A turbopump includes: a main shaft rotatably supported; a pump section including an impeller attached to one end of the main shaft; and a turbine section including: a disk attached to the other end of the main shaft, rotor blades provided on an outer periphery of the disk, and nozzles provided inclined to an entrance plane of a blade cascade constituted of the rotor blades, the nozzles having axisymmetric cross sections and arranged in at least two rows along a circumferential direction of the main shaft in a plane orthogonal to the main shaft.

A turbopump includes: a main shaft rotatably supported; a pump section including an impeller attached to one end of the main shaft; and a turbine section including: a disk attached to the other end of the main shaft, rotor blades provided on an outer periphery of the disk, and nozzles provided inclined to an entrance plane of a blade cascade constituted of the rotor blades, the nozzles having axisymmetric cross sections and arranged in at least two rows along a circumferential direction of the main shaft in a plane orthogonal to the main shaft.

System for chemical engine systems or air-breathing engine systems comprising: a catalytic combustion and/or addition of metallic additives, which can additionally adapt the combustion by homogeneous, respectively heterogeneous catalysts. The adaptation of combustion rate, combustion pressure, combustion temperature, latent heat and other conditions (e.g. heat reflections) can be used in a variety of technological ways. This enables optimization of combustion chamber geometry and, for example, reduction of profile losses. Lossy energy conversions are to be minimized, or specifically adapted (e.g. to a variable ambient pressure during vertical starts). To protect the adapted combustion, methods are named to avoid e.g. fouling, aging of the reactive surface, destructive pressure shocks and especially thermal damage. The potential through further technological additions, e.g. by means of contactless ignition or superordinate process concept is pointed out.

Passive reactivity control technologies that enable reactivity control of a nuclear thermal propulsion (NTP) system with little to no active mechanical movement of circumferential control drums. By minimizing or eliminating the need for mechanical movement of the circumferential control drums during an NTP burn, the reactivity control technologies simplify controlling an NTP reactor and increase the overall performance of the NTP system. The reactivity control technologies mitigate and counteract the effects of xenon, the dominant fission product contributing to reactivity transients. Examples of reactivity control technologies include, employing burnable neutron poisons, tuning hydrogen pressure, adjusting wait time between burn cycles or merging burn cycles, and enhancement of temperature feedback mechanisms. The reactivity control technologies are applicable to low-enriched uranium NTP systems, including graphite composite fueled and tungsten ceramic and metal matrix (CERMET), or any moderated NTP system, such as highly-enriched uranium graphite composite NTP systems.

A gas turbine main engine powered by a fuel, includes a combustion chamber configured to receive fuel through at least one injector, a turbopump including a pump, an inlet for introducing the fuel in a first state into the pump, a turbine, a turbine outlet for discharging the fuel in a second state, the outlet being fluidically connected to the combustion chamber through the injector, and a clutch further including a shaft, a heat exchanger comprising an inlet, fluidically connected to the turbopump pump, and an outlet, fluidically connected to the turbopump turbine. The heat exchanger heats fuel in the first state from the pump into fuel in the second state for the turbine. The engine further includes a bypass system fluidically connected with the heat exchanger outlet and the turbopump outlet. The clutch shaft is coupled both to a main engine accessory gearbox and to a turbopump shaft.

The method comprises depositing a coating of metal material on the inside surface of the body (4) of the stator (36), impregnating said coating with a self-lubricating composite material (20), machining internal cells (28) in the thickness of the coating (10), and machining orifices (34) leading into the cells.

A liquid rocket engine integrates tap-off openings at a combustion chamber wall to direct exhaust from the combustion chamber to a tap-off manifold that provides the exhaust to one or more auxiliary systems, such as a turbopump that pumps oxygen and/or fuel into the combustion chamber. The tap-off opening passes through a fuel channel formed in that combustion chamber exterior wall and receives fuel through a fuel opening that interfaces the fuel channel and tap-off opening. The tap-off manifold nests within a fuel manifold for thermal management. The fuel channel directs fuel into the combustion chamber through fuel port openings formed in the combustion chamber, the fuel port openings located closer to a headend of the combustion chamber than the tap-off openings.

A liquid rocket engine integrates tap-off openings at a combustion chamber wall to direct exhaust from the combustion chamber to a tap-off manifold that provides the exhaust to one or more auxiliary systems, such as a turbopump that pumps oxygen and/or fuel into the combustion chamber. The tap-off opening passes through a fuel channel formed in that combustion chamber exterior wall and receives fuel through a fuel opening that interfaces the fuel channel and tap-off opening. The tap-off manifold nests within a fuel manifold for thermal management. The fuel channel directs fuel into the combustion chamber through fuel port openings formed in the combustion chamber, the fuel port openings located closer to a headend of the combustion chamber than the tap-off openings.

A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.

A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.