A combustor for a gas turbine engine has an annular inner liner and an annular outer liner forming a combustion chamber therebetween. A dilution horn pair includes dilution horns that provide a flow of an oxidizer gas into the combustion chamber in a dilution zone. At least one of the dilution horns forming the dilution horn pair is arranged so as to provide a lateral flow component of the flow of oxidizer gas therethrough into the combustion chamber, the lateral flow component having a flow direction extending laterally across and non-orthogonal to an axial flow direction of combustion gases within the combustion chamber.

A combustor for a gas turbine engine has an annular inner liner and an annular outer liner forming a combustion chamber therebetween. A dilution horn pair includes dilution horns that provide a flow of an oxidizer gas into the combustion chamber in a dilution zone. At least one of the dilution horns forming the dilution horn pair is arranged so as to provide a lateral flow component of the flow of oxidizer gas therethrough into the combustion chamber, the lateral flow component having a flow direction extending laterally across and non-orthogonal to an axial flow direction of combustion gases within the combustion chamber.

Disclosed is an inlet system for a gas turbine engine that extends along a longitudinal axial centerline, the inlet system comprising: an inner dome, a shroud located axially aft and radially outward of the inner dome with respect to the centerline, a splitter nose located radially inward of the shroud with respect to the centerline, a first plurality of struts radially disposed between the shroud and the splitter nose with respect to the centerline, a second plurality of struts radially disposed between the splitter nose and a bearing with respect to the centerline, a plurality of inlet guide vanes radially disposed between the splitter nose and the bearing with respect to the centerline, and the plurality of inlet guide vanes axially aft of the plurality of second struts with respect to the centerline.

Sweep-based gas separation processes for reducing carbon dioxide emissions from gas-fired power plants. The invention involves at least two compression steps, a combustion step, a carbon dioxide capture step, a power generate step, and a sweep-based membrane separation step. One of the compression steps is used to produce a low-pressure, low-temperature compressed stream that is sent for treatment in the carbon dioxide capture step, thereby avoiding the need to expend large amounts of energy to cool an otherwise hot compressed stream from a typical compressor that produces a high-pressure stream, usually at 20-30 bar or more.

Sweep-based gas separation processes for reducing carbon dioxide emissions from gas-fired power plants. The invention involves at least two compression steps, a combustion step, a carbon dioxide capture step, a power generate step, and a sweep-based membrane separation step. One of the compression steps is used to produce a low-pressure, low-temperature compressed stream that is sent for treatment in the carbon dioxide capture step, thereby avoiding the need to expend large amounts of energy to cool an otherwise hot compressed stream from a typical compressor that produces a high-pressure stream, usually at 20-30 bar or more.

A process for cracking a hydrocarbon stream by: combusting fuel in a gas turbine in the presence of compressed air to produce a flue gas, wherein the flue gas drives a turbine to produce electricity in a coupled generator or work to power a coupled rotating equipment; (a) feeding a first portion of the flue gas to a heat exchanger; (b) feeding ambient air to the heat exchanger to be heated by the first portion of the flue gas to provide heated air; (c) feeding a furnace with fuel and a mixture of a second portion of the flue gas and the heated air obtained by step (c) and (d) cracking the hydrocarbon stream in the furnace.

An example engine control system may include an oxygen intake sensor; a fuel delivery device to control a rate of fuel delivery to the engine combustor; a combustor pressure sensor; a combustor temperature sensor; and a controller to receive at least one of an oxygen intake signal, a combustor pressure signal, and a combustor temperature signal; determine at least one of a reference specific fuel consumption (SFC) of the engine or a reference amount of a respective exhaust gas of a plurality of exhaust gases based on the oxygen signal, the pressure signal, and the temperature signal; compare at least one of the reference SFC or the reference amount of a respective exhaust gas to a respective threshold value; and control the fuel delivery device to control the rate of fuel delivery based on the comparison.

An engine assembly including an internal combustion engine, an impulse turbine, and an exhaust pipe providing fluid communication between the exhaust port of the internal combustion engine and the flow path of the turbine. The exhaust pipe terminates in a nozzle. A ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of the exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the internal combustion engine is at least 0.2. A method of compounding at least one internal combustion engine is also discussed.

An engine assembly including an internal combustion engine, an impulse turbine, and an exhaust pipe providing fluid communication between the exhaust port of the internal combustion engine and the flow path of the turbine. The exhaust pipe terminates in a nozzle. A ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of the exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the internal combustion engine is at least 0.2. A method of compounding at least one internal combustion engine is also discussed.

An engine component for a gas turbine engine includes a film-cooled recess comprising a contoured portion defining a step. A hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow are fluidly coupled by a passage through the engine component. The passage further comprises an inlet in the cooling surface and an outlet in the step. The inlet, passage and outlet are oriented such that the cooling fluid flowing through the passage and exiting the outlet diffuses within the contoured portion prevents premature mixing out with the hot fluid flow.