257results about How to "Reduce coating" patented technology

The present invention provides instrumentation that facilitates access to both sides of the vertebral body from a single access point. More particularly, the present invention provides bendable access devices that can be steered so as to traverse the vertebral body from the point of entry into the vertebral body, through the cancellous bone within the vertebral body, and to the contralateral side of the vertebral body. This steerability is provided by forming the access device with a series of slots, grooves, or notches in the side of the access device near the distal end of the access device, which slots, grooves, or notches reduce the bending stiffness of the access device. As a result, the distal end of the access device bends as it is being advanced into the vertebral body.

A hybrid power driving system for a vehicle comprises an internal-combustion engine, a first electric motor, a second electric motor, a planetary coupling mechanism, a speed-reduction mechanism and a differential mechanism. An output shaft of the internal-combustion engine is connected with an input shaft of the first electric motor, and an output shaft of the first electric motor is connected with an output shaft of the second electric motor via a first clutch. The output shaft of the second electric motor is connected with one of a sun gear and a ring gear of the planetary coupling mechanism at a position of the output shaft along its axial direction. And the output shaft of the second electric motor is connected with the other one of a sun gear and a ring gear at another position of the output shaft along the axial direction via a second clutch.

According to an embodiment of the invention, a method for repairing a coated high pressure turbine blade, which has been exposed to engine operation, to restore coated airfoil contour dimensions of the blade, and improve upon the prior bond coat is disclosed. The method comprises providing an engine run high pressure turbine blade including a base metal substrate made of a nickel-based alloy and having thereon a thermal barrier coating system. The thermal barrier coating system comprises a diffusion bond coat on the base metal substrate and a top ceramic thermal barrier coating comprising a yttria stabilized zirconia material. The top ceramic thermal barrier coating has a nominal thickness t. The method further comprises removing the thermal barrier coating system, wherein a portion of the base metal substrate also is removed, and determining the thickness of the base metal substrate removed. The portion of the base metal substrate removed has a thickness, Δt. The method also comprises applying a β phase NiAl overlay coating to the substrate, and determining the difference in thickness, Δx, between the β phase NiAl overlay coating and the previously removed bond coat. The method further comprises reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt−Δx, wherein Δt compensates for the portion of removed base metal substrate. Advantageously, the coated airfoil contour dimensions of the high pressure turbine blade are restored to about the coated dimensions preceding the engine run.

Negative-working imageable elements are prepared with radiation-sensitive imageable layers that contain surface-modified silica particles such as fumed silica particles and sol-gel silica particles, that are present in an amount of from about 1 to about 40 weight %, have an average particle size of from about 1 to about 500 nm, have surface hydroxy groups, and have a carbon content of from about 0.5 to about 15 weight % that is derived from surface hydrophobic groups having 1 to 30 carbon atoms. The presence of the surface-modified silica particles provides improved abrasion resistance, reduced tackiness, and various other desired properties.

The invention provides a turbocharger with a divided turbine housing and an annular rotary bypass valve for a turbine. The turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a divided volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines a pair of concentric annular bypass passages surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel as two separate bypass streams. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.