US3515501A - Rotor blade assembly - Google Patents

Rotor blade assembly Download PDF

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US3515501A
US3515501A US720600A US3515501DA US3515501A US 3515501 A US3515501 A US 3515501A US 720600 A US720600 A US 720600A US 3515501D A US3515501D A US 3515501DA US 3515501 A US3515501 A US 3515501A
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blades
blade assembly
fibers
rotor
recesses
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US720600A
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Jack Palfreyman
Henry Edward Middleton
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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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

Definitions

  • the invention concerns a method of making a rotor blade assembly comprising forming at least one row of angularly spaced apart blades, and interconnecting the root portions of the blades by means of at least one length of fibrous material through which are transmitted centrifugal stresses produced on rotation of the assembly.
  • This invention concerns a method of making a rotor blade assembly, for example a bladed rotor of a gas turbine engine.
  • a method of making a rotor blade assembly comprising forming at least one row of radially extending, fiber reinforced, angularly spaced apart rotor blades, each of said rotor blades having a root portion with at least one recess defined in the outer surfaces thereof, said recesses in said plurality of blades forming a continuous recess around the periphery of said blade assembly, winding a plurality of turns of the fibrous material circumferentially of said blade assembly in said recesses in a manner as to interconnect said root portions and in a manner such that centrifugal stresses produced on rotation of said blade assembly will be transmitted through said turns of said fibrous material and bonding said turns of said fibrous materials in said recesses.
  • the turns of fibrous material in addition to enabling the blade assembly to withstand centrifual stresses produced on rotation thereof, interconnect the blades by means of a construction which may be both stronger and lighter than that hitherto used.
  • each blade is preferably provided with two recesses which are respectively disposed on opposite sides of the blade profile.
  • the fibrous material preferably comprises carboniferous or boron fibers.
  • the fibers of the fibrous material may be coated with a synthetic resin material such, for example, as an epoxy, polyimide, polyquinoxaline or polythiazole resin.
  • the fibers may be coated with a metal or alloy.
  • the metal may be beryllium, cobalt, chromium, nickel, hafnium, niobium, osmium, paladium, platiniurn, rhenium, rhodium, tantalum or vanadium, while the said alloy may be a nickel-chromium alloy.
  • the fibers may be coated by passing them through a bath of the said metal or alloy.
  • the fibers may be coated by being electrolytically plated with the said metal or alloy.
  • the fibers may be coated by spraying or vacuum depositing the metal or alloy.
  • Carboniferous textile fibers may, for example, be passed through an oven and thence directly to the said bath.
  • the fibers, after passing through the said bath, may be wound directly about the said root portion.
  • the fibers which have been wound about the said root portions may thereafter be bonded thereto.
  • fibers which have been coated with a metal or plating brazing, electron beam Welding, or spraying with a metal or alloy.
  • the said blades may, if desired, be fiber-reinforced.
  • the invention also comprises a blade assembly when made by the method set forth above.
  • the invention also comprises a gas turbine engine provided with such a blade assembly.
  • the said gas turbine engine may have a blade assembly comprising a rotor drum which is provided externally with at least one row of fan blades and which is provided internally with a plurality of rows of rotatable guide blades of a compressor of the engine, the root portions of the said rows of rotatable guide blades being secured to the rotor drum by the said fibrous material.
  • FIG. 1 is a diagrammatic view illustrating the method of the present invention of making a blade assembly
  • FIG. 2 is a broken-away respective view of a part of the blade assembly made by the method illustrated in FIG. 1, and
  • FIG. 3 is a diagrammatic view, partly in section, of a gas turbine front fan engine having a blade assembly made by the said method.
  • a plurality of angularly spaced apart radially extending rotor blades 10 are held in juxtaposition by means of a jig (not shown) to form a rotor blade assembly comprising in this case a single row of blades.
  • each of the blades 10 has a root portion 12 having a curved radially inner surface 13 which forms a continuous cylindrical surface when the blades 10 are assembled.
  • Each of the root portions 12 is provided on opposite sides of its blade profile 14 with two recesses 15, 16 which extend to radially outer surfaces 17, 18 of the root portions 12.
