 Jr Andre J Meyer Mounting arrangement for turbine or compressor blading
US2997274A (en) * 1953-04-13 1961-08-22 Morgan P Hanson Turbo-machine blade vibration damper

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2819869A (en) * 1950-05-02 1958-01-14 Jr Andre J Meyer Mounting arrangement for turbine or compressor blading
US2772854A (en) * 1951-02-27 1956-12-04 Rateau Soc Vibration damping means for bladings of turbo-machines
US2997274A (en) * 1953-04-13 1961-08-22 Morgan P Hanson Turbo-machine blade vibration damper

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4452564A (en) * 1981-11-09 1984-06-05 The Garrett Corporation Stator vane assembly and associated methods
US5222865A (en) * 1991-03-04 1993-06-29 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
US5193982A (en) * 1991-07-17 1993-03-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Separate inter-blade platform for a bladed rotor disk
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
FR2715695A1 (en) * 1994-02-01 1995-08-04 Rolls Royce Plc Thrust reverser for a gas turbine engine with ducted fan.
US5791877A (en) * 1995-09-21 1998-08-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Damping disposition for rotor vanes
JP2001132407A (en) * 1999-09-17 2001-05-15 General Electric Co <Ge> Composite blade root mounting device
US6290466B1 (en) * 1999-09-17 2001-09-18 General Electric Company Composite blade root attachment
SG87167A1 (en) * 1999-09-17 2002-03-19 Gen Electric Composite blade root attachment
EP1085172A3 (en) * 1999-09-17 2003-09-17 General Electric Company Composite blade root attachment
US6832896B1 (en) * 2001-10-24 2004-12-21 Snecma Moteurs Blade platforms for a rotor assembly
US20040258528A1 (en) * 2001-10-24 2004-12-23 Snecma Moteurs Blade platforms for a rotor assembly
EP1312756A3 (en) * 2001-11-14 2006-02-01 United Technologies Corporation Blade for turbine engine
US20050084379A1 (en) * 2003-06-06 2005-04-21 Karl Schreiber Compressor blade root for engine blades of aircraft engines
FR2913735A1 (en) * 2007-03-16 2008-09-19 Snecma Sa ROTOR DISC OF A TURBOMACHINE
US20080226457A1 (en) * 2007-03-16 2008-09-18 Snecma Turbomachine rotor disk
EP1970538A1 (en) * 2007-03-16 2008-09-17 Snecma Turbomachine rotor disc
US8277188B2 (en) 2007-03-16 2012-10-02 Snecma Turbomachine rotor disk
US20110103960A1 (en) * 2009-11-03 2011-05-05 General Electric Company Apparatus and method for reducing wear in disk lugs
US8282356B2 (en) * 2009-11-03 2012-10-09 General Electric Company Apparatus and method for reducing wear in disk lugs
US9145784B2 (en) * 2011-04-14 2015-09-29 Rolls-Royce Plc Annulus filler system
US20120263595A1 (en) * 2011-04-14 2012-10-18 Rolls-Royce Plc Annulus filler system
EP2511480A3 (en) * 2011-04-14 2017-04-19 Rolls-Royce plc Annulus filler system
US20130052020A1 (en) * 2011-08-23 2013-02-28 General Electric Company Coupled blade platforms and methods of sealing
US8888459B2 (en) * 2011-08-23 2014-11-18 General Electric Company Coupled blade platforms and methods of sealing
US20130330196A1 (en) * 2012-06-07 2013-12-12 United Technologies Corporation Fan blade platform
US9017033B2 (en) * 2012-06-07 2015-04-28 United Technologies Corporation Fan blade platform
US20140286781A1 (en) * 2013-01-11 2014-09-25 United Technologies Corporation Integral fan blade wear pad and platform seal
US9650902B2 (en) * 2013-01-11 2017-05-16 United Technologies Corporation Integral fan blade wear pad and platform seal
US20150118055A1 (en) * 2013-10-31 2015-04-30 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
US9896946B2 (en) * 2013-10-31 2018-02-20 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
EP3913190A1 (en) * 2020-05-21 2021-11-24 Raytheon Technologies Corporation Airfoil attachment for gas turbine engines

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