Abstract: An apparatus and methods for measuring combustion parameters in the measurement zone of a gas turbine engine. The measurement zone is defined as being between an outer casing and an engine component having a reflecting surface inside the outer casing. The apparatus comprises a laser generating a transmitting beam of light of a select wavelength and a multimode transmitting fiber optically coupled to the laser. A transmitting optic is optically coupled to the multimode optical fiber for transmitting the beam into the measurement zone. The reflecting surface is configured to provide a Lambertian reflection. A receiving optic is positioned to receive the Lambertian reflection. Means are provided in operative association with the multimode transmitting fiber for averaging modal noise induced signal level variation of light propagating within the multimode transmitting fiber.

Abstract: A liquefied natural gas (LNG) transport vessel for transporting liquefied natural gas (LNG) is disclosed which is capable of storing excess boil off gas BOG until needed for combustion in one or more combustion apparatus on the vessel. A method for managing the delivery of the BOG to the combustion apparatus is also described. The LNG vessel includes at least one insulated LNG storage tank which stores LNG. A first stage LNG receiver receives and stores BOG from the at least one LNG storage tank. A second stage or high pressure BOG storage tank receives compressed BOG from the receiver and stores the BOG as needed for combustion by one or more combustion apparatus of the vessel. A pressure regulator allows BOG gas to be delivered to the combustion apparatus if there is sufficient pressure in the high pressure storage tank to passively deliver the BOG at a predetermined delivery pressure.

Abstract: A fuel delivery system for a combustion turbine engine, comprising: a fuel line having a fuel compressor and parallel branches downstream of the fuel compressor: a cold branch that includes an after-cooler; and a hot branch that bypasses the after-cooler; a rapid heating value meter configured to measure the heating value of the fuel from the fuel source and transmit heating value data relating to the measurements; means for controlling the amount of fuel being directed through the cold branch and the amount of fuel being directed through the hot branch; and a fuel-mixing junction at which the cold branch and the hot branch converge; wherein the fuel-mixing junction resides in close proximity to a combustor gas control valve.

Abstract: A method for operating a firing plant with at least one combustion chamber and at least one burner, especially a gas turbine, includes an operating characteristic for operating the combustion chamber close to the lean extinction limit defined as a burner group staging ratio (BGVRich). Pressure pulsations (PulsActual) measured in the combustion chamber are processed by a filter device (2) and converted into corresponding signals (PulsActual,Filter(t)). An exceeding/falling short of at least one pulsation limiting value (PulsLimit) is monitored by a monitoring device (3) and adapts a pulsation reference value (PulsRef) in dependence upon the monitoring. The processed pressure pulsations (PulsActual,Filter(t)) are then compared with the adapted pulsation reference value (PulsRef,adapt), and, from this, a correction value ?BGV is determined, by which the burner group staging ratio (BGVRich) is corrected, and as a result operation of the firing plant close to the lean extinction limit is realized.

Abstract: A tuning process is provided for dynamically tuning a gas-turbine (GT) engine to correct for flashback events without directly measuring occurrences of the flashback events at the GT engine. Initially, readings are taken that measure low-frequency dynamics at the GT engine. A determination of whether flashback criteria are met by an instantaneous signal that quantifies a detected spike within the measured low-frequency dynamics is carried out, where the flashback criteria include the following: identifying the spike overcomes a multiple of an average of the low-frequency dynamics measured over a predefined period of time; and identifying the spike overcomes a preestablished minimum amplitude. Upon the spike meeting the flashback criteria, a count is added to a running record of spikes, which is compared to an alarm limit. If the alarm limit is triggered, action(s) are invoked to address the flashback events, such as adjusting fuel-flow splits of the GT engine.

Abstract: A system includes a gas turbine engine that includes a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The fluid supply system is configured to route an inert gas to the exhaust section.

Abstract: Systems and methods for implementing engine cycle counts are disclosed. One method may include determining, by at least one processor, a plurality of cycles associated with an engine; determining a category, by at least one processor, for each of the plurality of cycles based at least in part on an acceleration value associated with each of the plurality of cycles; and predicting, by at least one processor, a life cycle associated with the engine based at least in part on the determined category.

