According to one embodiment, there is provided a propulsion apparatus of liquid propellant rocket engine. The propulsion apparatus of liquid propellant rocket engine, the propulsion apparatus including: a body in which liquid propellant flows; an injector core located inside the body; at least one outlet connected to the injector core to discharge combustion gas; and an injector for discharging the liquid propellant flowing into the body, wherein the injector is located in an area adjacent to the outlet, wherein the liquid propellant moves between a frame of the body and a frame of the injector core.

A combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.

A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts and a multiple of inlets to a respective diffusion passage, one of the multiple of inlets formed between each one of the multiple of hollow struts located between two diffusion passages.

An acoustic attenuator comprises a first attenuation unit, a second attenuation unit, a welded section, and a communication part. A first acoustic damper is provided on an outer surface of a first acoustic liner, which faces toward a side opposite from an object, to form a first damper space that communicates with an internal space of the object. The second attenuation unit is attached to an outer surface of the object. The welded section is provided at least between the first acoustic damper and a second acoustic damper. The welded section secures the second attenuation unit to the first acoustic liner. The communication part is disposed in a position farther from an outer surface of the object than the welded section, allowing communication between the first damper space and a second damper space.

A constant density heat exchanger is provided. The constant density heat exchanger includes a housing extending between a first end and a second end and defining a chamber having an inlet and an outlet. A first flow control device is positioned at the inlet of the chamber and movable between an open position in which a working fluid is permitted into the chamber and a closed position in which the working fluid is prevented from entering the chamber. A second flow control device is positioned at the outlet of the chamber and movable between an open position in which the working fluid is permitted to exit the chamber and a closed position in which the working fluid is prevented from exiting the chamber. A heat exchange fluid imparts thermal energy to the volume of working fluid held at constant density within the chamber by the first and second control devices.

The present disclosure provides devices for guiding an element in a combustion chamber wall opening. Between the welds or brazes joining a bushing with a cup and the trajectory of the ring edge, an intermediate space is reserved in an internal annular groove for said welds or brazes to protrude into, so that said welds or brazes lie outside the trajectory of the ring edge.

Combustor systems are provided. For example, a combustor system comprises a combustor having forward and aft ends and including annular inner and outer liners that each extend generally along an axial direction and define a combustion chamber therebetween. The combustor system also comprises a fuel nozzle having an outlet defined in an outlet end of the fuel nozzle and including a pilot swirler. The outlet is positioned at the forward end of the combustor to direct a fuel-air mixture into the combustion chamber. The combustor system further comprises a main mixer attached to the outlet end of the fuel nozzle and extending about the outlet. A total combustor airflow through the combustor comprises a pilot swirler airflow that is greater than about 14% of the total combustor airflow and a main mixer airflow that is less than about 50% of the total combustor airflow.

A system includes a combustor. The combustor has a combustor wall with a combustor dome at an upstream end of the combustor wall, and an outlet at a downstream end of the combustor wall opposite the upstream end. The combustor wall includes an inner wall portion and an outer wall portion defining an interior of the combustor therebetween. Each of the inner wall portion and outer wall portion extends from the combustor dome to the downstream end of the combustor wall. The combustor wall includes an air cooling passage embedded inside at least one of the inner wall portion and the outer wall portion. The air cooling passage extends from the upstream end of the combustor wall to the downstream end of the combustor wall.

A gas turbine combustion duct includes a duct body and a fluid intake hole. The duct body includes a duct wall defining a plenum for routing a flow of combustion products from a combustor downstream through the gas turbine combustion duct to a turbine section. The fluid intake hole extends from an outward-facing surface to an inward-facing surface through the duct wall for receiving an outside fluid flow into the plenum, and is laterally circumscribed about its entire periphery by a lateral-facing surface. The lateral-facing surface includes a curved surface portion along a shortest path from the inward-facing surface to the outward-facing surface and is free of angled surface transitions along the shortest path between the inward-facing surface and the outward-facing surface. The fluid intake hole is wider at the outward-facing surface than at the inward-facing surface. A boss may define the fluid intake hole and the lateral-facing surface.

A combustion chamber of a gas turbine having a peripheral support structure and a heat shield arranged therein. The support structure has a reduced cross-section on the downstream side and a stop element on the upstream side. There is a gap between the heat shield and the stop element to compensate for different strains and tolerances. For reduction of the cooling air consumption, a peripheral sealing groove which is open towards the heat shield and has a sealing element arranged therein is provided in the stop element, which sealing element rests against the heat shield and covers the gap.