Turbo expanders for turbine engines having hydrogen fuel systems
Aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander. The main engine core includes a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion. The turbo expander includes a rotor separated into a first expander portion and a second expander portion arranged about an output shaft and the output shaft is operably connected to a generator configured to generate electrical power.
1. An aircraft propulsion system, comprising:
aircraft systems comprising at least one hydrogen tank and an aircraft-systems heat exchanger; and
engine systems comprising at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section;
wherein hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion,
wherein the turbo expander comprises a rotor separated into a first expander portion and a second expander portion arranged about an output shaft, and
wherein the output shaft is operably connected to a generator configured to generate electrical power, and
a secondary tank configured to contain a secondary fluid that is supplied to the turbo expander and configured to provide at least one of seal buffering and a starting flow for the turbo expander.
2. The aircraft propulsion system of claim 1 , wherein the first expander portion of the rotor includes at least five blade rows and the second expander portion of the rotor includes at least seven blade rows.
3. The aircraft propulsion system of claim 1 , further comprising a gear box operably coupled between the output shaft and the generator.
4. The aircraft propulsion system of claim 1 , wherein the generator is configured to generate at least 1 MW of electrical power.
5. The aircraft propulsion system of claim 1 , wherein the secondary tank contains high pressure gaseous hydrogen.
6. The aircraft propulsion system of claim 1 , wherein electrical power from the generator is supplied to a wing anti-ice system.
7. The aircraft propulsion system of claim 1 , wherein the turbo expander is a radial inflow turbo expander.
8. The aircraft propulsion system of claim 1 , wherein the turbo expander is an axial inflow turbo expander.
9. The aircraft propulsion system of claim 1 , wherein a flow through the first expander portion is in a first direction and a flow through the second expander portion is in a second direction opposite the flow through the first expander portion.
10. An aircraft comprising:
a main engine core having a compressor section, a combustor section having a burner, a turbine section, and a turbo expander;
aircraft systems comprising at least one hydrogen tank and an aircraft-systems heat exchanger arranged remote from the main engine core;
wherein hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger and the turbo expander prior to being injected into the burner for combustion,
wherein the turbo expander comprises a rotor separated into a first expander portion and a second expander portion arranged about an output shaft, and
wherein the output shaft is operably connected to a generator configured to generate electrical power, and
a secondary tank configured to contain a secondary fluid that is supplied to the turbo expander and configured to provide at least one of seal buffering and a starting flow for the turbo expander.
11. The aircraft of claim 10 , further comprising a gear box operably coupled between the output shaft and the generator.
12. The aircraft of claim 10 , wherein the generator is configured to generate at least 1 MW of electrical power.
13. The aircraft of claim 10 , wherein the secondary tank contains high pressure gaseous hydrogen.
14. The aircraft of claim 10 , wherein electrical power from the generator is supplied to a wing anti-ice system of the aircraft.
15. The aircraft of claim 10 , wherein the turbo expander is a radial inflow turbo expander.
16. The aircraft of claim 10 , wherein the turbo expander is an axial inflow turbo expander.
17. The aircraft of claim 10 , wherein a flow through the first expander portion is in a first direction and a flow through the second expander portion is in a second direction opposite the flow through the first expander portion.
18. The aircraft of claim 10 , wherein the first expander portion of the rotor includes at least five blade rows and the second expander portion of the rotor includes at least seven blades rows.
19. An aircraft propulsion system, comprising:
aircraft systems comprising at least one hydrogen tank and an aircraft-systems heat exchanger; and
engine systems comprising at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section;
wherein hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion,
wherein the turbo expander comprises a rotor separated into a first expander portion and a second expander portion arranged about an output shaft,
wherein the output shaft is operably connected to a generator configured to generate electrical power, and
wherein a flow through the first expander portion is in a first direction and a flow through the second expander portion is in a second direction opposite the flow through the first expander portion.
20. An aircraft comprising:
a main engine core having a compressor section, a combustor section having a burner, a turbine section, and a turbo expander;
aircraft systems comprising at least one hydrogen tank and an aircraft-systems heat exchanger arranged remote from the main engine core;
wherein hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger and the turbo expander prior to being injected into the burner for combustion,
wherein the turbo expander comprises a rotor separated into a first expander portion and a second expander portion arranged about an output shaft,
wherein the output shaft is operably connected to a generator configured to generate electrical power, and
wherein a flow through the first expander portion is in a first direction and a flow through the second expander portion is in a second direction opposite the flow through the first expander portion.