GB1427339A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB1427339A
GB1427339A GB5279672A GB5279672A GB1427339A GB 1427339 A GB1427339 A GB 1427339A GB 5279672 A GB5279672 A GB 5279672A GB 5279672 A GB5279672 A GB 5279672A GB 1427339 A GB1427339 A GB 1427339A
Authority
GB
United Kingdom
Prior art keywords
impact
cone
bearing
fan
supported
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
GB5279672A
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB5279672A priority Critical patent/GB1427339A/en
Publication of GB1427339A publication Critical patent/GB1427339A/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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles

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

1427339 Gas turbine engines; ducted fan engines ROLLS-ROYCE (1971) Ltd 14 Nov 1973 [15 Nov 1972] 52796/72 Headings F1G and F1J The invention relates to gas turbine engines and to means for reducing the effects of impact thereon by foreign bodies such as birds during aircraft flight, the invention being described with reference to a ducted fan engine. The fan duct wall shown in Fig. 2 comprises an outer skin 11, an inner skin 12 which comprises a series of rigid panels 17 of acoustic honeycomb structure, and a leading edge portion 6 which is connected to the outer skin 11 by means of an all-round access panel 15 formed of three arcuate portions and which is so formed that it will break upon impact. The outer and inner skins are connected by a series of diaphragms 13 in the form of annular plates. The inner wall comprises also a further panel 17a which is adapted to crush upon impact. An arrangement 19, 20 is provided to limit axial movement. In the event of impact upon the leading edge portion 6, the panel 15 gives and the portion 6 and the panels 17 move axially rearwardly so crushing the panel 17a and causing the diaphragms 13 to be deformed to frusto-conical form - thus the force of the impact is absorbed. The diaphragms 13 may be resiliently deformable such that they recover their initial shape after deflection. In Fig. 3 the ducted fan is driven by shaft 36 supported in a bearing 41, the fan having variable pitch blades movable by control mechanism 35 acting through a drive cone 43 supported in a bearing 42. The rotor fairing cone 30 is slidably supported on an inner cone 33, a resilient bellows member 32 being disposed therebetween. In the event of impact on the fairing cone, the cone moves rearwardly against the compression of the bellows. In Fig. 4, the fan rotor shaft is formed in two parts, the forward part 36a being axially slidable with respect to the rearward part. The forward part 36a is supported in a bearing 41 the outer race 62 of which is connected to a piston 66 slidable in a cylinder 67. The piston is normally located by means of a shear pin 68. The cylinder 67 is formed with a restricted orifice 69. In the event of impact on the rotor fairing cone, the shaft part 36a moves rearwardly breaking the shear pin 68, and compressing the air in the cylinder, the air leaking through the orifice 69. Thus the energy of the impact is absorbed. In a further embodiment, the outer race of the bearing bears against a leaf-spring which absorbs the energy upon axial movement of the shaft and bearing resulting from impact.
GB5279672A 1972-11-15 1972-11-15 Gas turbine engine Expired GB1427339A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB5279672A GB1427339A (en) 1972-11-15 1972-11-15 Gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5279672A GB1427339A (en) 1972-11-15 1972-11-15 Gas turbine engine

Publications (1)

Publication Number Publication Date
GB1427339A true GB1427339A (en) 1976-03-10

Family

ID=10465356

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5279672A Expired GB1427339A (en) 1972-11-15 1972-11-15 Gas turbine engine

Country Status (1)