  • the recesses 15 of the row of blades 10 are aligned with each other so as to form portions of, in effect, a single circumferentially extending recesses when the blades 10 are assembled, and which also extends about the root portions 12 of all the blades of the said row of blades.
  • the recesses 16 are similarly aligned with each other.
  • a metal or alloy e.g. an nickel-20% chromium alloy.
  • the fibers 21, after passing through the bath 23, are identical to The fibers 21, after passing through the bath 23, are identical to The fibers 21, after passing through the bath 23, are identical to The fibers 21, after passing through the bath 23, are identical to The fibers 21, after passing through the bath 23, are identical to The fibers 21, after passing through the bath 23, are identical to The fibers 21, after passing through the bath 23, are identical to The fibers 21, after passing through the bath 23, are identical to The fibers 21, after passing through the bath 23, are
  • fibers 21 being adapted to withstand centrifugal forces to which the rotor blades 10 are subjected in operation. As will be appreciated,each turn of the coated fibers 21, will then extend circumferentially of the blade assembly,
  • the jig is removed by placing the jig with its blades 10 in an electrolytic plating bath and bonding the coated fibers 21 to the root portions 12 by the plating material, the jig having been coatedwith an insulating material which will prevent the jig itself being plated.
  • the bonding may be effected by brazing, explosion welding, electron beam welding, laser welding, diffusion welding, or hot pressing. When this has been done, the jig is removed.
  • the blades may be secured to a rotor disc or drum (not shown) of conventional type, for example by bonding.
  • spacer members may be secured to the sides of the root portions 12 to form an integral rotor structure.
  • the blades 10 may be formed of conventional mate rials. Alternatively they may be made of coated fibers which may, for axample, be the same as the coated fibers 21.
  • the carboniferous fibers referred to above may be replaced by boron or other fibers, while the nickel-chromium alloy coating on the fibers 21 may be replaced by a coating of beryllium, cobalt, chromium, nickel, haf nium, niobium, osmium, paladium, platinum, rhenium, rhodium, tantalum or vanadium.
  • the coating metal is chosen having regard to its mechanical properties at the temperature at which the bladed rotor is to operate.
  • a synthetic resin material such as an epoxy, polyimide, polyquinoxaline, or polythiazole resin.
  • the rotor blade assembly may comprise a plurality of rows of blades 10, some of the fibers 21 being arranged to extend over and to be drivingly connected to the portions of the outer surfaces 17, 18 of the root portions 12 between the adjacent recesses 15, 16.
  • the rotor blade assembly illustrated in FIGS. 1 and 2 is particularly suitable for use in the rotor of a compressor of a gas turbine engine, although it may also be used in the construction of the turbine thereof.
  • FIG. 3 there is illustrated, diagrammatically, one particular gas turbine engine, part of which may be made by the method illustrated in FIGS. 1 and 2.
  • FIG. 3 there is shown a gas turbine engine 24 which is provided with an engine casing 25 within which there are arranged in flow series, intake struts 26, a compressor 27, outlet guide vanes 28, combustion equipment 29, nozzle guide vanes 30, and a turbine 31.
  • the compressor 27 has three axially spaced rows of rotor blades 34, which are driven by the turbine 31 by way of a shaft 35.
  • the compressor 27 is also provided with four axially spaced rows of rotatable guide blades 36 which form, in eifect, stators of the compressor 27.
  • the rows of blades 36 are provided internally of a rotor drum 40, the drum 40 being provided externally with a row of fan blades 41 of a front fan 42.
  • the blades 41 are mounted within a fan duct 43 which is defined between the rotor drum 40 and an outer casing 44, the latter being supported from the casing 25 by way of front and rear struts 45, 46 respectively.
  • the air passing through and being compressed by the rotor blades 34 of the compressor 27 is arranged to drive the rotatable guide blades 36 which thus in turn drive the fan blades 41.
  • the rotatable guide blades 36 are of the form illustrated in FIGS. 1 and 2 and are interconnected by the fibers 21.
  • a method of making a rotor blade assembly comprising forming at least one row of radially extending, fiber reinforced, angularly spaced apart rotor blades, each.
  • said rotor blades having a root portion with at least one recess defined in the outer surface thereof, said recesses in said plurality of blades forming a continuous recess around the periphery of said blade assembly,
  • a rotor blade assembly comprising at least one row of radially extending, fiber reinforced, angularly spaced apart rotor blades, each of said rotor blades having a root portion with at least one recess defined in the outer surface thereof, said recesses in said plurality of blades forming a continuous recess around the periphery of said blade assembly, and
  • a method as claimed in claim 8 comprising the additional step of passing carboniferous textile fibers through an oven and thence directly to said bath.

