Abstract: A combustion chamber of an aircraft turbomachine having a main axis includes: a body of revolution coaxial with the main axis having a plurality of combustion tubes extending mainly in the direction of the main axis and being distributed in a ring about the main axis; a first perforated rotary disc mounted at a first axial end of the body and rotatable about the main axis to selectively open or close a first end of each of the combustion tubes; and a second perforated rotary disc mounted at a second axial end of the body and rotatable about the main axis to selectively open or close a second end of each of the combustion tubes. The body includes a plurality of cooling segments extending mainly in the direction of the main axis, which are distributed in a ring about the main axis and around the combustion tubes.

Abstract: A semi-passive cooling system for a component exposed to a fluid flow utilizes a hierarchical vasculature and a sacrificial transpirant to cool the component. The component includes a body that defines a transpirant reservoir and the hierarchical vasculature. The transpirant is configured to transition between a solid phase and a vapor phase over an operating temperature range of the component.

Abstract: Systems and methods for equalizing fluid levels within a vent line and a propellant tank in which the vent line is located are discussed herein. The vent line includes a vent valve and an equalization valve. The vent valve can be included in a vent duct of the vent line. The equalization valve is included in a bottom wall (i.e., a low point) of the vent duct of the vent line. A controller is also included in the system to instruct a vent valve and the equalization valve to open and close.

Abstract: A combustion chamber section for a combustion chamber for a rocket engine, the combustion chamber section including a combustion chamber body enclosing a combustion chamber volume and having coolant channels disposed therein, and at least one baffle integrally formed with the combustion chamber body and projecting from the combustion chamber body into the interior of the combustion chamber. The at least one baffle includes at least one coolant channel fluidly connected to at least one of the coolant channels in the combustion chamber body. Furthermore, an additive layer manufacturing method for manufacturing such a combustion chamber section is described.

Abstract: A combustion chamber for a rocket engine, the combustion chamber including a combustion chamber body enclosing a combustion chamber volume and a nozzle portion tapering in a longitudinal direction of the combustion chamber and adjoining the combustion chamber body. The combustion chamber body has at least one first portion and a second portion, wherein an inner surface of the at least one first portion facing the combustion chamber volume is closer to a cross-sectional center of the combustion chamber body than an inner surface of the second portion of the combustion chamber body. Furthermore, a additive layer manufacturing method for manufacturing such a combustion chamber is described.

Abstract: A novel method is described for water heating using stored solar heat. Solar heat is stored in an insulated tank by using scrap and inexpensive heat absorbing or heat storing materials. Stored solar heat can then be used to heat water in a storage tank by extracting the solar heat using an antifreeze liquid which in turn heat cold water in the water tank. Water temperature in the storage tank is controlled by a thermostat. When the water temperature drops below the set point on the thermostat, a circulating pump turns on and pump the cold water until it reaches the desired set temperature. Once it reaches the set point in the thermostat, the water circulation pump turns off.

Abstract: Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.

Abstract: A direct contact water heater for heating water by the hot exhaust gases from a torpedo propulsion engine by imparting a swirl velocity to the exhaust gases and injecting water into the swirling exhaust gases to form the water into droplets which by the swirl velocity are centrifuged into a liquid annulus in a mixing chamber and with the exhaust gases flowing centrally thereof to an outlet. Structure at an end of the mixing chamber withdraws water from the liquid annulus for use.