Aspects of the disclosure are directed to a system comprising: a rotatable seal runner, a stationary sealing member that includes a base and a nose that extends from the base in an axial direction and interfaces with the seal runner, a carrier that supports the sealing member, and a tab coupled to the carrier, where the tab extends from the carrier in the axial direction towards the seal runner.

A rocket engine has: a combustion chamber having a chamber inlet for receiving an oxidizer and a chamber outlet for expelling combustion gases in an environment outside the combustion chamber; a manifold having a manifold inlet fluidly connectable to a source of the oxidizer and a manifold outlet; a catalyst having a catalyst inlet fluidly connected to the manifold outlet and a catalyst outlet; and an injector plate having a injector inlet fluidly connected to the catalyst outlet and an injector outlet fluidly connected to the chamber inlet.

A repaired oxidation and corrosion resistant coating may comprise a repair material applied to a damaged portion of the oxidation and corrosion resistant coating. The repair material may be free of hexavalent chromium and may be compatible with a plurality of oxidation and corrosion resistant materials that comprise hexavalent chromium. The repair material may be burnished. The oxidation and corrosion resistant coating may comprise hexavalent chromium.

A magnetic impeller for a blood pump such as a magnetically driven, rotary ventricular assist device for pumping blood of a patient, the impeller comprising a magnetic alloy including platinum, cobalt, and boron.

An erosion resistant material has a continuous portion and discontinuous portions. The continuous portion has a continuous structure. The discontinuous portions are arranged inside the continuous portion to have a discontinuous structure. The discontinuous portions are formed of particles having an average particle diameter of 1 m or less. Further, the discontinuous portions are formed of a material having a surface hardness and a Young's modulus higher than those of the continuous portion.

An abrasive sheath for application to a component surface is disclosed. The abrasive sheath may comprise a metallic layer and an abrasive layer plated on a surface of the metallic layer. The abrasive layer may include a metal matrix and abrasive particles protruding from the matrix. An exposed surface of the metallic layer of the abrasive sheath may be joinable to the component surface by a heat treatment.

A hybrid rocket engine system has: an oxidizer tank containing a liquid oxidizer; a rocket engine having a combustion chamber operatively connected to the oxidizer tank; a solid propellant fuel within the combustion chamber; a nozzle fluidly connected to the combustion chamber, the nozzle having a convergent section and a divergent section downstream of the convergent section; and a thrust vector control device operatively connected to the divergent section of the nozzle and operable to inject a fluid through at least one aperture defined through the divergent section for controlling a direction of a thrust generated by the rocket engine.

The precipitation hardened martensitic stainless steel is characterized by containing, in percent by weight, 12.25 to 14.25% Cr, 7.5 to 8.5% Ni, 1.0 to 2.5% Mo, 0.05% or less C, 0.2% or less Si, 0.4% or less Mn, 0.03% or less P, 0.005% or less S, 0.008% or less N, 0.90 to 2.25% Al, the balance substantially being Fe, and the total content of Cr and Mo being 14.25 to 16.75%. A turbine moving blade and a steam turbine are manufactured by using this martensitic stainless steel.

A turbo-molecular pump comprises: a case having a suction port and a flange; a rotor assembly housed inside the case, the rotor assembly having a shaft and a rotor integrated with the shaft with a fastening bolt, the rotor having a plurality of rotor blades formed thereon; a plurality of stator blades housed inside the case and arranged to face the rotor blades; and a plurality of spacers stacked along a peripheral surface of the case, the spacer fixing the stator blades. An anti-corrosion treatment is applied to a gas contacting section in a component that is provided on an evacuation upstream side with respect to an evacuation downstream side end of the first rotor blade from the evacuation upstream side and made of an alloy containing Fe or Cr.

A hybrid rocket engine system has: an oxidizer tank containing a liquid oxidizer; a rocket engine having a combustion chamber operatively connected to the oxidizer tank; a solid propellant fuel within the combustion chamber; a nozzle fluidly connected to the combustion chamber, the nozzle having a convergent section and a divergent section downstream of the convergent section; and a thrust vector control device operatively connected to the divergent section of the nozzle and operable to inject a fluid through at least one aperture defined through the divergent section for controlling a direction of a thrust generated by the rocket engine.