US 12,736,011 B1Granted

Distillation system temperature control system

AssigneeHoneywell Aerospace US LLC

InventorsKevin Dittmar, Eric Shepard, Jeffrey Maldonado, Matthew Dunn

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Abstract

A gas turbine engine system includes a gas turbine engine, a bypass duct, and a bypass control valve. The gas turbine engine includes at least a compressor section, a combustion section, and a turbine section. The bypass duct has a bypass duct inlet that is disposed between the compressor section and the combustion section, and a bypass duct outlet that is disposed downstream of the turbine section. The bypass control valve is disposed on the bypass duct and is moveable to a commanded valve position, which is one of a closed position, in which compressed air from the compressor section does not flow through the bypass duct, and a plurality of open positions, in which compressed air discharged from the compressor section flows through the bypass duct and mixes with exhaust gas discharged from the turbine section to form the discharge gas that is supplied to the main chamber.

Claims8

Dependent claims

A distillation system temperature control system, comprising:

a tank having a first end wall, a second end wall, a front wall, a back wall, a top wall, and a bottom wall that together define an inner volume, a divider wall disposed within the tank and dividing the inner volume into a main chamber and a settling chamber, the main chamber having at least a fluid inlet port and an exhaust gas inlet port, the settling chamber having at least an exhaust gas outlet port, the divider wall having an opening formed therein that provides fluid communication between the main chamber and the settling chamber;
a diffuser disposed within the main chamber and coupled to the exhaust gas inlet port;
and
a gas turbine engine system in fluid communication with the exhaust gas inlet port, the gas turbine engine system configured, during operation thereof, to supply a discharge gas to the exhaust gas inlet port, the gas turbine engine system comprising:
a gas turbine engine including at least a compressor section, a combustion section, and a turbine section;
a bypass duct having a bypass duct inlet and a bypass duct outlet, the bypass duct inlet disposed between the compressor section and the combustion section to receive compressed air discharged from the compressor section, the bypass duct outlet disposed downstream of the turbine section;
and
a bypass control valve disposed on the bypass duct and moveable to a commanded valve position, the commanded valve position being one of a closed position, in which compressed air from the compressor section does not flow through the bypass duct, and a plurality of open positions, in which compressed air discharged from the compressor section flows through the bypass duct and mixes with exhaust gas discharged from the turbine section to form the discharge gas that is supplied to the exhaust gas inlet port.

5 more elements

A method of controlling temperature in a distillation system that comprises a tank, a diffuser, a gas turbine engine, a bypass duct, and a bypass control valve, wherein (i) the tank has a first end wall, a second end wall, a front wall, a back wall, a top wall, and a bottom wall that together define an inner volume, a divider wall disposed within the tank and dividing the inner volume into a main chamber and a settling chamber, the main chamber having at least a fluid inlet port and an exhaust gas inlet port, the exhaust gas inlet port coupled to receive a flow of discharge gas, (ii) the diffuser is disposed within the main chamber and is coupled to the exhaust gas inlet port, (iii) the gas turbine engine is in fluid communication with the exhaust gas inlet port, and includes at least a compressor section, a combustion section, and a turbine section, and is configured, during operation thereof, to discharge exhaust gas, (iv) the bypass duct has a bypass duct inlet disposed between the compressor section and the combustion section to receive compressed air discharged from the compressor section, and a bypass duct outlet disposed downstream of the turbine section, (v) the bypass control valve is mounted on the bypass duct and is movable to a commanded valve position, and wherein the method comprises the steps of:

sensing, via a temperature sensor, temperature of the discharge gas supplied to the exhaust gas inlet port and supplying a temperature signal indicative of the sensed temperature;
and
commanding, via a valve control in operable communication with the temperature sensor and the bypass control valve, the bypass control valve to move to a commanded position based at least in part on the temperature sensor signal, to thereby control:
(i) an amount of compressed air that flows through the bypass duct and mixes with exhaust gas discharged from the turbine section to form the discharge gas that is supplied to the main chamber, and
(ii) the temperature of the discharge gas.

2 more elements

Dependencies are inferred from the claim text.