Abstract: A combustor (36) for a gas turbine, the combustor (36) comprising a combustor axis (44) about which is arranged in flow sequence a radial swirler (40), a pre-chamber (42) and a combustion chamber (38). The radial swirler (40) comprises a base plate (45), an annular array of swirler vanes (46), defining swirler slots (47), arranged around the base plate (45), a main fuel injector (48A, 48B) for injecting a main fuel and a pilot fuel injector (50) for injecting a pilot fuel. The combustor comprises a premixer nozzle (70) located on the combustion chamber (38). The premixer nozzle (70) comprising a housing (78), an array of tubes (80) within the housing (78) and a first fuel gallery (72) for supplying a first fuel (83). Each tube (80) of the array of tubes (80) comprising an inlet (86), an outlet (88), a first aperture (90) and a second aperture (92). The first fuel gallery (72) is arranged to supply the first fuel (83) to the first aperture (90) and/or the second aperture (92).

Abstract: A swirler for creating a swirling fuel/air mix having vanes extending radially around a central axis of the swirler and positioned on an annular base. The swirler has mixing channels for mixing the fuel and the air. At least one mixing channel is defined by opposing walls of two adjacent vanes. At least one of the opposing walls includes a primary side injection opening for ejecting a stream of fuel into the mixing channel; and a secondary side injection opening which corresponds to the primary side injection opening and is for ejecting a jet of fuel into the mixing channel. The secondary side injection opening is positioned on the wall such that the jet from the secondary side injection opening creates turbulence, within the mixing channel, in the stream from the primary side injection opening. The turbulence increases mixing of fuel and air.

Abstract: A pilot burner assembly for a combustion volume in a gas turbine engine includes a pilot burner, a pilot-fuel supply line, and a pilot-air supply line. The pilot burner has a burner face that includes a plurality of pilot-fuel injection holes. The pilot-fuel injection holes provide a pilot-fuel to the combustion volume. The pilot-fuel supply line is fluidly connected to the pilot-fuel injection holes for supplying the pilot-fuel to the pilot-fuel injection holes. The pilot-air supply line provides a pilot-air to the pilot burner. The pilot-air is supplied to the combustion volume through the burner face. Pilot-air injection holes are located on the burner face and fluidly connected to the pilot-air supply line. The pilot-air injection holes inject the pilot-air into the combustion volume. A gas turbine has the pilot burner assembly.

Abstract: A method for controlling pilot-fuel/pilot-air ratio provided to a burner of a combustion system for altering its operating point. First, a value of a first parameter e.g. temperature, is checked, and if the value equals or exceeds a predetermined maximum limit of the first parameter that places the operating point in a first undesired region of operation, then a pilot-fuel/pilot-air ratio is altered such that the value of first parameter is moved to below the first parameter's predetermined maximum limit. Similarly, a value of a second parameter e.g., pressure, is checked, and if the value equals or exceeds a predetermined maximum limit of the second parameter that places the operating point in a second undesired region of operation, then again the pilot-fuel/pilot-air ratio is altered such that the value of second parameter is moved to below the second parameter's predetermined maximum limit. A combustion system operates according to the method.

Abstract: A combustor for a gas turbine engine having a central axis about which is arranged in flow sequence a radial swirler, a pre-chamber partly defined by a wall and a combustion chamber. The radial swirler has a base plate having an annular array of vanes and fuel injectors arranged to direct an air/fuel mixture radially inwardly and tangentially to create a vortex that flows through the pre-chamber and into the combustion chamber. The pre-chamber has a portion which is convergent in a downstream direction.

Abstract: A combustor for a gas turbine, having a pre-combustion chamber having a peripheral wall around a center axis of the pre-combustion chamber, the peripheral wall has an inner panel and an outer panel and a passage provided between the inner and the outer panels, a swirler which is connected to the pre-combustion chamber for providing pre-combustion chamber with a flow of an oxidant gas, at least a pilot fuel injector, wherein the swirler is connected to the peripheral wall in such a way that a portion of the oxidant gas from the swirler is channeled to the passage, and the pilot fuel injector is connected to the passage for injecting a flow of pilot fuel into the passage.

