Abstract: A device for preventing suck back of oral secretions into air-driven dental handpiece when the air-driven dental handpiece is stopped. The device includes a high-pressure valve to close a high-pressure inlet port and a low-pressure valve to close a low-pressure inlet port or an exhaust air outlet. The device further includes an actuating member that closes the high-pressure valve. High pressure air of the air-driven dental handpiece can push back the high-pressure valve to open state. The low-pressure valve is coupled to the high-pressure and moves with it. A compression member interrupts the low-pressure valve and the high-pressure valve, wherein the compression member causes the low-pressure valve to close first while allowing the high-pressure valve to keep moving further to close the first path with a time delay.

Abstract: According to an embodiment of the present disclosure, a thin film forming apparatus includes a chamber, a plurality of gas inlets that are formed at an upper portion of the chamber and receive at least two reaction gas and precursors for radical reaction, and a radical unit configured to generate radicals by reacting the reaction gas provided through the gas inlet and deposit a thin film on a substrate by spraying the radicals and the precursors downward. The radical unit is configured with a plurality of plates, a precursor spray path is configured to be sprayed from the radical unit after the precursors are sprayed to a plurality of paths greater than precursor spray paths of the gas inlet in an uppermost plate among the plurality of plates, and a reaction gas spray path is configured not to overlap with the precursor spray path.

Abstract: Disclosed is a power generating system for a rotatory dental apparatus that can power the illumination source. The rotatory dental apparatus includes a supply hose having a hose connector at its one end. A swivel coupling connects the hose connector to the dental handpiece. The power generating system can be configured in the hose supply. In one case, the power generating system can be installed in the hose connector of the hose supply. In one case, the power generating system can be interposed between the two sections of the hose supply. In one case, the power generating system can be installed in a hose coupling that is interposed between the swivel coupling and the hose connector.

Abstract: Disclosed is a power generating system for a rotatory dental apparatus that can power the illumination source. The rotatory dental apparatus includes a supply hose having a hose connector at its one end. A swivel coupling connects the hose connector to the dental handpiece. The power generating system can be configured in the hose supply. In one case, the power generating system can be installed in the hose connector of the hose supply. In one case, the power generating system can be interposed between the two sections of the hose supply. In one case, the power generating system can be installed in a hose coupling that is interposed between the swivel coupling and the hose connector.

Abstract: A pressure capture canister is disclosed. The pressure capture canister includes a body, a cap, and a seal. The cap and the seal are positioned within the body and are arranged to allow fluid communication from outside of the pressure capture canister to within the body. The seal can be selected to melt or soften at a temperature threshold.

Abstract: According to an embodiment of the present disclosure, a thin film forming apparatus includes a chamber, a plurality of gas inlets that are formed at an upper portion of the chamber and receive at least two reaction gas and precursors for radical reaction, and a radical unit configured to generate radicals by reacting the reaction gas provided through the gas inlet and deposit a thin film on a substrate by spraying the radicals and the precursors downward. The radical unit is configured with a plurality of plates, a precursor spray path is configured to be sprayed from the radical unit after the precursors are sprayed to a plurality of paths greater than precursor spray paths of the gas inlet in an uppermost plate among the plurality of plates, and a reaction gas spray path is configured not to overlap with the precursor spray path.

Abstract: Disclosed is a power generating system for a rotatory dental apparatus that can power the illumination source. The rotatory dental apparatus includes a supply hose having a hose connector at its one end. A swivel coupling connects the hose connector to the dental handpiece. The power generating system can be configured in the hose supply. In one case, the power generating system can be installed in the hose connector of the hose supply. In one case, the power generating system can be interposed between the two sections of the hose supply. In one case, the power generating system can be installed in a hose coupling that is interposed between the swivel coupling and the hose connector.

Abstract: An insert tube of a turbine vane is disclosed. The insert tube includes a pressure side wall, a suction side wall opposite and spaced apart from the pressure side wall, a leading edge, and a trailing edge opposite the leading edge. The insert tube includes a plurality of cooling channels spaced along the pressure side wall. The insert tube includes an indented portion located between the trailing edge and the pressure side wall.

