AIRCRAFT GAS TURBINE ENGINE OIL SYSTEM Russian patent published in 2010 - IPC F02C7/06 

FIELD: engines and pumps.

SUBSTANCE: invention relates to oil system to be incorporated with supersonic aircraft flying at M>2.3 to allow optimum use of insignificant fuel cold capacity and can by used for cooling down most critical temperature control section of oil system, i.e. pressure pump delivery line that accommodates oil system automatics elements, fuel-to-oil heat exchanger, filter and oil injectors. Engine oil system bypass valve connected in parallel to delivery line, downstream of fuel-to-oil heat exchanger that forces bypassed cooled oil directly into pressure pump suction chamber, hence bypassing suction line, allows significant oil temperature reduction at pressure pump outlet (≈5…8°C) depending upon bypassing magnitude.

EFFECT: ruling out of oil temperature overheating and origination of oil thermal decomposition products in delivery line.

1 dwg