The invention relates to a turbine engine combustion module (10), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: at least two combustion chambers (12A, 12B) arranged about an axis, each chamber (12A, 12B, 12C) comprising a compressed gas intake port (16) and a burnt gas exhaust port (18); and an ignition means that triggers combustion in the combustion chambers (12A, 12B, 12C). The module (10) comprises at least one duct (80) which establishes a communication between a first combustion chamber (12A) and at least one second combustion chamber (12B) in order to inject burnt gases from the first combustion chamber (12A) into the second combustion chamber (12B) so as to trigger combustion in the second combustion chamber (12B).

A cross-fire tube for connecting adjacent combustors in a gas turbine, and a combustion section including the cross-fire tube, are disclosed. The cross-fire tube includes a hollow tubular body having opposite ends, and a plurality of purge air hole pairs is defined in the hollow tubular body and located at more than two different axial positions between the opposite ends. Purge air flows through the plurality of purge air hole pairs to create a uniform distribution of the purge air between the adjacent combustors. The velocity of the purge air exiting the ends of the cross-fire tube can be, for example, 25% higher. The cross-fire tube having the hole arrangements described herein also extends the life expectancy of the tube by reducing oxidation.

A cross-fire tube for connecting adjacent combustors in a gas turbine, and a combustion section including the cross-fire tube, are disclosed. The cross-fire tube includes a hollow tubular body having opposite ends, and a plurality of purge air hole pairs is defined in the hollow tubular body and located at more than two different axial positions between the opposite ends. Purge air flows through the plurality of purge air hole pairs to create a uniform distribution of the purge air between the adjacent combustors. The velocity of the purge air exiting the ends of the cross-fire tube can be, for example, 25% higher. The cross-fire tube having the hole arrangements described herein also extends the life expectancy of the tube by reducing oxidation.

Combustors and gas turbines are provided. A combustor includes an axial centerline and an end cover. The combustor further includes at least one fuel nozzle that extends from the end cover and at is least partially surrounded by a combustion liner. The combustion liner extends between the at least one fuel nozzle and an aft frame and that defines a combustion chamber. An outer sleeve is spaced apart from and surrounds the combustion liner such that an annulus is defined therebetween. The outer sleeve defines at least one aperture. A wake energizer is mounted on the outer sleeve. The wake energizer defines at least one passage that is angled with respect to the axial centerline of the combustor. The at least one passage aligns and is in fluid communication with the at least one aperture of the outer sleeve.

Combustors and gas turbines are provided. A combustor includes an axial centerline and an end cover. The combustor further includes at least one fuel nozzle that extends from the end cover and at is least partially surrounded by a combustion liner. The combustion liner extends between the at least one fuel nozzle and an aft frame and that defines a combustion chamber. An outer sleeve is spaced apart from and surrounds the combustion liner such that an annulus is defined therebetween. The outer sleeve defines at least one aperture. A wake energizer is mounted on the outer sleeve. The wake energizer defines at least one passage that is angled with respect to the axial centerline of the combustor. The at least one passage aligns and is in fluid communication with the at least one aperture of the outer sleeve.

A combustor for a gas turbine is described. The combustor comprises a combustor liner, a metering plate attached to an end of the combustor liner and a combustor casing at least partially surrounding the combustor liner. An end cover is further connected to the combustor casing. The combustor liner is connected to the combustor casing by means of a retainer arranged between the metering plate and the end cover, and attached to the metering plate and to the end cover.

A combustor for a gas turbine is described. The combustor comprises a combustor liner, a metering plate attached to an end of the combustor liner and a combustor casing at least partially surrounding the combustor liner. An end cover is further connected to the combustor casing. The combustor liner is connected to the combustor casing by means of a retainer arranged between the metering plate and the end cover, and attached to the metering plate and to the end cover.

A combustor including a transition piece that defines a flow channel therein; a combustor basket inserted in the transition piece from an upstream side of the flow channel that sends a combustion gas through the flow channel and defines a gap through which a compressed air is sent with an inner peripheral surface of the transition piece; wherein the combustor basket includes a notch portion recessed from an end of the combustor basket on a downstream side toward the upstream side, and a purge air introduction hole through which the compressed air in the gap is introduced into the notch portion.

A plurality of gas turbine combustors having a cross fire tube assembly that connects adjacent combustors. The combustors include combustion chambers having annular combustion air passages on outer peripheries thereof. The cross fire tube assembly has a dual pipe configuration including an inner tube that connects the combustion chambers of the adjacent combustors and an outer tube that covers therein the inner tube and connects the combustion air passages of the adjacent combustors. The cross fire tube assembly further has openings disposed between the inner tube and the outer tube of outer peripheral partition walls of the combustion air passages that are connected with the outer tube of the cross fire tube assembly centering on the inner tube. The openings allow combustion air to flow in areas upstream and downstream of the inner tube with respect to a flow of the combustion air flowing through the combustion air passages.

A plurality of gas turbine combustors having a cross fire tube assembly that connects adjacent combustors. The combustors include combustion chambers having annular combustion air passages on outer peripheries thereof. The cross fire tube assembly has a dual pipe configuration including an inner tube that connects the combustion chambers of the adjacent combustors and an outer tube that covers therein the inner tube and connects the combustion air passages of the adjacent combustors. The cross fire tube assembly further has openings disposed between the inner tube and the outer tube of outer peripheral partition walls of the combustion air passages that are connected with the outer tube of the cross fire tube assembly centering on the inner tube. The openings allow combustion air to flow in areas upstream and downstream of the inner tube with respect to a flow of the combustion air flowing through the combustion air passages.