Abstract: A pilot burner assembly for a combustion volume in a gas turbine engine includes a pilot burner, a pilot-fuel supply line, and a pilot-air supply line. The pilot burner has a burner face that includes a plurality of pilot-fuel injection holes. The pilot-fuel injection holes provide a pilot-fuel to the combustion volume. The pilot-fuel supply line is fluidly connected to the pilot-fuel injection holes for supplying the pilot-fuel to the pilot-fuel injection holes. The pilot-air supply line provides a pilot-air to the pilot burner. The pilot-air is supplied to the combustion volume through the burner face. Pilot-air injection holes are located on the burner face and fluidly connected to the pilot-air supply line. The pilot-air injection holes inject the pilot-air into the combustion volume. A gas turbine has the pilot burner assembly.

Abstract: A swirler for creating a swirling fuel/air mix having vanes extending radially around a central axis of the swirler and positioned on an annular base. The swirler has mixing channels for mixing the fuel and the air. At least one mixing channel is defined by opposing walls of two adjacent vanes. At least one of the opposing walls includes a primary side injection opening for ejecting a stream of fuel into the mixing channel; and a secondary side injection opening which corresponds to the primary side injection opening and is for ejecting a jet of fuel into the mixing channel. The secondary side injection opening is positioned on the wall such that the jet from the secondary side injection opening creates turbulence, within the mixing channel, in the stream from the primary side injection opening. The turbulence increases mixing of fuel and air.

Abstract: A method for controlling pilot-fuel/pilot-air ratio provided to a burner of a combustion system for altering its operating point. First, a value of a first parameter e.g. temperature, is checked, and if the value equals or exceeds a predetermined maximum limit of the first parameter that places the operating point in a first undesired region of operation, then a pilot-fuel/pilot-air ratio is altered such that the value of first parameter is moved to below the first parameter's predetermined maximum limit. Similarly, a value of a second parameter e.g., pressure, is checked, and if the value equals or exceeds a predetermined maximum limit of the second parameter that places the operating point in a second undesired region of operation, then again the pilot-fuel/pilot-air ratio is altered such that the value of second parameter is moved to below the second parameter's predetermined maximum limit. A combustion system operates according to the method.

Abstract: A burner includes a pilot burner, a combustion chamber, and a swirler located radially outwardly of the combustion chamber and being adapted to impose a swirling motion on a fuel/air mixture about an axial centerline of the combustion chamber. The pilot burner has a pilot burner face located radially inwardly of the swirler and forms an axially upstream wall of the combustion chamber, the pilot burner face incorporating a pilot fuel injector and an ignitor, both being positioned radially offset from the axial centerline. A recess is positioned radially offset from the axial centerline within the pilot burner face.

Abstract: A combustor for a gas turbine, having a pre-combustion chamber having a peripheral wall around a center axis of the pre-combustion chamber, the peripheral wall has an inner panel and an outer panel and a passage provided between the inner and the outer panels, a swirler which is connected to the pre-combustion chamber for providing pre-combustion chamber with a flow of an oxidant gas, at least a pilot fuel injector, wherein the swirler is connected to the peripheral wall in such a way that a portion of the oxidant gas from the swirler is channeled to the passage, and the pilot fuel injector is connected to the passage for injecting a flow of pilot fuel into the passage.

Abstract: A combustor for a gas turbine having: a pre-combustion chamber, a swirler, a pilot burner upstream the pre-combustion chamber which has a pilot burner surface separating the pilot burner from the pre-combustion chamber. The pilot burner further includes at least a pilot fuel injector, wherein the combustor includes a lip extending from the pilot burner surface in the pre-combustion chamber, the lip including an internal surface oriented towards the pilot fuel injector, the internal surface being inclined of an inclination angle of between 0 degrees and 90 degrees with respect to the center axis of the pre-combustion chamber, and the lip has at least a feed passage for connecting the internal surface with the flow of oxidant gas coming from the swirler.

Abstract: A combustor for a gas turbine includes a pre-combustion chamber, a swirler, a burner plenum, wherein the swirler and the burner plenum surround the pre-combustion chamber in a circumferential direction with respect to the centre axis of the combustor. The swirler has a plurality of slots through which an oxidant/fuel mixture is injectable into the pre-combustion chamber, the each slot with at least a fuel injector through which fuel is injectable into the slot. The peripheral wall of the pre-combustion chamber includes a plurality of mixing holes downstream of the swirler for letting a portion of the oxidant gas in burner plenum to flow from the burner plenum to the pre-combustion chamber.

