There is provided a burner for a gas turbine engine, the burner comprising a radially inner pilot fuel flow passage surrounded by a radially outer main fuel flow passage. The main fuel flow passage is interposed between concentrically arranged radially inner and radially outer air flow passages. The inner and outer air flow passages are in fluid communication with one another via at least one diverting passage at an upstream end of the burner. The burner further comprises at least one control duct connectable to a reduced pressure/vacuum source for selectively reducing the air pressure in the vicinity of the diverting passage such that air flow is selectively diverted from the inner air flow passage to the outer flow passage via the diverting passage.

The invention relates to a combustion chamber module for an aircraft turbine engine, comprising a combustion chamber defined by an internal annular wall and an external annular wall provided with air intake openings, the module further comprising an internal housing and an external housing. According to the invention, at least one of the internal and external housings has, on the surface thereof facing the combustion chamber, a marking system comprising a plurality of different marks angularly spaced apart from each other, each mark being produced facing one of the air intake openings in order to be visible from inside the combustion chamber and each indicating the angular position of a zone of the combustion chamber comprising the air intake opening.

A tubular combustion chamber system for a gas turbine unit includes a plurality of annularly arranged transition lines, which are designed to be connected at the upstream ends thereof to respective burners and to conduct hot gas produced by the burners to a turbine. The tubular combustion chamber system has a hot gas distributor, which is designed to be connected to the turbine and defines a ring channel, which is open to the turbine and into which the downstream ends of the transition lines lead. A gas turbine unit includes a plurality of annularly arranged burners, a turbine and a tubular combustion chamber system which connects the burners to the turbine.

A tubular combustion chamber system for a gas turbine unit includes a plurality of annularly arranged transition lines, which are designed to be connected at the upstream ends thereof to respective burners and to conduct hot gas produced by the burners to a turbine. The tubular combustion chamber system has a hot gas distributor, which is designed to be connected to the turbine and defines a ring channel, which is open to the turbine and into which the downstream ends of the transition lines lead. A gas turbine unit includes a plurality of annularly arranged burners, a turbine and a tubular combustion chamber system which connects the burners to the turbine.

A combustion system with surface-less heat energy exchange for efficient heat energy capture and lower pollutant emission, comprising: a first line feeding an oxygen-rich reactive; a second line feeding a hydrogen fuel; a vessel containing feed-water, a combustion enclosure without a bottom wall submersed into the feed water contained in a vessel, the combustion enclosure configured to receive the feed from each of the first and second line and combust a mixture of the two feeds in a pocket formed between an inner top and side walls of the combustion enclosure and a top surface of the feed-water contained in the vessel; and the combustion within the pocket yielding a high temperature and pressure combustion product and by-product directly into the feed-water of the vessel.

A combustion system with surface-less heat energy exchange for efficient heat energy capture and lower pollutant emission, comprising: a first line feeding an oxygen-rich reactive; a second line feeding a hydrogen fuel; a vessel containing feed-water, a combustion enclosure without a bottom wall submersed into the feed water contained in a vessel, the combustion enclosure configured to receive the feed from each of the first and second line and combust a mixture of the two feeds in a pocket formed between an inner top and side walls of the combustion enclosure and a top surface of the feed-water contained in the vessel; and the combustion within the pocket yielding a high temperature and pressure combustion product and by-product directly into the feed-water of the vessel.

A combustor structure of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor in a suprecritical CO.sub.2 gas turbine which uses supercritical CO.sub.2 for a working fluid, a casing of the suprecritical CO.sub.2 gas turbine. The combustor structure includes a plurality of combustors. Each of the combustors includes: a combustor liner in a cylindrical shape, which combusts fuel and an oxidant; a fuel supply part which is provided at an upstream end of the combustor liner and supplies the fuel into the combustor liner; and an oxidant supply part which is provided at the upstream end of the combustor liner and supplies the oxidant into the combustor liner.

A combustor structure of an embodiment is disposed to penetrate, from a direction perpendicular to an axial direction of a turbine rotor in a suprecritical CO.sub.2 gas turbine which uses supercritical CO.sub.2 for a working fluid, a casing of the suprecritical CO.sub.2 gas turbine. The combustor structure includes a plurality of combustors. Each of the combustors includes: a combustor liner in a cylindrical shape, which combusts fuel and an oxidant; a fuel supply part which is provided at an upstream end of the combustor liner and supplies the fuel into the combustor liner; and an oxidant supply part which is provided at the upstream end of the combustor liner and supplies the oxidant into the combustor liner.

A combustor may comprise a combustion chamber encapsulated by a combustor casing, wherein the combustor casing comprises a casing forward portion, a casing radially inward portion, a casing radially outward portion, and a casing aft portion. The casing radially inward portion may comprise a dirt collector system comprising a hot panel adjacent to the combustion chamber; a cold shell panel coupled to the hot panel such that the hot panel is between the combustion chamber and the cold shell panel; and a dirt collector panel coupled to the cold shell panel such that the cold shell panel is between the hot panel and the dirt collector panel. The cold shell panel and the dirt collector panel at least partially define a dirt collecting space.

A combustor may comprise a combustion chamber encapsulated by a combustor casing, wherein the combustor casing comprises a casing forward portion, a casing radially inward portion, a casing radially outward portion, and a casing aft portion. The casing radially inward portion may comprise a dirt collector system comprising a hot panel adjacent to the combustion chamber; a cold shell panel coupled to the hot panel such that the hot panel is between the combustion chamber and the cold shell panel; and a dirt collector panel coupled to the cold shell panel such that the cold shell panel is between the hot panel and the dirt collector panel. The cold shell panel and the dirt collector panel at least partially define a dirt collecting space.