Abstract: Systems, methods, and apparatus are provided for controlling the oxidant feed in low emission turbine systems to maintain stoichiometric or substantially stoichiometric combustion conditions. In one or more embodiments, such control is achieved by diverting a portion of the recirculating exhaust gas and combining it with the oxidant feed to maintain a constant oxygen level in the combined oxidant-exhaust stream fed to the combustion chamber.

Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Abstract: A decongealing channel for use in a heat exchanger apparatus, including a supersaturated solution contained therein and an actuation component in fluid communication with a lubricating fluid coupled to the decongealing channel. The actuation component is responsive to a change in pressure exerted thereon by the lubricating fluid so as to actuate an exothermic response in the supersaturated solution. The heat exchanger apparatus is disposed in a bypass fan duct of an aircraft engine. The heat exchanger apparatus including a manifold portion, one or more flow through openings extending therethrough the manifold portion to define one or more flow through channels having contained therein the lubricating fluid. In addition, the manifold portion including one or more additional openings extending therethrough to define one or more decongealing channels. Further disclosed is an engine including the heat exchanger apparatus and a method of decongealing a lubricating fluid in the heat exchanger apparatus.

Abstract: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a plurality of positions in a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit injects a mixed fuel prepared by mixing water and the liquid fuel evenly from the liquid fuel injecting hole to the vane pressure surface of the swirler vane.

Abstract: A mixture of air and fuel is received into a reaction chamber of a gas turbine system. The fuel is oxidized in the reaction chamber, and a maximum temperature of the mixture in the reaction chamber is controlled to be substantially at or below an inlet temperature of a turbine of the gas turbine system. The oxidation of the fuel is initiated by raising the temperature of the mixture to or above an auto-ignition temperature of the fuel. In some cases, the reaction chamber may be provided without a fuel oxidation catalyst material.

Abstract: A jet engine includes at least one oil separator, through which an air-oil volume flow can be guided out of several areas supplied with oil for separating the oil, where a device for spraying oil into the air-oil volume flow is provided. Oil can be sprayed in using the device in the area of each connection between an area supplied with oil and the oil separator and/or downstream of a combining area between at least two air-oil volume flows from two or more areas supplied with oil.

Abstract: A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust section disposed downstream of the turbine section, an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof, and an oxygen sensor disposed in the oxygen sensor adaptor housing. The oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold.

Abstract: The present disclosure relates to a power production system that is adapted to achieve high efficiency power production with complete carbon capture when using a solid or liquid hydrocarbon or carbonaceous fuel. More particularly, the solid or liquid fuel first is partially oxidized in a partial oxidation reactor. The resulting partially oxidized stream that comprises a fuel gas is quenched, filtered, cooled, and then directed to a combustor of a power production system as the combustion fuel. The partially oxidized stream is combined with a compressed recycle CO2 stream and oxygen. The combustion stream is expanded across a turbine to produce power and passed through a recuperator heat exchanger. The expanded and cooled exhaust stream is scrubbed to provide the recycle CO2 stream, which is compressed and passed through the recuperator heat exchanger and the POX heat exchanger in a manner useful to provide increased efficiency to the combined systems.

Abstract: An annular combustion chamber of a turbine engine, the chamber including inner and outer coaxial walls forming two surfaces of revolution, which are connected together upstream by an annular chamber end wall including injection systems passing therethrough, each including an injector and at least one swirler for producing a rotating air stream that mixes downstream with fuel from the injector, and at least one ignition spark plug mounted in an orifice of the outer wall downstream from the injection systems. The spark plug is situated circumferentially between two adjacent injection systems that are configured to produce two air/fuel mixture sheets rotating in opposite directions.

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: A combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged in a circumferential direction on an external circumferential surface of the fuel nozzle, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane pressure surface of each of the swirler vanes, and a cooling unit that cools a part of the vane pressure surface on which the liquid fuel hits. The cooling unit includes a multi-purpose injecting hole that is arranged on the vane pressure surface of each of the swirler vanes, and from which a gas fuel is injected during gas combustion, and water is injected to the vane pressure surface of the swirler vane during combustion of the liquid fuel.

Abstract: A direct metering architecture is provided having a metering pump and a servo pump wherein the metering and servo pumps are driven by an engine shaft by way of a gearbox transmission. The system reduces wasted horsepower previously occurring with oversized fixed displacement pumps, reduces instances of engine flameout and reduces the amount of heat added to fuel which ultimately improves engine oil cooling.

Abstract: A diffuser is disclosed that includes a splitter having a blunt forebody useful in re-starting a boundary layer. The blunt forebody can be used to create a static pressure bow wave and interaction with a passing fluid stream that reduces a thickness of boundary layer formed on an opposing wall. The re-start in boundary layer can be used in a way that allows an upstream portion of the diffuser to be sized approaching a separation limit and a downstream portion of the diffuser to also be sized approaching a separation limit. In some forms the passages split by the blunt forebody can be sized relative to each other to balance flow between the branches.

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 combustion burner including a fuel nozzle, a burner tube that surrounds the fuel nozzle to form an air passage between the burner tube and the fuel nozzle, swirler vanes that are arranged a circumferential direction on an external circumferential surface of the fuel nozzle, each of which extends along an axial direction of the fuel nozzle, and gradually curves from upstream to downstream so as to swirl air flowing in the air passage from the upstream to the downstream, a liquid fuel injecting hole that is formed on the fuel nozzle, and from which a liquid fuel is injected to a vane surface of each of the swirler vanes, and a cooling unit that cools a part of the vane surface on which the liquid fuel hits. The cooling unit includes a water cooling circuit formed inside the swirler vane.

Abstract: A system for cooling a fuel injector extending into a combustion gas flow field includes a liner that defines a combustion gas flow path within a combustor and a fuel injector that extends through the liner. The fuel injector includes a main body having an annular first portion that extends outward from the liner and a second portion that extends from the first portion inward into the combustion gas flow path. The main body defines a cooling channel that is fully circumscribed within the main body and that extends between the first portion and the second portion. A cooling air inlet is defined within the annular first portion and is in fluid communication with the cooling channel. A cooling air outlet is in fluid communication with the cooling channel and is defined within the second portion downstream from the cooling air inlet.

Abstract: A device capable of collecting a condensate from a working fluid is disclosed. The condensate can take the form of a liquid and can be injected into a flow path of an engine. In one form the engine is a gas turbine engine and the liquid is injected upstream of a combustor. The liquid can be produced using a component that cools the working fluid to condense a vapor within it. In one non-limiting form the component is part of a refrigeration system. In addition to producing condensate, the refrigeration system can cool the working fluid to be used as cooled cooling air to a turbine of a gas turbine engine. In another non-limiting embodiment a liquid derived from a blackwater containing waste from an organism can be delivered in whole or in part to a flow path of the engine.

Abstract: An air cooled heat exchanger, such as a combustion turbine intercooler or rotor cooler or an air cooled condenser, utilizes a pressurized gas fluid entraining misting device that evaporatively cools conduits carrying the cooled fluid medium. Evaporative cooling liquid is entrained in the pressurized gas where it is atomized for evaporative cooling of the heat exchanger conduits. In some exemplary embodiments of the invention the misting device is a jet pump or ejector that entrains a supply of non-pressurized cooling liquid. In other exemplary embodiments of the invention the misting device is a misting emitter that entrains a supply of pressurized cooling liquid.

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.

Abstract: A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.