Abstract: A grommet for a combustor of a gas turbine engine is disclosed. The grommet includes a lower platform and a raised platform. The lower platform includes a plurality of top slots located in the top surface and a plurality of bottom slots located in the bottom surface. Each top slot and bottom slot may extend radially along the lower platform. The plurality of top slots may be spaced equidistantly from one another along the circumference of the lower platform. The plurality of bottom slots may be spaced equidistantly from one another along the circumference of the lower platform.

Abstract: A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between. The turbine stage also includes an exit flow discourager comprised of at least two teeth. The teeth may be located radially apart from each other, each tooth including a length extending in the axial direction and a width extending in the radial direction. A channel is formed between the teeth and an axially adjacent surface. A recirculation region may be formed in between each pair of teeth.

Abstract: A grommet for a combustor of a gas turbine engine is disclosed. The grommet includes a lower platform and a raised platform. The lower platform includes a plurality of top slots located in the top surface and a plurality of bottom slots located in the bottom surface. Each top slot and bottom slot may extend radially along the lower platform. The plurality of top slots may be spaced equidistantly from one another along the circumference of the lower platform. The plurality of bottom slots may be spaced equidistantly from one another along the circumference of the lower platform.

Abstract: A nozzle segment for a turbine nozzle of a gas turbine engine is disclosed. The nozzle segment includes an upper endwall, a lower endwall spaced apart from the upper endwall, a pressure portion, and a suction portion. The pressure portion extends between the upper endwall and the lower endwall adjacent a first side of the nozzle segment. The suction portion is spaced apart from the pressure portion and extends between the upper endwall and the lower endwall adjacent a second side of the nozzle segment. The second side is opposite the first side.

Abstract: An insert tube of a turbine vane is disclosed. The insert tube includes a pressure side wall, a suction side wall opposite and spaced apart from the pressure side wall, a leading edge, and a trailing edge opposite the leading edge. The insert tube includes a plurality of cooling channels spaced along the pressure side wall. The insert tube includes an indented portion located between the trailing edge and the pressure side wall.

Abstract: An apparatus for measuring temperature parameters of a structure is provided. The apparatus comprises: a carrier including at least one receiving portion; and a plurality of temperature sensors disposed within the at least one receiving portion and secured to the receiving portion via a bonding medium, the sensors being distributed along at least one direction of the carrier and configured to measure and record temperature information through microstructural changes corresponding to temperatures experienced by the respective sensors.

Abstract: A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between. The turbine stage also includes an exit flow discourager comprised of at least two teeth. The teeth may be located radially apart from each other, each tooth including a length extending in the axial direction and a width extending in the radial direction. A channel is formed between the teeth and an axially adjacent surface. A recirculation region may be formed in between each pair of teeth.

Abstract: A heat shield for a combustion chamber of a gas turbine engine is disclosed. The heat shield includes a plate portion, an inner ring, and a plurality of standoffs. The plate portion includes an annular sector shape. The inner ring extends from an inner part of the plate portion. The inner ring includes a hollow cylinder shape. The plurality of standoffs extends from the plate portion, proximate outer edges of the plate portion and in the same direction as the inner ring. The plurality of standoffs forms a plurality of scallops. Each scallop is located between adjacent standoffs.

Abstract: The present disclosure describes a turbine blade for a turbine section of a gas turbine engine. The turbine blade includes an airfoil, a platform extending from one side of the airfoil, a root extending from the platform, and at least one purging fin. The at least one purging fin is connected to the root and an underside of the platform, and the at least one purging fin extends along a wall of the root.

Abstract: A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper may have a forward plate. The damper may further have an aft plate including a larger surface area than the forward plate. The aft plate may have at least one aperture for regulating a flow of gas through the aft plate. The damper may also have a longitudinal structure connecting the forward plate and the aft plate.

Abstract: A turbine blade of a gas turbine engine is disclosed. The blade may comprise a first cooling passage and a second cooling passage, where the second cooling passage may be located adjacent a leading edge of the blade. The blade may further comprise at least one slot formed in a partition disposed between the first and second cooling passages, and at least one turbulator disposed within the second passage and downstream the at least one slot.

Abstract: An apparatus for measuring temperature parameters of a structure is provided. The apparatus comprises: a carrier including at least one receiving portion; and a plurality of temperature sensors disposed within the at least one receiving portion and secured to the receiving portion via a bonding medium, the sensors being distributed along at least one direction of the carrier and configured to measure and record temperature information through microstructural changes corresponding to temperatures experienced by the respective sensors.