Abstract: A gas turbine facility includes: a gas turbine; an ammonia supply device that supplies ammonia to a combustor of the gas turbine; a flow path forming frame forming an exhaust gas flow path through which exhaust gas from the gas turbine flows; a sprinkling device having a sprinkler that sprinkles water into the exhaust gas flow path; and a sprinkling controller that controls an operation of the sprinkling device. The sprinkling controller instructs the sprinkling device to start sprinkling the water on condition that an instruction to start supply of the ammonia to the combustor from the ammonia supply device or an instruction to stop the supply of the ammonia is received.

Abstract: An adapter element for a turbine is disclosed. The adapter element defines a longitudinal axis and comprises a first connection portion, a second connection portion, an outer wall and a dosing structure. The first connection portion is configured to engage the turbine. The second connection portion is configured to engage a conduit. The outer wall extends between the first and second connection portions, the outer wall defining an inner surface and an outer surface. The dosing structure is configured to receive, and expel, reductant.

Abstract: A system may include a turbine and a recuperative heat exchanger system. The recuperative heat exchanger system is configured to receive exhaust gases from the turbine. The recuperative heat exchanger system may include a precool section to cool the exhaust gases, a major heating section to receive the cooled the exhaust gases, and a minor heating section to receive the cooled the exhaust gases.

Abstract: A facility for generating mechanical energy by means of a combined power cycle is disclosed herein, which includes at least means for carrying out a closed or semi-closed, constituent regenerative Brayton cycle, which uses water as a heat-transfer fluid, means for carrying out at least one Rankine cycle, a constituent fundamental Rankine cycle, interconnected with the regenerative Brayton cycle, and a heat pump (UAX) including a closed circuit that regenerates the constituent regenerative Brayton cycle, as well as to the method for generating energy using the facility.

Abstract: Provided is a supersonic aircraft including: a shield that shields an engine exhaust flow discharged from a jet engine accommodated in an engine nacelle mounted on a fuselage of the aircraft to thereby reduce sonic booms due to the engine exhaust flow; and an exhaust nozzle that is provided in an exhaust port of the engine nacelle and that generates a sound source for high-frequency components at a position at which the shield is capable of shielding the high-frequency components of the engine exhaust flow, to thereby reduce jet noise having the high-frequency components, and promotes mixing of the engine exhaust flow that generates low-frequency noise components with an external air flow to thereby reduce jet noise having the low-frequency components.

Abstract: A turbine engine assembly includes a core engine that generates an exhaust gas flow, a condenser where water is extracted from the exhaust gas flow, an evaporator where heat is input into the water that is extracted by the condenser into a first steam flow, a steam turbine where the first steam flow is expanded and cooled, and a superheater where additional heat is input into the first steam flow that is exhausted from the steam turbine to generate a second steam flow. The second steam flow is injected into a core flow path of the core engine.

Abstract: A method of operating an aircraft power plant having an interburner fluidly connected between a combustion engine and a turbine, includes: operating the combustion engine at an air-fuel ratio corresponding to a nominal air-fuel ratio to generate combustion gases; receiving the combustion gases generated by the combustion engine into the interburner; increasing a temperature of the combustion gases generated by a combustion chamber of the combustion engine by lowering the air-fuel ratio to an ignition air-fuel ratio lower than the nominal air-fuel ratio; injecting fuel into the interburner to cause ignition of a mixture of the combustion gases and the fuel received into the interburner; and after ignition of the interburner, increasing the air-fuel ratio above the ignition air-fuel ratio.

Abstract: A method is provided during which an aircraft powerplant is provided. The aircraft powerplant includes a combustor and a water recovery system. The water recovery system includes a condenser and a reservoir. Fuel is combusted within the combustor to provide combustion products. Water is extracted from the combustion products using the condenser. The water recovery system is operated in one of a plurality of modes based on likelihood of contrail formation. The modes include a first mode and a second mode, where the water is collected within the reservoir during the first mode, and where the water passes through the water recovery system during the second mode.

