A device (20, 29, 48, 64) for cooling a supporting structure of a heat shield (33, 60) to avoid scaling of the supporting structure due to the intake of hot gas. The device has a longitudinal axis (21) and a cooling air duct (22). The device is on the supporting structure with the longitudinal axis (21) intersecting the surface (51) of the supporting structure (34). In this position, the cooling air duct (22) extends from a device end (23) pointing towards the supporting structure. The device has at least one outlet duct downstream in the cooling air duct. The duct emerges out of the device (20, 29, 48, 64) laterally with respect to the longitudinal axis (21). The cooling air duct (22) corresponds to at least one cooling air passage (50) in the supporting structure (34).

A retaining element (22, 54) for retaining a heat shield tile on a supporting structure: A fastening section (23) fastened to the supporting structure. A retaining section (24) having a retaining head (25), which engages an engagement device on the heat shield tile. The fastening section (23) top side (28) faces the cold side of the heat shield tile when the retaining section engages the heat shield tile. Scaling of the supporting structure due to the entry of hot gas can be avoided particularly effectively by means of the retaining element. At least one cooling-air passage (34, 55) arranged in the fastening section (23) has an inlet opening (35, 68) and at least one outlet opening (37, 38, 62) which is arranged in a lateral surface (32) and/or on the top side (28) of the fastening section. Cooling air, which enters the inlet opening (35, 68) and exits from the at least one outlet opening, can be conducted in a respective outflow direction (50, 51, 59, 63, 61) by the cooling-air passage, which outflow is parallel to the cold side and avoids impingement cooling of the heat shield tile. The fastening section is arranged on the supporting structure such that the cooling-air passage (34, 55) corresponds to at least one cooling-air channel (45) in the supporting structure.

A cooling device is provided with a hot-part cooling system that guides air to a hot part of a gas turbine. The hot-part cooling system includes a compressor capable of operating independently of the gas turbine, and extracts air inside a casing of the gas turbine to pressurize the air with the compressor and guides the air to the hot part. The cooling device is further provided with a rotor cooling system that extracts the air inside the casing from the casing and guides the air to a turbine rotor, and a connecting system that guides the air pressurized by the compressor to the rotor cooling system while a fuel supply to the gas turbine is stopped.

A combustor for a gas turbine engine comprises a combustion liner to define a combustion chamber for burning fuel to drive to turbine. The combustion liner comprises a plurality of nugget holes for providing cooling fluid to create a cooling film over the surface of the combustion liner adjacent the combustion chamber. The nugget holes can be circumferentially angled relative to the engine centerline to provide the flow of cooling fluid in an angled manner to align with a local streamline for the flow of fluid from the combustor.

The present invention relates to a device for cooling a wall of a component, where a fluid flow flows parallel to the wall, with at least one inflow duct, the center axis of which being arranged inclined to the plane of the wall, with a groove provided in the wall, into which issues the inflow duct, where a wall of the groove is designed contoured downstream of a discharge opening of the inflow duct and has an inflow edge facing the discharge opening, characterized in that the groove extends on both sides of the discharge opening and adjacent to the inflow edge at an angle to the direction of the fluid flow, and has a narrowing width.

An internal combustion burner including a combustion chamber supplied with fuel and with oxidant and at least two combustion devices supplied with oxidant and with fuel. Combining two combustion devices of distinct configurations, which respectively generate two distinct types of flames with a system for cooling the walls of the burner by introducing air along the walls, makes it possible to obtain a burner that supplies a combustion gas temperature of up to 1700 C., while at the same time being easily cooled and occupying very little space so that it can, for example, be housed in an existing installation used in the manufacture of rock wool or glass wool.

The cooling system includes a jacket disposed at least partially around a combustor having a combustor channel opening. The jacket includes a slot having an opening oriented towards a downstream end of the combustor. The slot may include a width ranging from around 0.5% to around 100% of a width of the combustor channel opening. The slot accepts a coolant through the opening of the slot.

The present disclosure discloses a combustion chamber and a combustion apparatus. The combustion chamber includes: a first surrounding plate located on an outer side and a second surrounding plate located on an inner side. A combustion cavity is defined by the second surrounding plate. The first surrounding plate and the second surrounding plate are spaced apart from each other to define at least one air duct in communication with the combustion cavity. Each of the at least one air duct has an air inlet hole formed in the first surrounding plate, and an air outlet hole formed in the second surrounding plate.

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.

The invention relates to the field of power engineering and can be used in heating systems, more particularly in water heaters or boilers, in disposal systems fueled by the combustion of associated gas, and in electrical energy generating systems. A pulse combustion apparatus comprises a combustion chamber 14, at least one resonant channel 28 connected to the combustion chamber 14, a device 15 for removing heat which is linked to the combustion chamber and to the resonant channel and which consists of at least one chamber and/or at least one tube for a heat-exchanging agent 16. A device for supplying air and combustible gas, which is connected to the combustion chamber 14, comprises at least one gaseous medium nonreturn valve 17 and at least one guard chamber 18 of said valve 17. The at least one gaseous medium nonreturn valve 17 is directly or indirectly linked to the device 15 for removing heat via a vibration isolator 19, 24.