Abstract: A turbomachine combustor is provided. The turbomachine includes a combustion chamber and multiple micro-mixer nozzles arranged concentrically within a radial combustion liner and configured to receive fuel from one or more fuel supply pipes affixed to each of the plurality of micro-mixer nozzles at an upstream face. The multiple micro-mixer nozzle are also configured to receive air from a flow sleeve surrounding the radial combustion liner. Each of the micro-mixer nozzles include an annular strip having a multiple tubes or passages extending axially from the upstream face to a downstream face of each of the micro-mixer nozzles.

Abstract: Disclosed in various exemplary embodiments are turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same. In one exemplary embodiment, disclosed is a combustor for a turbine engine that includes an annular liner portion including a first metering hole positioned on a cold side annular surface of the annular liner portion and an impingement chamber positioned in the annular liner. The impingement chamber connects to an entry hole on the cold side annular surface and includes a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to an exit hole positioned on the hot side annular surface of the annular liner portion. The first metering hole is connected to the impingement chamber. The cooling air outlet passageway directs the air onto the hot side annular surface and spreads the airflow axially and laterally parallel to the hot side annular surface.

Abstract: A thermal/electrical power converter includes a gas turbine with an input couplable to an output of an inert gas thermal power source, a compressor including an output couplable to an input of the inert gas thermal power source, and a generator coupled to the gas turbine. The thermal/electrical power converter also includes a heat exchanger with an input coupled to an output of the gas turbine and an output coupled to an input of the compressor. The heat exchanger includes a series-coupled super-heater heat exchanger, a boiler heat exchanger and a water preheater heat exchanger. The thermal/electrical power converter also includes a reservoir tank and reservoir tank control valves configured to regulate a power output of the thermal/electrical power converter.

Abstract: A combustor for a gas turbine engine includes an forward fuel injection system in communication with a combustion chamber and a downstream fuel injection system that communicates with the combustion chamber downstream of the forward fuel injection system.

Abstract: A gas turbine engine device is disclosed for mixing fuel and air prior to a combustion. The device includes a pilot mixer and a main mixer each having a fuel opening for the delivery of fuel to one or more passages. In one form the main mixer includes an inner passage and an outer passage and in which a fuel opening delivers fuel to the inner passage. The main mixer can include swirlers in the inner and/or outer passages. The pilot mixer can also include a swirler. In one embodiment the main mixer includes a converging flow path and/or a diverging flow path. The pilot mixer can also include a converging and/or diverging flow path and in one form is sheltered from an exit of the device. The main mixer fuel opening can be disposed between an upstream end and a downstream end of the mixer.

Abstract: An igniter tube assembly includes an igniter, an igniter tower with a radially extending portion, a ferrule with a radially extending portion, and a retainer with a radially extending portion. The ferrule and retainer capture the radially extending portion of the igniter tower and sealing surface provides an area for the ferrule to interface with the igniter tower. The igniter moves relative to the casing in which it is secured while a fluid seal between the igniter and ferrule controls air flow.

Abstract: A combustor (10) includes a cap (16), a liner (20), a transition piece (24), and a combustion chamber (22) located downstream from the cap (16) and defined by the cap and liner. A secondary nozzle (40) circumferentially arranged around the liner (20) or transition piece (24) includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding the center body, and an annular passage between the center body and the shroud. A method for supplying fuel to a combustor (10) includes flowing fuel through a primary nozzle radially disposed in a breech end of the combustor and flowing fuel through a secondary nozzle (40) circumferentially arranged around and passing through at least one of a liner (20) or a transition piece. The secondary nozzle (40) includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding at least a portion of the center body (44), and an annular passage between the center body and the shroud.

Abstract: A recuperator inserted in the exhaust duct of a gas turbine engine includes a casing surrounding a core having spiral cross channels. Inlet and outlet openings are defined in the casing for the passage of hot exhaust gases through the exhaust channels in the core. Feeder members extend radially across the outlet opening for passing the pre-combustion stage air through the air channels of the core, and header members extend radially across the inlet opening of the casing for receiving and redirecting air from the air channels in the core towards the combustor section. The feeder and header members each have a tapered configuration from the casing to the axial center of the casing so as to maintain a relatively constant pressure over the radial extent of the respective feeders and headers.

