Turbine engine assembly and dual fuel aircraft system
A turbine engine assembly having a turbine core with a compressor section, a combustion section, a turbine section, and a nozzle section and a liquid natural gas (LNG) fuel system having a LNG reservoir, a vaporizer heat exchanger, a first liquid supply line operably coupling the LNG reservoir to an input of the vaporizer heat exchanger, a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section, a second liquid supply line operably coupling the LNG reservoir to the gas supply line and a thermostatic expansion valve (TEV) and a dual fuel aircraft control system.
1. A turbine engine assembly comprising:
a turbine core comprising:
a compressor section;
a combustion section;
a turbine section; and
a nozzle section; wherein the sections are axially aligned; and
a liquid natural gas (LNG) fuel system comprising:
a LNG reservoir;
a vaporizer heat exchanger located within the turbine core;
a first liquid supply line operably coupling the LNG reservoir to an input of the vaporizer heat exchanger;
a gas supply line operably coupling an output of the vaporizer heat exchanger to the combustion section;
a second liquid supply line operably coupling the LNG reservoir to the gas supply line; and
a thermostatic expansion valve (TEV) controlling a flow of LNG from the second liquid supply line to the gas supply line and having a temperature sensor operably coupled to the gas supply line downstream of the TEV, wherein a flow rate of LNG through the second liquid supply line is controlled by the TEV based on a temperature of fluid within the gas supply line.
2. The turbine engine assembly of claim 1 wherein the second liquid supply line is branched from the first liquid supply line.
3. The turbine engine assembly of claim 2 wherein the branch occurs upstream of the TEV.
4. The turbine engine assembly of claim 1 wherein the vaporizer heat exchanger is immersed in an exhaust flow of the turbine core.
5. The turbine engine assembly of claim 1 wherein the vaporizer heat exchanger is mounted on a wall of an exhaust passage of the turbine core.
6. The turbine engine assembly of claim 1 , further comprising a flow control valve controlling the flow of fluid through the gas supply line.
7. The turbine engine assembly of claim 6 wherein the flow control valve is downstream of the TEV.
8. The turbine engine assembly of claim 1 , wherein the TEV is moveable between a fully opened position and a fully closed position.
9. The turbine engine assembly of claim 8 wherein the TEV further comprises an inlet fluidly coupled with the second liquid supply line and an exit selectively fluidly coupled to the gas supply line allowing LNG to bypass the vaporizer heat exchanger when the TEV is in a partially opened position or the fully opened position.
10. The turbine engine assembly of claim 9 wherein when the temperature is too hot, the TEV is configured to move towards the fully opened position and when the temperature is too cold, the TEV is configured to move towards the fully closed position.
11. A dual fuel aircraft system for a turbine engine of an aircraft, comprising:
a first fuel system for controlling a flow of a first fuel from a first fuel tank to the turbine engine; and
a second fuel system for controlling a flow of a liquid natural gas (LNG) to the turbine engine, comprising:
a LNG reservoir;
a vaporizer heat exchanger mounted on or near the turbine engine;
a first liquid supply line operably coupling the LNG reservoir to an input of the vaporizer heat exchanger;
a gas supply line operably coupling an output of the vaporizer heat exchanger to the turbine engine;
a second liquid supply line operably coupling the LNG reservoir to the gas supply line; and
a thermostatic expansion valve (TEV) controlling a flow of LNG from the second liquid supply line to the gas supply line and having a temperature sensor operably coupled to the gas supply line downstream of the TEV, wherein a flow rate of LNG through the second liquid supply line is controlled by the TEV based on a temperature of fluid within the gas supply line.
12. The dual fuel aircraft system of claim 11 wherein the second fuel system further comprises a flow control valve controlling the flow of fluid through the gas supply line to the turbine engine.
13. The dual fuel aircraft system of claim 11 , wherein the TEV is moveable between a fully opened position and a fully closed position.
14. The dual fuel aircraft system of claim 13 wherein when the temperature is too hot, the TEV is configured to move towards the fully opened position and when the temperature is too cold, the TEV is configured to move towards the fully closed position.
15. The dual fuel aircraft system of claim 14 wherein the temperature sensor comprises a thermal sensing bulb fluidly coupled with a moveable element of the TEV.