A coating for a blade root/disk interface includes a layer of soft metal matrix, and a solid lubricant distributed through the soft metal matrix. Examples of materials include CuAl as the soft metal matrix and MoS.sub.2 as the solid lubricant, although others are also disclosed.

A thrust chamber liner for a rocket engine includes a main combustion chamber (MCC) and a nozzle. A composite wrap covers the outside surface of the MCC and the outside surface of the nozzle.

A thrust chamber liner includes a main combustion chamber (MCC) with MCC coolant channels extending axially there along. Each MCC coolant channel has a port at an outside surface of the MCC. A nozzle is integrated with the MCC. The nozzle has nozzle coolant channels extending axially there along. A coolant-supply manifold, integrated with one of the MCC and the MCC and nozzle, is in fluid communication with each port in the MCC coolant channels.

The present invention relates to a method for producing a component of a composite material comprising a metal matrix and incorporated intermetallic phases, which method comprises providing powders of at least one member of the group which comprises pure chemical elements, alloys, chemical compounds and material composites, the powder corresponding overall to the chemical composition which the composite material to be produced is intended to have, each individual powder being different to the chemical composition of the composite material to be produced, compacting the powders, bonding the powders to one another to form a unit and thermoplastically shaping the unit.

A rocket engine combustion chamber (1) extending along a longitudinal axis A may have a longitudinal envelope, the longitudinal envelope having a longitudinal inner wall (10) made of a first alloy, which is a copper alloy, and that is extended over its radially outer face (15) by a plurality of fins (20) extending radially outwards, each of the fins presenting a proximal portion (22), a middle portion (25), and a distal portion (28), and having an outer shell (30) surrounding the inner wall (10) and the fins (20), the shell (30) being made of a third alloy distinct from the first alloy. The proximal portion (22) is made of the first alloy, and the distal portion (28) is made of a second alloy that is an alloy distinct from the first alloy.

The present invention discloses an elastic sheet used for a turbine follow-up suspended steam seal belt and a steam seal structure thereof, which comprises a plurality of elastic L-shaped metal sheets correspondingly overlapped on the same rim, one rim of the L-shaped metal sheet is a toothed rim, the toothed notches of the toothed rim extend laterally through the entire toothed rim so that the other rim of the L-shaped metal sheet can be bent longitudinally toward the toothed rim to form an arc shape; the toothed notches and the toothed tabs of the toothed rims of the plurality of L-shaped metal sheets are misoriented with each other to cover the toothed notches, and the other rim of the L-shaped metal sheet is fixed within the arc-shaped steam seal ring block along the steam seal ring teeth, the steam seal ring teeth extend out from the top of the toothed rim to seal the gap between the seal ring teeth and the turbine main shaft, and the toothed rims of the L-shaped metal sheet perform elastic beating reciprocately down after being subjected to the force at the top; the invention has the advantages of simple structure and the sealing of the main shaft side is well achieved; and the main shaft of the turbine can be completely achieved by utilizing the elastic characteristics of the seal elastic sheet of the invention.

A method of applying a nanocrystalline metal coating to a titanium or titanium alloy blade of a gas turbine engine is described. The method includes selecting an intermediate bond coat from the group consisting of nickel, nickel alloy, P, B, Tl and combinations thereof, and applying the intermediate bond coat to at least a portion of the blade. A nanocrystalline metal coating having an average grain size of between 10 nm and 500 nm is then applied to the portion of the blade overtop of the intermediate bond coat.

A gas turbine engine includes an inlet duct, a compressor section, a combustor section, and a turbine section connected to drive the compressor section. The compressor section includes circumferentially-spaced blades having abrasive blade tips. A seal is disposed radially outwards of the blades. The seal includes a substrate that has a substrate hardness, an abradable layer that has an abradable layer hardness, and a hard interlayer between the substrate and the abradable layer. The hard interlayer has an interlayer hardness that is higher than the abradable layer hardness and higher than the substrate hardness.

A rotor shaft for a high speed motor that has a coating that is secured to a shaft body. The coating and the shaft body are formed from dissimilar materials. More specifically, the coating may be an alloy material, such as, for example, a copper alloy, while the shaft body may be a steel material. According to certain embodiments, the alloy material of the coating may be secured to at least a portion of a rotor body blank in a solution treated condition via a low temperature welding procedure. Additionally, the coating may be hardened, such as for example, through the use of an age hardening process. The coating and the rotor body blank may be machined together to form the rotor shaft. According to certain embodiments, such machining may configure the rotor shaft for use with a turbo-compressor that is configured for air compression.

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.