Patent application number | Description | Published |
20090308077 | HOLE PATTERN FOR GAS TURBINE COMBUSTOR - A combustor for a turbine engine includes an outer liner having a row of circumferentially distributed outer combustion air holes and an inner liner circumscribed by the outer liner and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners each include at least a major air hole having a first hole size, an intermediate air hole having a second hole size, and a minor air hole having a third hole size. The first, second, and third hole sizes are all different from each other. | 12-17-2009 |
20110120134 | GAS TURBINE COMBUSTOR - An annular combustor for a gas turbine has a combustion chamber having an interior volume that, in longitudinal section, includes a forward volume, an intermediate volume and an aft volume. The forward volume represents from about 30% to about 40% of the combustor interior volume, the intermediate volume represents from about 10% to about 20% of the combustor interior volume, and the aft volume represents from about 40% to about 60% of the combustor interior volume. | 05-26-2011 |
20110314824 | SWIRLER, FUEL AND AIR ASSEMBLY AND COMBUSTOR - An air swirler, a fuel and air admission assembly, and a staged combustor are disclosed. The staged combustor may be equipped with the fuel and air admission assemblies incorporating the air swirlers for use in gas turbine engines, such as for example gas turbine engines powering aircraft having supersonic cruise capability. | 12-29-2011 |
20120017599 | ANNULAR GAS TURBINE COMBUSTOR - A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly. | 01-26-2012 |
20130000307 | SWIRLER FOR GAS TURBINE ENGINE FUEL INJECTOR - A swirler for fuel injection in a gas turbine engine includes a frustoconical swirler body. A first and a second air flow path direct air in generally opposed circumferential directions into the swirler. These air paths intermix and create turbulence. As this turbulence encounters fuel droplets, the fuel is atomized, and uniformly distributed within the air flow. A shear layer is created adjacent an inner surface of the swirler body. In a separate feature, a third air flow path is directed into the air. | 01-03-2013 |
20130192233 | HEAT SHIELD FOR A COMBUSTOR - A heat shield includes a panel having a forward face and an aft face, a circumferential outer side and a circumferential inner side such that the panel subtends a predetermined arc, and a first radially extending side and a second radially extending side each extending from the circumferential outer side to the circumferential inner side. The panel defines an opening extending between the forward face and the aft face, a lip projecting from the forward face and extending around the opening, a rail projecting from the forward face and extending around the lip to define a cavity region between the lip and the rail, and a plurality of holes in the cavity region. Each of the plurality of holes extends from the forward face to the aft face. A region of the panel extending from the lip to the circumferential outer side is free of any aft-projecting features. | 08-01-2013 |
20130340437 | TURBINE ENGINE COMBUSTOR WALL WITH NON-UNIFORM DISTRIBUTION OF EFFUSION APERTURES - A turbine engine combustor wall includes support shell and a heat shield. The support shell includes shell quench apertures, first impingement apertures, and second impingement apertures. The combustor heat shield includes shield quench apertures fluidly coupled with the shell quench apertures, first effusion apertures fluidly coupled with the first impingement apertures, and second effusion apertures fluidly coupled with the second impingement apertures. The shield quench apertures and the first effusion apertures are configured in a first axial region of the heat shield, and the second effusion apertures are configured in a second axial region of the heat shield located axially between the first axial region and a downstream end of the heat shield. A density of the first effusion apertures in the first axial region is greater than a density of the second effusion apertures in the second axial region. | 12-26-2013 |
20140123655 | SWIRLER FOR GAS TURBINE ENGINE FUEL INJECTOR - A swirler for a gas turbine engine fuel injector comprises a swirler body extending from an upstream end to a downstream end. A fuel injector extends into the body, and has a downstream end for injecting fuel in a downstream direction. A first flow path directs air in a first circumferential direction about a central axis of the swirler body. A second flow path directs air to intermix with the air in the first flow path, and then to mix with fuel injected by the fuel injector. The first and second flow paths are positioned to inject air upstream of the downstream end of the fuel injector where fuel is injected. The first flow path is provided in a greater volume than the volume provided in the second flow path. The second flow path directs air at a location downstream of the first flow path. | 05-08-2014 |