Abstract: A gas turbine engine fuel supply system includes a primary gear pump and a secondary gear pump. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The supercharger pump is preferably activated only during high demand conditions as an additional energy conservation measure.

Abstract: A fuel delivery system for delivering fuel to a gas turbine engine includes a fixed critical flow nozzle, a first fuel nozzle and a second fuel nozzle. The fixed critical flow nozzle and the variable critical flow nozzle are connected to a fuel source in parallel. The fixed critical flow nozzle has an orifice throat with a fixed effective cross-sectional area. The variable critical flow nozzle has an orifice throat with a variable effective cross-sectional area. The first fuel nozzle is connected to the fixed critical flow nozzle for delivering fuel to the gas turbine engine, and the second fuel nozzle is connected to the variable critical flow nozzle for delivering fuel to the gas turbine engine.

Abstract: The disclosure relates to a method for operating a gas turbine plant which is supplied with a fuel gas via a compressor station. The compressor station includes a compressor which compresses the fuel gas which is fed via a gas feed line and delivers it via at least one control valve to a combustion chamber of the gas turbine plant. A bypass system is arranged in parallel to the compressor via which fuel gas can be directed in a switchable manner past the compressor to the at least one control valve. An energy-saving operation can be achieved in a simple manner by continuously measuring the fuel gas pressure at the outlet of the at least one control valve. A minimum fuel gas pressure, which is desired (e.g., necessary) for operation of the gas turbine, at the inlet of the at least one control valve is determined from the measured pressure values in each case.

Abstract: A multi-stage, two-flow, axial flow expander close-coupled to a driven machine, such as a generator. The expander includes one or more expansion stages separated by a series of flow stream dividers that separate each expansion stage into outer and inner expander flowpaths. Working fluid at a first temperature is directed into the outer expander flowpath for expansion, and working fluid at a second, lesser temperature is directed into the inner expander flowpath for expansion. Expansion of the working fluid drives the driven machine.

Abstract: The disclosure is concerned with generating power using new organic fuel that is generated at wastewater purification plants in the form of sewage sludge with moisture content up to 90-95%. The world supplies this new orgabic fuel in very high quantites that are estimated to be more than 25-40 gr of dry mass/man/day. The new composite fuel comprises a coal suspension with the new dispersed medium, which is the liquid sewage sludge. The composite fuel is introduced into a furnace for combustion and generating power.

Abstract: A method is provided for use with an annular gas turbine engine component that includes a main body and an annular seal engaged to the main body with an interference fit. The method includes rotating the annular gas turbine engine component, directing thermal energy from a heat source at the annular seal to thermally expand the annular seal relative to the main body while the annular gas turbine engine component rotates, removing the heated annular seal from the main body, providing a newly manufactured replacement detail having substantially the same configuration as the main body, and engaging the removed annular seal to the replacement detail with an interference fit.

Abstract: A heating medium supply system is provided which, even when a temperature fluctuation of a heating medium occurs continuously, is capable of relieving a bad thermal influence upon a heat exchanging device due to the temperature fluctuation. The heating medium supply system includes: a heating system configured to heat a liquid heating medium by sunlight; a heat exchanging device configured to heat feedwater; heating medium supply piping for circulating the heating medium; a heating medium temperature detecting device, a heating medium flow rate detecting device and a first heating medium flow control valve; and a control device capable of calculating a value of supply thermal energy from results of detections by the heating medium temperature detecting device and the heating medium flow rate detecting device and controlling an operation of the heating medium flow control valve based on the value of supply thermal energy thus calculated.

Abstract: According to one embodiment of the present disclosure, an exhaust apparatus for an auxiliary power unit is disclosed. The exhaust apparatus may include an exhaust housing including a perforated body surrounding an exhaust airflow of the auxiliary power unit. The perforated body may include an outer surface, an inner surface, and a plurality of holes through which ambient air passes to mix with the exhaust airflow, the plurality of holes extending through the body from the outer surface to the inner surface.