Abstract: An assembly is provided for a turbine engine. This assembly includes a fuel injector assembly, and the fuel injector assembly includes a fuel passage, an air passage and a steam passage. The fuel injector assembly is configured to direct fuel out of the fuel passage along an axis into a volume as a fuel flow. The fuel injector assembly is configured to direct air out of the air passage along the axis into the volume as an air flow, where the air flow circumscribes the fuel flow. The fuel injector assembly is configured to direct steam out of the steam passage along the axis into the volume as a steam flow, where the steam flow circumscribes the fuel flow and provides a radial buffer between the fuel flow and the air flow.

Abstract: Various configurations of a power plant are described. The power plant is configured to supply power to a receiving electrical grid by the combustion of metal powder. The power plant is also configured absorb power by recovering the metal powder from the metal oxide produced by the combustion of the metal powder, with electricity from a source electrical grid.

Abstract: A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.

Abstract: A propulsion system for an aircraft includes a hydrogen fuel system suppling hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from a high energy gas flow. The condenser includes a plurality of rotating passages that are disposed within a collector. The passages are configured to rotate about a condenser axis to generate a transverse pressure gradient to direct water out of the high energy gas flow toward the collector.

Abstract: A method for producing a ceramic honeycomb structure including at least one slit filled with a filling material in a cross section in an axial direction of the honeycomb structure, wherein the honeycomb structure includes: an outer peripheral wall; and a partition wall, the partition wall defining a plurality of cells, wherein the method includes the steps of: preparing a honeycomb structure element comprising at least one slit; masking one end face of the honeycomb structure element except for the slit; and providing the honeycomb structure comprising the at least one slit filled with the filling material by applying a pressure to an axial direction of the honeycomb structure element and feeding the filling material from the one end face to intrude the filling material from the slit on the one end face side to the slit on the other end face side.

Abstract: The present disclosure provides methods whereby products can be prepared in a manner that adds value to the products beyond the market value of such products, and the present disclosure further provides methods for optimizing production of products toward processes that yield a positive net result. The methods for preparing a product can utilize a synthesized oxide compound and, depending upon the order of combination, can modify the synthesized oxide compound by combination with both of carbon dioxide and a secondary component.

Abstract: A system may include a turbine and a recuperative heat exchanger system. The recuperative heat exchanger system is configured to receive exhaust gases from the turbine. The recuperative heat exchanger system may include a precool section to cool the exhaust gases, a major heating section to receive the cooled the exhaust gases, and a minor heating section to receive the cooled the exhaust gases.

Abstract: A liquefied natural gas compression system includes: a first gas turbine that drives a rotary machine; a first steam boiler including a first heat recovery steam generator that recovers heat from exhaust gas from the first gas turbine; a first steam turbine that drives a first refrigerant compressor; a common header steam line through which steam from the first steam boiler flows to an inlet of the first steam turbine; an auxiliary steam line; and a letdown valve that connects the common header steam line to the auxiliary steam line and that opens in response to pressure of the common header steam line exceeding a predetermined threshold value.

Abstract: A method of manufacturing an on-board diagnostic (OBD) limit part and a method of testing to evaluate an OBD system. The method of manufacturing the OBD limit part includes introducing a contaminant to a selective catalytic reduction (SCR) catalyst and contacting the contaminant with the SCR catalyst for a selected period of time. The method of manufacturing utilizes a vessel, the contaminant, and the SCR catalyst. The OBD limit part is a combination of the contaminant and the SCR catalyst within the vessel. The method of testing to evaluate the OBD system includes collecting data related to an exhaust gas before and after the exhaust gas is exposed to the OBD limit part, collecting an indication provided by the OBD system, and comparing the data related to the exhaust gas and the indication provided by the OBD system. The method of testing to evaluate the OBD system utilizes a system that includes an exhaust gas source, a first and a second fluid path, the OBD limit part, and the OBD system.

Abstract: The turbine exhaust case (TEC) mixer assembly for an aircraft engine includes a center body including a hub that encloses a center body cavity and has a first wall portion and a second wall portion that are axially spaced apart. The first and second wall portions having axial end segments which are removably coupled to each other radially inwardly from the outer periphery of the center body via a fixing arrangement including a fastener that is enclosed within the center body cavity. An axial spring includes a gap axially defined between portions of the axial end segments and located at the outer periphery of the center body. A mixer extends peripherally about the center body and is spaced radially outward from the hub by a plurality of struts extending between the hub and the mixer, the plurality of struts being axially offset from the gap at a strut-hub interface.