Country Link
GB (1) GB1427339A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2320526A (en) * 1996-12-20 1998-06-24 Rolls Royce Plc Shaft support and bearing arrangement for ducted fan engine
GB2385382A (en) * 2002-02-13 2003-08-20 Rolls Royce Plc A cowl structure for a gas turbine engine
FR2868123A1 (en) * 2004-03-29 2005-09-30 Airbus France Sas AIR INTAKE STRUCTURE FOR AN AIRCRAFT ENGINE
EP1621744A1 (en) * 2004-07-28 2006-02-01 Snecma A turbine engine nose cone
WO2008085542A2 (en) * 2006-07-19 2008-07-17 Rohr, Inc. Aircraft engine inlet having zone of deformation
FR2954282A1 (en) * 2009-12-22 2011-06-24 Airbus Operations Sas NACELLE INCORPORATING A JUNCTION ELEMENT BETWEEN A LIP AND AN ACOUSTICAL ATTENUATION PANEL
FR3057909A1 (en) * 2016-10-21 2018-04-27 Safran Aircraft Engines AIRCRAFT TURBOMACHINE COMPRISING A FUSIBLE ZONE AGENCED ON A SWIVEL ARBOR
CN113935116A (en) * 2021-12-16 2022-01-14 清华大学 Low-speed impact response analysis method for aircraft engine corrugated pipe
US11624295B2 (en) 2018-12-20 2023-04-11 Rolls-Royce Plc Gas turbine engine

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6009701A (en) * 1996-12-20 2000-01-04 Rolls-Royce, Plc Ducted fan gas turbine engine having a frangible connection
GB2320526B (en) * 1996-12-20 2000-09-20 Rolls Royce Plc Ducted fan gas turbine engine
GB2320526A (en) * 1996-12-20 1998-06-24 Rolls Royce Plc Shaft support and bearing arrangement for ducted fan engine
GB2385382B (en) * 2002-02-13 2006-02-15 Rolls Royce Plc A cowl structure for a gas turbine engine
GB2385382A (en) * 2002-02-13 2003-08-20 Rolls Royce Plc A cowl structure for a gas turbine engine
FR2868123A1 (en) * 2004-03-29 2005-09-30 Airbus France Sas AIR INTAKE STRUCTURE FOR AN AIRCRAFT ENGINE
EP1582701A1 (en) * 2004-03-29 2005-10-05 Airbus France Air intake structure for an airplane engine
US7506838B2 (en) 2004-03-29 2009-03-24 Airbus France Air intake structure for aircraft engine
US7419364B2 (en) 2004-07-28 2008-09-02 Snecma Nose cone for a turbomachine
EP1621744A1 (en) * 2004-07-28 2006-02-01 Snecma A turbine engine nose cone
FR2873751A1 (en) * 2004-07-28 2006-02-03 Snecma Moteurs Sa INPUT CONE OF A TURBOMACHINE
US8438857B2 (en) 2006-07-19 2013-05-14 Rohr, Inc. Aircraft engine inlet having zone of deformation
WO2008085542A3 (en) * 2006-07-19 2008-10-02 Rohr Inc Aircraft engine inlet having zone of deformation
US7721525B2 (en) 2006-07-19 2010-05-25 Rohr, Inc. Aircraft engine inlet having zone of deformation
EP2336500A3 (en) * 2006-07-19 2012-09-05 Rohr, Inc. Aircraft engine inlet having zone of deformation
WO2008085542A2 (en) * 2006-07-19 2008-07-17 Rohr, Inc. Aircraft engine inlet having zone of deformation
FR2954282A1 (en) * 2009-12-22 2011-06-24 Airbus Operations Sas NACELLE INCORPORATING A JUNCTION ELEMENT BETWEEN A LIP AND AN ACOUSTICAL ATTENUATION PANEL
WO2011086281A1 (en) 2009-12-22 2011-07-21 Airbus Operations Sas Nacelle incorporating an element for connecting a lip and an acoustic attenuation panel together
CN102686480A (en) * 2009-12-22 2012-09-19 空中客车运营简化股份公司 Nacelle incorporating an element for connecting a lip and an acoustic attenuation panel together
US9352844B2 (en) 2009-12-22 2016-05-31 Airbus Operations Sas Nacelle incorporating an element for connecting a lip and an acoustic attenuation panel together
FR3057909A1 (en) * 2016-10-21 2018-04-27 Safran Aircraft Engines AIRCRAFT TURBOMACHINE COMPRISING A FUSIBLE ZONE AGENCED ON A SWIVEL ARBOR
US11624295B2 (en) 2018-12-20 2023-04-11 Rolls-Royce Plc Gas turbine engine
CN113935116A (en) * 2021-12-16 2022-01-14 清华大学 Low-speed impact response analysis method for aircraft engine corrugated pipe

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee