FUEL NOZZLE FOR A GAS TURBINE ENGINE

FUEL NOZZLE FOR A GAS TURBINE ENGINE

13DV-7453 FUEL NOZZLE FOR A GAS TURBINE ENGINE In one form, a fuel nozzle includes a primary flowpath and a secondary flowpath, each of which includes a pair of axially opposing input and output ends disposed along a common central longitudinal axis. The secondary path is circumferentially disposed...

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Hauptverfasser: SETO, STANFORD P, RICHEY, JOHN M, STENGER, RICHARD E, KUTZKO, GUSTAVE G
Format: Patent
Sprache:eng ; fre
Schlagworte:
BLASTING
BURNERS
COMBUSTION APPARATUS
COMBUSTION PROCESSES
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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creator SETO, STANFORD P
RICHEY, JOHN M
STENGER, RICHARD E
KUTZKO, GUSTAVE G
description 13DV-7453 FUEL NOZZLE FOR A GAS TURBINE ENGINE In one form, a fuel nozzle includes a primary flowpath and a secondary flowpath, each of which includes a pair of axially opposing input and output ends disposed along a common central longitudinal axis. The secondary path is circumferentially disposed around the primary path. A nozzle discharge portion is circumferentially disposed around the primary and secondary output ends for receiving interacting output flows from the first and second paths and developing a nozzle output therefrom. The nozzle discharge portion includes a conical portion having an input end of smaller diameter which increases along the longitudinal axis to an output end of relatively larger diameter. In a preferred embodiment, the conical portion defines an included solid angle of 60 degrees with respect to the central longitudinal axis. Other embodiments are disclosed.
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The secondary path is circumferentially disposed around the primary path. A nozzle discharge portion is circumferentially disposed around the primary and secondary output ends for receiving interacting output flows from the first and second paths and developing a nozzle output therefrom. The nozzle discharge portion includes a conical portion having an input end of smaller diameter which increases along the longitudinal axis to an output end of relatively larger diameter. In a preferred embodiment, the conical portion defines an included solid angle of 60 degrees with respect to the central longitudinal axis. 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subjects BLASTING
BURNERS
COMBUSTION APPARATUS
COMBUSTION PROCESSES
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
title FUEL NOZZLE FOR A GAS TURBINE ENGINE
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