A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.

A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.

A low nitrogen coupling combustion system for the disposal of waste stink gas and solid waste including a waste pit, at least one stink gas incineration equipment and a waste incinerator, wherein the waste pit is equipped with stink gas outlets and the stink gas incineration equipment is provided with an incineration chamber for burning stink gas, as well as a stink gas inlet, a fuel inlet and a burned stink gas outlet which are connected with the incineration chamber; the stink gas inlet is connected with the stink gas outlet of the waste pit through a stink gas delivery pipe, and the fuel inlet is connected with a fuel source through a fuel delivery pipe; the burned stink gas outlet is connected with a combustion-supporting air inlet of the waste incinerator through a flue gas discharge pipe.

A low nitrogen coupling combustion system for the disposal of waste stink gas and solid waste including a waste pit, at least one stink gas incineration equipment and a waste incinerator, wherein the waste pit is equipped with stink gas outlets and the stink gas incineration equipment is provided with an incineration chamber for burning stink gas, as well as a stink gas inlet, a fuel inlet and a burned stink gas outlet which are connected with the incineration chamber; the stink gas inlet is connected with the stink gas outlet of the waste pit through a stink gas delivery pipe, and the fuel inlet is connected with a fuel source through a fuel delivery pipe; the burned stink gas outlet is connected with a combustion-supporting air inlet of the waste incinerator through a flue gas discharge pipe.

The turbine (12) for a turbine engine (100) extends around a major axis (X-X) and comprises: - a casing (4) comprising an annular hook (38), - a movably mounted impeller (16), - a ring (30) extending opposite the impeller in a direction radial to the major axis (XX), - a distributor (14) comprising a blade provided with a platform (11), the platform being extended radially outwards by a spoiler (22, 24), the spoiler (22, 24) being radially mounted on the hook (38), and - foils (40) each having a profiled trough shape in a direction circumferential to the axis, the foils extending in succession in the circumferential direction, each foil (40) extending between the spoiler (22, 24) and the hook (38). The turbine comprises stops (162) to prevent the foils (40) from moving in the circumferential direction. Each foil (40) comprises a protrusion (162) arranged so as to extend circumferentially opposite another protrusion (162) of another adjacent foil (40).

The turbine (12) for a turbine engine (100) extends around a major axis (X-X) and comprises: - a casing (4) comprising an annular hook (38), - a movably mounted impeller (16), - a ring (30) extending opposite the impeller in a direction radial to the major axis (XX), - a distributor (14) comprising a blade provided with a platform (11), the platform being extended radially outwards by a spoiler (22, 24), the spoiler (22, 24) being radially mounted on the hook (38), and - foils (40) each having a profiled trough shape in a direction circumferential to the axis, the foils extending in succession in the circumferential direction, each foil (40) extending between the spoiler (22, 24) and the hook (38). The turbine comprises stops (162) to prevent the foils (40) from moving in the circumferential direction. Each foil (40) comprises a protrusion (162) arranged so as to extend circumferentially opposite another protrusion (162) of another adjacent foil (40).

A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.

An integral cooling system for a turbine casing and guide vanes in an aeroengine is provided, belonging to the field of research on flow and heat exchange of a turbine casing in an aeroengine. An inner guide ring and multiple of guide vanes are mounted on the turbine casing; the cooling system includes an electromagnetic pump, a heat exchanger, an expansion joint and a cooling pipeline; an annular cavity is provided in the turbine casing, the cooling pipeline is mounted on the inner wall of the annular cavity and periodically and uniformly distributed along the circumferential direction of the turbine casing, and the cooling pipeline is filled with cooling liquid; a mounting cavity is further provided in the turbine casing, and the mounting cavity communicates with the annular cavity; the electromagnetic pump, the expansion joint and the heat exchanger are all mounted in the mounting cavity.

An integral cooling system for a turbine casing and guide vanes in an aeroengine is provided, belonging to the field of research on flow and heat exchange of a turbine casing in an aeroengine. An inner guide ring and multiple of guide vanes are mounted on the turbine casing; the cooling system includes an electromagnetic pump, a heat exchanger, an expansion joint and a cooling pipeline; an annular cavity is provided in the turbine casing, the cooling pipeline is mounted on the inner wall of the annular cavity and periodically and uniformly distributed along the circumferential direction of the turbine casing, and the cooling pipeline is filled with cooling liquid; a mounting cavity is further provided in the turbine casing, and the mounting cavity communicates with the annular cavity; the electromagnetic pump, the expansion joint and the heat exchanger are all mounted in the mounting cavity.

A radio frequency waveguide communication system includes a guided electromagnetic transmission network, and a cooling air source. The guided electromagnetic transmission network includes one or more remote node in fluid communication with one or more waveguides. The cooling air source is in fluid communication with the guided electromagnetic transmission network and is configured to provide pressurized cooling air to the waveguide. The waveguides direct the pressurized cooling air to the remote node.