The secondary turbine (134) drives a secondary compressor (142) which compresses natural gas fuel to be delivered to a combustor (110) of the gas turbine.

A sealing mechanism for minimizing the leakage of air through the mechanical coupling of the combustor and the transition section of a gas turbine.

A swirled diffusion dump combustor of the present invention includes a cylindrical combustor can and a fuel and air mixer attached to the upstream end of the combustor can.

In accordance with a preferred embodiment of the invention, the sealing mechanism comprises a brush seal that can be mounted to the transition section or to the combustor.

A direct-fired biomass-fueled pressurized gas turbin system comprising a pressurized feed system, the cyclonic combustor, and a gas turbine.

An electricity generating system having a body (159), an annular combustor (14), a turbine (16), a compressor chamber and a compressor (102) positioned within the compressor chamber.

Efficient mixing of the oxidant and fuel prior to entry into the ramjet combustor, and the short residence times in the combustion chamber minimize the formation of NOx.

The brush seal minimizes leakage of air into the transition section due to tendency of such air to flow past the mechanical coupling of the combustor and transition piece.

Efficient mixing of the oxidant and fuel prior to entry into the ramjet combustor, and the short residence times in the combustion chamber, minimize the formation of undesirable oxides of nitrogen.

The core engine (54) includes a compressor (62), a combustor (64), a high pressure turbine (66), and a first shaft (70) interconnecting the compressor (62) and high pressure turbine (66).

A gas turbine engine combustor (26) includinga primary combustion chamber (28), a mixer element (34), a mixing chamber (46) and a secondary combustion chamber (48).

A hybrid combustor (10) of a gas turbine engine includes a plurality of circularly arrayed ceramic can combustors (12) whose outlets communicate with the inlet of an annular, metal combustor (16).

The fluid delivery nozzle (90) is configured to deliver a non-combustible fluid into the at least one of the plurality of combustor nozzles (44-49) and the combustion chamber (30).

Internal components of gas or steam turbines are inspected with a 3D scanning camera inspection system that is inserted and positioned within the turbine, for example through a gas turbine combustor nozzle port.