SG165406A1 - Fan case reinforcement in a gas turbine jet engine - Google Patents

Fan case reinforcement in a gas turbine jet engine

Info

Publication number
SG165406A1
SG165406A1 SG201006844-3A SG2010068443A SG165406A1 SG 165406 A1 SG165406 A1 SG 165406A1 SG 2010068443 A SG2010068443 A SG 2010068443A SG 165406 A1 SG165406 A1 SG 165406A1
Authority
SG
Singapore
Prior art keywords
fan case
fan
ring
gas turbine
jet engine
Prior art date
Application number
SG201006844-3A
Inventor
L James Cardarella
Original Assignee
Carlton Forge Works
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
Priority claimed from PCT/US2005/033564 external-priority patent/WO2006137875A2/en
Application filed by Carlton Forge Works filed Critical Carlton Forge Works
Publication of SG165406A1 publication Critical patent/SG165406A1/en

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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • 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
    • 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
    • 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
    • F02K3/06—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 with front fan
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/40—Heat treatment
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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

Described is reinforcement of a fan case (302) in a gas turbine jet engine. In one embodiment, a containment ring (702) and a hear resistance ring (1112) are shrink interference fit on the inside diameter of the fan case, the containment ring where the large fan blades (104) turn, and the heat resistance ring where heated air from backfiring heats up the fan case. In one example, the containment ring is made of a sue alloy to provide added strength to the fan case should a fan blade break, containing the fan blade within the fan case. Also, the containment ring may extent forward of at least the leading edge (1604) of each fan blade and aft of at least the trailing edge (1608) of each fan blade. The heat resistance ring (1112) is made of titanium or other suitable material. Additionally, one or more stiffener rings (1104, 1106) may be shrink interference fit on the outside diameter of the fan case. (Figure 3)
SG201006844-3A 2005-09-20 2005-11-16 Fan case reinforcement in a gas turbine jet engine SG165406A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2005/033564 WO2006137875A2 (en) 2004-09-23 2005-09-20 Fan case reinforcement in a gas turbine jet engine

Publications (1)

Publication Number Publication Date
SG165406A1 true SG165406A1 (en) 2010-10-28

Family

ID=37835253

Family Applications (1)

Application Number Title Priority Date Filing Date
SG201006844-3A SG165406A1 (en) 2005-09-20 2005-11-16 Fan case reinforcement in a gas turbine jet engine

Country Status (11)

Country Link
EP (1) EP1841950A2 (en)
JP (1) JP2009515075A (en)
KR (1) KR20080034086A (en)
CN (1) CN101163863A (en)
AU (1) AU2005335919A1 (en)
BR (1) BRPI0517330A (en)
CA (1) CA2584641A1 (en)
IL (1) IL181845A0 (en)
RU (1) RU2406877C2 (en)
SG (1) SG165406A1 (en)
WO (1) WO2007035184A2 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8191254B2 (en) 2004-09-23 2012-06-05 Carlton Forge Works Method and apparatus for improving fan case containment and heat resistance in a gas turbine jet engine
FR2968364B1 (en) * 2010-12-01 2012-12-28 Snecma DUAL FLOW TURBOREACTOR BLOWER ELEMENT
US9249681B2 (en) 2012-01-31 2016-02-02 United Technologies Corporation Fan case rub system
US9200531B2 (en) 2012-01-31 2015-12-01 United Technologies Corporation Fan case rub system, components, and their manufacture
US10669936B2 (en) 2013-03-13 2020-06-02 Raytheon Technologies Corporation Thermally conforming acoustic liner cartridge for a gas turbine engine
GB201313594D0 (en) 2013-07-30 2013-09-11 Composite Technology & Applic Ltd Fan Track Liner
FR3016187B1 (en) * 2014-01-09 2016-01-01 Snecma PROTECTION AGAINST THE FIRE OF A BLOWER HOUSING OF COMPOSITE MATERIAL
EP3032043A1 (en) * 2014-12-12 2016-06-15 Rolls-Royce plc A fan casing arrangement with a liner ring for a gas turbine engine
US10458433B2 (en) 2015-06-17 2019-10-29 United Technologies Corporation Co-molded metallic fan case containment ring
GB201804568D0 (en) * 2018-03-22 2018-05-09 Rolls Royce Plc Fan track liner

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1085329A (en) * 1964-01-21
US3888602A (en) * 1974-06-05 1975-06-10 United Aircraft Corp Stress restraining ring for compressor rotors
FR2574476B1 (en) * 1984-12-06 1987-01-02 Snecma RETENTION HOUSING FOR TURBOJET BLOWER
GB2192238B (en) * 1986-07-02 1990-05-23 Rolls Royce Plc Gas turbine engine power turbine
DE3704197C1 (en) * 1987-02-11 1987-08-20 Mtu Muenchen Gmbh Removable burst protection ring
US5163809A (en) * 1991-04-29 1992-11-17 Pratt & Whitney Canada, Inc. Spiral wound containment ring
GB9922618D0 (en) * 1999-09-25 1999-11-24 Rolls Royce Plc A gas turbine engine blade containment assembly
DE60108037T2 (en) * 2000-10-13 2005-09-15 General Electric Co. Nickel-based alloy and its use in forgings or welding operations
FR2845436B1 (en) * 2002-10-02 2004-12-31 Snecma Moteurs DRUM FORMING PARTICULARLY A TURBOMACHINE ROTOR, COMPRESSOR AND TURBOMOTOR COMPRISING SUCH A DRUM

Also Published As

Publication number Publication date
JP2009515075A (en) 2009-04-09
KR20080034086A (en) 2008-04-18
EP1841950A2 (en) 2007-10-10
WO2007035184A2 (en) 2007-03-29
WO2007035184A8 (en) 2008-01-03
IL181845A0 (en) 2009-02-11
CN101163863A (en) 2008-04-16
BRPI0517330A (en) 2008-10-07
WO2007035184A3 (en) 2007-08-23
RU2406877C2 (en) 2010-12-20
RU2007115082A (en) 2008-10-27
AU2005335919A1 (en) 2007-04-05
CA2584641A1 (en) 2007-03-29

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