US3719439A - Bladed rotor for a gas turbine engine - Google Patents

Bladed rotor for a gas turbine engine Download PDF

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Publication number
US3719439A
US3719439A US00131698A US3719439DA US3719439A US 3719439 A US3719439 A US 3719439A US 00131698 A US00131698 A US 00131698A US 3719439D A US3719439D A US 3719439DA US 3719439 A US3719439 A US 3719439A
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US
United States
Prior art keywords
blades
blade
gas turbine
turbine engine
bladed 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
US00131698A
Other languages
English (en)
Inventor
K Bracey
L Dawson
J Petrie
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
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
Publication of US3719439A publication Critical patent/US3719439A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like

Definitions

  • the present invention provides a bladed rotor having tie members which carry out this function in a simple fashion.
  • a bladed rotor for a gas turbine engine comprises a row of blades, each blade being connected to the next adjacent blade by an outwardly curved tie member attached to the blades by means of threaded extensions at each end of the tie member which pass through the respective blades and are retained by a spherically shaped convexly faced nut which co-operates with a spherically shaped concavely surfaced depression in the face of the blade opposite to the respective tie member.
  • the concavely surfaced depression is formed in a bushing which is sunk into the blade section.
  • Said tie members are preferably formed with a substantially aerofoil cross-section over at least part of their extent; thus the tie member may comprise a substantially cylindrical rod which is flattened over its central section.
  • the points of attachment of the ties to the blades are staggered so that under the effect of centrifugal force the tie members exert a force on the blades which acts against the tendency of the blades to untwist due to centrifugal effects.
  • the invention is particularly useful in the case of blades formed from fibre reinforced materials.
  • FIG. 1 is a frontal view of the fan of a gas turbine engine in accordance with the invention
  • FIG. 2 is a section through two adjacent blades of the fan of FIG. 1, and
  • FIG. 3 is a section on the line 33 of FIG. 2.
  • FIG. 1 there is shown a fan for a gas turbine engine "ice comprising a rotor 10 supporting a row of blades 11 which run in an annular shroud 12. The remainder of the engine and its drive to the fan is not shown, but is in accordance with conventional practice.
  • Each tie member 13 comprises a central outwardly curved portion 14 and a pair of threaded extensions 15 forming the ends of the curved portion.
  • the curved portion of the tie members is arranged to be of substantially aerofoil section.
  • the tie members are made from a rod which is flattened over its central portion, the flattened portion having its longest axis lying in the direction of the air flow. This has the effect of increasing the width of the tie member when seen in the FIG. 3 view.
  • the remaining cylindrical portions are threaded to form two threaded extensions 15.
  • the extensions 15 pass through flanged bushings ⁇ 16 which are buried in the blade section.
  • the bushes are provided with flanges to enable transfer of stresses into the blade section.
  • Each bushing has a concave part spherical face as shown at 17, and the face 17 is engaged by the convexly part spherical face of a self-locking nut 18 which is engaged with the threaded extension 15.
  • the tie members are fastened to the blades in a staggered fashion so that tension in the tie members cause a torque to be exerted on the blades, and it is arranged that the torque on the blades due to the tie members tends to counteract the torque due to the centrifugal loads on the blades which tend to untwist the blades.
  • the present invention provides a way in which adjacent blades of a row can be simply and easily tied together with a little aerodynamic interference and as little modification of the blade as is possible.
  • a bladed rotor for a gas turbine engine comprising: a row of blades, each of said blades at least having an aerofoil shaped part made of a fiber reinforced composite material; and means for connecting adjacent blades to each other, said means comprising at least one outwardly curved tie member connecting one blade to the next adjacent blade, said tie member having threaded extensions at each end thereof which extend through the fiber reinforced parts of the adjacent blade, a bushing sunk into the fiber reinforced part of each blade and through which one threaded extension of one of the tie members extends, each of said bushings having a spherically shaped concave face remote from the tie member, and a nut member for each of the threaded extensions of each end of each tie member, each said nut member including a spherically shaped convex face cooperating with the respective concave face in said bushing.
  • a bladed rotor as claimed in claim 1 in which there are two of said bushings sunk into each fiber reinforced part of each blade, each of said bushings having a flanged end in which said concavely part-spherical surface is provided, one of said bushings having its concavely partspherical surface facing opposition of the concavely partspherical surface of the other of said bushings.
  • each said tie member is formed with a substantially aerofoil cross-section over at least part of their extent.
  • each said tie member comprises a substantially cylindrical rod which is flattened over its central section.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00131698A 1970-04-10 1971-04-06 Bladed rotor for a gas turbine engine Expired - Lifetime US3719439A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1715470 1970-04-10

Publications (1)

Publication Number Publication Date
US3719439A true US3719439A (en) 1973-03-06

Family

ID=10090247

Family Applications (1)

Application Number Title Priority Date Filing Date
US00131698A Expired - Lifetime US3719439A (en) 1970-04-10 1971-04-06 Bladed rotor for a gas turbine engine

Country Status (5)

Country Link
US (1) US3719439A (2)
JP (1) JPS5217181B1 (2)
DE (1) DE2116883A1 (2)
FR (1) FR2089456A5 (2)
GB (1) GB1309646A (2)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4137008A (en) * 1977-09-21 1979-01-30 The United States Of America As Represented By The Secretary Of The Navy Adjustable blowing slot for circulation control airfoil
US20110274549A1 (en) * 2010-05-06 2011-11-10 General Electric Company Blade having asymmetrical mid-span structure portions and related bladed wheel structure
US11454122B2 (en) * 2018-08-03 2022-09-27 Ge Renewable Technologies Pre-formed plug with inter-blade profiles for hydraulic turbines

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5984638A (en) * 1994-08-12 1999-11-16 Elliott Turbomachinery Co., Inc. Turbomachine radial impeller vibration constraining and damping mechanism
GB9609721D0 (en) * 1996-05-09 1996-07-10 Rolls Royce Plc Vibration damping
DE102008052021A1 (de) * 2008-10-16 2010-04-22 Siemens Aktiengesellschaft Dämpfungseinrichtung für einen Laufschaufelkranz einer Axialturbine
DE102017203308A1 (de) * 2017-03-01 2018-09-06 Siemens Aktiengesellschaft Turbinenstufe mit Koppelelement

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4137008A (en) * 1977-09-21 1979-01-30 The United States Of America As Represented By The Secretary Of The Navy Adjustable blowing slot for circulation control airfoil
US20110274549A1 (en) * 2010-05-06 2011-11-10 General Electric Company Blade having asymmetrical mid-span structure portions and related bladed wheel structure
US11454122B2 (en) * 2018-08-03 2022-09-27 Ge Renewable Technologies Pre-formed plug with inter-blade profiles for hydraulic turbines
US11692445B2 (en) 2018-08-03 2023-07-04 Ge Renewable Technologies Pre-formed plug with inter-blade profiles for hydraulic turbines

Also Published As

Publication number Publication date
JPS5217181B1 (2) 1977-05-13
DE2116883A1 (de) 1971-11-11
FR2089456A5 (2) 1972-01-07
GB1309646A (en) 1973-03-14

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