Abstract: A diffuser assembly is provided herein. In certain embodiments, the diffuser assembly may include an outer boundary member and an inner boundary member, with the inner boundary member being positioned radially inward of the outer boundary member. The diffuser assembly also may include an exhaust flow path defined between the outer boundary member and the inner boundary member. Further, the diffuser assembly may include at least one flow deflecting member operatively attached to the outer boundary member. The flow deflecting member may be adjustable about the outer boundary member to produce a substantially uniform velocity distribution within the exhaust flow path.

Abstract: A gas turbine engine lube oil system (740) includes a first passage (750) and a second passage (760). The first passage (750) includes a first elongated compartment (751) with a closed end (752) and a first open end (753) distal to the closed end (752). The first passage (750) also includes a plurality of bearing return line connection points. The second passage (760) includes a second elongated compartment (761) with a suction end (762) and a second open end (763) distal to the suction end (762). The first open end (753) is in flow communication with the second open end (763).

Abstract: A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a forward pressure differential of the fuel system used to maintain fuel supply for engine operation, and under the reversed pressure differential substantially purging the fuel remaining in the system therefrom to a fuel source.

Abstract: The speed of a high-pressure turbine of a gas turbine engine may be determined using known centrifugal pump affinity relationships for a fuel pressure apparatus, fuel pressure apparatus input and output pressures, and gear ratios for a mechanical linkage between the high-pressure turbine and the fuel pressure apparatus. The technique avoids wear-related variations in gas pressure based measurements and also applies to fuel pressure apparatus using both single pump and multiple pump configurations.

Abstract: A fuel routing system of a gas turbine engine includes a primary fuel circuit in communication with a fuel source and a fuel distribution manifold. Also included is a secondary fuel circuit extending from the primary fuel circuit to a plurality of fuel nozzles configured to direct fuel to a plurality of combustor chambers. Further included is a main fuel flow control valve disposed in the primary fuel circuit for restricting a fuel flow to the fuel distribution manifold upon removal of an electrical load operably coupled to the gas turbine engine. Yet further included is a plurality of check valves disposed between the secondary fuel circuit and the primary fuel circuit for restricting the fuel flow between the secondary fuel circuit and the primary fuel circuit.

Abstract: A late lean injection combustor assembly may include a first interior in which a first fuel supplied thereto is combustible, a flow sleeve annulus including a second interior in which a second fuel supplied thereto is combustible, at least one fuel injector disposed about the second interior, and at least one elongate premixing conduit disposed about the flow sleeve annulus and in fluid communication with the at least one fuel injector. The at least one elongate premixing conduit may be in fluid communication with a compressor discharge air and the second fuel such that the compressor discharge air and the second fuel are premixed within the elongate premixing conduit before entering the second interior by way of the at least one fuel injector.

Abstract: It is desirable for a gas turbine system to operate in a wide range operating conditions. However, under certain conditions there exist dynamic boundaries that limit a combustor from reaching its designated condition. Perturbation devices formed of electromagnetic plates can be incorporated into fuel nozzles of the combustor to influence the dynamics so that the range of operating conditions can be widened. The perturbation devices vibrate according to the perturbation signals provided from a dynamics controller. The vibration characteristics of the perturbation devices can be controlled by controlling the attributes of the perturbation signals. The vibrations influence the dynamics of fluid—fuel, oxidant, or both—flowing past the perturbation devices within the fuel nozzles.

Abstract: A gas turbine engine includes a fan section and an intercooling turbine section along an engine axis aft of a fan section and forward of a combustor section.

Abstract: Systems and methods for controlling mode transfers of a turbine combustor are provided. According to one embodiment, a system may include a controller to control a combustor, and a processor communicatively coupled to the controller. The processor may be configured to receive current operating conditions, target operating limits, and combustor transfer functions. The combustor transfer functions may be evaluated to estimate operating limits associated with one or more combustion modes under the current operating conditions. The estimated operating limits associated with the one or more combustor modes may be compared to the target operating limits, and, based on the comparison, at least one of the combustion modes may be selected. The combustor may then be selectively transferred to the selected combustion mode.

Abstract: In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter greater than that of a minor diameter such that the shrouds define an ovate shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds.

