GB1324385A - Supporting and angular adjusting structure for axially loaded shafts and variable blade angle bladed rotor structures - Google Patents

Supporting and angular adjusting structure for axially loaded shafts and variable blade angle bladed rotor structures

Info

Publication number
GB1324385A
GB1324385A GB5014370A GB5014370A GB1324385A GB 1324385 A GB1324385 A GB 1324385A GB 5014370 A GB5014370 A GB 5014370A GB 5014370 A GB5014370 A GB 5014370A GB 1324385 A GB1324385 A GB 1324385A
Authority
GB
United Kingdom
Prior art keywords
blade
disc
pinion
shaft
revolution
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
Application number
GB5014370A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1324385A publication Critical patent/GB1324385A/en
Expired legal-status Critical Current

Links

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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F04D29/323—Blade mountings adjustable
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources

Abstract

1324385 Axial-flow fans and compressors; gas turbine ducted fan engines GENERAL ELECTRIC CO 22 Oct 1970 [23 Oct 1969] 50143/70 Headings F1C F1J and FIT A variable pitch bladed rotor assembly, e.g. for the fan (as shown) or the fan turbine of a turbofan engine or for the compressor or turbine of a gas generator, comprises a disc 28, Figs.1 and 4, fixed to shaft 24, and a disc 30 rotatably mounted on the shaft. Each disc includes a respective surface of revolution 70, 72 about rotor axis 74, which co-operates with a respective surface of revolution 76, 78 formed on the blade root about blade axis 88. The curvature of surfaces 76, 78 is less than that of surfaces 70, 72 so that point contact is established therebetween. The surfaces 70, 72, 76, 78 are part spherical, but the surfaces 70, 72 instead may be frusto-conical and the surfaces 76, 78 segments of other surfaces of revolution about the blade axis. Annular ledges 110 maintain the radial position of the blades when the rotor is at rest. Each blade root carries a respective pinion 90 in mesh with gear rings 92, 94 on discs 28, 30. The blade root is connected to the pinion by a member 100 which has radial arms 102 engaging a recess in the pinion and which is adequately flexible to isolate the pinion from blade loadings. Moreover, the blade root has a pair of lugs (96), Fig. 5 (not shown), received in slots (98) in the pinion. Pitch adjustment of the blade is effected by angularly moving the disc 30 about the shaft 24 by means 38 comprising a series of circumferentially-spaced fluid-actuated adjustors (113), Fig.6 (not shown). Blade platforms 50 have curved upstream and downstream ends (58), Fig.2 (not shown), located in complementary scollops formed in a ring 52 movable relative to disc 28. The blades are retained in either of their two pitch limit positions by a mechanism 40, Figs. 1 and 7, having weighted links 120 which, due to centrifugal effects, maintain rings 117, 122, connected to disc 30 and shaft 24 respectively, in their chosen relative angular position. The mechanism may instead be arranged to operate unilaterally to bias the blades towards only one of the limit positions.
GB5014370A 1969-10-23 1970-10-22 Supporting and angular adjusting structure for axially loaded shafts and variable blade angle bladed rotor structures Expired GB1324385A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US86875369A 1969-10-23 1969-10-23

Publications (1)

Publication Number Publication Date
GB1324385A true GB1324385A (en) 1973-07-25

Family

ID=25352256

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5014370A Expired GB1324385A (en) 1969-10-23 1970-10-22 Supporting and angular adjusting structure for axially loaded shafts and variable blade angle bladed rotor structures

Country Status (2)

