FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engines, particularly to maneuverable aircraft gas turbine engine (GTE) oil system. Proposed oil system comprises rotor bearing oil chambers accommodating rotor thrust bearing and nozzles connected to oil feed device made up of a system of two interacting delivery pumps, one communicating with oil intake arranged in oil tank lower space and another communicated with oil intake arranged in oil tank upper space. Note here that both pumps outlets are intercommunicated. Device feeding oil to nozzles incorporates oil accumulator with its inlet connected, in parallel and via check valve, with pipeline that communicates outlets of delivery pumps, and its outlet communicated with duplicate oil feed nozzle arranged in thrust bearing oil chamber.
EFFECT: longer acrobatic flight in case of near-zero overloads.
1 dwg
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