Abstract: A gas turbine engine combustor liner with at least one of the inner and outer liners that is effusion cooled and has a row of groups of circumferentially spaced apart dilution holes defined therethrough. Each group is located within a respective zone of the combustor liner defined by an overlap of adjacent conical sections corresponding to the sprays of adjacent fuel nozzles.

Abstract: A combustor is provided having one or more apertures adapted to asymmetrically introduce air adjacent the fuel nozzles to reduce smoke resulting from unburned hydrocarbons in a gas turbine engine combustion system by impeding escape of unburned hydrocarbons.

Abstract: A combustor having liners with a plurality of angled effusion holes defined therethrough at a first angle with respect to a surface of the liners and at a second angle with respect to a corresponding radial plane. A density of the effusion holes defined in a primary section receiving the fuel nozzles is at least equal to a density of the effusion holes defined in a secondary downstream section.

Abstract: A gas turbine engine combustor liner with at least one of the inner and outer liners that is effusion cooled and has a row of groups of circumferentially spaced apart dilution holes defined therethrough. Each group is located within a respective zone of the combustor liner defined by an overlap of adjacent conical sections corresponding to the sprays of adjacent fuel nozzles.

Abstract: A combustor having a combustor wall with a plurality of angled effusion holes defined therethrough. The tangential component of the hole direction of the effusion holes corresponds to a same rotational direction about the central axis of the combustor. The effusion holes directional arrangement is angled from a radial plane and the combustor liner surfaces in order to promote swirl at the combustor exit.

Abstract: A fuel nozzle having a fuel conveying member surrounded by a sheath. An air passage is defined between the fuel conveying member and the sheath for directing air to an air swirler provided at one end of the fuel conveying member. At one flow director is provided in the air passage for promoting air and fuel uniformity and distribution at a spray tip of the fuel nozzle.

Abstract: A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor to the turbine. An aerodynamic trip is disposed in at least one of; a combustor wall; and an inner shroud of the nozzle guide vane ring, and is adapted to emit jets of compressed air from cross flow ports into the flow of hot gas from the combustor. The air jets from the cross flow ports increase turbulence and equalize temperature distribution in addition to decoupling the attenuation and pressure fluctuations between the combustor and the turbine.

Abstract: A apparatus and method for improving combustion by improving at least one of temperature distribution in the combustor, pressure distribution around the combustor and combustion noise level in the combustor, by redistributing air around the combustor to modify the structure of the air flow prior to entry into the combustor.

Abstract: A combustor having a combustor wall with a plurality of angled effusion holes defined therethrough, the tangential component of the hole direction of the effusion holes corresponding to a same rotational direction with respect to the central axis of the combustor.

Abstract: A combustor having liners with a plurality of angled effusion holes defined therethrough at a first angle with respect to a surface of the liners and at a second angle with respect to a corresponding radial plane. A density of the effusion holes defined in a primary section receiving the fuel nozzles is at least equal to a density of the effusion holes defined in a secondary downstream section.

Abstract: A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor to the turbine. An aerodynamic trip is disposed in at least one of; a combustor wall; and an inner shroud of the nozzle guide vane ring, and is adapted to emit jets of compressed air from cross flow ports into the flow of hot gas from the combustor. The air jets from the cross flow ports increase turbulence and equalize temperature distribution in addition to decoupling the attenuation and pressure fluctuations between the combustor and the turbine.

Abstract: A combustor is provided having one or more apertures adapted to asymmetrically introduce air adjacent the fuel nozzles to reduce smoke resulting from unburned hydrocarbons in a gas turbine engine combustion system by impeding escape of unburned hydrocarbons.

Abstract: A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor to the turbine. An aerodynamic trip is disposed in at least one of; a combustor wall; and an inner shroud of the nozzle guide vane ring, and is adapted to emit jets of compressed air from cross flow ports into the flow of hot gas from the combustor. The air jets from the cross flow ports increase turbulence and equalize temperature distribution in addition to decoupling the attenuation and pressure fluctuations between the combustor and the turbine.

Abstract: A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor to the turbine. An aerodynamic trip is disposed in at least one of; a combustor wall; and an inner shroud of the nozzle guide vane ring, and is adapted to emit jets of compressed air from cross flow ports into the flow of hot gas from the combustor. The air jets from the cross flow ports increase turbulence and equalize temperature distribution in addition to decoupling the attenuation and pressure fluctuations between the combustor and the turbine.

Abstract: A fuel nozzle having a fuel conveying member surrounded by a sheath. An air passage is defined between the fuel conveying member and the sheath for directing air to an air swirler provided at one end of the fuel conveying member. At one flow director is provided in the air passage for promoting air and fuel uniformity and distribution at a spray tip of the fuel nozzle.

Abstract: A method of reducing engine noise generation by decoupling: acoustic and hydrodynamic fluctuation generated by a compressor and a fuel supply system; from acoustic and hydrodynamic fluctuation of a combustor, by: deflecting fuel jets into a fuel nozzle mixing chamber in a number of counter-rotating adjacent pairs of fuel laden vortices; emitting a resulting fuel-air mixture into the combustor downstream from the fuel nozzle mixing chamber.

Abstract: A apparatus and method for improving combustion by improving at least one of temperature distribution in the combustor, pressure distribution around the combustor and combustion noise level in the combustor, by redistributing air around the combustor to modify the structure of the air flow prior to entry into the combustor.

Abstract: A gas turbine engine combustor defining a combustion zone therein and being adapted for receiving compressed air from a compressor. The combustor comprises inner and outer walls spaced-apart by a predetermined spacing distance and defines a cavity therebetween. The outer wall has a first area defining at least an impingement aperture therein, the impingement aperture permits fluid flow communication between the compressor and the cavity. The inner wall has a second area corresponding to the first area and defines a plurality of effusion apertures therein, the effusion apertures permitting fluid flow communication between the cavity and the combustion zone, and each of the effusion aperture defines a cross-sectional area smaller than that of the impingement aperture. The effusion apertures are disposed in groups having a predetermined geometric arrangement relative to the impingement aperture and define a ratio of number of effusion apertures to the impingement aperture of between about 2:1 and about 4:1.

Abstract: A method of reducing engine noise generation by decoupling: acoustic and hydrodynamic fluctuation generated by a compressor and a fuel supply system; from acoustic and hydrodynamic fluctuation of a combustor, by: deflecting fuel jets into a fuel nozzle mixing chamber in a number of counter-rotating adjacent pairs of fuel laden vortices; emitting a resulting fuel-air mixture into the combustor downstream from the fuel nozzle mixing chamber.

Abstract: A fuel nozzle with a ring of fuel spray orifices directing fuel jets at a fuel vortex generator having a fuel deflecting surface disposed downstream a distance from each fuel spray orifice. A mixing chamber is defined between the fuel spray orifices and the fuel deflecting surface having a surface contour oriented to deflect fuel jets into the mixing chamber in counter-rotating adjacent pairs of fuel laden vortices. An air inlet supplies air to the mixing chamber via an airflow vortex generator having an airflow deflecting surface with a surface contour oriented to deflect airflow into the mixing chamber in counter-rotating adjacent pairs of airflow vortices. A fuel-air mixture outlet downstream from the mixing chamber releases the fuel-air mixture into a combustor for ignition.