Gas turbine engine blade containment assembly

A gas turbine engine rotor blade containment assembly ( 38 ) comprises a generally cylindrical, or frustoconical, metal casing ( 40 ). The metal casing ( 40 ) has at least one arched portion ( 62,64,66 ) and each arched portion ( 62,64,66 ) extends circumferentially around the metal casing ( 40 ). E...

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Bibliographische Detailangaben
Hauptverfasser:	LAWSON MICHAEL R, SATHIANATHAN SIVASUBRAMANIAM K
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine rotor blade containment assembly ( 38 ) comprises a generally cylindrical, or frustoconical, metal casing ( 40 ). The metal casing ( 40 ) has at least one arched portion ( 62,64,66 ) and each arched portion ( 62,64,66 ) extends circumferentially around the metal casing ( 40 ). Each arched portion ( 62,64,66 ) comprises a radially inwardly extending arch ( 68 ) in which the trough ( 74 ) of the arch ( 68 ) is radially inwardly of a straight line ( 76 ) interconnecting the axial ends ( 70,72 ) of the arch ( 68 ). The trough ( 74 ) of the arch ( 68 ) is radially inwardly of the at least one of the axial ends ( 70,72 ) of the at least one arch ( 68 ). The arched portions ( 62,64,66 ) introduce compressive stresses into the metal casing ( 40 ) during a fan blade 34 impact and enable the metal casing ( 40 ) to withstand the impact. The fan blade containment assembly ( 38 ) is lighter for large diameter turbofan gas turbine engine ( 10 ).