Gas turbine engines having cryogenic fuel systems
Turbine engine systems are described. The turbine engine systems include a combustor arranged along a core flow path of the turbine engine, a cryogenic fuel tank configured to supply a fuel to the combustor, a fuel supply line having a first flow supply line and a second flow supply line, the first flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a first core flow path heat exchanger, and the second flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a second core flow path heat exchanger, and a flow controller arranged along the fuel supply line and configured to respectively control a flow of fuel into the first flow supply line and the second flow supply line.
1. A propulsion system, comprising:
a turbine engine having a combustor arranged along a core flow path of the turbine engine;
an auxiliary power unit;
a cryogenic fuel tank configured to supply a fuel to at least one of the combustor and the auxiliary power unit;
a fuel supply line having a first flow supply line, a second flow supply line, and a third flow supply line, wherein the first flow supply line fluidly connects the cryogenic fuel tank to the combustor through a first core flow path heat exchanger, the second flow supply line fluidly connects the cryogenic fuel tank to the combustor through a second core flow path heat exchanger, and the third flow supply line fluidly connects the cryogenic fuel tank to the auxiliary power unit to supply fuel to the auxiliary power unit;
a first flow controller arranged along the fuel supply line and configured to respectively control a flow of fuel into at least one of the first flow supply line during a first operational parameter of the propulsion system, the second flow supply line during a second operational parameter of the propulsion system that is different from the first operational parameter, and the third flow supply line during a first third operational parameter of the propulsion system that is different from the first operational parameter and the second operational parameter,
an expansion turbine configured to receive fuel from at least one of the first flow supply line and the second flow supply line downstream of the respective first core flow path heat exchanger and second core flow path heat exchanger and upstream of the combustor; and
a second flow controller arranged between the expansion turbine and the combustor and configured to selectively divert at least a portion of fuel that exits the expansion turbine to the auxiliary power unit.
2. The propulsion system of claim 1 , wherein the first core flow path heat exchanger is a waste heat recovery heat exchanger arranged downstream form the combustor and proximate a core nozzle at an outlet of the core flow path.
3. The propulsion system of claim 1 , wherein the second core flow path heat exchanger is an intercooler heat exchanger arranged upstream from the combustor and between a low pressure compressor and a high pressure compressor arranged along the core flow path.
4. The propulsion system of claim 1 , wherein the second core flow path heat exchanger is a pre-cooler heat exchanger arranged upstream of a low pressure compressor arranged along the core flow path upstream from the combustor.
5. The propulsion system of claim 1 , further comprising a power electronics cooling heat exchanger arranged along the fuel supply line and configured to cool a working fluid associated with power electronics.
6. The propulsion system of claim 5 , wherein the power electronics cooling heat exchanger is arranged between the cryogenic fuel tank and the first flow controller.
7. The propulsion system of claim 5 , wherein the power electronics cooling heat exchanger is arranged along the fuel supply line downstream from each of the first core flow path heat exchanger and the second core flow path heat exchanger.
8. The propulsion system of claim 1 , further comprising a supplemental cooling heat exchanger arranged along the fuel supply line and configured to cool at least one of engine oil, environmental control system fluids, and cooled cooling air fluids.
9. The propulsion system of claim 8 , wherein the supplemental cooling heat exchanger is arranged between the cryogenic fuel tank and the first flow controller.
10. The propulsion system of claim 1 , wherein the expansion turbine is configured to generate work.
11. The propulsion system of claim 1 , further comprising at least one additional heat exchanger arranged between the expansion turbine and the combustor.
12. The propulsion system of claim 11 , wherein the at least one additional heat exchanger is a supplemental cooling heat exchanger arranged along the fuel supply line and configured to cool at least one of engine oil, environmental control system fluids, and cooled cooling air fluids.
13. The propulsion system of claim 11 , wherein the at least one additional heat exchanger includes a power electronics heat cooling heat exchanger.
14. The propulsion system of claim 1 , wherein the fuel includes liquid, compressed, or supercritical hydrogen or methane.
15. The propulsion system of claim 1 , wherein the turbine engine includes:
a fan, a low pressure compressor, a high pressure compressor, a high pressure turbine, and a low pressure turbine arranged sequentially along the core flow path,
wherein the fan, the low pressure compressor, and the high pressure compressor are arranged upstream of the combustor along the core flow path and the high pressure turbine and the low pressure turbine are arranged downstream of the combustor along the core flow path.
16. The propulsion system of claim 1 , wherein the auxiliary power unit includes a combustor configured to receive the fuel.
17. The propulsion system of claim 1 , wherein the auxiliary power unit includes a fuel cell configured to receive the fuel.
18. The propulsion system of claim 17 , further comprising a water tank configured to receive water from the fuel cell.