Oil cooling system for a gas turbine engine

Power plants – Combustion products used as motive fluid – Combined with regulation of power output feature

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Details

60 3966, 415180, 123 4133, 123122E, 137104, F02C 908

Patent

active

040416976

ABSTRACT:
A gas turbine engine fuel delivery and control system is provided with means to recirculate all fuel in excess of fuel control requirements back to the aircraft fuel tank, thereby increasing the fuel pump heat sink and decreasing the pump temperature rise without the addition of valving other than that normally employed. A fuel/oil heat exchanger and associated circuitry is provided to maintain the hot engine oil in heat exchange relationship with the cool engine fuel. Where anti-icing of the fuel filter is required, means are provided to maintain the fuel temperature entering the filter at or above a minimum level to prevent freezing thereof. In one embodiment, a divider valve is provided to take all excess fuel from either upstream or downstream of the fuel filter and route it back to the tanks, the ratio of upstream to downstream extraction being a function of fuel pump discharge pressure. In addition, fluid circuitry is provided to route hot engine oil through a plurality of heat exchangers disposed within the system to provide for selective cooling of the oil.

REFERENCES:
patent: 2865580 (1958-12-01), Marshall
patent: 2925712 (1960-02-01), Johnson
patent: 2979293 (1961-04-01), Mount
patent: 3080716 (1963-03-01), Cummings
patent: 3307355 (1967-03-01), Bahr
patent: 3420055 (1969-01-01), Lavash
patent: 3627239 (1971-12-01), Hull
patent: 3658249 (1972-04-01), Sharpe
patent: 3733816 (1973-05-01), Nash
patent: 3779007 (1973-12-01), Lavash
patent: 3874168 (1975-04-01), Toure

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