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 engineInfo
- 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
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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
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.
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)
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 |
FR2946010B1 (en) * | 2009-05-29 | 2011-06-24 | Snecma | FIXED CYLINDER DEVICE FOR CONTROLLING BLOWER BLADES OF A TURBOPROPULSER |
FR2946012B1 (en) * | 2009-05-29 | 2011-06-24 | Snecma | DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSEUR |
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)
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 |
CH457976A (en) * | 1966-05-25 | 1968-06-15 | Dowty Rotol Ltd | Turboprop |
US3467198A (en) * | 1966-12-05 | 1969-09-16 | Rolls Royce | Gear transmission |
GB1195964A (en) * | 1966-12-05 | 1970-06-24 | Rolls Royce | Fan. |
FR1555814A (en) * | 1967-12-12 | 1969-01-31 | ||
GB1294898A (en) * | 1969-12-13 | 1972-11-01 |
-
1973
- 1973-02-16 DE DE2307656A patent/DE2307656C3/en not_active Expired
-
1974
- 1974-01-29 GB GB418074A patent/GB1453519A/en not_active Expired
- 1974-02-15 FR FR7405212A patent/FR2218471B3/fr not_active Expired
- 1974-02-19 US US443189A patent/US3869221A/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
FR2218471A1 (en) | 1974-09-13 |
FR2218471B3 (en) | 1976-11-26 |
DE2307656B2 (en) | 1978-05-11 |
DE2307656C3 (en) | 1979-01-04 |
US3869221A (en) | 1975-03-04 |
DE2307656A1 (en) | 1974-08-29 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB1453519A (en) | Apparatus for varying the stagger angle of the fan blades of a rotor wheel of a gas turbine ducted fan engine | |
US5035573A (en) | Blade tip clearance control apparatus with shroud segment position adjustment by unison ring movement | |
US11585354B2 (en) | Engine having variable pitch outlet guide vanes | |
GB1235006A (en) | Improvements in or relating to blading arrangements for turbo-machines | |
US3861822A (en) | Duct with vanes having selectively variable pitch | |
US2360130A (en) | High-speed propulsion plant | |
US3487992A (en) | Stator adjusting mechanism for axial flow compressors | |
GB1427983A (en) | Compound bearing for connecting a helicopter blade to helicopter rotor | |
US10533573B2 (en) | Fan module with variable pitch blades | |
US3873236A (en) | Fan with variable pitch blades and translating bearing actuation system | |
US11021230B2 (en) | Aircraft turbine engine with a pair of rotating and non-ducted propellers | |
GB2155110A (en) | High bypass ratio counter-rotating turbofan engine | |
GB1430596A (en) | Multi-bladed fans | |
US4021142A (en) | Pitch-change apparatus for a ducted thrust fan | |
US3870434A (en) | Gear arrangement for variable pitch fan | |
US4718823A (en) | Pitch changing mechanism for fan blades | |
US2842305A (en) | Compressor stator assembly | |
GB1306908A (en) | Helicopter rotor assembly | |
US3528752A (en) | Gas turbine engines | |
GB757230A (en) | Improvements in or relating to stator blade ring assemblies for axial flow compressors and the like | |
US3089679A (en) | Gas turbine nozzle suspension and adjustment | |
US2862654A (en) | Variable pitch guide vanes | |
US2972441A (en) | Variable blade system | |
US11085319B2 (en) | Gas turbine engine tip clearance control system | |
US2932440A (en) | Compressor blade adjustment means |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PCNP | Patent ceased through non-payment of renewal fee |