Abstract: A combustor for a gas turbine engine having a central axis about which is arranged in flow sequence a radial swirler, a pre-chamber partly defined by a wall and a combustion chamber. The radial swirler has a base plate having an annular array of vanes and fuel injectors arranged to direct an air/fuel mixture radially inwardly and tangentially to create a vortex that flows through the pre-chamber and into the combustion chamber. The pre-chamber has a portion which is convergent in a downstream direction.

Abstract: A swirler for use in a combustor of a gas turbine engine, having a plurality of generally radially inwardly extending passages arranged circumferentially staggered in a circle, each passage having a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending lateral surfaces, and a base surface and top surface, in use of the swirler fuel and air travelling along the passages from their inlet ends to their outlet ends so as to create adjacent to the outlet ends a swirling fuel/air mixture. At least one surface of at least one passage has at least one gas fuel injection hole, wherein the surface, having the gas fuel injection hole, has at least one counterbore radially surrounding the gas fuel injection hole, wherein the gas fuel injection hole is arranged at a base of the counterbore.

Abstract: A combustor for a gas turbine is provided. The combustor includes a pre-combustion chamber having a center axis and a swirler which is mounted to the pre-combustion chamber. The swirler surrounds the pre-combustion chamber in a circumferential direction with respect to the center axis. The swirler has a bottom surface which forms a part of a slot through which oxidant/fuel mixture is injectable into the pre-combustion chamber, wherein the bottom surface is located in a bottom plane. The swirler further includes a fuel injector which is arranged to the bottom surface such that a fuel is injectable into the slot with a fuel injection direction, wherein a first component of the fuel injection direction is non-parallel to the normal (n) of the bottom plane.

Abstract: A burner for a combustor having a burner axis, a fuel lance, an igniter and a main air flow passage(s). The passage is angled relative to the burner axis and creates a main vortex thereabout in a first rotational direction. The main vortex travels in a direction along the burner axis, away from the surface. The fuel lance is located downstream of the igniter with respect to the first rotational direction of the main vortex so that a part of a main air flow washes over the fuel lance and over the igniter. The fuel lance has a fuel lance axis, a liquid fuel tip having a fuel outlet and an array of air assist passages having outlets arranged thereabout. The air assist passages are angled relative to create an air assist vortex about the fuel lance axis in the same rotational direction to the first rotational direction.

Abstract: A burner includes a pilot burner, a combustion chamber, and a swirler located radially outwardly of the combustion chamber and being adapted to impose a swirling motion on a fuel/air mixture about an axial centerline of the combustion chamber. The pilot burner has a pilot burner face located radially inwardly of the swirler and forms an axially upstream wall of the combustion chamber, the pilot burner face incorporating a pilot fuel injector and an ignitor, both being positioned radially offset from the axial centerline. A recess is positioned radially offset from the axial centerline within the pilot burner face.

Abstract: A combustor for a gas turbine is provided. The combustor includes a pre-combustion chamber having a centre axis and a swirler which is mounted to the pre-combustion chamber. The swirler surrounds the pre-combustion chamber in a circumferential direction with respect to the centre axis. The swirler has a bottom surface which forms a part of a slot through which oxidant/fuel mixture is injectable into the pre-combustion chamber, wherein the bottom surface is located in a bottom plane. The swirler further includes a fuel injector which is arranged to the bottom surface such that a fuel is injectable into the slot with a fuel injection direction, wherein a first component of the fuel injection direction is non-parallel to the normal (n) of the bottom plane.

Abstract: A gas turbine combustion system is provided. In an embodiment, the system includes a first radial inflow swirler having first radial outer intake openings, first radial inner outlet openings and first flow passages, each first flow passage including a first angle (a) with respect to the radial direction, a second radial inflow swirler having second radial outer intake openings, each second flow passage including a second angle (p) with respect to the radial direction, where the radial outer circumference of the second radial inflow swirler has a diameter that is smaller than the diameter of the radial inner circumference of the first radial inflow swirler and the second radial inflow swirler is located coaxially with and radially inside the first radial inflow swirler. The first angle (a) has a different sign than the second angle (p) with respect to the radial direction.