US3924404A - Apparatus for adjusting fan blades in a turbojet engine - Google Patents

Apparatus for adjusting fan blades in a turbojet engine Download PDF

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Publication number
US3924404A
US3924404A US353387A US35338773A US3924404A US 3924404 A US3924404 A US 3924404A US 353387 A US353387 A US 353387A US 35338773 A US35338773 A US 35338773A US 3924404 A US3924404 A US 3924404A
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US
United States
Prior art keywords
engine
annular piston
piston
compressed air
annular
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
US353387A
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English (en)
Inventor
Wolfgang Pollert
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 AG
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 USB353387I5 publication Critical patent/USB353387I5/en
Application granted granted Critical
Publication of US3924404A publication Critical patent/US3924404A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates to apparatus for changing the blade angle of fan blades in a turbojet engine of ductedfan construction
  • French Pat. No. 2,046,297 proposes to vary the angle of the fan blades in a turbojet engine of the above-discussed type by means of a complex planetary gear arranged within a centrally disposed member downstream of the hub of the compressor of the basic engine. At least one power shaft extends from said planetary gear and through the primary flow duct of this compressor to transfer the actuating movements from the gear to the fan blades via further geared arrangements in the space between the primary duct and the secondary duct.
  • a further disadvantage of said apparatus is that it will scarcely ensure uniformity and directness of transfer of the torque needed to operate the fan blades.
  • the present invention contemplates providing improved apparatus for operably changing the angle of the fan rotor blades of a turbojet engine of the ductedfan construction such that direct transfer of the actuating movement from the drive system to the fan blades is ensured at relatively little complexity, that uniform .transfer of the actuating moment and proper locking of the fan blades in all selected end positions is possible and that the drive system, as well as the actuating mechanism, will economize space.
  • the present invention also contemplates a novel arrangement of compressed air controlled actuating piston means for adjusting the fan blade angle and compressed air auxiliary piston means for controlling arresting plunger means to lock the fan blades in respective adjusting positions.
  • the present invention also contemplates a valving and conduit system for selectively supplying compressed air from a compressor rotor of the engine to actuate the actuating and auxiliary piston means.
  • the present invention also contemplates an electrical switching means for controlling a threeway valve of the valving and conduit system in response to the position of the actuating piston means.
  • the compressed air supplying system optimally connects the fixed and rotatable parts of the engine so as to minimize space and constructional expenditures while assuring a reliable control of the respective arresting plunger means and blade angle adjusting rack means.
  • an axial fan 1 essentially consists of variable-pitch rotor blades 2 and downstream of them, fixedly connected guide vanes 3.
  • An outer bypass casing 4 externally confines secondary or bypass duct 6 by its inner wall 5.
  • the unitary rotating portion of the axial fan 1 further comprises, read from left to right, a central member 8 having a flow-promoting leading edge contour 7, and a supporting means 9 to carry the variable-pitch fan rotor blades 2 which extends to form an inner wall section 10 of the secondary duct 6 between the fan rotor blades 2 and the bottom platforms 11 of the guide vanes 3.
  • Fixedly connected to the rotating portion of the axial fan 1 are further supporting blades 13 which extend through the primary duct 12 to form a unitary arrangement, through a centrally disposed enging hub 16, with an inner shaft 17 of the turbine engine.
  • Arranged in and extending through the primary duct 12 are stay vanes 14 dowmstream of supporting blades 13.
  • Hub 16 rotates along with shaft 17, blades 13, central member 8, blades 2, and below described piston housing 22 and piston 20.
  • the stay vanes 14 are followed by further compressor rotor blades 15 which connect, through a rotor disk 16', to a further shafting 18 which envelops the inner shaft 17.
  • the rotating unitary portion of the axial fan 1 further comprises and communicates with an annular piston 20 which extends coaxially to the longitudinal centerline 19 of the engine, said piston being arranged for axially directed sliding motion within a correspondingly arranged, equally cylindrical piston chamber 21.
  • the annular piston 20 is further surrounded by a shroud 22 which extends coaxially to the longitudinal centerline 19of the engine and the lower wall 23 of which serves to guide the annular piston 20.
  • the shroud 22 further confines a separately sealed cylinder chamber 25 formed between it and an upper guide wall 24 for the annular piston 20 and that side of the annular piston 20 which opposes the cylinder 3 chamber 21.
  • the annular piston 20 is connected, through an annular support 26, to toothed racks 27 the teeth of which cooperate with the mating teeth on the necks 28 of the variable-pitch fan rotor blades 2 which are supported in needle bearings 29, 30.
  • toothed racks 27 the teeth of which cooperate with the mating teeth on the necks 28 of the variable-pitch fan rotor blades 2 which are supported in needle bearings 29, 30.
  • extensions 31 of the racks 27 are carried over rollers 32 which are supported in ball bearings.
  • a stationary threeway control valve 34 energized with air from the engine compressor in a manner which is not detailed on the drawing.
  • Inlet lines 35, 36 which extend and are energized commonly or independently with compressor air from the threeway control valve 34, lead respectively to chambers 37, 38 which in turn communicate, via ducts 39, 40 through the stationary vanes 14, with chambers 41, 42 which are arranged separately from one another within an air manifolding system 43.
  • the compressor air is directed along the direction depicted by arrowheads G, H and into annular chambers 46, 47 of an auxiliary piston 48 which is arranged adjacent to the shafting 17 and extends coaxially to the longitudinal centerline 19 of the engine.
  • the auxiliary piston 48 is movable towards the lefthand side in response to a pressure build up in the annular chamber 47.
  • a toothed rack 49 of this auxiliary piston 48 cooperates with mating teeth 50 on a bellcrank 51.
  • Engagement of a further toothed portion 52 of this bellcrank 51 with a sleeve 53 causes a springloaded plunger 54 to move downward and clear a slot 55 in the toothed rack 27 so that the fan blade 2 is free to move under the action of the annular piston 20.
  • a plurality of such disengageable arresting devices may be provided to suit any number of supporting blades 13.
  • the air displaced from the cylinder chamber 21 by the annular piston 20 during the said movement of the fan blades 2 is allowed to flow, through a line 62, annular chamber 63 and a further hole 64 extending through the supporting blade 13, into a chamber 65 of the air manifolding system 43, continue through holes 66 to the chamber 46 of the auxiliary piston 48 and leave the air manifolding system 43 through the hole or cavity 39 in the guide vane 14 in a direction opposite to that indicated by the arrowhead G.
  • the annular piston 20 cannot be pressurized with air from the compressor so long as the fan blades 2 are arrested in one or the other end position, e.g., decelerating or cruise position, by means of the arresting plungers 54.
  • a further useful aspect of the present invention involves functionally interrelating the control of the annular piston 20 with the actuation of the threeway control valve 34 so that the auxiliary piston 48 is automatically restored to secure the fan blades 2 again in position or for other purposes when a predetermined axial displacement of the annular piston 20 and proportionally therewith a certain stagger angle of the fan blades 2 are reached.
  • iron cores 68 which project from the shroud 22, connect to the annular piston 20 and corotate with the axial-flow fan or engine in operation, are slideably arranged between oppositely connected secondary windings 69, 70 of a differential transformer and induce voltages between the secondary windings that tend to cancel each other out to a degree dependent on the position of the iron cores 68.
  • drive system and actuating mechanism means positioned substantially inside of an annulus arranged between said primary and secondary ducts and including a piston connected to toothed rack means mounted for movement within said annulus, said fan blades including blade teeth which matingly engage corresponding rack teeth of said toothed rack means,
  • said arresting means includes resiliently biased plunger means extending through cavity means in said supporting blade means, said plunger means being engageable with respective spaced slots in said toothed rack means for arresting said toothed rack means in positions corresponding to predetermined adjusted positions of said fan blades.
  • said primary duct is a duct for supplying air to a compressor rotor of said engine
  • said secondary duct is a bypass duct with said fan blades forming part of an axial flow fan of said engine.
  • Apparatus according to claim 5 wherein means are provided for directing compressed air from a compressor rotor of said engine as said pressurized air to move said annular piston.
  • toothed rack means are connected to the annular piston through a ring-shaped rack carrier which extends coaxially to the engine centerline.
  • control means are provided for controlling the supply of compressed air to said annular piston such that supply of .compressed air to said annular piston is prevented until an auxiliary piston disposed adjacent central shafting of said engine has first released said arresting means.
  • auxiliary piston is operated by compressed air and is movable in a direction parallel to said engine centerline.
  • said piston is an annular piston which is supplied with said compressed air by way of an air manifolding system adjacent to central shaftin g means of the engine, through ducts in supporting blades extending across said primary duct, and through line means within said annulus to said annular piston.
  • annular piston is supplied with said compressed air by way of an air manifolding system adjacent to said central shafting means, through ducts in said supporting blade means, and through line means within said annulus to said annular piston.
  • Apparatus according to claim 11 further comprising valve means interposed downstream of a compressor rotor of said engine for selectively controlling the supply of compressed air from said compressor rotor to actuate said annular and auxiliary pistons.
  • Apparatus according to claim 9, further comprising valve means interposed downstream of a compressor rotor of said engine for selectively controlling the supply of compressed air from said compressor rotor to actuate said annular and auxiliary pistons.
  • valve control means includes iron core means connected to said annular piston and electrical coil means adjacent said iron core means, said iron core means and coil means being operatively arranged to generate electrical signals for controlling the valve means as a result of inductive voltage changes upon changes in position of said annular piston.
  • valve means is a threeway valve.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US353387A 1972-04-19 1973-04-19 Apparatus for adjusting fan blades in a turbojet engine Expired - Lifetime US3924404A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2218874A DE2218874C3 (de) 1972-04-19 1972-04-19 Vorrichtung zur Verstellung der Gebläseschaufeln eines Turbinenstrahltriebwerks

