A gas turbine combustor is provided that can stably burn two kinds of gas fuels having different heating values by means of the same burner. In the gas turbine combustor that includes a combustion chamber for mixing fuel and air for combustion and a burner, disposed upstream of the combustion chamber, for jetting fuel and air into the combustion chamber and holding flames, the burner has a first swirler including a plurality of fuel holes and of air holes circumferentially alternately and a second swirler including a plurality of holes through which to jet fuel or air, the second swirler is disposed on the outer circumference of the first swirler, and each of the holes of the second swirler is greater in width than each of the air holes of the first swirler.

Provided is a combustor assembly. The combust assembly includes: a plurality of swirlers through which a first fluid that is a part of a fluid discharged from a compressor passes; a base portion, in which the plurality of swirlers are provided, comprising a first through hole formed between one swirler and another swirler from among the plurality of swirlers so that a second fluid that is another part of the fluid discharged from the compressor and different from the first fluid passes through the first through hole; and a deflector provided in the base portion so as to face the first through hole for changing a moving direction of the second fluid.

Provided is a combustor assembly. The combust assembly includes: a plurality of swirlers through which a first fluid that is a part of a fluid discharged from a compressor passes; a base portion, in which the plurality of swirlers are provided, comprising a first through hole formed between one swirler and another swirler from among the plurality of swirlers so that a second fluid that is another part of the fluid discharged from the compressor and different from the first fluid passes through the first through hole; and a deflector provided in the base portion so as to face the first through hole for changing a moving direction of the second fluid.

A fuel nozzle includes a shroud; an injection cylinder surrounded by the shroud and configured to supply fuel to a combustion chamber; a swirler disposed between the injection cylinder and the shroud; and a porous disk disposed downstream of the swirler to surround an outer peripheral surface of the injection cylinder in order to prevent a flashback phenomenon occurring due to a reduction in pressure around the swirler. The porous disk includes a disk body to block a flame produced in the combustion chamber, and a plurality of flow holes are formed in the disk body through which the fuel flows. It is possible to prevent flashback by installing the porous disk downstream of the swirler, and to impart linearity and a swirling effect to the fuel passing through the fuel nozzle by forming variously configured flow holes in the porous disk.

A fuel nozzle includes a shroud; an injection cylinder surrounded by the shroud and configured to supply fuel to a combustion chamber; a swirler disposed between the injection cylinder and the shroud; and a porous disk disposed downstream of the swirler to surround an outer peripheral surface of the injection cylinder in order to prevent a flashback phenomenon occurring due to a reduction in pressure around the swirler. The porous disk includes a disk body to block a flame produced in the combustion chamber, and a plurality of flow holes are formed in the disk body through which the fuel flows. It is possible to prevent flashback by installing the porous disk downstream of the swirler, and to impart linearity and a swirling effect to the fuel passing through the fuel nozzle by forming variously configured flow holes in the porous disk.

A fuel spray nozzle arrangement for a combustor, the fuel spray nozzle arrangement comprising a fuel spray nozzle connected to a feed arm, wherein the feed arm comprises an aerofoil.

A fuel spray nozzle arrangement for a combustor, the fuel spray nozzle arrangement comprising a fuel spray nozzle connected to a feed arm, wherein the feed arm comprises an aerofoil.

A tuned cavity rotating detonation combustion system includes a an annular chamber having an inlet and an outlet; a valve plate at the inlet of the annular chamber and comprising a plurality of openings spaced circumferentially around the inlet; a plurality of tubes each having an open end in communication with a corresponding opening of the valve plate and a closed end forming a tuned cavity, and a first opening between the open end and the closed end for injection of air; and a plurality of fuel injectors corresponding to the plurality of tubes, each fuel injector being configured to inject fuel into the tube between the first opening and the open end. Each of the tuned cavities has a length sized to resonate at a same frequency as a continuous detonation frequency of at least one detonation wave in the annular chamber. Alternately, or additionally, a plurality of flame arresters corresponding to the plurality of tubes are configured to arrest the at least one detonation wave generated in the detonation chamber from travelling into the tube.

The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirler assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.

The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirler assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.