A turbine engine includes a combustion chamber, comprising two coaxial axisymmetric walls extending one inside the other and delimiting between one another an annular air-circulation, an exterior wall, and at least one injector passing through the walls via ports, wherein the injector comprises a peripheral tube connected to the walls by three connections, at least two connections being of the slideway and/or ball-joint or bellows type.

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).

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).

In a gas turbine combustor, a sectional shape in a radial direction of either one of an inner peripheral surface of a second inner tube member and an outer peripheral surface of a first inner tube member, in a fitting portion of a crossfire tube assembly, has a plurality of small-curvature portions having a curvature smaller than a reference curvature, the reference curvature being a curvature of a portion at a maximum distance from the center of the sectional shape. This configuration ensures the crossfire tube assembly is cooled, and the Possibility of thermal deformation or fire damage is lowered, without lowering the temperature of a combustion exhaust gas passing through the crossfire tube assembly of the gas turbine combustor.

In a gas turbine combustor, a sectional shape in a radial direction of either one of an inner peripheral surface of a second inner tube member and an outer peripheral surface of a first inner tube member, in a fitting portion of a crossfire tube assembly, has a plurality of small-curvature portions having a curvature smaller than a reference curvature, the reference curvature being a curvature of a portion at a maximum distance from the center of the sectional shape. This configuration ensures the crossfire tube assembly is cooled, and the Possibility of thermal deformation or fire damage is lowered, without lowering the temperature of a combustion exhaust gas passing through the crossfire tube assembly of the gas turbine combustor.

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.

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

A system for retaining a cross fire tube in a multi-combustor gas turbine engine is disclosed. The system comprises a flow sleeve having a generally annular body, and a flange at a forward end thereof and having one or more recessed portions. A cross fire tube extends through one or more openings in the flow sleeve and is secured in place by a retention clip. The retention clip includes a plurality of fingers which engage the cross fire tube and a mounting plate engaging the one or more recessed portions of the flow sleeve flange so as to create a clip engagement having a lower profile than prior art configurations.