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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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

June 2, 1970 J'. PALFREYMAN ETAL ,5 5,
- ROTOR BLADE ASSEMBLY Filed April 11, 1968 SSheets-Shet 1' Inventors A Home 3,15
June 2, 1970 J. PALFREYMAN ETAL ,5 0
ROTQR BLADE ASSEMBLY Filed April 11, 1968 l 3 Sheets-Sheet 2 Inveniors (,ZV/ WWI/MAW WWW W Aurneys 5mm 2, 1970 J. PALF'REYMAN ETAL 3,515,501
ROTOR BLADE ASSEMBLY 3 Sheets-Sheet 5 Filed April 13., 3.968
Inventors AHorneyQ- United States Patent ()ffice 3,515,501 Patented June 2, 1970 3,515,501 ROTOR BLADE ASSEMBLY Jack Palfreyman, Tansley, near Matlock, Derby, and Henry Edward Middleton, Derby, England, assignors to Rolls-Royce Limited, Derby, England, a British company Filed Apr. 11, 1968, Ser. No. 720,600 Claims priority, application Great Britain, Apr. 12, 1967, 16,873/ 67 Int. Cl. F01d /24 US. Cl. 416-193 11 Claims ABSTRACT OF THE DISCLOSURE The invention concerns a method of making a rotor blade assembly comprising forming at least one row of angularly spaced apart blades, and interconnecting the root portions of the blades by means of at least one length of fibrous material through which are transmitted centrifugal stresses produced on rotation of the assembly.
This invention concerns a method of making a rotor blade assembly, for example a bladed rotor of a gas turbine engine.
According to the present invention, there is provided a method of making a rotor blade assembly comprising forming at least one row of radially extending, fiber reinforced, angularly spaced apart rotor blades, each of said rotor blades having a root portion with at least one recess defined in the outer surfaces thereof, said recesses in said plurality of blades forming a continuous recess around the periphery of said blade assembly, winding a plurality of turns of the fibrous material circumferentially of said blade assembly in said recesses in a manner as to interconnect said root portions and in a manner such that centrifugal stresses produced on rotation of said blade assembly will be transmitted through said turns of said fibrous material and bonding said turns of said fibrous materials in said recesses.
As will be appreciated, the turns of fibrous material in addition to enabling the blade assembly to withstand centrifual stresses produced on rotation thereof, interconnect the blades by means of a construction which may be both stronger and lighter than that hitherto used.
The root portion of each blade is preferably provided with two recesses which are respectively disposed on opposite sides of the blade profile.
After the said blades have been wound in the said recesses, they may be compacted therein.
The fibrous material preferably comprises carboniferous or boron fibers.
The fibers of the fibrous material may be coated with a synthetic resin material such, for example, as an epoxy, polyimide, polyquinoxaline or polythiazole resin.
Alternatively, the fibers may be coated with a metal or alloy. Thus, the metal may be beryllium, cobalt, chromium, nickel, hafnium, niobium, osmium, paladium, platiniurn, rhenium, rhodium, tantalum or vanadium, while the said alloy may be a nickel-chromium alloy.
The fibers may be coated by passing them through a bath of the said metal or alloy. Thus the fibers may be coated by being electrolytically plated with the said metal or alloy. Alternatively, the fibers may be coated by spraying or vacuum depositing the metal or alloy.
Carboniferous textile fibers may, for example, be passed through an oven and thence directly to the said bath.
The fibers, after passing through the said bath, may be wound directly about the said root portion.
The fibers which have been wound about the said root portions may thereafter be bonded thereto. Thus, in the case of fibers which have been coated with a metal or plating, brazing, electron beam Welding, or spraying with a metal or alloy.
The said blades may, if desired, be fiber-reinforced.
The invention also comprises a blade assembly when made by the method set forth above. Moreover, the invention also comprises a gas turbine engine provided with such a blade assembly. Thus, the said gas turbine engine may have a blade assembly comprising a rotor drum which is provided externally with at least one row of fan blades and which is provided internally with a plurality of rows of rotatable guide blades of a compressor of the engine, the root portions of the said rows of rotatable guide blades being secured to the rotor drum by the said fibrous material.
The invention is illustrated, merely by way of example, in the accompanying drawings, in which:
FIG. 1 is a diagrammatic view illustrating the method of the present invention of making a blade assembly,
