Abstract: An airfoil for an internal combustion engine, such as a gas turbine, formed by use of a preform. The airfoil includes: an outer surface forming the foil shape; and a plurality of craze-free cooling passages extending through the airfoil. In the preferred embodiment, a root on the airfoil joins the airfoil to the hub of a gas turbine vane assembly. Also, in the preferred embodiment, the gas turbine vane assembly is adapted to receive replaceable airfoils.

Abstract: The invention relates to an axial compressor disk for a turbomachine, the disk including a bleed system for bleeding air centripetally from the compressor stream in order to cool a turbine, said bleed system comprising channels formed outside the working section of the disk and parallel to said section in an extra thickness projecting away from said working section on a face of said disk, wherein the bleed channels are axially open over substantially their entire radial extent.

Abstract: A turbine bucket and cover assembly includes a bucket having a shank portion and an airfoil portion separated by a platform portion; and a bucket cover arranged on a sloped radially outer tip of the airfoil portion, the bucket cover having a radially inner surface matching the sloped edge and a radially outer surface lying in a plane parallel to a longitudinal axis of a rotor on which the bucket is adapted to be mounted. A related method includes the steps of a) providing a bucket cover having substantially parallel radially inner and outer surface; b) removing material from the bucket cover so as to form a new radially outer surface defining an acute angle relative to the radially inner surface; and c) securing the bucket cover on the sloped airfoil tip of the turbine bucket such that the radially outer surface is substantially parallel to the turbine rotor axis.

Abstract: The present invention is to provide a mechanism for fast fastening fans of a server, comprising a fastening frame of hollow parallelepiped shape having at least one divider for dividing an internal space thereof into a plurality of compartments, each compartment being adapted to fasten a fan therein; a plurality of first fastening members each disposed inside the compartment perpendicular to the divider and having a positioning groove abutted on the divider; and a plurality of second fastening member disposed on a housing of the server and being adapted to the corresponding first fastening members so that the fastening frame along with the fans can be assembled to or detached from housing quickly, resulting in an increase of the assembly and maintenance efficiency.

Abstract: A snubber inner member has a doubly convex outer surface portion having a central longitudinal axis. A shim/spacer stack secured to the outer surface portion couples the snubber inner member to the second member. A retainer having one or more engagement surfaces cooperates with one or more engagement surfaces of the snubber inner member to constrain lateral movement of the snubber inner member relative to the retainer while permitting longitudinal movement of the snubber inner member away from the retainer. An elastomer secures the retainer to the first member.

Abstract: A blower having a discharge tube, which can be secured to a housing, for guiding a stream of air is provided. The air stream flows in a main stream direction in the discharge tube and in a discharge stream direction out of the discharge tube. The discharge stream direction forms an angle of greater than 0° with the main stream direction. The discharge stream direction has a transverse component that extends perpendicular to the main stream direction, which produces a force in the discharge tube perpendicular to the main stream direction. To reduce the transverse force produced in the discharge tube, a partial air stream is branched off out of the discharge tube and flows in a partial stream direction that has a compensation component that is directed opposite to the transverse component.

Abstract: An installation comprising a turbine equipped with a wheel rotatable about an axis (X-X′), and a tank feeding the turbine. The feed tank having, projecting on a plane globally perpendicular to the axis (X-X′), an external spiral shape. The feed tank forms a helico-convergent duct centered on the axis (X-X′) and convergent towards the turbine. The duct is bordered by an outer partition, an inner partition and at least an intermediate partition contributing to the reinforcement of the tank.

Abstract: A turbine blade includes a hollow airfoil integrally joined to a dovetail. The airfoil includes a perforate first bridge defining a flow channel behind the airfoil leading edge. A second bridge is spaced behind the first bridge and extends from a pressure sidewall of the airfoil short of the airfoil trailing edge. A third bridge has opposite ends joined to the pressure sidewall and the second bridge to define with the first bridge a supply channel for the leading edge channel, and defines with the second bridge a louver channel extending aft along the second bridge to its distal end at the pressure sidewall.

Abstract: A self-tuning impact damper is disclosed that absorbs and dissipates vibration energy in the blades of rotors in compressors and/or turbines thereby dramatically extending their service life and operational readiness. The self-tuning impact damper uses the rotor speed to tune the resonant frequency of a rattling mass to an engine order excitation frequency. The rattling mass dissipates energy through collisions between the rattling mass and the walls of a cavity of the self-tuning impact damper, as well as through friction between the rattling mass and the base of the cavity. In one embodiment, the self-tuning impact damper has a ball-in-trough configuration with tire ball serving as the rattling mass.

Abstract: A gas turbine engine 10 includes an intermediate pressure compressor 14 connected to an intermediate pressure turbine 22 by a driveshaft 28. The driveshaft 28 comprises a downstream turbine shaft 34 attached to the intermediate pressure turbine 22 and an upstream compressor shaft 32 attached to the intermediate pressure compressor 14. The compressor shaft 32 and turbine shaft 34 are connected together by a splined connection 36 which allows the turbine shaft 34 to drive the compressor shaft 32. If the splined connected 36 should fail, so that it no longer transmits torque, a further splined connection 41 comes into operation to transmit torque between the turbine shaft 34 and compressor shaft 32. When this happens, torque is transmitted via a torsionally weakened, shear section 48 of the turbine shaft 34 which tends to break under certain engine conditions. The turbine shaft 34 is then released axially and turbine overspeed is restrained.

