A gas turbine engine has a converging duct that has combustion products flow at low mach speeds through a first portion and a high mach speeds through a second portion. The converging duct has two types of cooling schemes formed. One type of cooling scheme is beneficial for the low mach speed combustion product flow and one type of cooling scheme is beneficial for the high mach speed combustion product flow. The two cooling schemes are blended together in order increase the efficiency of the cooling of the converging duct.

A main mixer including a swirler along an axis, the swirler including an outer swirler with a multiple of outer vanes, and a center swirler with a multiple of center vanes and a swirler hub along the axis, the swirler hub including a fuel manifold and an inner swirler with a multiple of inner vanes that support a centerbody, the multiple of inner vanes interconnect the fuel manifold and the centerbody.

A grommet may define a dilution hole in a combustor panel. The grommet may comprise a ridge having a stepped geometry formed about an inner diameter of the grommet, the ridge comprising a passage. The passage may comprise an outlet. The ridge may further comprise a fillet about the inner diameter of the grommet, wherein the outlet is configured to direct a cooling flow circumferentially along the fillet and fill the ridge with the cooling flow.

A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.

A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.

A burner of a turbomachine has an upstream burner section providing a first fuel and an oxygen containing fluid to an upstream end of a burner interior, a downstream burner section for providing a second fuel to a downstream end of the burner interior, and an intermediate burner section between the two sections. The intermediate burner section has an annular wall surrounding a mid-section of the burner interior. The annular wall has an annular cooling fluid passage, for guiding the oxygen containing fluid, and an annular fuel passage for guiding the second fuel to the downstream burner section, the annular fuel passage being more distant to the burner interior than the annular cooling fluid passage. Two annular slots are incorporated into the annular wall. The upstream burner section has at least one integrated fuel tube through a body of the upstream burner section, configured to feed the annular fuel passage.

Method for constructing impingement/effusion cooling features in a component of a combustion turbine engine is provided. A pocket 102 may be arranged between an outer wall 104 and an inner wall 106 of the component. A lasing device 108 allows drilling through the component to form an effusion hole 110. The lasing device further allows welding closed an opening 117 formed at outer wall 104 of the component during the drilling with the lasing device through the component. Lasing device 108 further allows drilling through outer wall 104 of the component to form an impingement hole 118 for the impingement/effusion cooling feature. The proposed methodology in a multi-panel arrangement, for example, eliminates a need of having to pre-drill such holes in individual panels prior to the bonding and forming of the component, which overcomes various drawbacks commonly associated with such pre-drilling.

A gas turbine hot part includes: a body portion; a porous portion forming at least a part of the body portion or disposed on at least a part of the body portion and allowing a cooling gas to pass therethrough; and at least one filter disposed upstream of the porous portion in a flow direction of the cooling gas and capable of trapping foreign substances that cannot pass through the porous portion.

A gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface wherein the first component includes a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a deflector forming a passageway with the second surface of the first component, the passageway configured to direct airflow into the cooling channel in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.

A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection device secured to first component, the lateral flow injection device fluidly connecting a flow path located proximate to the second surface of the first component to the cooling channel, the lateral flow injection device being configured to direct airflow from the airflow path into the cooling channel in about a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.