GAS TURBINE COMPRESSOR

To predict and prevent fretting fatigue damage which may occur in accompany with vibration at a contact end portion of a moving blade and a rotor disc, in a dovetail groove as a blade planting portion of the moving blade.SOLUTION: In a gas turbine combustor, a plurality of gap sensors are disposed o...

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Bibliographische Detailangaben
1. Verfasser:	SEKIHARA TAKASHI
Format:	Patent
Sprache:	eng ; jpn
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC ORINFRASONIC WAVES MEASURING MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PHYSICS STEAM ENGINES TESTING TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR WEAPONS
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