Abstract: An apparatus for reducing emissions that has a combustion turbine that feeds exhaust into a heat recovery steam generator (or HRSG) casing in which is positioned an emission reduction system featuring, in gas flow sequence, a first reducing reductant injector (RRI1), as in an ammonia injection grid, for providing reducing reductant, preferably ammonia, into turbine exhaust travelling within the HRSG, followed by a first SCR reactor positioned downstream of the first RRI1, followed by one of either (i) a turbulence generator (TG) as in a static mixer, or (ii) a second RRI2 as in a second ammonia injection grid, or (iii) an RRI2 with integrated TG supported on injectors of RRI2, then followed by a second SCR reactor. The emission reduction system preferably is free of a separate body oxidation catalyst or a separate body ammonia slip catalyst in an effort to utilize a limited volume within the HRSG. Methods of assembling and operating the ERS or T-H combination with ERS are also featured.

Abstract: A system is provided with an ejector having an outer wall extending circumferentially about a flow path, wherein the outer wall has a throat section along the flow path, and a diverging section downstream from the throat section along the flow path. The ejector includes a gas inlet configured to supply a gas into the flow path, and a water inlet configured to supply water into the flow path. The ejector is configured to produce steam in response to mixing of the water and the gas along the flow path. The system also includes a controller configured to control flows of the gas and the water to produce the steam for a steam purge of a liquid fuel circuit.

Abstract: A method, system and computer-readable medium where an integrator application identifies an excess energy condition based on a supply load of electricity exceeding a consumptive load. The integrator application directs an air scrubber to utilize the excess electricity to remove carbon dioxide from the ambient air and routes the carbon dioxide to an enhanced coal bed methane well where methane is displaced by the carbon dioxide. In response to identifying an energy deficient condition based on the consumptive load exceeding the supply load, the integrator application routes the methane to a gas power plant and directs the gas power plant to convent the methane to electricity.

Abstract: A denitration device comprising a duct (22) that leads and distributes exhaust gas from a turbine (56) of a gas turbine (50) including a compressor (52) and the turbine (56), an ammonia injection grid (24) that sprays, into the duct (22), an mixed gas in which ammonia gas and dilution air are mixed with each other, and a denitration catalyst (26) that is installed on a downstream side of flow of the exhaust gas of the ammonia injection grid in the duct (22), and there is provided an air bleeding line (76) that is connected to a low compression portion of the compressor (52) of the gas turbine (50) and supplies air bled of the compressor (52) into the ammonia injection grid (24) as the dilution air.

Abstract: A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.

Abstract: A fluid injection system for a gas turbine engine may comprise a fluid injector configured to inject a fluid into an exhaust flow exiting a turbine section of the gas turbine engine. The fluid injector may be coupled to a turbine exit guide vane located at a forward end of an exhaust system of the gas turbine engine. The fluid may decrease a temperature of the exhaust flow exiting the turbine section and/or increase a thrust of the gas turbine engine.

Abstract: The present disclosure provides methods, assemblies, and systems for power production that can allow for increased efficiency and lower cost components arising from the control, reduction, or elimination of turbine blade mechanical erosion by particulates or chemical erosion by gases in a combustion product flow. The methods, assemblies, and systems can include the use of turbine blades that operate with a blade velocity that is significantly reduced in relation to conventional turbines used in typical power production systems. The methods and systems also can make use of a recycled circulating fluid for transpiration protection of the turbine and/or other components. Further, recycled circulating fluid may be employed to provide cleaning materials to the turbine.

Abstract: An integrated ITM micromixer burner shell and tube design for clean combustion in gas turbines includes an oxy-fuel micromixer burner for separating oxygen from air within the burner to perform oxy-combustion, resulting in an exhaust stream that consists of CO2 and H2O. The shell and tube combustion chamber is designed so that preheated air enters a headend having an array of ion transfer membrane (ITM) tubes that separate oxygen from the preheated air and anchor flamelets on the shell side. The combustion products of the oxy-fuel flamelets expand through a turbine for power generation, before H2O is separated from CO2 by condensation. A portion of the effluent CO2 is compressed back into the burner system, while the remainder is captured for sequestration/utilization.