Country Link
CA (1) CA930670A (en)
GB (1) GB1324385A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2190964A (en) * 1986-05-28 1987-12-02 Messerschmitt Boelkow Blohm Combined turbojet, ramjet, rocket propulsion unit
US4732536A (en) * 1985-06-20 1988-03-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbo-machine compressor with variable incidence stator vanes
GB2237072A (en) * 1989-09-06 1991-04-24 Rolls Royce Plc A variable pitch arrangement for a gas turbine engine
WO1994009264A1 (en) * 1992-10-14 1994-04-28 ABB Fläkt Aktiebolag An angle adjustable vane suspension
GB2301868A (en) * 1995-06-05 1996-12-18 Rolls Royce Plc Actuator mechanism with emergency drive for variable angle vane arrays
US5630701A (en) * 1995-06-05 1997-05-20 Rolls-Royce Plc Variable angle vane arrays
FR2914944A1 (en) * 2007-04-13 2008-10-17 Snecma Sa High pressure compressor for e.g. jet prop engine of aircraft, has blades each including pivot connected to actuating ring by toothed wheel, where wheel is rotatably connected to pivot and engaged with corresponding gear teeth of ring
US8177493B2 (en) 2007-03-30 2012-05-15 Snecma Airtight external shroud for a turbomachine turbine wheel
EP3392461A1 (en) * 2017-04-21 2018-10-24 United Technologies Corporation Gas turbine engine and method of assembling a gas turbine engine
CN112360815A (en) * 2020-11-10 2021-02-12 沈观清 Adjustable stator mechanism for multistage ducted fan and control system of adjustable stator mechanism

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3108142B1 (en) * 2020-03-11 2022-08-19 Safran Aircraft Engines Blade comprising a composite material structure and associated manufacturing method
FR3115071B1 (en) * 2020-10-08 2023-12-22 Safran Aircraft Engines Composite blade and anti-rotation blade root attachment

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4732536A (en) * 1985-06-20 1988-03-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbo-machine compressor with variable incidence stator vanes
GB2190964A (en) * 1986-05-28 1987-12-02 Messerschmitt Boelkow Blohm Combined turbojet, ramjet, rocket propulsion unit
GB2237072A (en) * 1989-09-06 1991-04-24 Rolls Royce Plc A variable pitch arrangement for a gas turbine engine
GB2237072B (en) * 1989-09-06 1993-12-01 Rolls Royce Plc A variable pitch arrangement for a gas turbine engine
WO1994009264A1 (en) * 1992-10-14 1994-04-28 ABB Fläkt Aktiebolag An angle adjustable vane suspension
US5545011A (en) * 1992-10-14 1996-08-13 Abb Flakt Ab Angle adjustable vane suspension
CN1046572C (en) * 1992-10-14 1999-11-17 Abb.弗拉克特有限公司 An angle adjustable vane suspension
AU675255B2 (en) * 1992-10-14 1997-01-30 Abb Flakt Ab An angle adjustable vane suspension
US5620301A (en) * 1995-06-05 1997-04-15 Rolls-Royce Plc Actuator mechanism for variable angle vane arrays
US5630701A (en) * 1995-06-05 1997-05-20 Rolls-Royce Plc Variable angle vane arrays
GB2301868B (en) * 1995-06-05 1999-08-11 Rolls Royce Plc Improved actuator mechanism for variable angle vane arrays
GB2301868A (en) * 1995-06-05 1996-12-18 Rolls Royce Plc Actuator mechanism with emergency drive for variable angle vane arrays
US8177493B2 (en) 2007-03-30 2012-05-15 Snecma Airtight external shroud for a turbomachine turbine wheel
FR2914944A1 (en) * 2007-04-13 2008-10-17 Snecma Sa High pressure compressor for e.g. jet prop engine of aircraft, has blades each including pivot connected to actuating ring by toothed wheel, where wheel is rotatably connected to pivot and engaged with corresponding gear teeth of ring
EP3392461A1 (en) * 2017-04-21 2018-10-24 United Technologies Corporation Gas turbine engine and method of assembling a gas turbine engine
US10465701B2 (en) 2017-04-21 2019-11-05 United Technologies Corporation Variable pitch fan blade system
CN112360815A (en) * 2020-11-10 2021-02-12 沈观清 Adjustable stator mechanism for multistage ducted fan and control system of adjustable stator mechanism

Also Published As

Publication number Publication date
CA930670A (en) 1973-07-24

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee