A flameless combustor usable with multiple fuels comprises a combustion chamber and fuel lines in communication with the chamber.

Provided is an injector (30) having a plurality of injector modules (44) that include a spray cup having a chamber and a plurality of radial air passages for directing air radially into the chamber, and a pressure swirl atomizer attached to the spray cup and having a fluid passage for directing fluid axially into chamber and an air passage for directing air axially into the chamber. By providing radial and axial air flow and axial fuel flow into the chamber, the fuel may be mixed to prevent local hot spots that lead to high NOx emissions, and a stable flame may be maintained without autoignition and flashback. The axial air flow also prevents recirculation zones from forming at a base of the spray cup, provides improved atomization and enhanced combustion.

A nameless combustor usable with multiple fuels comprises a combustion chamber and fuel lines in communication with the chamber.

A multiphase fuel injector has an injector body with a fuel inlet at a first end and a fuel outlet at a second end opposite the first end. A primary circuit disposed proximate the fuel inlet extends into a central portion of the injector body. The primary circuit is configured to receive a first flow of pressurized fuel from the fuel inlet that discharges into a spin chamber in the injector body downstream from the fuel inlet. The primary circuit is configured to impart a swirling action to the first flow of pressurized fuel. A secondary circuit is located in the injector body radially outward from the primary circuit. The secondary circuit is configured to receive a second flow of pressurized fuel from the fuel inlet that discharges into the fuel outlet. The secondary circuit is configured to impart a swirling action to the second flow of pressurized fuel.

An inward-firing dual fuel combustion burner system comprising a burner casing configured to receive a gaseous mixture at a burner inlet and to provide hot combustion gas at a burner output; a combustion substrate disposed within the burner casing, the substrate having a shape comprising at least a semi-cone, having a substrate angle measured from a longitudinal axis, having a substrate porosity defined by a plurality of pores, and having a substrate inner surface and a substrate outer surface; the substrate configured to receive the fuel-air mixture at the outer surface of the substrate, the fuel-air mixture passing through the pores at a mixture flow rate from the substrate outer surface toward the substrate inner surface; one or a plurality of oil nozzles disposed within the combustion cavity defined by the substrate in fluidic communication with a source of pre-heated and pre-pressurized oil fuel, an oil nozzle configured to receive the oil fuel and disperse the oil fuel into the cavity; the burner configured to be operated using either a gaseous premix fuel air mixture or a pre-heated and pre-pressurized liquid fuel oil; the burner configured such that, during gaseous premix fuel operation, the fuel-air mixture ignites near the plurality of pores to form a respective plurality of flamelets, each flamelet corresponding to one of the pores; and the burner configured such that, during oil fuel operation, the oil mixture ignites during isenthalpic expansion.

An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.

An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.

An air and fuel injection system for a turbine engine combustion chamber dome, including at least two fuel injection devices including a central injector and a peripheral annular injector arranged around the central injector, and an inner annular air inlet channel into which the central injector opens up to enable mixing between the fuel from the central injector and the air inlet into the inner annular channel, and at least one outer annular air inlet channel to enable enrichment of this mix with air and to stabilize the pilot combustion zone, wherein the inner annular channel and at least one outer annular channel are separated by an intermediate annular wall extending around the central injector and having a convergent inner profile.