EXHAUST NOZZLE FOR GAS TURBINE ENGINE AND METHOD OF REDUCING ORIENTATION SENSING NOISE FROM EXHAUST NOZZLE FOR GAS TURBINE ENGINE

PROBLEM TO BE SOLVED: To provide an exhaust nozzle having improved noise reduction characteristics and less thrust loss. SOLUTION: This exhaust nozzle comprises flow bodies 30A, 30B receiving an exhaust gas flow from a turbine and a leading edge part 32 and a trailing edge part 42. The leading edge...

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Hauptverfasser:	NARAYANAN SATISH, SCHLINKER ROBERT HANS, SIMONICH JOHN
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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creator	NARAYANAN SATISH SCHLINKER ROBERT HANS SIMONICH JOHN
description	PROBLEM TO BE SOLVED: To provide an exhaust nozzle having improved noise reduction characteristics and less thrust loss. SOLUTION: This exhaust nozzle comprises flow bodies 30A, 30B receiving an exhaust gas flow from a turbine and a leading edge part 32 and a trailing edge part 42. The leading edge part 32 is so connected to a gas turbine engine 12 that the flow bodies 30A, 30B surround the centerline 40 of the engine. The trailing edge part 42 includes a serrated portion 28 and a non-serrated portion 29. The serrated portion 28 is formed of tabs 44, and mixes the gas discharged from the flow bodies 30A, 30B with the gas passing through the outside of the flow bodies 30A, 30B. The non-serrated portion 29 is disposed on the trailing edge part 42 along the lower portion of the centerline 40 of the engine. COPYRIGHT: (C)2008,JPO&INPIT
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SOLUTION: This exhaust nozzle comprises flow bodies 30A, 30B receiving an exhaust gas flow from a turbine and a leading edge part 32 and a trailing edge part 42. The leading edge part 32 is so connected to a gas turbine engine 12 that the flow bodies 30A, 30B surround the centerline 40 of the engine. The trailing edge part 42 includes a serrated portion 28 and a non-serrated portion 29. The serrated portion 28 is formed of tabs 44, and mixes the gas discharged from the flow bodies 30A, 30B with the gas passing through the outside of the flow bodies 30A, 30B. The non-serrated portion 29 is disposed on the trailing edge part 42 along the lower portion of the centerline 40 of the engine. 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SOLUTION: This exhaust nozzle comprises flow bodies 30A, 30B receiving an exhaust gas flow from a turbine and a leading edge part 32 and a trailing edge part 42. The leading edge part 32 is so connected to a gas turbine engine 12 that the flow bodies 30A, 30B surround the centerline 40 of the engine. The trailing edge part 42 includes a serrated portion 28 and a non-serrated portion 29. The serrated portion 28 is formed of tabs 44, and mixes the gas discharged from the flow bodies 30A, 30B with the gas passing through the outside of the flow bodies 30A, 30B. The non-serrated portion 29 is disposed on the trailing edge part 42 along the lower portion of the centerline 40 of the engine. COPYRIGHT: (C)2008,JPO&INPIT</abstract><oa>free_for_read</oa></addata></record>
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subjects	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
title	EXHAUST NOZZLE FOR GAS TURBINE ENGINE AND METHOD OF REDUCING ORIENTATION SENSING NOISE FROM EXHAUST NOZZLE FOR GAS TURBINE ENGINE
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