Abstract: A fuel nozzle configured to channel fluid toward a combustion chamber within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a first hollow tube fabricated from a first material that has a first coefficient of thermal expansion and a second tube fabricated from a second material that has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The second tube is coupled within the first tube such that the first tube substantially circumscribes the second tube, and the second tube thermally expands approximately at a same rate as the first tube during fuel nozzle operation.

Abstract: A system includes a fuel supply system. The fuel supply includes a primary fuel supply, a fuel additive supply, and a common pipeline coupled to the primary fuel and fuel additive supplies. The primary fuel supply includes a primary fuel having a first average molecular weight. The fuel additive includes a fuel additive having a second molecular weight that is greater than the first average molecular weight. The common pipeline is configured to direct a mixture of the primary fuel and the fuel additive into a fuel nozzle.

Abstract: The present invention relates to a power plant for generating electrical power having a burner unit, wherein thermal energy can be produced by burning a fuel, a turbine unit, wherein a rotational movement can be produced with the thermal energy, and a generator unit which is driven by the rotational movement to generate electrical power. The power plant is characterised according to the invention in that in order to produce the thermal energy, in addition to the burner unit, an electric heating unit is provided, through which electrical energy can be converted into thermal energy to drive the turbine unit. In addition the invention relates to a method for generating electrical power.

Abstract: Systems, methods and apparatus for noise attenuation of a generator set are disclosed. The generator set includes an internal combustion engine enclosed within a compartment that substantially isolates the internal combustion from ambient air and a load connected to the internal combustion engine. A heat exchanger is disposed within or coupled to the compartment and is operable to cool air in the compartment without directly exchanging ambient air with compartment air.

Abstract: A gas turbine engine includes, among other things, a propulsion assembly situated to rotate about an engine central axis. Operation of the propulsion assembly requires a first amount of fluid during a first operating condition and a second, greater amount of the fluid during a second operating condition. A first pump is operatively associated with a low speed spool that rotates with a low pressure turbine. The first pump has a first fluid delivering capacity corresponding to at least the first amount. A second pump has a second fluid delivering capacity configured to correspond to at least a difference between the first amount and the second amount. The first pump provides the fluid for propulsion assembly during the first and second operating conditions and the second pump provides the fluid for propulsion assembly operation only during the second operating condition.

Abstract: A gas-turbine combustion chamber arrangement includes at least one centrifugal compressor as well as one centripetal annular combustion chamber, with a stator vane arrangement being provided between the centrifugal compressor and the annular combustion chamber. The stator vane arrangement for diverting the air flowing out of the centrifugal compressor is designed at an angle ? of 20° to 30°, preferably 25°, relative to the engine axis, so the airflow is passed at essentially this angle ? to the combustion chamber. The inflow area into the combustion chamber for supplying air is designed at an angle of 20° to 30°, preferably 25°, relative to the meridional plane, and the center axes of the burners or of the injection nozzles of the combustion chamber are arranged inclined at an angle ? of 30° to 40°, preferably 35°, relative to a meridional plane passing through the engine axis.

Abstract: A system for operating a thermal power plant during off-peak demand intervals includes a gas turbine having a compressor, a combustor connected to a fuel control system, a turbine and a sensor configured to sense ambient conditions around the gas turbine. The fuel control system and the sensor are in communication with a controller. The controller is configured to receive a user input that corresponds to a value for an operational boundary condition of the thermal power plant and to monitor ambient conditions through the sensor. The controller is further configured to generate a predicted emissions level value for the gas turbine based on the monitored ambient conditions and to generate a command signal to adjust at least one operational parameter of the gas turbine based at least in part on the predicted emissions level value and the value of the operational boundary condition of the thermal power plant.

Abstract: A lubrication system is disclosed. The lubrication system may be used in conjunction with a gas turbine engine for generating power or lift. The lubrication system utilized a flow scheduling valve which reduces lubricant flow to at least one component based on an engine load. The lubrication system may further include a main pump which may be regulated by an engine speed. Thus, a lubrication system which provides a lubricant to engine components based on the load and speed of the engine is possible. The system may improve efficiency of the engine by reducing the power previously spent in churning excess lubricant by at least one engine component as well as reducing the energy used by a lubricant cooler in cooling the excess lubricant. The lubricant cooler size may also be minimized to reduce weight and air drag due to the reduced lubricant flow.