FIG. 2 is a broken-away respective view of a part of the blade assembly made by the method illustrated in FIG. 1, and
FIG. 3 is a diagrammatic view, partly in section, of a gas turbine front fan engine having a blade assembly made by the said method.
Referring first to FIG. 1, a plurality of angularly spaced apart radially extending rotor blades 10 are held in juxtaposition by means of a jig (not shown) to form a rotor blade assembly comprising in this case a single row of blades.
As best shown in FIG. 2, each of the blades 10 has a root portion 12 having a curved radially inner surface 13 which forms a continuous cylindrical surface when the blades 10 are assembled. Each of the root portions 12 is provided on opposite sides of its blade profile 14 with two recesses 15, 16 which extend to radially outer surfaces 17, 18 of the root portions 12.
The recesses 15 of the row of blades 10 are aligned with each other so as to form portions of, in effect, a single circumferentially extending recesses when the blades 10 are assembled, and which also extends about the root portions 12 of all the blades of the said row of blades. The recesses 16 are similarly aligned with each other.
Carboniferous textile fibers 21, e.g. as suggested in our copending British patent applications Nos. 14,476/ 65 and 49,850/ 65, are passed through an oven 22 and are thence passed directly to an electrolytic plating bath 23 where the fibers are plated electrolytically with a metal or alloy, e.g. an nickel-20% chromium alloy.
The fibers 21, after passing through the bath 23, are
' then Wound directly about the root portions 12 of the row of blades 10 by winding a large number of turns of the coated fibers 21 in each of the recesses 15, 16, egg. by rotating the blade assembly about its axis of rotation. In this way the root portions 12 are interconnected, the
, fibers 21 being adapted to withstand centrifugal forces to which the rotor blades 10 are subjected in operation. As will be appreciated,each turn of the coated fibers 21, will then extend circumferentially of the blade assembly,
and will extend about the root portions 12 of all the in the recesses 15, 16 are thereafter bonded therein. This may be done before the jig is removed by placing the jig with its blades 10 in an electrolytic plating bath and bonding the coated fibers 21 to the root portions 12 by the plating material, the jig having been coatedwith an insulating material which will prevent the jig itself being plated. Alternatively, the bonding may be effected by brazing, explosion welding, electron beam welding, laser welding, diffusion welding, or hot pressing. When this has been done, the jig is removed.
During or after assembly the blades may be secured to a rotor disc or drum (not shown) of conventional type, for example by bonding. Alternatively spacer members (not shown) may be secured to the sides of the root portions 12 to form an integral rotor structure.
The blades 10 may be formed of conventional mate rials. Alternatively they may be made of coated fibers which may, for axample, be the same as the coated fibers 21.
The carboniferous fibers referred to above may be replaced by boron or other fibers, while the nickel-chromium alloy coating on the fibers 21 may be replaced by a coating of beryllium, cobalt, chromium, nickel, haf nium, niobium, osmium, paladium, platinum, rhenium, rhodium, tantalum or vanadium. The coating metal is chosen having regard to its mechanical properties at the temperature at which the bladed rotor is to operate.
Moreover, the fibers 21, instead of being coated with a metal or alloy, may be coated with a synthetic resin material such as an epoxy, polyimide, polyquinoxaline, or polythiazole resin. In this case, however, after the fibers 21 have been wound into the recesses 15, 16 they are resin bonded therein by injecting further synthetic resin material.
If desired, the rotor blade assembly may comprise a plurality of rows of blades 10, some of the fibers 21 being arranged to extend over and to be drivingly connected to the portions of the outer surfaces 17, 18 of the root portions 12 between the adjacent recesses 15, 16.
The rotor blade assembly illustrated in FIGS. 1 and 2 is particularly suitable for use in the rotor of a compressor of a gas turbine engine, although it may also be used in the construction of the turbine thereof.
In FIG. 3, there is illustrated, diagrammatically, one particular gas turbine engine, part of which may be made by the method illustrated in FIGS. 1 and 2.
In FIG. 3 there is shown a gas turbine engine 24 which is provided with an engine casing 25 within which there are arranged in flow series, intake struts 26, a compressor 27, outlet guide vanes 28, combustion equipment 29, nozzle guide vanes 30, and a turbine 31.
