FIELD: engine industry.
SUBSTANCE: invention relates to the engine industry, and in particular to the designs of the drive boxes of drive units of bypass gas turbine engines (GTE). The gas turbine engine with a box of drive units (1), located in the engine nacelle (2) is proposed. An additional drive (11) with a hydraulic pump (12) is installed on the box of drive units (9) located in the intercircuit space (10) or mounted on the outer casing of the engine, rotated at an angle of 60 to 120 degrees relative to the horizontal axis of the engine, ensuring reduction of the length of the hydraulic lines (17) of the hydraulic pump, the minimum hydraulic resistance and the smoothest entry of these hydraulic lines into the technological rack (7) and further through the pylon (18) into the aircraft wing (19) to the consumers of hydraulic energy, for example, to flaps, fenders or landing gear.
EFFECT: invention is aimed at obtaining the shortest possible hydraulic lines with fewer kinks, minimizing hydraulic losses and saving aircraft weight.
1 cl, 2 dwg
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