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The present application provides a gas turbine engine system for combusting a flow of fuel. The gas turbine engine system may include a combustor and a fuel system for providing the flow of fuel to the combustor. The fuel system may include a fuel heat exchanger so as to provide the flow of fuel to

The present application provides a gas turbine engine system for combusting a flow of fuel. The gas turbine engine system may include a combustor and a fuel system for providing the flow of fuel to the combustor. The fuel system may include a fuel heat exchanger so as to provide the flow of fuel to the combustor at a substantially constant temperature.

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1. A gas turbine engine system for combusting a flow of fuel, comprising: a combustor; anda fuel system, comprising: a fuel line configured to provide the flow of fuel to the combustor;a fuel heat exchanger positioned on the fuel line, wherein the fuel heat exchanger is configured to provide the flo

1. A gas turbine engine system for combusting a flow of fuel, comprising: a combustor; anda fuel system, comprising: a fuel line configured to provide the flow of fuel to the combustor;a fuel heat exchanger positioned on the fuel line, wherein the fuel heat exchanger is configured to provide the flow of fuel to the combustor at a substantially constant temperature to maintain a Modified Wobbe Index (MWI) of the flow of fuel within a desired range;a temperature control valve positioned on the fuel line upstream of the fuel heat exchanger, wherein the temperature control valve divides the fuel line into a bypass line and a heat exchanger line such that the flow of fuel in the bypass line bypasses the fuel heat exchanger and the flow of fuel in the heat exchanger line is directed to the heat exchanger, and wherein the bypass line and the heat exchanger line merge together downstream of the heat exchanger to reform the fuel line;a first temperature sensor positioned on the fuel line upstream of the temperature control valve;a second temperature sensor positioned on the fuel line downstream of the merger of the bypass line and the heat exchanger line, wherein the temperature control valve is configured to control the fuel based on temperatures from the first and second sensors; anda gas control valve positioned downstream of the second temperature sensor and upstream of the combustor, wherein the gas control valve is configured to control the volume or flow rate of the flow of fuel entering the combustor. 2. The gas turbine engine system of claim 1, wherein the fuel heat exchanger comprises an electric heater. 3. The gas turbine engine system of claim 2, wherein the electric heater comprises one or more heating elements and a heat exchanger portion. 4. The gas turbine engine system of claim 1, wherein the fuel heat exchanger comprises an oil or water bath heater. 5. The gas turbine engine system of claim 1, wherein the fuel heat exchanger comprises a direct fired heater. 6. The gas turbine engine system of claim 1, wherein the fuel heat exchanger comprises a heat pipe heat exchanger. 7. The gas turbine engine system of claim 6, wherein the heat pipe heat exchanger comprises a plurality of conductive pipes in communication with a heat exchange portion. 8. The gas turbine engine system of claim 1, wherein the fuel heat exchanger is in communication with a heat source. 9. The gas turbine engine system of claim 8, wherein the heat source comprises heat utilized from a source other than combustion gases exiting the combustor. 10. A method of operating a gas turbine with Modified Wobbe Index control without evaluating the constituents of an incoming flow of fuel, comprising: determining a first temperature of the incoming flow of fuel with a first temperature, sensor positioned on a fuel line upstream of a temperature control valve;providing at least a portion of the incoming flow of fuel to a fuel heat exchanger by way of the temperature control valve, wherein the a temperature control valve is positioned on the fuel line upstream of the fuel heat exchanger, wherein the temperature control valve divides the fuel line into a bypass line and a heat exchanger line to control the fuel based on the first temperature and a second temperature downstream of the bypass line, and wherein the bypass line and the heat exchanger line merge together downstream of the heat exchanger to reform the fuel line;bypassing at least a portion of the incoming flow of fuel from the heat exchanger by way of the bypass line;heating or cooling the flow of fuel with the fuel heat exchanger to a substantially constant temperature to maintain a Modified Wobbe Index (MWI) of the flow of fuel within a desired range; anddelivering the flow of fuel to a combustor at the substantially constant temperature by way of a gas control valve positioned on the fuel line downstream of the merger of the bypass line and the heat exchanger line and upstream of the combustor, wherein the gas control valve is configured to control the volume or flow rate of the flow of fuel entering the combustor. 11. A gas turbine engine system for combusting a flow of fuel, comprising: a combustor; anda fuel system, comprising: a fuel line configured to provide the flow of fuel to the combustor;a fuel heat exchanger positioned on the fuel line, wherein the fuel heat exchanger is configured to provide the flow of fuel to the combustor at a substantially constant temperature to maintain a Modified Wobbe Index (MWI) of the flow of fuel within a desired range;a temperature control valve positioned on the fuel line upstream of the fuel heat exchanger, wherein the temperature control valve divides the fuel line into a bypass line and a heat exchanger line such that the flow of fuel in the bypass line bypasses the fuel heat exchanger and the flow of fuel in the heat exchanger line is directed to the heat exchanger, and wherein the bypass line and the heat exchanger line merge together downstream of the heat exchanger to reform the fuel line;a first temperature sensor positioned on the fuel line upstream of the temperature control valve, wherein the temperature control valve is configured to control the fuel based on temperatures from the first sensor and a second sensor downstream of the bypass line; anda gas control valve positioned on the fuel line downstream of the merger of the bypass line and the heat exchanger line and upstream of the combustor, wherein the gas control valve is configured to control the volume or flow rate of the flow of fuel entering the combustor. 12. The gas turbine engine system of claim 11, wherein the fuel heat exchanger comprises an electric heater. 13. The gas turbine engine system of claim 11, wherein the fuel heat exchanger comprises an oil or water bath heater. 14. The gas turbine engine system of claim 11, wherein the fuel heat exchanger comprises a direct fired heater. 15. The gas turbine engine system of claim 11, wherein the fuel heat exchanger comprises a heat pipe heat exchanger.