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.
Turbine engine assembly and dual fuel aircraft system
2017-07-04
Patent
Electronic Resource
English
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F23K Brennstoffzufuhr zu Feuerungen , FEEDING FUEL TO COMBUSTION APPARATUS / F23R Erzeugen von Verbrennungsprodukten hohen Druckes oder hoher Geschwindigkeit, z.B. Gasturbinenbrennkammern , GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS |
AIRCRAFT TURBINE ENGINE FUEL SYSTEM COMPONENT ENDURANCE TEST (CONTAMINATED FUEL)
SAE Technical Papers | 1981
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CONTAMINANTS FOR AIRCRAFT TURBINE ENGINE FUEL SYSTEM COMPONENT TESTING
SAE Technical Papers | 1994
Contaminants for Aircraft Turbine Engine Fuel System Component Testing
SAE Technical Papers | 2017