초록 ▼

The present invention comprises a gas turbine engine augmentor including a new and improved fuel spraybar therein. The spraybar includes a base having a manifold for receiving fuel, and a plurality of fuel tubes extending from the base and in flow communication with the manifold. The invention furth

The present invention comprises a gas turbine engine augmentor including a new and improved fuel spraybar therein. The spraybar includes a base having a manifold for receiving fuel, and a plurality of fuel tubes extending from the base and in flow communication with the manifold. The invention further includes means for cooling the fuel tubes for allowing independent thermal movement between the cooling means and the fuel tubes. In one embodiment of the invention, the cooling means comprises an elongate shield disposed upstream of the fuel tubes to block direct impingement of combustion gases against the fuel tubes while channeling a cooling fluid such as air over the fuel tubes. In accordance with another embodiment, the invention includes means for securing the shield to the fuel tubes for allowing unrestrained longitudinal thermal movement while restraining lateral movement therebetween beyond a predetermined amount. In yet another embodiment, the invention includes means for laterally dispersing fuel from discharge ports disposed in the fuel tubes. The means may include a delta wing.

대표청구항 ▼

A fuel spraybar for a gas turbine engine comprising: a base including a manifold for receiving fuel; a plurality of fuel tubes extending from said base and including a trailing edge portion defined by side surfaces of said fuel tubes joined at a trailing edge, each fuel tube having a distal end, a p

A fuel spraybar for a gas turbine engine comprising: a base including a manifold for receiving fuel; a plurality of fuel tubes extending from said base and including a trailing edge portion defined by side surfaces of said fuel tubes joined at a trailing edge, each fuel tube having a distal end, a proximate end fixedly joined to said base, a fuel passage disposed in fluid communication with said manifold, and a discharge port disposed in said tube distal end of said trailing edge portion in flow communication with said fuel passage; means for cooling said fuel tubes including said distal ends, spaced from said fuel tubes for allowing independent thermal movement between said cooling means and said fuel tubes; and said fuel tubes and said cooling means being positionable together in combustion gases in the gas turbine engine with said trailing edge portion being directly exposed to said combustion gases.