The present disclosure relates to a rocket engine, and more particularly, a rocket engine with an integrated combustor head and turbopump in which a turbopump of the rocket engine is formed integrally with a combustor head.

Provided is a canned motor in which vaporization of the handling liquid is reduced in a case where a rotor rotates at high speed. A canned motor 10 includes a stator 18 disposed in a stator chamber 26, a rotor 14 disposed in a rotor chamber 12, and a stator can 7 enclosing the rotor 14. Furthermore, the canned motor 10 includes a stator chamber inlet portion 43 configured such that a cooling liquid for cooling the stator 18 flows into the stator chamber 26, and a stator chamber outlet portion 44 configured such that the cooling liquid flows out from the stator chamber 26.

Provided is a canned motor in which vaporization of the handling liquid is reduced in a case where a rotor rotates at high speed. A canned motor 10 includes a stator 18 disposed in a stator chamber 26, a rotor 14 disposed in a rotor chamber 12, and a stator can 7 enclosing the rotor 14. Furthermore, the canned motor 10 includes a stator chamber inlet portion 43 configured such that a cooling liquid for cooling the stator 18 flows into the stator chamber 26, and a stator chamber outlet portion 44 configured such that the cooling liquid flows out from the stator chamber 26.

An example turbo-pump for a rocket is provided. The example turbo-pump includes a turbine. A first chamber, coupled to the turbine, receives oxidizer fluid resulting in the oxidizer fluid leaving the first chamber at a faster rate to a reaction chamber. A select amount of the oxidizer fluid enters the turbine. A second chamber, coupled to the turbine, receives fuel resulting in the fuel leaving the second chamber at a faster rate to the reaction chamber. A select amount of the fuel enters the turbine. A plurality of pipes is positioned around the turbine. The plurality of pipes is configured to distribute cooling fluid around the turbine to lower the kinetic energy of the select amount of the fuel and the oxidizer fluid within the turbine.

An example turbo-pump for a rocket is provided. The example turbo-pump includes a turbine. A first chamber, coupled to the turbine, receives oxidizer fluid resulting in the oxidizer fluid leaving the first chamber at a faster rate to a reaction chamber. A select amount of the oxidizer fluid enters the turbine. A second chamber, coupled to the turbine, receives fuel resulting in the fuel leaving the second chamber at a faster rate to the reaction chamber. A select amount of the fuel enters the turbine. A plurality of pipes is positioned around the turbine. The plurality of pipes is configured to distribute cooling fluid around the turbine to lower the kinetic energy of the select amount of the fuel and the oxidizer fluid within the turbine.

Provided is an electric motor-integrated rocket engine pump. The electric motor-integrated rocket engine pump comprises: a housing; a rotating body provided in one direction inside the housing; an electric motor provided inside the housing, and integrally shaft-coupled to the rotating body; and a plurality of fluid bearings are mounted on front and rear rotating bodies of the electric motor to support rotation of the rotating body.

Provided is an electric motor-integrated rocket engine pump. The electric motor-integrated rocket engine pump comprises: a housing; a rotating body provided in one direction inside the housing; an electric motor provided inside the housing, and integrally shaft-coupled to the rotating body; and a plurality of fluid bearings are mounted on front and rear rotating bodies of the electric motor to support rotation of the rotating body.

A sealing device includes a plurality of non-contact seals provided along a sealed shaft; a contact seal provided on at least one of two sides of the plurality of non-contact seals; an injection part that supplies purge gas into a first space of spaces arranged in an axial direction of the sealed shaft, the spaces being between the plurality of non-contact seals and the contact seal; and a collector that collects the purge gas from a second space of the spaces between the plurality of non-contact seals and the contact seal, the second space being positioned to be next to the first space in the axial direction.

Apparatus and associated methods relate to an in-space propulsion system configured to generate propulsion from a recirculated working fluid. In an illustrative example, the propulsion system may include a boiler configured to generate high pressure gas from the working fluid. The gas may, for example, be ejected from a nozzle into a distributor tube. A radiator coupled to the distributor tube may, for example, facilitate phase transition of the gas back into the working fluid. The fluid may be collected via one or more collection ducts coupled to the radiator. One or more pumps may recirculate the working fluid from the one or more collection ducts back into the boiler. Various embodiments may advantageously recirculate the working fluid such that propulsion is generated in response to an external power source while substantially an entire mass of the working fluid is preserved in the propulsion system.

Apparatus and associated methods relate to an in-space propulsion system configured to generate propulsion from a recirculated working fluid. In an illustrative example, the propulsion system may include a boiler configured to generate high pressure gas from the working fluid. The gas may, for example, be ejected from a nozzle into a distributor tube. A radiator coupled to the distributor tube may, for example, facilitate phase transition of the gas back into the working fluid. The fluid may be collected via one or more collection ducts coupled to the radiator. One or more pumps may recirculate the working fluid from the one or more collection ducts back into the boiler. Various embodiments may advantageously recirculate the working fluid such that propulsion is generated in response to an external power source while substantially an entire mass of the working fluid is preserved in the propulsion system.