Publications (2)

Publication Number Publication Date
USB353387I5 USB353387I5 (enrdf_load_stackoverflow) 1975-01-28
US3924404A true US3924404A (en) 1975-12-09

Family

ID=5842410

Family Applications (1)

Application Number Title Priority Date Filing Date
US353387A Expired - Lifetime US3924404A (en) 1972-04-19 1973-04-19 Apparatus for adjusting fan blades in a turbojet engine

Country Status (4)

Country Link
US (1) US3924404A (enrdf_load_stackoverflow)
DE (1) DE2218874C3 (enrdf_load_stackoverflow)
FR (1) FR2181021B1 (enrdf_load_stackoverflow)
GB (1) GB1420679A (enrdf_load_stackoverflow)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4261686A (en) * 1978-08-09 1981-04-14 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Variable flow divider for turbomachines
US4657484A (en) * 1984-09-04 1987-04-14 General Electric Company Blade pitch varying means
US4704862A (en) * 1985-05-29 1987-11-10 United Technologies Corporation Ducted prop engine
US4718823A (en) * 1987-02-24 1988-01-12 United Technologies Corporation Pitch changing mechanism for fan blades
US4758129A (en) * 1985-05-31 1988-07-19 General Electric Company Power frame
US20040169108A1 (en) * 2003-02-27 2004-09-02 Terpay Gregory W. Fluid conduit for use with hydraulic actuator
US20100162683A1 (en) * 2006-10-12 2010-07-01 Grabowski Zbigniew M Turbofan engine
US7878764B2 (en) 2007-07-23 2011-02-01 Caterpillar Inc. Adjustable fan and method

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114810416B (zh) * 2022-06-27 2022-09-23 中国航发四川燃气涡轮研究院 一种锯齿形的变循环发动机可调前涵道引射器结构