Abstract: An integrated ITM micromixer burner shell and tube design for clean combustion in gas turbines includes an oxy-fuel micromixer burner for separating oxygen from air within the burner to perform oxy-combustion, resulting in an exhaust stream that consists of CO2 and H2O. The shell and tube combustion chamber is designed so that preheated air enters a headend having an array of ion transfer membrane (ITM) tubes that separate oxygen from the preheated air and anchor flamelets on the shell side. The combustion products of the oxy-fuel flamelets expand through a turbine for power generation, before H2O is separated from CO2 by condensation. A portion of the effluent CO2 is compressed back into the burner system, while the remainder is captured for sequestration/utilization.

Abstract: An integrated ITM micromixer burner shell and tube design for clean combustion in gas turbines includes an oxy-fuel micromixer burner for separating oxygen from air within the burner to perform oxy-combustion, resulting in an exhaust stream that consists of CO2 and H2O. The shell and tube combustion chamber is designed so that preheated air enters a headend having an array of ion transfer membrane (ITM) tubes that separate oxygen from the preheated air and anchor flamelets on the shell side. The combustion products of the oxy-fuel flamelets expand through a turbine for power generation, before H2O is separated from CO2 by condensation. A portion of the effluent CO2 is compressed back into the burner system, while the remainder is captured for sequestration/utilization.

Abstract: An integrated ITM micromixer burner shell and tube design for clean combustion in gas turbines includes an oxy-fuel micromixer burner for separating oxygen from air within the burner to perform oxy-combustion, resulting in an exhaust stream that consists of CO2 and H2O. The shell and tube combustion chamber is designed so that preheated air enters a headend having an array of ion transfer membrane (ITM) tubes that separate oxygen from the preheated air and anchor flamelets on the shell side. The combustion products of the oxy-fuel flamelets expand through a turbine for power generation, before H2O is separated from CO2 by condensation. A portion of the effluent CO2 is compressed back into the burner system, while the remainder is captured for sequestration/utilization.

Abstract: An integrated ITM micromixer burner shell and tube design for clean combustion in gas turbines includes an oxy-fuel micromixer burner for separating oxygen from air within the burner to perform oxy-combustion, resulting in an exhaust stream that consists of CO2 and H2O. The shell and tube combustion chamber is designed so that preheated air enters a headend having an array of ion transfer membrane (ITM) tubes that separate oxygen from the preheated air and anchor flamelets on the shell side. The combustion products of the oxy-fuel flamelets expand through a turbine for power generation, before H2O is separated from CO2 by condensation. A portion of the effluent CO2 is compressed back into the burner system, while the remainder is captured for sequestration/utilization.

Abstract: An exhaust duct of a gas turbine engine comprises a hub defining a radially-inner surface of a substantially annular exhaust gas path, and a strut extending into the exhaust gas path. The strut is attached to the hub via a first fastener at a forward fastening location closer to a leading edge of the strut than to a trailing edge of the strut, and via a second fastener at an aft fastening location closer to the trailing edge than to the leading edge. The second fastener is engaged with an appendage of the strut. The appendage is received into a receptacle formed in the hub open to the radially-inner surface.

Abstract: An aircraft having a blended-wing-body configuration includes a centerbody, a pair of wings, at least one pair of engines, a pair of air inlets, and a pair of exhaust outlets. The centerbody has an airfoil-shaped cross section, an aircraft centerline, an aft portion, an upper mold line, a lower mold line, and a pair of centerbody leading edge portions respectively on opposite sides of the aircraft centerline. The wings are integral with the centerbody. The pair of engines are located on opposite sides of the aircraft centerline and are mounted within the centerbody between the upper mold line and the lower mold line. The pair of air inlets are located respectively along the centerbody leading edge portions and are respectively fluidly coupled to the pair of engines. The pair of exhaust outlets our located in the aft portion of the centerbody and our respectively fluidly coupled to the pair of engines.

