GB1196589A - Improvements relating to Turbo-fan Aircraft Engines - Google Patents

Improvements relating to Turbo-fan Aircraft Engines

Info

Publication number
GB1196589A
GB1196589A GB5203166A GB5203166A GB1196589A GB 1196589 A GB1196589 A GB 1196589A GB 5203166 A GB5203166 A GB 5203166A GB 5203166 A GB5203166 A GB 5203166A GB 1196589 A GB1196589 A GB 1196589A
Authority
GB
United Kingdom
Prior art keywords
fan
blade
annulus
root
blades
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
GB5203166A
Inventor
John Wotton
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.)
British Aircraft Corp Ltd
Original Assignee
British Aircraft Corp Operating Ltd
British Aircraft Corp Ltd
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 British Aircraft Corp Operating Ltd, British Aircraft Corp Ltd filed Critical British Aircraft Corp Operating Ltd
Priority to GB5203166A priority Critical patent/GB1196589A/en
Publication of GB1196589A publication Critical patent/GB1196589A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • 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
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • 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
    • F05D2260/75—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism not using auxiliary power sources, e.g. by "servos"

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,196,589. Gas turbine jet propulsion plant; axial-flow fans; fan blades. BRITISH AIRCRAFT CORP. Ltd. Feb. 13, 1968 [Nov. 21, 1966], No.52031/66. Headings F1C; F1J; F1T. In a gas turbine ducted fan aircraft engine having variable pitch fan blades, the fan comprises a rotatable annulus and each blade is adjustably mounted in a radial bore in the annulus by antifriction bearing elements accommodated in matching bearing grooves in the bore and in the blade root. In a three-spool type front fan engine, Fig. 1 (not shown), the fan annulus 23, Fig. 2, is formed in two halves 23a, 23b secured together by bolts 23c and abutting in a plane X-X. Each fan blade 24 is mounted on the annulus 23 by engagement of its root portion 25 in a radial bore in the annulus via ball or roller bearings 26 which run in matching grooves in the root and bore. The blade 24 is attached to its root 25 by a transverse hinge bolt 24a allowing slight freedom of movement of the blade in a fore and aft plane and thus eliminating bending stresses at the root. The blade material may be a plastic reinforced with glass or carbon fibres. The fan is driven from the drum 16 of a five-stage turbine by a frusto-conical connection 22, the latter carrying an air motor 31 for adjusting the pitch of the blades 24. The motor 31 has a control valve 311 and operates as described in Specification 1,196, 588, an output pinion 32 of the motor meshing with a peripheral rack 33 attached to an annular ring 34 which is connected to the blades 24 by links 37. The ring 34 is located on roller bearings 35 in an annular track member 36 attached to the fan. In a modification, Fig.4, applicable to a front fan engine, the fan blades 241 are mounted as before in ball bearings 261 but the rack 331 meshes with a pinion 321 connected by a worm and wheel 40, radial shaft 41, level gears 42, 43 and shaft 44 with an epicyclic gearbox 45 and a hydraulic motor 51. The latter operates in steps under the pilot's control and drives the gearbox input through a counter type feedback mechanism 52. There are several radial shafts 41 and each passes through a vane 46 extending across the compressor inlet from a spinner 47 to a housing 48 containing the pitch adjusting mechanism 271.
GB5203166A 1966-11-21 1966-11-21 Improvements relating to Turbo-fan Aircraft Engines Expired GB1196589A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB5203166A GB1196589A (en) 1966-11-21 1966-11-21 Improvements relating to Turbo-fan Aircraft Engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5203166A GB1196589A (en) 1966-11-21 1966-11-21 Improvements relating to Turbo-fan Aircraft Engines

Publications (1)

Publication Number Publication Date
GB1196589A true GB1196589A (en) 1970-07-01

Family

ID=10462367

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5203166A Expired GB1196589A (en) 1966-11-21 1966-11-21 Improvements relating to Turbo-fan Aircraft Engines

Country Status (1)

Country Link
GB (1) GB1196589A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2572769A1 (en) * 1984-11-02 1986-05-09 Gen Electric AVERAGE SUPPORT OF DAWN
GB2176246A (en) * 1985-05-31 1986-12-17 Gen Electric Rotor stage in a turbomachine
US4913623A (en) * 1985-11-12 1990-04-03 General Electric Company Propeller/fan-pitch feathering apparatus
US4934901A (en) * 1989-04-21 1990-06-19 Duchesneau Jerome G Pitch change actuation system
US5263898A (en) * 1988-12-14 1993-11-23 General Electric Company Propeller blade retention system
EP3018300A1 (en) * 2014-11-10 2016-05-11 MTU Aero Engines GmbH Gas turbine
CN114354608A (en) * 2021-10-18 2022-04-15 中国民用航空飞行学院 Automatic detection device is visited in aeroengine blade hole

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2572769A1 (en) * 1984-11-02 1986-05-09 Gen Electric AVERAGE SUPPORT OF DAWN
GB2176246A (en) * 1985-05-31 1986-12-17 Gen Electric Rotor stage in a turbomachine
GB2176246B (en) * 1985-05-31 1989-10-25 Gen Electric Improvements in turbomachines
US4913623A (en) * 1985-11-12 1990-04-03 General Electric Company Propeller/fan-pitch feathering apparatus
US5263898A (en) * 1988-12-14 1993-11-23 General Electric Company Propeller blade retention system
US4934901A (en) * 1989-04-21 1990-06-19 Duchesneau Jerome G Pitch change actuation system
EP3018300A1 (en) * 2014-11-10 2016-05-11 MTU Aero Engines GmbH Gas turbine
CN114354608A (en) * 2021-10-18 2022-04-15 中国民用航空飞行学院 Automatic detection device is visited in aeroengine blade hole

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees