GB1453519A - Apparatus for varying the stagger angle of the fan blades of a rotor wheel of a gas turbine ducted fan engine - Google Patents

Apparatus for varying the stagger angle of the fan blades of a rotor wheel of a gas turbine ducted fan engine

Info

Publication number
GB1453519A
GB1453519A GB418074A GB418074A GB1453519A GB 1453519 A GB1453519 A GB 1453519A GB 418074 A GB418074 A GB 418074A GB 418074 A GB418074 A GB 418074A GB 1453519 A GB1453519 A GB 1453519A
Authority
GB
United Kingdom
Prior art keywords
fan
blades
fan blades
gas turbine
movement
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
GB418074A
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.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of GB1453519A publication Critical patent/GB1453519A/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
    • 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

1453519 Gas turbine ducted fan engines MOTOREN-UND TURBINEN-UNION MUNCHEN GmbH 29 Jan 1974 [16 Feb 1973] 04180/74 Heading F1C and F1J The invention relates to a gas turbine ducted fan engine and to means for varying the pitch of the fan blades thereof, the fan blades being mounted on a rotor which carries also another row of blades such as compressor or turbine blades. In the embodiment, the rotor 1 comprises an inner row of compressor blades 2 which are disposed in the flow-path 3 and an outer row of fan blades 4 which are disposed in the fan duct 5, the fan blades being formed with spindles 28 which are mounted for angular movement by means of needle bearings 31 in structure 29 mounted at the tips of the compressor blades 2. A lever 27 is secured to the platform portion of each fan blade, the levers of all the fan blades being pivotally connected to projections 25 formed at the periphery of a ring member 24 which is arranged to rotate with the rotor 1 being connected to the inner race 19 of a bearing assembly 15. The bearing assembly 15 and so also the ring member is mounted for axial movement, such movement causing variation in pitch of the fan blades as indicated in Fig. 3. A series of actuators 8 are fixedly mounted within a space 7 defined between the inner air-flow duct 3 and the outer fan flow duct 5, the actuators being mounted on stator structure 9. The rod 10 of each actuator is connected to annular structure 18' which is mounted for axial movement within a fixed cylindrical member 17, 20, 16, 18 secured to stator structure. The outer race 14 of the bearing assembly 15 is mounted in an annular member 13 which is secured to the annular structure and is guided for axial sliding movement within the part 20 of the cylindrical member by means of interengaging splines 21, 21'. Thus axial movement of the pistonrods 10 causes axial movement of the rotating ring member 24 and so variation in pitch of the fan blades 4.
GB418074A 1973-02-16 1974-01-29 Apparatus for varying the stagger angle of the fan blades of a rotor wheel of a gas turbine ducted fan engine Expired GB1453519A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2307656A DE2307656C3 (en) 1973-02-16 1973-02-16 Device for adjusting the fan blades of an impeller for turbine jet engines

Publications (1)

Publication Number Publication Date
GB1453519A true GB1453519A (en) 1976-10-27

Family

ID=5872104

Family Applications (1)

Application Number Title Priority Date Filing Date
GB418074A Expired GB1453519A (en) 1973-02-16 1974-01-29 Apparatus for varying the stagger angle of the fan blades of a rotor wheel of a gas turbine ducted fan engine

Country Status (4)