The compressor 27 has three axially spaced rows of rotor blades 34, which are driven by the turbine 31 by way of a shaft 35. The compressor 27 is also provided with four axially spaced rows of rotatable guide blades 36 which form, in eifect, stators of the compressor 27. The rows of blades 36 are provided internally of a rotor drum 40, the drum 40 being provided externally with a row of fan blades 41 of a front fan 42. The blades 41 are mounted within a fan duct 43 which is defined between the rotor drum 40 and an outer casing 44, the latter being supported from the casing 25 by way of front and rear struts 45, 46 respectively.
The air passing through and being compressed by the rotor blades 34 of the compressor 27 is arranged to drive the rotatable guide blades 36 which thus in turn drive the fan blades 41.
The rotatable guide blades 36 are of the form illustrated in FIGS. 1 and 2 and are interconnected by the fibers 21.
We claim:
1. A method of making a rotor blade assembly comprising forming at least one row of radially extending, fiber reinforced, angularly spaced apart rotor blades, each.
of said rotor blades having a root portion with at least one recess defined in the outer surface thereof, said recesses in said plurality of blades forming a continuous recess around the periphery of said blade assembly,
winding a plurality of turns of a fibrous material circumferentially of said blade assembly in said recesses in a manner as to interconnect said root portions and in a manner such that centrifugal stresses produced on rotation of said blade assembly will be transmitted through said turns of fibrous material and bonding said turns of said fibrous materials in said recesses.
2. A rotor blade assembly comprising at least one row of radially extending, fiber reinforced, angularly spaced apart rotor blades, each of said rotor blades having a root portion with at least one recess defined in the outer surface thereof, said recesses in said plurality of blades forming a continuous recess around the periphery of said blade assembly, and
a plurality of turns of a fibrous material wound circumferentially of said blade assembly in said recesses and bonded in said recesses in a manner as to interconnect said root portions and in a manner such that centrifugal stresses produced on rotation of said blade assembly will be transmitted through said turns of fibrous material.
3. A blade assembly comprising a rotor drum having mounted externally thereon at least one row of fan blades and having mounted internally thereon a plurality of rows of rotatable guide blades of a gas turbine engine compressor,
each of said rotatable guide blades having a root portion with at least one recess defined in the outer surface thereof such that said recesses in the rotatable guide blades forming each of said rows forms a continuous recess around the periphery of each of said rows,
a plurality of turns of a fibrous material wound circumferentially of each of said rows in said recesses and bonded therein in a manner as to connect said root portions in each of said rows and in a manner such that centrifugal stresses produced on rotation of said rotor drum will be transmitted through said turns of said fibrous material, said root portion of said rows of rotatable guide blades being secured to the rotor drum by said fibrous material.
4. A method as claimed in claim 1 in which the root portion of each blade is provided with two of said recesses which are respectively disposed on opposite sides of the blade profile.
5. A method as claimed in claim 4 in which, after the said turns have been'wound in the said recesses, they are compacted therein.
6. A method as claimed in claim 1 comprising the additional step of coating the fibers of the fibrous material with a synthetic resin material.
7. A method as claimed in claim 1 comprising the additional step of coating the fibers with a metal or alloy.
8. A method as claimed in claim 7 in which said coating step comprises passing the fibers through a bath of said metal or alloy.
9. A method as claimed in claim 8 in which the fibers are coated by being electrolytically plated with the said metal or alloy.
10. A method as claimed in claim 8 comprising the additional step of passing carboniferous textile fibers through an oven and thence directly to said bath.
11. A method as claimed in claim 8 in which the fibers, after passing through the said bath, are passed directly to the said root portions.
References Cited UNITED STATES PATENTS (Other references on following page) 5 References Cited 6 FOREIGN PATENTS 611,006 12/1960 Canada.
EVERETTE A. POWELL, JR., Primary Examiner Secord et a1.
Erwin.
Neumann 25377.2 Martin et a1.
Banger et a1.
Blackhurst et a1.
US. C1. X.R.
US720600A 1967-04-12 1968-04-11 Rotor blade assembly Expired - Lifetime US3515501A (en)

