An abradable powder composition is includes a metal component, a lubricant component, and a polymer component. A portion of the metal component is wrapped in the lubricant component to achieve high lubricity and abradability. The abradable powder composition can be used to form an abradable seal coating provided for use in a turbo machinery having a housing and a wheel having multiple blades. The housing houses the wheel which rotates therein. The seal coating is formed on the inner walls of housing adjacent where the wheel blades pass during their rotation. When the wheel is rotated such that the blades contact the seal coating, it is abraded to form a close fit gap. The abradable seal coating preferably does not produce significant wear of the blade tips or transfer abradable material significantly to the blade tips upon being abraded.

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 compressor housing for a turbocharger, which is composed of a scroll piece, a shroud piece, and an outer-circumferential annular piece. The scroll piece includes a through part constituting a discharge port, a first intermediate wall surface extended from an intake-side wall surface of a scroll chamber and smoothly connected with the discharge port, and a scroll outer-circumferential part. The outer-circumferential annular piece includes an outer-circumferential annular press-fit part press fitted into the scroll outer-circumferential part, and a protruding part bent from an outer-circumference-side wall surface of the scroll chamber. The protruding part is inserted into the through part to form an inner wall surface of an intermediate part that communicates the discharge port with the scroll chamber. Then, the compressor housing is fixed to a center housing that is made of iron with high rigidity through joining parts provided at the scroll piece.

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.

An assembly is provided for a turbine engine with a flowpath. This assembly includes a fuel source and an engine component. The engine component forms a peripheral boundary of the flowpath. The engine component includes a component internal passage. The engine component is configured to receive fuel from the fuel source. The engine component is configured to crack at least some of the fuel within the component internal passage thereby cooling the engine component and providing at least partially cracked fuel. The assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion.

A rocket engine has a combustion chamber having an inlet and an outlet, the inlet fluidly connectable to a source of oxidizer, the outlet in fluid communication with an environment outside the combustion chamber for expelling combustion gases, a first fuel having a first solid propellant and a second fuel having a second solid propellant, the first and second fuels located within the combustion chamber and configured to be exposed to the oxidizer injected in the combustion chamber via the inlet, the first solid propellant having a regression rate greater than that of the second solid propellant.

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.

An engine turning clock work motor including two shape memory alloy (SMA) torque tube actuators, ratcheting mechanisms, and gearing. The gearing communicates the SMA torque tube actuators with a common gear that applies torque to a shaft, so that while one torque tube is heated and applying torque, the other torque tube is relaxed (using a cooling mechanism). The ratchet prevents the relaxing torque tube from applying torque in the incorrect direction.

A system for airfoil vibration control is generally provided. The system includes an airfoil including a ferromagnetic material, and a static structure including an electromagnet adjacent to the ferromagnetic material of the airfoil. A method for controlling vibration at an airfoil of a turbo machine is further provided. The method includes placing a ferromagnetic material at the airfoil, placing an electromagnet at a static structure adjacent to the ferromagnetic material at the airfoil, and applying an electromagnetic force to the ferromagnetic material at the airfoil via the electromagnet at the static structure.

A nickel- and chrome-rich highly heat-resistant, austenitic iron based alloy. The alloy exhibits an improved fine dendritic carbide structure and can withstand repeated thermal elongation and strain which is particularly important for an exhaust-gas turbocharger component exposed to exhaust gas flow, such as a turbine housing. The alloy also guarantees very good thermo-mechanical fatigue (TMF) loading performance. A thermal cracking problem of the component is significantly reduced. The alloy is influenced by the relationship between the elements nickel, niobium, cerium and vanadium. The invention further concerns a method for prevention of crack formation and for minimizing oxidization in a turbocharger turbine housing.