TURBINE NOZZLE SUPPORT DEVICE FOR GAS TURBINE FOR USE IN JET ENGINE

PROBLEM TO BE SOLVED: To reduce the weight of turbine nozzles and seal them with reliability. SOLUTION: An inner diametral nozzle flange 26 projected from the rear end of a turbine nozzle 11 is attached for longitudinal inclination to a support flange 28 on a rotor-side casing 16. An outer diametral...

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Bibliographische Detailangaben
1. Verfasser:	TAO SHINYA
Format:	Patent
Sprache:	eng
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 JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To reduce the weight of turbine nozzles and seal them with reliability. SOLUTION: An inner diametral nozzle flange 26 projected from the rear end of a turbine nozzle 11 is attached for longitudinal inclination to a support flange 28 on a rotor-side casing 16. An outer diametral nozzle flange 24 projected from the rear end of the turbine nozzle 11 is opposed to a support flange 25 on a stator-side casing. A circumferentially separated inner diametral seal ring 31, 35 is installed for longitudinal displacement at the front end of the turbine 11. The seal ring elements 31 and 35 are pressed against the back ends of an inner diametral frame portion 3a and an outer diametral frame portion 3b of a combustor 3.