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1085964A (en) * 1914-02-03 John J Briggs Device for setting and locking the reverse mechanism of locomotives.
GB430557A (en) * 1933-09-19 1935-06-20 Georges Lafond Improvements in and relating to variable pitch propellers
US2118890A (en) * 1936-11-27 1938-05-31 Servo Frein Dewandre Sa Control device with predetermined successive positions
US2969118A (en) * 1957-08-21 1961-01-24 United Aircraft Corp Motor utilizing combined action of splines and cams
US3251278A (en) * 1964-12-16 1966-05-17 Robert H Royster Fluid pressure actuator with fluid pressure controlled locking means
US3467198A (en) * 1966-12-05 1969-09-16 Rolls Royce Gear transmission
US3498187A (en) * 1968-05-13 1970-03-03 Sargent Industries Hydraulically operated rack and pinion actuator
GB1196588A (en) * 1966-11-09 1970-07-01 British Aircraft Corp Ltd Form Improvements relating to Turbo-fan Aircraft Engines
US3720060A (en) * 1969-12-13 1973-03-13 Dowty Rotol Ltd Fans

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1296063A (enrdf_load_stackoverflow) * 1969-05-03 1972-11-15

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1085964A (en) * 1914-02-03 John J Briggs Device for setting and locking the reverse mechanism of locomotives.
GB430557A (en) * 1933-09-19 1935-06-20 Georges Lafond Improvements in and relating to variable pitch propellers
US2118890A (en) * 1936-11-27 1938-05-31 Servo Frein Dewandre Sa Control device with predetermined successive positions
US2969118A (en) * 1957-08-21 1961-01-24 United Aircraft Corp Motor utilizing combined action of splines and cams
US3251278A (en) * 1964-12-16 1966-05-17 Robert H Royster Fluid pressure actuator with fluid pressure controlled locking means
GB1196588A (en) * 1966-11-09 1970-07-01 British Aircraft Corp Ltd Form Improvements relating to Turbo-fan Aircraft Engines
US3467198A (en) * 1966-12-05 1969-09-16 Rolls Royce Gear transmission
US3498187A (en) * 1968-05-13 1970-03-03 Sargent Industries Hydraulically operated rack and pinion actuator
US3720060A (en) * 1969-12-13 1973-03-13 Dowty Rotol Ltd Fans

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4261686A (en) * 1978-08-09 1981-04-14 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Variable flow divider for turbomachines
US4657484A (en) * 1984-09-04 1987-04-14 General Electric Company Blade pitch varying means
US4704862A (en) * 1985-05-29 1987-11-10 United Technologies Corporation Ducted prop engine
EP0203881B1 (en) * 1985-05-29 1988-08-17 United Technologies Corporation Ducted prop engine
US4758129A (en) * 1985-05-31 1988-07-19 General Electric Company Power frame
US4718823A (en) * 1987-02-24 1988-01-12 United Technologies Corporation Pitch changing mechanism for fan blades
US20040169108A1 (en) * 2003-02-27 2004-09-02 Terpay Gregory W. Fluid conduit for use with hydraulic actuator
US6863239B2 (en) 2003-02-27 2005-03-08 General Dynamics Advanced Information Systems, Inc. Fluid conduit for use with hydraulic actuator
US20100162683A1 (en) * 2006-10-12 2010-07-01 Grabowski Zbigniew M Turbofan engine
US7878764B2 (en) 2007-07-23 2011-02-01 Caterpillar Inc. Adjustable fan and method

Also Published As

Publication number Publication date
FR2181021A1 (enrdf_load_stackoverflow) 1973-11-30
DE2218874B2 (de) 1978-09-21
DE2218874A1 (de) 1973-10-25
USB353387I5 (enrdf_load_stackoverflow) 1975-01-28
FR2181021B1 (enrdf_load_stackoverflow) 1977-07-29
GB1420679A (en) 1976-01-07
DE2218874C3 (de) 1979-05-17

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