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GB06873/67A GB1170593A (en) 1967-04-12 1967-04-12 Method of making a Bladed Rotor

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US3610772A (en) * 1970-05-04 1971-10-05 Gen Motors Corp Bladed rotor
US3801221A (en) * 1970-09-21 1974-04-02 Seeber Willi Impeller and method for manufacturing said impeller
US3813185A (en) * 1971-06-29 1974-05-28 Snecma Support structure for rotor blades of turbo-machines
US3905722A (en) * 1972-03-15 1975-09-16 Rolls Royce 1971 Ltd Fluid flow machines
US4080101A (en) * 1973-12-17 1978-03-21 Willi Seeber Bladed rotor for fans
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
DE3446732A1 (en) * 1984-12-21 1986-07-03 Süddeutsche Kühlerfabrik Julius Fr. Behr GmbH & Co KG, 7000 Stuttgart FAN WHEEL
US4676722A (en) * 1983-01-26 1987-06-30 Arap-Applications Rationnelles De La Physique High peripheral speed wheel for a centrifugal compressor including fiber loaded scoops and a method of making such a wheel
US4762466A (en) * 1986-10-22 1988-08-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Carrier ring for a propeller blade system
US4840536A (en) * 1987-04-07 1989-06-20 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Axial guide blade assembly for a compressor stator
GB2229230A (en) * 1988-12-29 1990-09-19 Gen Electric Ring for supporting aircraft propeller
DE19525829A1 (en) * 1995-07-15 1997-01-16 Abb Research Ltd Fan
US5941688A (en) * 1996-11-07 1999-08-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Fibre-reinforced rotor stage for a turbomachine
US5971706A (en) * 1997-12-03 1999-10-26 General Electric Company Inter-rotor bearing assembly
US6213720B1 (en) 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
US20030233822A1 (en) * 2002-04-25 2003-12-25 Guenter Albrecht Compressor in a multi-stage axial form of construction
US20070231144A1 (en) * 2006-04-03 2007-10-04 Karl Schreiber Axial-flow compressor for a gas turbine engine
US20100272565A1 (en) * 2009-04-22 2010-10-28 Kin-Leung Cheung Vane assembly with removable vanes
US8540482B2 (en) 2010-06-07 2013-09-24 United Technologies Corporation Rotor assembly for gas turbine 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
US9011098B2 (en) 2009-04-07 2015-04-21 Airbus Operations S.A.S. Propeller for an aircraft turbine engine comprising a vane retaining ring mounted about the hub
US20170363104A1 (en) * 2016-06-16 2017-12-21 Rolls-Royce North American Technologies, Inc. Composite rotatable assembly for an axial-flow compressor
US10294954B2 (en) * 2016-11-09 2019-05-21 Rolls-Royce North American Technologies Inc. Composite blisk