Abstract: Systems and methods for injection of feedstock are included. In one embodiment, a system includes a solid fuel injector. The solid fuel injector includes a solid fuel passage, a first gas passage, and a second gas passage. The solid fuel passage is configured to inject a solid fuel through a fuel outlet in a fuel direction. The first gas passage is configured to inject a first gas through a first gas outlet in a first gas direction. The second gas passage is configured to inject a second gas through a second gas outlet in a second gas direction. The first gas direction is oriented at a first angle relative to the fuel direction. The second gas direction is oriented at a second angle relative to the fuel direction, and the first and second angles are different from one another.

Abstract: A gas turbine engine includes: a compressor; a combustor downstream of the compressor along a gaspath; a turbine downstream of the combustor along the gaspath; a plurality of wash nozzles having outlets along the gaspath; and at least one inlet fitting coupled to the wash nozzles to bound a wash flowpath from an inlet port of the at least one inlet fitting to said outlets of said nozzles. The plurality of stages include: a stage upstream of blades of one compressor section; and another stage between said blades of one compressor section and blades of another compressor section.

Abstract: Embodiments of the disclosure include a combustor assembly. The combustor assembly may include one or more fuel plenums. The combustor assembly may also include one or more fuel distribution plates disposed within the fuel plenums. Moreover, the combustor assembly may include a number of mixing tubes disposed at least partially within the fuel plenums and extending through the fuel distribution plates. In certain aspects, the mixing tubes may each include a reduced diameter about the fuel distribution plates to form an annulus therebetween.

Abstract: A fuel nozzle for use in a turbine engine is provided. The fuel nozzle includes a fuel injector configured to discharge a flow of fuel therefrom and a premixer tube coupled in flow communication with the fuel injector. The premixer tube is configured to receive the fuel flow and a flow of air at an upstream end of the premixer tube, wherein the fuel and air are progressively mixed as the fuel and air are channeled through the length of the premixer tube.

Abstract: A cooled combustor seal having a plurality of channels enabling cooling air to pass from outside of a combustion chamber to cool an area inside the combustion chamber around the seal is disclosed. The channels may be provided through a slider, a housing, and/or a washer of the combustor seal. One set of channels or multiple of sets of channels may be provided in the combustor seal. Each of these sets of channels may be in the slider, housing, or washer. The cooled combustor seal may be used in conjunction with an igniter to purge a cavity between the seal and the igniter.

Abstract: An integrated plate is provided for use with a combustor including a casing, a fuel plenum extending circumferentially about the casing, and a fuel nozzle extending axially through the casing. The integrated plate includes a plurality of fuel injection pegs that extend radially between the fuel plenum and the fuel nozzle.

Abstract: A system for reducing modal coupling of combustion dynamics includes a plurality of combustors, and at least one fuel injector in each of the plurality of combustors. The system also includes structure for dithering a combustion instability frequency in at least one combustor in the plurality of combustors. A method for reducing modal coupling of combustion dynamics includes flowing a compressed working fluid at a temperature to a plurality of combustors and flowing a fuel to at least one fuel injector in each of the plurality of combustors. The method further includes dithering at least one of the temperature of the compressed working fluid flowing to the plurality of combustors or the fuel flow to the at least one fuel injector in at least one combustor in the plurality of combustors.

Abstract: A method for operating a compressed air energy storage system is provided. The method can include compressing a process gas with a compressor train to produce a compressed process gas and storing the compressed process gas in a compressed gas storage unit. The method can also include extracting the compressed process gas from the compressed gas storage unit to an expansion assembly through a feed line. A valve assembly fluidly coupled to the feed line can be actuated to control a mass flow of the compressed process gas from the compressed gas storage unit to the expansion assembly. The method can further include heating the compressed process gas in a preheater fluidly coupled to the feed line upstream from the expansion assembly, and generating a power output with the expansion assembly.