Abstract: A vacuum pump is removably connected to the underside of a chamber for exhausting gas molecules from the chamber. The vacuum pump has a pump case having a flange extending circumferentially around a top portion thereof, a suction port and an exhaust port. Stator blades are fixedly mounted within the pump case, and a rotor is rotatably mounted in the pump case and has rotor blades alternately disposed with respect to the stator blades. A driving motor rotationally drives the rotor so that the rotating rotor blades coact with the stator blades to evacuate gas molecules from the chamber and pump the gas molecules from the suction port to the exhaust port. Bolt insertion holes are formed in the flange and each hole has a smaller diameter portion opening at a lower surface of the flange and a larger diameter portion opening at an upper surface of the flange which faces the underside of the chamber.

Abstract: A centrifugal blower with an eddy blade is disclosed. The centrifugal blower includes a multiblade impeller with a plurality of blades, and a scroll casing surrounding the multiblade impeller, with a spiral passage defined between the scroll casing and the impeller to guide air radially accelerated in the impeller to an air outlet port of the scroll casing, thus discharging the air from the scroll casing through the air outlet port. The eddy blade is installed in the spiral passage at a position around the air outlet port to generate a uniform current velocity distribution of air, thus preventing generation of an eddy at variance with a main current in a stream of air.

Abstract: The present invention provides a vacuum pump which reduces a damaging torque produced when a rotor rotating at high-speed crashes into a screw stator or the like. The vacuum pump has a rigid ring disposed around the screw stator such that a shock load from the screw stator causes the rigid ring to rotate. When a brittle facture occurs in the rotor rotating at high-speed, for example, and a part of the rotor crashes into the screw stator, a rotating torque, i.e., a damaging torque causing the entire vacuum pump to rotate is likely to occur. However, this damaging torque is absorbed by the rotation of the rigid ring and eventually subsides.

Abstract: The invention recites a power turbine assembly including a turbine rotor and a plurality of turbine blades mounted to said rotor and adapted to rotate said rotor in response to a flow of hot gas over said blades. A support structure having a journal bearing and at least one other bearing supports said rotor for rotation, said journal bearing having a proximal end and a distal end with respect to said turbine blades. A supply of lubricant communicates with said journal bearing to provide lubricant between said rotor and an inner surface of said journal bearing, said lubricant damping rotational frequencies of said rotor and creating a temperature gradient from greater than about 1000° F. at said blades to less than about 350° F. at said distal end.

Abstract: A method of modifying a rotor blade, and a rotor blade are provided. The rotor blade is for a steam turbine and it is modified to facilitate altering a natural vibratory frequency of the rotor blade, the rotor blade includes a leading edge, a trailing edge, a first sidewall, and a second sidewall, wherein the first and second sidewalls are connected axially at the leading and trailing edges, and the sidewalls extending radially between a rotor blade root to a rotor blade tip. The method includes determining a vibratory resonance condition of the rotor blade and forming a blade extension between the rotor blade root and the rotor blade tip that alters the determined resonance condition.

Abstract: A device at an acoustic liner for an apparatus generating sound comprises means (12) adapted to enable changes of the value of the acoustic impedance of the liner.

Abstract: A device and a method are for producing a blade including two outer walls and at least one cavity between the outer walls, for a turbine. An outer mould and several cores are used in forming the outer walls and the at least one cavity of the blade. At least one of the cavities is divided into two channels by a middle segment. One channel is located between the first outer wall and the middle segment, while the other channel is located between the middle segment and the second outer wall. Two cores which are separate from each other are used accordingly. This provides a simple and economical means of reducing the thickness of the outer wall.

Abstract: A cooled fluid flow component for a combustion engine which employs internal impingement and exterior surface film cooling is disclosed. The fluid flow component has improved tolerance to assembly and manufacturing variations. The fluid flow component includes at least one interior cavity having an associated impingement sleeve. An impingement annulus surrounding the impingement sleeve is divided into more than one region, with each region forced to have a pressure equal, pressure, with the pressure induced being sufficient to provide adequate backflow margin. The external cooling holes are shaped to address possible overflow tendencies, and the impingement holes are adapted to reduce or eliminate possible losses of impingement cooling effectiveness.

Abstract: Abnormality in an amount of a working gas leaked from between a rotating ring adapted to rotate with a rotor and a stationary ring of a turbo fluid machine is detected by a pressure switch and a flow meter, which are provided in a primary seal vent line, the working gas leaking from sealing surfaces of the labyrinth seal and the secondary dry gas seal, together with a purge gas purged to the space from outside is discharged outside the machine from a flow passage via a space. When abnormality generates in the secondary dry gas seal, a control valve provided in the purge gas line operates to secure a flow rate in the purge gas line, so that a flow rate detected by the flow meter provided in the purge gas line increases, and thus abnormality in the secondary dry gas seal is detected.

Abstract: A spring (15) of angular shape is placed between the lug (17) of a connecting rod (10) controlling the orientation of a stator blade and the pivot (3) of said blade, such that its edge (18) bends against one edge face (19) of the connecting rod (10) and the washer (16) moves the pivot (3) in the play of the bore (21) of the connecting rod and sets and maintains the contact between two plane faces (12 and 13), so as to reduce the differences in angular displacements between the connecting rod and pivot due to the play remaining in the bore (21).