Abstract: The present disclosure relates to an exhaust gas cooling device and method, and more particularly, to a device and method for installing an exhaust gas cooling device on the upper end of a duct of a heat recovery steam generator to cheaply cool the exhaust gas without occupying an additional dedicated area. An object of the present disclosure is to reduce the costs using a cheap cooling device in the cooling path for cooling the exhaust gas. In one aspect, the exhaust gas cooling device includes an exhaust gas cooling unit located on the upper end of a duct of a heat recovery steam generator connected with a gas turbine and for cooling the exhaust gas discharged from the gas turbine; and a control unit for controlling the exhaust gas cooling unit to lower the increase rate of the energy of the exhaust gas flowed into the heat recovery steam generator through the duct.

Abstract: A flex seal assembly includes a plurality of duct segments configured to be disposed about a joint between a turbine of a turbine system and a diffuser of the turbine system. The plurality of duct segments includes a groove configured to extend circumferentially around the joint. Additionally, the plurality of duct segments includes a first duct segment of the plurality of duct segments and a second duct segment of the plurality of duct segments. The second duct segment includes a drain. Furthermore, the plurality of duct segments include insulation disposed within the groove of the plurality of duct segments.

Abstract: The present invention discloses a novel modular system and methods of operating an increased air supply to a gas turbine engine such that the upon supplying a source of external air to the system, a bias is added to the exhaust temperature such that a firing temperature with air injection is substantially equivalent to the firing temperature without air injection.

Abstract: A turbine includes a diffuser. The diffuser includes a combustor basket, an outer shell, a plurality of struts, and a protrusion. A front end of the protrusion is between a leading edge position of an adjacent pair of the struts and a trailing edge position of the adjacent pair of the struts, and a rear end of the protrusion extends further than the trailing edge position of the adjacent pair of the struts in an axial direction.

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

Abstract: A gas turbine includes an outer casing having an annular shape; an inner casing disposed inside the outer casing; and a plurality of struts, each strut having a first end fixed to an outer surface of the inner casing, a second end fixed to an inner surface of the outer casing, and an inclined portion for guiding a flow of combustion gas, wherein the inclined portion is inclined from a front side to a rear side.

Abstract: An apparatus (2) includes an internal combustion engine (4) and an inverted Brayton cycle heat engine (6). Hot exhaust gas from the internal combustion engine (4) contains water. The hot exhaust gas drives the inverted Brayton cycle heat engine. A condenser (22) in a fluid path of the exhaust gas between an inverted-Brayton-cycle turbine and an inverted-Brayton-cycle compressor condenses at least some of the water from the exhaust gas to form condensed water. This condensed water follows a recirculation path (30) so as to be re-introduced as a working fluid into one or more of the heat engines described above, or further heat engines, e.g. the condensed water is heated by the exhaust gas using a steam-generating heat exchanger (20) to generate steam which drives a steam turbine (32).

Abstract: A carbon dioxide capture system includes a first heat exchanger that exchanges heat between an exhaust stream and a lean carbon dioxide effluent stream. The carbon dioxide capture system also includes a second heat exchanger in flow communication with the first heat exchanger. The second heat exchanger is configured to cool the exhaust stream such that a condensate is formed, and the second heat exchanger is configured to channel a condensate stream for injection into the lean carbon dioxide effluent stream. A first turboexpander including a first compressor is driven by a first turbine. The first compressor is coupled in flow communication with the first heat exchanger. The first turbine is coupled in flow communication with the first heat exchanger and configured to expand the lean carbon dioxide effluent stream. The carbon dioxide capture system further includes a carbon dioxide membrane unit coupled in flow communication with the first compressor.

Abstract: A turbine engine has a core with a compressor, combustor, and turbine sections in axial flow arrangement and with corresponding rotating elements mounted to a shaft defining engine rotor elements. The turbine engine has a rotary driver operably coupled to the engine rotor elements. The turbine engine has at least one thermoelectric generator in thermal communication with the core and in electrical communication with the rotary driver to provide power to the rotary driver to turn the engine rotor elements.

Abstract: A method of reducing the emission of nitrogen oxides (NOx) during system startup of a power generating system may include igniting a combustion turbine thereby generating exhaust, supplying the exhaust to a catalyst bed comprising a selective catalytic reduction (SCR) catalyst, injecting an initial pulse of ammonia into the exhaust during a storage period such that the NOx reacts with the ammonia and is stored in the catalyst bed as ammonium nitrate (AN) during the storage period; and injecting a scheduled amount of ammonia into the exhaust during a transition period such that the stored AN is decomposed as temperatures increase and NOx is converted via standard and fast SCR reactions during the transition period.