Abstract: A hydrogen generator having one or more actuators coupled to one or more heating elements in which the actuator(s) are used to improve the transfer of thermal energy from heating element(s) to one or more fuel units contained within the generator. In one embodiment, an actuator allows insertion and/or removal of packaged fuel units without the need of removing the heating element(s) and/or the actuator(s). When the actuator is in a retracted state (e.g., a low temperature state), the packaged fuel unit may be inserted and/or removed from a cavity of the hydrogen generator. When the actuator is in an extended state (e.g., a higher temperature state), the actuator forces contact between itself or the heating element and the fuel unit when a prescribed operating temperature is reached.

Abstract: In a temperature estimation apparatus for an aeroplane gas turbine engine, there are provided with a calculator that calculates a low-pressure turbine outlet temperature change (dEGT) based on low-pressure turbine rotational speed (N1) and ambient temperature (T1), a calculator that calculates a model outlet temperature (MODEL-EGTC) based on corrected high-pressure turbine rotational speed (N2C) and atmospheric pressure (P0) to calculate a model outlet temperature difference (dEGTC) by subtracting the calculated temperature (MODEL-EGTC) from a corrected low-pressure turbine outlet temperature (EGTC), a calculator that calculates a correction amount (dEGTad) relative to the model outlet temperature difference (dEGTC) based on the model outlet temperature difference (dEGTC) and low-pressure turbine rotational speed (N1), and a calculator that calculates an estimation value of the low-pressure turbine inlet temperature (ITT) based on the low-pressure turbine outlet temperature (EGT), etc.

Abstract: A pulse detonation device contains a pulse detonation combustor which detonates a mixture of oxidizer and fuel. The fuel is supplied through fuel ducts and the fuel flow is controlled by fuel flow control devices. Oxidizer flow is provided through a main inlet portion and a flow control device directs the oxidizer flow to either the combustor or to a bypass duct, or both. The combustor further contains an ignition source. Each of the flow control devices, fuel flow control devices and ignition source are controlled by a control system to optimize performance at different thrust/power settings for the device.

Abstract: A cross-fire tube purging arrangement includes a cross-fire tube extending from proximate a combustor chamber to proximate an adjacent combustor chamber for fluidly coupling the combustor chamber and the adjacent combustor chamber. Also included is a compressed air supply arrangement for selectively delivering a compressed air to the cross-fire tube, the compressed air supply arrangement comprising a regulating component for controlling delivery of the compressed air to the cross-fire tube.

Abstract: A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, a combustor assembly including at least one combustor fluidically connected to the turbine portion, and an accessory mechanically linked with and driven by the turbine portion. The gas turbomachine also includes a fuel pre-heat system including a fuel pre-heat element having a fuel circuit fluidically connected to the at least one combustor arranged in a heat exchange relationship with a heating medium circuit fluidically connected to at least one of the compressor portion, the turbine portion, and the accessory.

Abstract: A system for cooling a hot gas path component for a combustor generally includes an impingement sleeve that circumferentially surrounds an outer surface of the hot gas path component. A first cooling chamber is defined between the impingement sleeve and a first portion of the outer surface of the hot gas path component. A second cooling chamber is disposed downstream from the first cooling chamber. The second cooling chamber is defined between the impingement sleeve and a second portion of the outer surface of hot gas path component. An inlet extends through the impingement sleeve so as to define a first flow path into the first cooling chamber. An outlet defines a second flow path between the first cooling chamber and the second cooling chamber.

Abstract: A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.

Abstract: A system includes a turbine combustor, which includes a first wall disposed about a combustion chamber, a second wall disposed about the first wall, and a third wall disposed about the second wall. The third wall is configured to combine an exhaust gas with an oxidant and the combustion chamber is configured to combust a mixture of a fuel, the oxidant, and the exhaust gas.

Abstract: A system, including a combustor cap assembly, including a first plate configured to divide a combustion chamber from a head end chamber of a combustor, a first sleeve disposed about the first plate, and a first stiffening rib coupled to the combustor cap assembly, wherein the combustor cap assembly is configured to mount in a combustor, and the first stiffening rib is configured to damp vibration caused by combustion dynamics in the combustor.