Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.

Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.

A turbulence generating structure for liner cooling enhancement is a liner cooling structure applied to a double-structured side portion formed by a liner and a flow sleeve and includes the liner and a first turbulence generator protruding from a surface space of the liner and including a plurality of ribs arranged in an axial direction, each of the ribs comprising blocks arranged at regular distances in the axial direction and interspaced by cooling holes. The ribs include a first set of adjacent ribs separated by a first passage distance, the first passage distance being repeated in a circumferential direction, and a second set of adjacent ribs separated by a second passage distance, the second passage distance being repeated in the circumferential direction, wherein the first and second sets of adjacent ribs have exactly one rib in common, and the first passage distance is greater than the second passage distance.

A turbulence generating structure for liner cooling enhancement is a liner cooling structure applied to a double-structured side portion formed by a liner and a flow sleeve and includes the liner and a first turbulence generator protruding from a surface space of the liner and including a plurality of ribs arranged in an axial direction, each of the ribs comprising blocks arranged at regular distances in the axial direction and interspaced by cooling holes. The ribs include a first set of adjacent ribs separated by a first passage distance, the first passage distance being repeated in a circumferential direction, and a second set of adjacent ribs separated by a second passage distance, the second passage distance being repeated in the circumferential direction, wherein the first and second sets of adjacent ribs have exactly one rib in common, and the first passage distance is greater than the second passage distance.

A crossfire tube to pass a flame from a combustor chamber of a first combustor to a combustor chamber of a second combustor adjacent to the first combustor is provided. The crossfire tube includes a first insertion pipe configured to connect an inner liner and an outer liner of the first combustor, the inner liner defining the combustion chamber and the outer liner surrounding the inner liner, a second insertion pipe configured to connect an inner liner and an outer liner of a liner of the second combustor, and a connection pipe disposed between the first combustor and the second combustor and connected to the first insertion pipe and the second insertion pipe at respective ends thereof so that the combustion chamber of the first combustor communicates with the combustion chamber of the second combustor via the connection pipe.

A crossfire tube to pass a flame from a combustor chamber of a first combustor to a combustor chamber of a second combustor adjacent to the first combustor is provided. The crossfire tube includes a first insertion pipe configured to connect an inner liner and an outer liner of the first combustor, the inner liner defining the combustion chamber and the outer liner surrounding the inner liner, a second insertion pipe configured to connect an inner liner and an outer liner of a liner of the second combustor, and a connection pipe disposed between the first combustor and the second combustor and connected to the first insertion pipe and the second insertion pipe at respective ends thereof so that the combustion chamber of the first combustor communicates with the combustion chamber of the second combustor via the connection pipe.

A combustor according to an embodiment includes: a cylinder body that demarcates a space between a combustor casing and a combustor liner; a pipe that guides a combustion gas between the combustor liner and the cylinder body; a pipe that guides a combustion gas having a temperature lower than a combustion gas to be guided to the pipe between the combustor casing and the cylinder body; a pipe-shaped member provided so as to penetrate the combustor casing, the cylinder body, and the combustor liner; a heat-resistant glass that is provided in the pipe-shaped member; a condensing lens provided in a manner to face the heat-resistant glass; and a laser oscillator that emits laser light to the inside of the combustor liner through the condensing lens.

A combustor according to an embodiment includes: a cylinder body that demarcates a space between a combustor casing and a combustor liner; a pipe that guides a combustion gas between the combustor liner and the cylinder body; a pipe that guides a combustion gas having a temperature lower than a combustion gas to be guided to the pipe between the combustor casing and the cylinder body; a pipe-shaped member provided so as to penetrate the combustor casing, the cylinder body, and the combustor liner; a heat-resistant glass that is provided in the pipe-shaped member; a condensing lens provided in a manner to face the heat-resistant glass; and a laser oscillator that emits laser light to the inside of the combustor liner through the condensing lens.

The present disclosure provides devices for guiding an element in a combustion chamber wall opening. Between the welds or brazes joining a bushing with a cup and the trajectory of the ring edge, an intermediate space is reserved in an internal annular groove for said welds or brazes to protrude into, so that said welds or brazes lie outside the trajectory of the ring edge.

The present disclosure provides devices for guiding an element in a combustion chamber wall opening. Between the welds or brazes joining a bushing with a cup and the trajectory of the ring edge, an intermediate space is reserved in an internal annular groove for said welds or brazes to protrude into, so that said welds or brazes lie outside the trajectory of the ring edge.