CPC F02C 7/12 (2013.01) [F05D 2220/32 (2013.01); F05D 2260/20 (2013.01)] | 20 Claims |
1. A thermal management system for incorporation into a gas turbine engine, the thermal management system comprising:
a thermal transport bus having a thermal fluid flowing therethrough;
a plurality of heat source exchangers in thermal communication with the thermal fluid in the thermal transport bus; and
a pump assembly in flow communication with the thermal transport bus, the pump assembly comprising:
a pump positioned at a first height; and
a pump protection device positioned at a second height, wherein the second height is lower than the first height along a vertical direction during a normal engine attitude, wherein the gas turbine engine, an aircraft, or both define the vertical direction.
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