초록 ▼

A plurality of circumferentially displaced hollow members are positioned between an outer bypass duct and the center body of the core engine. Each of the hollow members is open at the radially outward end thereof for receiving relatively cool gas from the bypass duct. Each hollow member is formed wi

A plurality of circumferentially displaced hollow members are positioned between an outer bypass duct and the center body of the core engine. Each of the hollow members is open at the radially outward end thereof for receiving relatively cool gas from the bypass duct. Each hollow member is formed with an opening in the side thereof extending substantially the full length of the hollow member near the trailing edge thereof for discharging bypass gas from the bypass duct in a direction facilitating thorough mixing of the bypass gas and core gases. A pivoted vane is provided in this opening of each of the hollow members and these vanes are controlled to vary the airflow through the aforementioned openings. Radially extending spraybars or fuel rods are provided within each hollow member adjacent opposite sides thereof so as to be cooled by the bypass air flowing through the hollow member. The spraybars are provided with a plurality of openings adjacent the sidewalls of the hollow members and corresponding openings are provided in these walls so that fuel, during augmentor operation, is directed into the area between adjacent hollow members. The aft end of each hollow member is formed as a relatively wide flat surface which acts as a flameholder for the fuel supplied from the spraybars and burned in the augmentor. The forward end of each hollow member is curved to an angle corresponding generally to the swirl angle of core gases exhausted from the core engine so as to effect a deswirling of this gas.

대표청구항 ▼

A gas turbine engine including a core engine and a center body associated therewith, an inlet for supplying gas flow to the core engine, a bypass duct surrounding the core engine for bypassing a portion of the gas around the core engine, and an augmentor aft of the core engine, for providing augment

A gas turbine engine including a core engine and a center body associated therewith, an inlet for supplying gas flow to the core engine, a bypass duct surrounding the core engine for bypassing a portion of the gas around the core engine, and an augmentor aft of the core engine, for providing augmented thrust, comprising: (a) a plurality of circumferentially disposed hollow members positioned in the path of core gases from the the core engine; (b) each of said members extending generally radially from said bypass duct to said center body; (c) each of said members being open at the radially outward end for receiving bypass gas from said bypass duct; (d) each of said members including spaced apart sidewalls and an opening in one of said side walls near the trailing edge and extending substantially the length of each of said members for discharging bypass gas in a direction which provides thorough mixing of said core gases and said bypass gas throughout substantially the entire region between adjacent hollow members.