Abstract: Systems and methods for suppressing infrared radiation generated by a turbine engine. A system comprises a primary assembly having a center body, a plurality of vanes extending from the center body, an outer radial duct with the plurality of vanes extending therethrough, a structural baffle, and a mixer. The primary assembly is disposed in the exhaust flow path of a turbine engine and encased in ducting and/or an airfoil. An air flow path defined between the center body and outer radial duct is axially spit by an interface rim and flow segregator. The flow segregator segregates engine core flow from ambient air flow.

Abstract: The present invention relates generally to the field of emission control equipment for boilers, heaters, kilns, or other flue gas-, or combustion gas-, generating devices (e.g., those located at power plants, processing plants, etc.) and, in particular to a new and useful method and apparatus for reducing or preventing the poisoning and/or contamination of an SCR catalyst. In still another embodiment, the present invention relates to a method and apparatus for increasing the service life and/or catalytic activity of an SCR catalyst while simultaneously controlling various emissions. In yet another embodiment, the present invention relates to a method and apparatus for controlling, mitigating and/or reducing the amount of selenium contained in and/or emitted by one or more pieces of emission control equipment for boilers, heaters, kilns, or other flue gas-, or combustion gas-, generating devices (e.g., those located at power plants, processing plants, etc.).

Abstract: A method for operating a gas turbine plant having a gas turbine and an electric generator driven by the gas turbine. The method includes detecting an instantaneous power of the gas turbine plant; comparing the detected instantaneous power with a power limit value; and limiting the instantaneous power when the result of the comparison is that the detected instantaneous power is equal to or greater than the power limit value. A step of detecting at least one operating parameter of the gas turbine plant and a step of determining the power limit value as a function of the at least one detected operating parameter are then implemented, wherein the at least one operating parameter of the gas turbine plant includes an ambient pressure and the power limit value is increased when the ambient pressure increases.

Abstract: A technique for mounting a turbine retention device is provided. The technique comprises forming openings in a diffuser, aligning a mounting bracket with the openings, and installing fasteners through the openings and the mounting bracket. A turbine retention device mounted to a diffuser may is also provided. The turbine retention device may comprise a bullet, wings coupled to the bullet, mounting brackets coupled to the wings, and fasteners disposed through the mounting brackets and openings formed in the diffuser.

Abstract: A gas turbine system may include an exhaust gas processing system configured to process exhaust gas received from a gas turbine engine of the system. An exhaust path of the exhaust processing system is configured to flow the exhaust gas through the exhaust processing system. A tempering air system of the exhaust processing system is configured to introduce tempering air into the exhaust path to cool the exhaust gas. The tempering air system includes a tempering air pathway extending from an air inlet of the tempering air system to a tempering air outlet where tempering air is introduced from the tempering air system and into the exhaust path. A filter system of the tempering air system has a hydrophobic filter positioned along the tempering air pathway, the hydrophobic filter being configured to remove hygroscopic and deliquescent materials from the air flowing through the tempering air pathway.

Abstract: A gas turbine engine including a compressor section and a turbine section, coupled by one or more shafts, is provided. The compressor section progressively compresses air and includes an aft-stage of rotor blades rotatable about an axial direction of the gas turbine engine. A cooling system is included with the gas turbine engine for cooling compressed air in or from the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and one or more fluid lines in fluid communication with the fluid tank. The one or more fluid lines include an outlet positioned adjacent to the aft-stage of rotor blades for injecting cooling fluid into the compressed air proximate the aft-stage of rotor blades.

Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.

Abstract: A power generation system may include: a first gas turbine system including a first turbine component, a first integral compressor and a first combustor to which air from the first integral compressor and fuel are supplied. The first integral compressor has a flow capacity greater than an intake capacity of the first combustor and/or the first turbine component, creating an excess air flow. A second gas turbine system may include similar components to the first except but without excess capacity in its compressor. A turbo-expander may be operatively coupled to the second gas turbine system. Control valves may control flow of the excess air flow from the first gas turbine system to at least one of the second gas turbine system and the turbo-expander, and flow of a discharge of the turbo-expander to an inlet of at least one of the first integral compressor and the second compressor.