Pumped two-phase cooling of aircraft electronics
An aircraft cooling system comprises an evaporator, condenser, an accumulator, and a pump system. The evaporator is configured to cool a set of heat loads in an aircraft using a liquid. The liquid forms a vapor in response to cooling the set of heat loads. The condenser is configured to receive the vapor from the evaporator and cool the vapor in which cooling the vapor forms the liquid. The accumulator is configured to receive the liquid from the condenser and store the liquid. The pump system is configured to pump the liquid stored in the accumulator to the evaporator.
1 . An aircraft cooling system comprising:
an evaporator configured to cool a set of heat loads in an aircraft using a first liquid in a liquid loop, wherein a second liquid in a liquid-vapor loop forms a vapor in response to cooling the set of heat loads;
a condenser configured to receive the vapor from the evaporator and cool the vapor in which cooling the vapor forms the second liquid;
an accumulator configured to receive the second liquid from the condenser and store the second liquid; and
a pump system comprising a first pump and a second pump, the first pump configured to pump the first liquid in the liquid loop to the set of heat loads and the second pump configured to pump the second liquid stored in the accumulator to the evaporator and pump the second liquid from the condenser to the evaporator.
2 . The aircraft cooling system of claim 1 , wherein the condenser is configured to reject heat from the vapor into air traveling through a nacelle.
3 . The aircraft cooling system of claim 1 further comprising:
a generator; and
a turbine connected to the generator, wherein the turbine turns in response to receiving the vapor from the evaporator and causes the generator to generate power and wherein the condenser receives the vapor from the turbine.
4 . The aircraft cooling system of claim 1 , wherein the condenser comprises a nacelle heat exchanger.
5 . The aircraft cooling system of claim 4 , wherein the condenser further comprises a fan system.
6 . The aircraft cooling system of claim 1 , wherein the condenser rejects heat into air traveling through a nacelle.
7 . The aircraft cooling system of claim 1 , wherein the aircraft cooling system is located in a nacelle of an engine for the aircraft.
8 . The aircraft cooling system of claim 1 , wherein the set of heat loads in the aircraft is selected from at least one of a fuel cell, a fuel cell stack, a power circuit, an electric motor, a computer system, an electronics enclosure, or a laser.
9 . The aircraft cooling system of claim 1 wherein the condenser is a ram air condenser.
10 . An aircraft cooling system comprising:
a first pump configured to pump a first liquid in a liquid loop to a set of heat loads, wherein the set of heat loads heats the first liquid in which heating the first liquid forms a heated liquid;
an evaporator configured to receive the heated liquid and cool the heated liquid, wherein cooling the heated liquid causes a second liquid in a liquid-vapor loop to form a vapor;
a condenser configured to receive the vapor and cool the vapor in which cooling the vapor forms the second liquid; and
a second pump configured to pump the second liquid from the condenser to the evaporator.
11 . The aircraft cooling system of claim 10 , wherein the condenser comprises a nacelle heat exchanger.
12 . The aircraft cooling system of claim 10 , wherein the condenser further comprises a fan system.
13 . The aircraft cooling system of claim 10 , wherein the condenser rejects heat from the vapor into air traveling through a nacelle.
14 . The aircraft cooling system of claim 10 , wherein the aircraft cooling system is located in a nacelle of an engine for an aircraft.
15 . An aircraft cooling system comprising:
an evaporator configured to cool a set of heat loads in an aircraft using a first liquid in a liquid loop, wherein a second liquid in a liquid-vapor loop forms a fluid selected at least one of a vapor or a superheated gas in response to cooling the set of heat loads;
a condenser configured to receive the fluid from the evaporator and cool the fluid in which cooling the vapor forms the second liquid;
an accumulator configured to receive the second liquid from the condenser and store the second liquid; and
a pump system comprising a first pump and a second pump, the first pump configured to pump the first liquid in the liquid loop to the set of heat loads and the second pump configured to pump the second liquid stored in the accumulator to the evaporator and pump the second liquid from the condenser to the evaporator.
16 . An aircraft cooling system comprising:
a first pump configured to pump a first liquid in a liquid loop to a set of heat loads, wherein the set of heat loads heats the first liquid in which heating the first liquid forms a heated liquid;
an evaporator configured to receive the heated liquid and cool the heated liquid, wherein cooling the heated liquid causes a second liquid in a liquid-vapor loop to form a fluid selected at least one of a vapor or a superheated gas;
a condenser configured to receive the fluid and cool the fluid in which cooling the vapor forms the second liquid; and
a second pump configured to pump the second liquid from the condenser to the evaporator.
17 . An aircraft comprising:
a fuselage;
wings;
a number of engines connected to the wings;
an evaporator configured to cool a set of heat loads in the aircraft using a first liquid in a liquid loop, wherein cooling the set of heat loads forms a vapor from a second liquid in a liquid-vapor loop;
a condenser configured to receive the vapor from the evaporator and cool the vapor in which cooling the vapor forms the second liquid;
an accumulator configured to receive the second liquid from the condenser and store the second liquid; and
a pump system comprising a first pump and a second pump, the first pump configured to pump the first liquid in the liquid loop to the set of heat loads and the second pump configured to pump the second liquid stored in the accumulator to the evaporator and pump the second liquid from the condenser to the evaporator.
18 . The aircraft of claim 17 , wherein the condenser comprises a nacelle heat exchanger.
19 . The aircraft of claim 18 , wherein the condenser further comprises a fan system.
20 . The aircraft of claim 17 , wherein the condenser rejects heat into air traveling through a nacelle.
21 . The aircraft of claim 17 , wherein the condenser is located in a nacelle for an engine in the number of engines.
22 . A method for cooling a set of heat loads in an aircraft, the method comprising:
cooling the set of heat loads in the aircraft using a first liquid in a liquid loop in an evaporator, wherein cooling the set of heat loads forms a vapor from a second liquid in a liquid-vapor loop;
cooling the vapor with a condenser to form the second liquid;
receiving the second liquid from the condenser;
storing the second liquid in an accumulator; and
pumping the first liquid to the set of heat loads, pumping the second liquid stored in the accumulator to the evaporator, and pumping the second liquid from the condenser to the evaporator.
23 . A method for cooling a set of heat loads in an aircraft, the method comprising:
pumping a first liquid to the set of heat loads, wherein the set of heat loads heats in which heating the first liquid forms a heated liquid;
cooling the heated liquid in an evaporator, wherein cooling the heated liquid causes a second liquid in the evaporator to form a vapor;
sending the vapor to a condenser;
cooling the vapor in the condenser to form the second liquid; and
pumping the second liquid from the condenser to the evaporator.