System for temperature and actuation control and method of controlling fluid temperatures in an aircraft
A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels. The system includes a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tank fluidly coupled to the engine, with the second fuel being different from the first fuel and having a different temperature than the first fuel, a fuel distribution unit (FDU) fluidly coupled to the first fuel tank of the first fuel system, and a fuel-to-fuel cooler (FFC) configured to transfer heat between the first fuel in the first fuel system and the second fuel in the second fuel system.
1. A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels, comprising:
a first fuel system having a first fuel tank fluidly coupled to the engine;
a second fuel system having a second fuel tank fluidly coupled to the engine, with the second fuel being different from the first fuel and having a different temperature than the first fuel;
a fuel distribution unit (FDU) fluidly coupled to the first fuel tank of the first fuel system and configured to distribute the first fuel from the first fuel tank to the engine; and
a fuel-to-fuel cooler (FFC) fluidly coupled with the first fuel system and the second fuel system and configured to transfer heat between the first fuel in the first fuel system and the second fuel in the second fuel system,
wherein said second fuel is liquefied natural gas (LNG).
2. The system of claim 1 , wherein the FDU is further configured to distribute the first fuel to additional portions of the first fuel system including the first fuel tank.
3. The system of claim 2 , further comprising a main fuel pump fluidly coupled between the first fuel tank and the FDU.
4. The system of claim 3 , wherein the FDU is further configured to distribute the first fuel to an inlet of the main fuel pump or to an intermediate main fuel pump location.
5. The system of claim 4 , further comprising a controller configured to control the FDU such that the FDU performs a dynamic distribution of the first fuel to portions of the first fuel system.
6. The system of claim 5 , wherein the controller utilizes engine based sensors.
7. The system of claim 5 , wherein the controller only operates the FDU in a cruise phase.
8. The system of claim 1 , wherein the first fuel is a liquid kerosene-based jet fuel.
9. The system of claim 8 , wherein the FFC is configured to transfer heat from gasified LNG to jet fuel at low LNG splits.
10. The system of claim 8 , wherein the FFC is configured to transfer heat from jet fuel to gasified LNG at high LNG demands.
11. The system of claim 1 , further comprising a fuel-to-fan-air cooler configured to supplement fuel temperature management within the first fuel system.
12. The system of claim 1 , wherein the FFC is located downstream of a supply of the second fuel and upstream of nozzles for outputting the second fuel.
13. A method of controlling fluid temperatures in an aircraft utilizing dual fuels for fueling an engine, comprising:
distributing, by a fuel distribution unit, a jet fuel from a first fuel system tank to a portion of the first fuel system;
distributing LNG from a second fuel system tank to a portion of the second fuel system, with the LNG having a different temperature than the jet fuel; and
transferring heat between the jet fuel in the first fuel system and the LNG in the second fuel system utilizing a FFC.
14. The method of claim 13 , wherein the fuel is dynamically distributed based on a commanded split between the LNG and jet fuel to the engine, system fuel pressures, temperatures, or a flight condition.
15. The method of claim 13 , wherein heat is transferred from the LNG to the jet fuel at low LNG splits and heat is transferred from the jet fuel to the LNG at high LNG demands.
16. The system of claim 2 , further comprising a fuel-to-fan-air cooler configured to supplement fuel temperature management within the first fuel system.
17. The system of claim 3 , further comprising a fuel-to-fan-air cooler configured to supplement fuel temperature management within the first fuel system.
18. The system of claim 4 , further comprising a fuel-to-fan-air cooler configured to supplement fuel temperature management within the first fuel system.
19. The system of claim 5 , further comprising a fuel-to-fan-air cooler configured to supplement fuel temperature management within the first fuel system.
20. The method of claim 14 , wherein heat is transferred from the LNG to the jet fuel at low LNG splits and heat is transferred from the jet fuel to the LNG at high LNG demands.