초록 ▼

A mixed flow, high bypass, gas turbofan engine that is small and compact, and that develops a thrust in the range of approximately 200-300 pounds. The engine has an axial length of approximately 18 inches, an air inlet of approximately 10 inches in diameter, and an exhaust nozzle of approximately 6

A mixed flow, high bypass, gas turbofan engine that is small and compact, and that develops a thrust in the range of approximately 200-300 pounds. The engine has an axial length of approximately 18 inches, an air inlet of approximately 10 inches in diameter, and an exhaust nozzle of approximately 6 inches in diameter. To reduce engine length high pressure compressor diameter, a high pressure compressor is positioned in a location that is displaced from and is preferably parallel to the engine axis (i.e., centerline), a burner (i.e., combustion chamber) is similarly positioned on the other side of the engine axis, only one turbine is used, and a unique flow path also is used. In addition, a heat exchanger of the regenerative type which includes a plurality of pipe diffusers is used, and it is positioned in the hot exhaust flow of the single turbine to pre-heat the compressor air prior to entry into the burner. Further, a gear shift may be used with the compressor to give better part-power performance. The small size, the thrust capability, and the good fuel consumption during part-power operation, make this engine ideal for use in air-launched cruise missiles.

대표청구항 ▼

A small gas turbofan engine having a longitudinal axis and comprising: a. an outer casing encircling said axis and disposed such that it is positioned symmetrically around said axis, with said casing having a forwardly located air inlet and a rearwardly located exhaust nozzle; b. a fan disposed in

A small gas turbofan engine having a longitudinal axis and comprising: a. an outer casing encircling said axis and disposed such that it is positioned symmetrically around said axis, with said casing having a forwardly located air inlet and a rearwardly located exhaust nozzle; b. a fan disposed in said air inlet, and positioned perpendicular to, and symmetrical with respect to, said axis; c. an annular fan air duct located internally of said outer casing and leading from said fan to said exhaust nozzle; d. a high pressure compressor located internally of said outer casing, operatively connected to said turbine, and disposed such that it is displaced from said axis and also is concurrently positioned within said fan air duct, with said high pressure compressor having an open, forwardly positioned, first end and an open, rearwardly positioned, second end; e. a plurality of pipe diffusers disposed internally of said outer casing, with each pipe diffuser having an open first end in communication with said open, rearwardly positioned, second end of said high pressure compressor, and with each pipe diffuser having an open second end, with all said second ends collectively terminating in a pipe bundle; f. a burner disposed internally of said outer casing, and positioned offset from said axis, with said burner having an open, rearwardly facing, first end in communication with said pipe bundle of said pipe diffusers, and with said burner having an open, rearwardly facing, second end disposed forwardly of said first end thereof; g. a toroidally-shaped plenum chamber in communication with said open second end of said burner; h. a multiple-stage turbine disposed internally of said outer casing, operatively connected to said fan and to said compressor, with said turbine having an open, forwardly facing, inlet first end in communication with said toroidally-shaped plenum chamber, and with said turbine also having an open, rearwardly facing, outlet second end across which are positioned said pipe diffusers which, thereby, form a stationary heat exchanger of the regenerator type; i. and, a mixer assembly disposed internally of said outer casing, interposed between said multiple-stage turbine and said exhaust nozzle, operatively connected to said outlet second end of said multiple-stage turbine, and positioned in part in said fan air ducts.