A method for routing computer messages between parties is provided. The method is implemented using a message gateway computing system including a processor and a memory. The method includes receiving a message routing offer from a seller and a representing an offer to process payment card transactions. The method also includes receiving a message routing request from a buyer. The method further includes first message route between the buyer party and a first seller party of the plurality of seller parties on a message processing network. The method also includes receiving a payment card transaction from the buyer party. The method further includes identifying the first message route associated with the payment card transaction. The method also includes transmitting the payment card transaction to the first seller party based at least in part on the first message route.

The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine and includes a plurality of cooling elements integrally formed with the annular ring and projecting therefrom into impingement airflow. The cooling elements increase the effective surface area of the inner surface of the annular ring, which is adapted to be cooled by the impingement airflow.

The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine and includes a plurality of cooling elements integrally formed with the annular ring and projecting therefrom into impingement airflow. The cooling elements increase the effective surface area of the inner surface of the annular ring, which is adapted to be cooled by the impingement airflow.

A nozzle includes a nozzle body with an inner air passage fed by a first radial swirler and a second radial swirler axially downstream of the first radial swirler. A first fuel circuit is axially between the first and second radial swirlers. A second fuel circuit is axially downstream of the second radial swirler, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet. An outer air passage is defined between a fuel circuit outer wall of the second fuel circuit and an outer air passage wall, wherein the outer air passage is a converging non-swirling air passage. An intermediate air passage can be defined between an intermediate wall and the second radial swirler, wherein the intermediate air passage is a converging non-swirling air passage.

A trapped vortex reverse flow combustor for a gas turbine includes a first dome structure having a plurality of first-dome vortex driver airflow openings for providing a first vortex generating mid airflow therethrough to a trapped vortex cavity. A second dome structure is arranged downstream of the first dome structure and includes a plurality of second-dome vortex driver airflow openings providing a first vortex generating outer airflow therethrough to the trapped vortex cavity, and a plurality of primary driver airflow openings providing a primary driver airflow therethrough radially inward of the trapped vortex cavity.

A combustion module for a turbomachine is provided and includes an annular casing extending about a longitudinal axis; an annular combustion chamber located inside the casing and comprising coaxial annular walls connected to one another by an annular chamber dome, the walls and the chamber dome consisting of at least two annular envelopes, which are made of a ceramic-matrix composite material. The module can include anti-disengagement devices to keep the annular edges pressing axially against one another and fuel injectors borne by the casing and engaged in apertures of one of the envelopes.

A combustion module for a turbomachine is provided and includes an annular casing extending about a longitudinal axis; an annular combustion chamber located inside the casing and comprising coaxial annular walls connected to one another by an annular chamber dome, the walls and the chamber dome consisting of at least two annular envelopes, which are made of a ceramic-matrix composite material. The module can include anti-disengagement devices to keep the annular edges pressing axially against one another and fuel injectors borne by the casing and engaged in apertures of one of the envelopes.

Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object. The heat-transfer device for facilitating heat exchange between combustion air (heat transfer medium) flowing along an outer surface of a combustor liner (heat transfer object), and the combustor liner, the heat-transfer device including at least one longitudinal vortex generating device protruding toward a annular passage (flow passage) of the combustion air and formed to generate a longitudinal vortex E with a central axis in a flow direction of the combustion air, and stir the combustion air flowing in the annular passage; and at least one radiator fin provided in a region A on the outer surface of the combustor liner, the region A being where a flow of the vortex E, on a swirling plane thereof, that are generated by the vortex generating device is directed from a side of the combustor liner, toward a side of a flow sleeve, the fin exchanging heat with the combustion air stirred by the vortex generating device.

Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object. The heat-transfer device for facilitating heat exchange between combustion air (heat transfer medium) flowing along an outer surface of a combustor liner (heat transfer object), and the combustor liner, the heat-transfer device including at least one longitudinal vortex generating device protruding toward a annular passage (flow passage) of the combustion air and formed to generate a longitudinal vortex E with a central axis in a flow direction of the combustion air, and stir the combustion air flowing in the annular passage; and at least one radiator fin provided in a region A on the outer surface of the combustor liner, the region A being where a flow of the vortex E, on a swirling plane thereof, that are generated by the vortex generating device is directed from a side of the combustor liner, toward a side of a flow sleeve, the fin exchanging heat with the combustion air stirred by the vortex generating device.

A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.