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FR2448626A1 (en) * 1979-02-08 1980-09-05 Snecma IMPROVEMENT IN ROTORS OF ROTATING MACHINES
DE2915201C2 (en) * 1979-04-14 1986-02-27 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Impeller for axial flow machines, in particular compressors
DE3037388C1 (en) * 1980-10-03 1982-06-16 Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5300 Bonn Bandage for the radial tensioning of the segments of a compressor impeller for gas turbines constructed from individual segments
DE3101250C2 (en) * 1981-01-16 1983-12-01 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Compressor rotor for gas turbine engines
DE4321173C2 (en) * 1993-06-25 1996-02-22 Inst Luft Kaeltetech Gem Gmbh Radial impeller
FR2712630B1 (en) * 1993-11-17 1995-12-15 Snecma Segmented turbomachine rotor.
DE10358421A1 (en) 2003-12-13 2005-07-07 Mtu Aero Engines Gmbh Rotor for a turbomachine
FR3057905B1 (en) * 2016-10-25 2020-06-12 Safran Aircraft Engines TURBOMACHINE TURNING PART
RU181073U1 (en) * 2018-01-09 2018-07-04 Федеральное государственное бюджетное образовательное учреждение высшего образования "Санкт-Петербургский государственный архитектурно-строительный университет" AXIAL COMPRESSOR DRUM TYPE ROTOR
CN114934815B (en) * 2022-05-12 2023-10-31 中国航发四川燃气涡轮研究院 Metal matrix composite hoop type engine rotor blade ring structure

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US3610772A (en) * 1970-05-04 1971-10-05 Gen Motors Corp Bladed rotor
US3801221A (en) * 1970-09-21 1974-04-02 Seeber Willi Impeller and method for manufacturing said impeller
US3813185A (en) * 1971-06-29 1974-05-28 Snecma Support structure for rotor blades of turbo-machines
US3905722A (en) * 1972-03-15 1975-09-16 Rolls Royce 1971 Ltd Fluid flow machines
US4080101A (en) * 1973-12-17 1978-03-21 Willi Seeber Bladed rotor for fans
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
US4676722A (en) * 1983-01-26 1987-06-30 Arap-Applications Rationnelles De La Physique High peripheral speed wheel for a centrifugal compressor including fiber loaded scoops and a method of making such a wheel
DE3446732A1 (en) * 1984-12-21 1986-07-03 Süddeutsche Kühlerfabrik Julius Fr. Behr GmbH & Co KG, 7000 Stuttgart FAN WHEEL
US4762466A (en) * 1986-10-22 1988-08-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Carrier ring for a propeller blade system
US4840536A (en) * 1987-04-07 1989-06-20 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Axial guide blade assembly for a compressor stator
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US5941688A (en) * 1996-11-07 1999-08-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Fibre-reinforced rotor stage for a turbomachine
US5971706A (en) * 1997-12-03 1999-10-26 General Electric Company Inter-rotor bearing assembly
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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
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US7918644B2 (en) 2006-04-03 2011-04-05 Rolls-Royce Deutschland Ltd & Co Kg Axial-flow compressor for a gas turbine engine
US9011098B2 (en) 2009-04-07 2015-04-21 Airbus Operations S.A.S. Propeller for an aircraft turbine engine comprising a vane retaining ring mounted about the hub
US8182213B2 (en) 2009-04-22 2012-05-22 Pratt & Whitney Canada Corp. Vane assembly with removable vanes
US20100272565A1 (en) * 2009-04-22 2010-10-28 Kin-Leung Cheung Vane assembly with removable vanes
US8540482B2 (en) 2010-06-07 2013-09-24 United Technologies Corporation Rotor assembly for gas turbine engine
US20170363104A1 (en) * 2016-06-16 2017-12-21 Rolls-Royce North American Technologies, Inc. Composite rotatable assembly for an axial-flow compressor
US10710317B2 (en) * 2016-06-16 2020-07-14 Rolls-Royce North American Technologies Inc. Composite rotatable assembly for an axial-flow compressor
US10294954B2 (en) * 2016-11-09 2019-05-21 Rolls-Royce North American Technologies Inc. Composite blisk

Also Published As

Publication number Publication date
DE1751156A1 (en) 1970-10-01
GB1170593A (en) 1969-11-12
FR1575682A (en) 1969-07-25
CH497641A (en) 1970-10-15
BE713585A (en) 1968-08-16

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