Abstract: A waste heat utilization system and associated methods for preheating fuel for a turbine engine component. The turbine engine component includes at least one heat generating source. The system includes structure for applying heat from the at least one heat generating source to relatively cold fuel for the turbine engine component to preheat the fuel prior to ignition.

Abstract: Methods and apparatus for thermal barrier coatings are provided. The thermal barrier coating system includes a bond coat, a first thermal barrier coating comprising a thermal conductivity, kA having a first value, and a second thermal barrier coating including a thermal conductivity, kB having a second value wherein the second value is different than the first value.

Abstract: Disclosed is a solution to automate a seal oil float trap by-pass for a hydrogen cooled generator. An automated by-pass system is coupled to an existing manual by-pass system for a float trap for a hydrogen cooled generator. The automated by-pass system includes at least one solenoid valve and a controller that controls opening and closing of the solenoid valve. The automated by-pass system can also include manual valves, orifices and limit switches. The controller activates the solenoid valve to allow the seal oil to drain. The controller can also provide a notification alarm that the hydrogen cooled generator is being purged.

Abstract: A flexible and automatic system and method for blending an inexpensive secondary gas with a primary gas fuel for operation of a Dry Low NOx gas turbine. The secondary gas may be a gas fuel such as hydrogen, ethane, butane, propane and liquefied natural gas or an inert gas. Combustion dynamics are avoided by controlling the blended fuel within a permissible range for a Modified Wobbe Index. Combustion dynamics and gas turbine exhaust emissions may also be monitored to maintain safe combustion with the blended fuel. A gas turbine control system may adjust the blend and temperature of the primary gas fuel and the secondary gas to promote desired combustion.

Abstract: A waste heat utilization system and associated methods for preheating fuel for a turbine engine component. The turbine engine component includes at least one heat generating source. The system includes structure for applying heat from the at least one heat generating source to relatively cold fuel for the turbine engine component to preheat the fuel prior to ignition.

Abstract: Disclosed is a solution to automate a seal oil float trap by-pass for a hydrogen cooled generator. An automated by-pass system is coupled to an existing manual by-pass system for a float trap for a hydrogen cooled generator. The automated by-pass system includes at least one solenoid valve and a controller that controls opening and closing of the solenoid valve. The automated by-pass system can also include manual valves, orifices and limit switches. The controller activates the solenoid valve to allow the seal oil to drain. The controller can also provide a notification alarm that the hydrogen cooled generator is being purged.

Abstract: A flexible and automatic system and method for blending an inexpensive secondary gas with a primary gas fuel for operation of a Dry Low NOx gas turbine. The secondary gas may be a gas fuel such as hydrogen, ethane, butane, propane and liquefied natural gas or an inert gas. Combustion dynamics are avoided by controlling the blended fuel within a permissible range for a Modified Wobbe Index. Combustion dynamics and gas turbine exhaust emissions may also be monitored to maintain safe combustion with the blended fuel. A gas turbine control system may adjust the blend and temperature of the primary gas fuel and the secondary gas to promote desired combustion.

Abstract: Methods and systems for operating a gas turbine engine system include an electrical generator configured to provide electrical energy to a load, a gas turbine engine including at least one combustor that includes a plurality of fuel injection points configured to inject a fuel into the combustor at a plurality of different locations wherein the combustor configured to combust the fuel and the gas turbine engine is rotatably coupled to the generator through a shaft. The gas turbine engine system includes a control system including a plurality of sensors positioned about the gas turbine engine system and configured to measure at least one parameter associated with the sensor, a processor programmed to receive a signal indicative of a heating value of the fuel, and automatically control a fuel split between the fuel injection points on the combustor using the determined heating value.

Abstract: A fiber gas sensor includes a fiber core with first and second refractive index periodic modulated grating structures having different amplitude modulation profiles positioned about the fiber core. A fiber cladding is positioned about the first and second refractive index periodic modulated grating structures. A sensing layer is positioned about the fiber cladding of one of the refractive index periodic modulated grating structures. The sensing layer includes a sensing material made of a Pd-based alloy, such as nano-PdOx, nano-Pd(x)Au(y)Ni(1-x-y) or nano-Pd/Au/WOx. The fiber gas sensor provides a measurement of localized, temperature-corrected gas concentration and composition from a combustion environment. A reflection-based or a transmission-based sensing system with an array of one or more fiber gas sensors is also described.

Abstract: Methods and apparatus for thermal barrier coatings are provided. The thermal barrier coating system includes a bond coat, a first thermal barrier coating comprising a thermal conductivity, kA having a first value, and a second thermal barrier coating including a thermal conductivity, kB having a second value wherein the second value is different than the first value.

Abstract: Methods and systems for operating a gas turbine engine system include an electrical generator configured to provide electrical energy to a load, a gas turbine engine including at least one combustor that includes a plurality of fuel injection points configured to inject a fuel into the combustor at a plurality of different locations wherein the combustor configured to combust the fuel and the gas turbine engine is rotatably coupled to the generator through a shaft. The gas turbine engine system includes a control system including a plurality of sensors positioned about the gas turbine engine system and configured to measure at least one parameter associated with the sensor, a processor programmed to receive a signal indicative of a heating value of the fuel, and automatically control a fuel split between the fuel injection points on the combustor using the determined heating value.

Abstract: Method of stabilizing adherence of a ceramic layer to a bond coat of a TBC system, comprising incorporating silicon into the bond coat and maintaining cobalt present in the bond coat at a minimum level.

Abstract: A method of removing the damaged surface layer beneath a coating on a component. The method includes evaluating the component to assess the depth of the damaged substrate layer, followed by sensing a plurality of points over the outer surface of the component to determine a three-dimensional outer surface profile thereof. A three-dimensional grinding profile beneath the outer surface profile is then established based on the depth of the damaged substrate layer beneath the outer surface profile. The component is then ground along the grinding profile such that the damaged substrate layer is substantially removed without significantly removing an undamaged region of the substrate beneath the damaged substrate layer.

Abstract: A method of removing the damaged surface layer beneath a coating on a component. The method includes evaluating the component to assess the depth of the damaged substrate layer, followed by sensing a plurality of points over the outer surface of the component to determine a three-dimensional outer surface profile thereof. A three-dimensional grinding profile beneath the outer surface profile is then established based on the depth of the damaged substrate layer beneath the outer surface profile. The component is then ground along the grinding profile such that the damaged substrate layer is substantially removed without significantly removing an undamaged region of the substrate beneath the damaged substrate layer.