Abstract: An oxygen transport reactor for boiler furnaces and gas turbine combustors that utilizes a liquid fuel that is oxidized as a gaseous fuel in a membrane reactor. A liquid fuel is introduced by vaporizing the fuel inside a porous pipe surrounded by an annulus reaction zone which is surrounded by an annulus air zone. An oxygen transport membrane separates the annulus reaction zone containing the porous vaporized fuel and sweeping CO2 from the air feed side zone. Oxygen is transported from the outer annulus through the membrane to the annulus reaction zone containing the vaporized fuel and sweeping CO2. Fuel is first cracked to very small droplets in the intake fuel atomizer utilizing part of the intake CO2 then completely vaporized inside the porous pipe utilizing the heat coming from the surrounding reaction zone. The oxygen transport reactor is applicable for carbon free boiler furnaces and gas turbine combustors which utilize oxygen transport reactors for combined oxygen separation and combustion.

Abstract: A method of operating a compressed air energy storage (CAES) system includes operating a compressor train of the CAES system, thereby compressing air. The method further includes, while operating the compressor train: inter-cooling a first portion of the compressed air; further compressing the inter-cooled first portion; after-cooling the further compressed first portion; supplying the after-cooled first portion to a storage vessel; supplying a second portion of the compressed air to a combustor; combusting the second portion; and operating a turbine train of the CAES system using the combusted second portion.

Abstract: A mid-turbine frame buffer system for a gas turbine engine includes a mid-turbine frame that supports a shaft by a bearing. An air compartment and a bearing compartment are arranged radially inward of the mid-turbine frame. The bearing compartment is arranged within the air compartment and includes first and second contact seals arranged on either side of the bearing. The air compartment includes multiple air seals. A high pressure compressor is fluidly connected to the air compartment and is configured to provide high pressure air to the air compartment. A method of providing pressurized air to a buffer system includes sealing a bearing compartment with contact seals, surrounding the bearing compartment with an air compartment, and supplying high pressure air to the air compartment.

Abstract: Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber.

Abstract: A gas turbine engine includes an engine core, a core cowl extending circumferentially around the engine core, and a pressure actuated latch assembly. The core cowl includes a first cowl section on a first side of the engine core and a second cowl section on a second side of the engine core. The pressure actuated latch assembly connects the first cowl section to a support structure and is actuatable between an unlatched position when pressure within the core cowl is relatively low and a latched position when pressure within the core cowl is relatively high.

Abstract: A combustor includes an end cover having an outer side and an inner side, an outer barrel having a forward end that is adjacent to the inner side of the end cover and an aft end that is axially spaced from the forward end. An inner barrel is at least partially disposed concentrically within the outer barrel and is fixedly connected to the outer barrel. A fluid conduit extends downstream from the end cover. A first bundled tube fuel injector segment is disposed concentrically within the inner barrel. The bundled tube fuel injector segment includes a fuel plenum that is in fluid communication with the fluid conduit and a plurality of parallel tubes that extend axially through the fuel plenum. The bundled tube fuel injector segment is fixedly connected to the inner barrel.

Abstract: Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber.

Abstract: A sealing component (61) for a turbine (15) positionable at an interface between a transition section (21) for carrying exhaust gas and a turbine inlet section (32). A U-shaped section (45) includes first and second legs (67, 69). When the sealing component is positioned at the interface, the legs extend about the turbine axis. A seal flange (75) connects to the U-shaped section. The positioned sealing component extends about the axis and in a direction away from the first leg. The seal flange faces the inner surface (76) of the flange. A flexible strip (79), positioned radially outward with respect to the seal flange, extends about the axis and extends along the axis between the U-shaped section and the flange. The flexible strip acts as a spring member pressing against the outer surface (96) of the flange.

Abstract: A fuel injection device is provided. The device includes a pilot injector opening out into a venturi and an annular row of multipoint injection orifices opening out axially in a downstream direction and radially outside the venturi, the venturi being connected at its downstream end to a separation wall. The outer peripheral edge of the separation wall has a diameter greater than the diameter of the annular row of injection orifices, whereby the separation wall forms a thermal protection screen for these orifices against heat radiation coming from the chamber.

Abstract: An inlet system for a gas turbine includes an inlet air duct; a silencer disposed in the inlet air duct, the silencer including a plurality of panels with spaces between the panels; and a conduit with orifices disposed to inject inlet bleed heat into each of the spaces. A method of conditioning inlet air for a gas turbine includes flowing air through spaces between panels of a silencer in an inlet air duct of the gas turbine, and injecting inlet bleed heat through orifices and into each of the spaces.

Abstract: Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber.

Abstract: Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber.