GB1420679A - Turbojet engine having variable-angle fan blades - Google Patents

Turbojet engine having variable-angle fan blades

Info

Publication number
GB1420679A
GB1420679A GB1886473A GB1886473A GB1420679A GB 1420679 A GB1420679 A GB 1420679A GB 1886473 A GB1886473 A GB 1886473A GB 1886473 A GB1886473 A GB 1886473A GB 1420679 A GB1420679 A GB 1420679A
Authority
GB
United Kingdom
Prior art keywords
chamber
piston
annular
racks
duct
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
GB1886473A
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 GB1420679A publication Critical patent/GB1420679A/en
Expired legal-status Critical Current

Links

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

Landscapes

  • 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)

Abstract

1420679 Axial-flow fans; gas-turbine ducted-fan engines MOTOREN-UND TURBINEN-UNION MUNCHEN GmbH 18 April 1973 [19 April 1972] 18864/73 Headings F1C and F1J In a gas turbine ducted-fan engine, an annular piston arranged for energization by compressor air and connected to drive an actuating mechanism for changing the fan blade angle is arranged coaxially with the engine centreline and disposed, together with the actuating mechanism, substantially in an annular region located between the main duct of the engine and the fan duct. When the angle of the fan blades 2 is to be changed, compressed air is supplied via a control valve 34 to either of two pipes 35, 36. When the air is supplied to pipe 35, it passes, via a duct 40 in a stay vane 14, a chamber 42 and an annular chamber 47 to act on a portion 48' of an annular piston 48, whereby the annular piston is moved to the left and acts, via gearing 49, 50, 52, 53 to withdraw spring-loaded plungers 54 from engagement with slots 55 in racks 27. This unlocks the fan blades 2, each of which is adjustable by a corresponding one of the racks. The piston is now in a position in which the portion 48' is to the left of a duct 56, whereby compressed air can flow from the chamber 47 to the duct 56 and thence via a chamber 57, a passage 58, a chamber 59 and a pipe 60 to an annular chamber 25, where it acts on an annular piston 20 to move the racks 27 to the left and therefore change the blade angle, e.g., for cruising or for reverse thrust. The valve 34 is then actuated to relieve the pressure, allowing the piston 48 and the plungers 54 to be returned by springs to their original positions. The plungers 54 then engage slots 61 in the racks 27 to retain the blades 2 in their new positions. When the blades 2 are to be returned to their original positions, the control valve 34 supplies compressed air to the pipe 36 and hence, via a duct 39, a chamber 41 and an annular chamber 46 to act on a portion 48"of the piston 48, whereby the piston is again moved to the left to withdraw the plungers 54 from engagement with the racks 27 to unlock the blades 2. The portion 48" will now be to the left of a port 66, allowing the compressed air to pass from the chamber 46 via the port 66, a chamber 65, a passage 64, a chamber 63 and a pipe 62 to an annular chamber 21, where it acts on the annular piston 20 to move the racks 27 to the right. The position of the annular piston 20 may be sensed by means of iron cores 68 carried by the piston and moving relatively to the windings 69, 70 of a differential transformer to provide a control voltage to actuate the control valve 34 when the blades 2 have reached the required position.
GB1886473A 1972-04-19 1973-04-18 Turbojet engine having variable-angle fan blades Expired GB1420679A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2218874A DE2218874C3 (en) 1972-04-19 1972-04-19 Device for adjusting the fan blades of a turbine jet engine

Publications (1)

Publication Number Publication Date
GB1420679A true GB1420679A (en) 1976-01-07

Family

ID=5842410

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1886473A Expired GB1420679A (en) 1972-04-19 1973-04-18 Turbojet engine having variable-angle fan blades

Country Status (4)

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

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2834860A1 (en) * 1978-08-09 1980-03-13 Motoren Turbinen Union ADJUSTABLE FLOW DIVIDER FOR FLOW MACHINES, ESPECIALLY GAS TURBINE JET ENGINES
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
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
US6863239B2 (en) * 2003-02-27 2005-03-08 General Dynamics Advanced Information Systems, Inc. Fluid conduit for use with hydraulic actuator
EP2074322B1 (en) * 2006-10-12 2013-01-16 United Technologies Corporation Turbofan engine
US7878764B2 (en) 2007-07-23 2011-02-01 Caterpillar Inc. Adjustable fan and method
CN114810416B (en) * 2022-06-27 2022-09-23 中国航发四川燃气涡轮研究院 Zigzag variable cycle engine adjustable front duct ejector structure

Family Cites Families (10)

* 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
GB1296063A (en) * 1969-05-03 1972-11-15
GB1294898A (en) * 1969-12-13 1972-11-01

Also Published As

Publication number Publication date
FR2181021B1 (en) 1977-07-29
USB353387I5 (en) 1975-01-28
DE2218874A1 (en) 1973-10-25
DE2218874B2 (en) 1978-09-21
FR2181021A1 (en) 1973-11-30
DE2218874C3 (en) 1979-05-17
US3924404A (en) 1975-12-09

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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