Country Link
US (1) US3869221A (en)
DE (1) DE2307656C3 (en)
FR (1) FR2218471B3 (en)
GB (1) GB1453519A (en)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2501813B1 (en) * 1981-03-13 1986-06-13 Amiot Expl Procedes Felix IMPROVEMENTS IN DEVICES FOR SELECTIVELY COUPLING TO A DRIVING SHAFT TWO SEPARATE DRIVING ORGANS
US4534705A (en) * 1983-01-21 1985-08-13 Selestam Rune K Horizontal-shaft wind turbine with few blades
FR2542695B1 (en) * 1983-03-18 1985-07-26 Aerospatiale MULTI-BLADE PROPELLER WITH VARIABLE PITCH WITH BLADES IN COMPOSITE MATERIALS INDIVIDUALLY REMOVABLE, PROCESS FOR MANUFACTURING SUCH BLADES AND BLADES THUS REALIZED
US4842484A (en) * 1983-08-29 1989-06-27 General Electric Company Blade gearing and pitch changing mechanisms for coaxial counterrotating propellers
GB2145777B (en) * 1983-08-29 1987-07-22 Gen Electric Aircraft propeller system
US4657484A (en) * 1984-09-04 1987-04-14 General Electric Company Blade pitch varying means
DE3514354A1 (en) * 1985-04-20 1986-10-23 MTU Motoren- und Turbinen-Union München GmbH, 8000 München COOLED GAS TURBINE WITH LOAD-ADJUSTABLE COOLING AIR AMOUNT
GB2199378B (en) * 1986-12-24 1991-02-13 Rolls Royce Plc Pitch change arrangement for a variable pitch fan
US4718823A (en) * 1987-02-24 1988-01-12 United Technologies Corporation Pitch changing mechanism for fan blades
US6071076A (en) * 1997-12-16 2000-06-06 General Electric Company Actuation system for a gas turbine rotor blade
FR2946011B1 (en) * 2009-05-29 2013-01-11 Snecma MOBILE ROLLER DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSOR
FR2946012B1 (en) * 2009-05-29 2011-06-24 Snecma DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSEUR
FR2946010B1 (en) * 2009-05-29 2011-06-24 Snecma FIXED CYLINDER DEVICE FOR CONTROLLING BLOWER BLADES OF A TURBOPROPULSER
FR2956378B1 (en) * 2010-02-15 2012-05-11 Snecma TURBOPROPULSER WITH A PULSE ORIENTATION DEVICE
FR2957329B1 (en) 2010-03-15 2012-08-03 Snecma VARIABLE BLADE TIMING MECHANISM FOR A CONTRAROTATIVE PROPELLER SYSTEM AND A CONTRAROTATIVE PROPELLER SYSTEM COMPRISING AT LEAST ONE SUCH MECHANISM
FR2980770B1 (en) * 2011-10-03 2014-06-27 Snecma AIRBORNE TURBINE ENGINE (S) FOR AIRCRAFT WITH SYSTEM FOR CHANGING THE PROPELLER STEP.
DE102012000889A1 (en) * 2012-01-18 2013-07-18 Rolls-Royce Deutschland Ltd & Co Kg Air turbine with adjustable fan
FR2997138B1 (en) * 2012-10-18 2014-11-14 Snecma DEVICE AND METHOD FOR CONTROLLING THE SHIFT OF THE BLADES
US10221706B2 (en) * 2015-11-17 2019-03-05 General Electric Company Variable pitch fan actuator
FR3046407B1 (en) * 2016-01-05 2022-03-25 Snecma FIXED CYLINDER DEVICE FOR A TURBOMACHINE FAN BLADES ORIENTATION CONTROL SYSTEM
US10801339B2 (en) * 2017-07-11 2020-10-13 General Electric Company Aircraft gas turbine engine variable fan blade mechanism
US20200017229A1 (en) * 2018-07-13 2020-01-16 Bell Helicopter Textron Inc. Fan clutch for convertible engine
FR3108142B1 (en) * 2020-03-11 2022-08-19 Safran Aircraft Engines Blade comprising a composite material structure and associated manufacturing method

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1942100A (en) * 1930-10-31 1934-01-02 Bendix Res Corp Propeller
US3476486A (en) * 1966-04-12 1969-11-04 Dowty Rotol Ltd Gas turbine engines
US3468473A (en) * 1966-05-25 1969-09-23 Dowty Rotol Ltd Gas turbine engines
GB1195964A (en) * 1966-12-05 1970-06-24 Rolls Royce Fan.
US3467198A (en) * 1966-12-05 1969-09-16 Rolls Royce Gear transmission
FR1555814A (en) * 1967-12-12 1969-01-31
GB1294898A (en) * 1969-12-13 1972-11-01

Also Published As

Publication number Publication date
FR2218471B3 (en) 1976-11-26
DE2307656B2 (en) 1978-05-11
DE2307656A1 (en) 1974-08-29
FR2218471A1 (en) 1974-09-13
DE2307656C3 (en) 1979-01-04
US3869221A (en) 1975-03-04

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee