The present invention relates to a boltless bonnet assembly for use in a blowout preventer (BOP). In some embodiments, the boltless bonnet assembly includes a bonnet having a forward end facing a ram body of the BOP stack, and a bonnet latch disposed within the bonnet, the bonnet latch attached to the forward end of the bonnet. The boltless bonnet assembly further includes a bonnet positioning mechanism in communication with the bonnet latch to move the bonnet latch into and out of engagement with the ram body.

A tool for manipulating flexible and non-flexible fastening devices. The tool assembly has a flexible rod for insertion into the distal end of the fastening device. A handle assembly interacts with proximal end of the flexible rod and the proximal end of the fastening device to control of the fastening device by initiating rotation at the distal end of the fastening device.

A tool for manipulating flexible and non-flexible fastening devices. The tool assembly has a flexible rod for insertion into the distal end of the fastening device. A handle assembly interacts with proximal end of the flexible rod and the proximal end of the fastening device to control of the fastening device by initiating rotation at the distal end of the fastening device.

Provided is a black coupling member for vehicles, comprising a trivalent chromium black chemical conversion film and a black coating film upon the trivalent chromium black chemical conversion film, on the surface of a zinc-plated metal substrate. The trivalent chromium black chemical conversion film is formed using a hexavalent chromium-free trivalent chromium black chemical conversion treatment solution having a Zn ion concentration of no more than 20 g/L. The lightness (L) of the trivalent chromium black chemical conversion film is no more than 33. The black coating film includes a black chemical conversion component, a modified organopolysiloxane, and a friction coefficient-adjustment component. The black chemical conversion component content is 2-25 wt % relative to 100 wt % of the black coating film. The lightness (L) is no more than 28.

Provided is a black coupling member for vehicles, comprising a trivalent chromium black chemical conversion film and a black coating film upon the trivalent chromium black chemical conversion film, on the surface of a zinc-plated metal substrate. The trivalent chromium black chemical conversion film is formed using a hexavalent chromium-free trivalent chromium black chemical conversion treatment solution having a Zn ion concentration of no more than 20 g/L. The lightness (L) of the trivalent chromium black chemical conversion film is no more than 33. The black coating film includes a black chemical conversion component, a modified organopolysiloxane, and a friction coefficient-adjustment component. The black chemical conversion component content is 2-25 wt % relative to 100 wt % of the black coating film. The lightness (L) is no more than 28.

Steel for a high-strength bolt contains: from 0.50 mass % to 0.65 mass % carbon, from 1.5 mass % to 2.5 mass % silicon, 1.0 mass % or more chromium, 0.4 mass % or less manganese, greater than 1.5 mass % molybdenum, 0.03 mass % or less phosphorus and sulfur combined, and balance iron and inevitable impurities.

A high-strength bolt is formed using steel for a high-strength bolt that contains: from 0.50 mass % to 0.65 mass % carbon, from 1.5 mass % to 2.5 mass % silicon, 1.0 mass % or more chromium, 0.4 mass % or less manganese, greater than 1.5 mass % molybdenum, 0.03 mass % or less phosphorus and sulfur combined, and balance iron and inevitable impurities.

An assembly for a turbomachine turbine includes at least one ring sector made of CMC material and a support casing including an upstream flange and a downstream flange between which each ring sector is disposed, each ring sector including a base that has a radially external face from which radially extend two lugs, the lugs of each ring sector being retained between the two flanges of the support casing by axial pins each engaged in one of the flanges of the ring support casing and in the lug of the ring sector facing said flange, the assembly further including, for each ring sector, at least one radial retaining pin screwed into the support casing and coming to radially bear against a lug of the at least one ring sector to retain it in position, and anti-rotation system for rotationally locking the radial retaining pin.

An assembly for a turbomachine turbine includes at least one ring sector made of CMC material and a support casing including an upstream flange and a downstream flange between which each ring sector is disposed, each ring sector including a base that has a radially external face from which radially extend two lugs, the lugs of each ring sector being retained between the two flanges of the support casing by axial pins each engaged in one of the flanges of the ring support casing and in the lug of the ring sector facing said flange, the assembly further including, for each ring sector, at least one radial retaining pin screwed into the support casing and coming to radially bear against a lug of the at least one ring sector to retain it in position, and anti-rotation system for rotationally locking the radial retaining pin.

A hollow screw and related process of making is provided, wherein the hollow screw is formed from a generally circular corrosion resistant stainless steel disk cut from flat roll stock. The hollow screw includes a head and an elongated and hollow shaft having a wall thickness between about 0.2 to about 0.7 millimeters extending therefrom and defining a shank portion and a threaded portion having a plurality of threads thereon with a rotational drive mechanism configured to facilitate tightening via the threads. The process involves annealing to soften the stamped hollow screw, followed by thread rolling, and then age hardening the hollow screw. As such, the resultant hollow screw is relatively lightweight, about 50% the mass of a solid core screw made from the same material, with a sufficient thread strength to meet most aerospace applications and contributes to important aircraft fuel economy.

Provided in the context of a bolt is a method for achieving antiloosening capability such as will make it possible for tightening operations to be carried out easily and rapidly, and such as will make it possible to obtain antiloosening effect in robust and reliable fashion. Comprised, in such form as if a single bolt had been cut into two perpendicularly with respect to an axis thereof at a location midway along the axis thereof, of first bolt 11 having a bolt head and second bolt 12 having a threaded tip; second bolt 12 being such that an eccentric columnar portion 123 which is smaller in diameter than a diameter of the shaft of the second bolt 12 is provided at cutting plane 122 in such fashion as to protrude outward in an axial direction in eccentric fashion with respect to a direction perpendicular to a central axis, and such that side face protrusion 124 is formed at an outside circumferential side face of eccentric columnar portion 123; first bolt 11 being such that eccentric cylindrical portion 113 that mates with eccentric columnar portion 123 is formed at cutting plane 112 in eccentric fashion with respect to a direction perpendicular to a central axis, axial groove 114 being formed in a direction parallel to the central axis and radial groove 115 being formed in a radial direction at the interior thereof; the entirety constituting locking bolt 1.