Abstract: A tip treatment bar (16) for use in a gas turbine engine casing is provided with a cavity which is open on one side of the bar (16), the cavity being filled with a damping material (24). The bars (16) may be open ended. The damping material (24) reduces vibration amplitudes in the bar (16) caused by aerodynamic excitation, thus reducing high cycle fatigue of the tip treatment bars (16).

Abstract: The second stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z value is non-dimensional along the bucket centerline coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.160 inches.

Abstract: An object of the present invention is to provide a turbofan in an air conditioner, which facilitates unitary formation of a turbofan, and easy formation of a turbofan mold, and has a longer lifetime of the mold. Another object of the present invention is to provide a turbofan in an air conditioner, which can minimize noise produced during operation of the turbofan.

Abstract: A gas-handling centrifugal pump has impellers for pumping gaseous materials containing up to 50% by volume free gas. The impellers have split vanes with high exit angles up to about 90 degrees and preferably greater than 50 degrees. The split vanes define flow passages that contain large diameter balance holes that typically range between 45% to 100% of the width between each split vane. The gas-handling centrifugal pump can be used as a charge pump for a centrifugal pump in a lower tandem configuration within a well.

Abstract: A ceiling fan and pendent chandelier wherein the ceiling fan is provided with a chandelier adaptor which adapts the ceiling fan to hang a pendent chandelier therefrom.

Abstract: A method and apparatus for casting a near-net-shape article from a high temperature material, such as a refractory metal intermetallic composite material. The apparatus includes: a means for forming a molten material comprising at least one of a metal and an alloy; a means for pouring the molten material; a mold assembly comprising a solid shell having a face coat interposed between the solid shell and molten material; and a heater assembly for maintaining the solid shell at a temperature. The molten material solidifies within the solid shell to form a near-net shape of the article. The near-net shape article may be a turbine assembly component, such as, but not limited to, a vane or airfoil.

Abstract: An electric fan having an electric motor and a fan wheel connected to the electric motor. The fan wheel has a hub and fan blades extending from the hub. The fan blades include a proximal section at the hub, a distal section and a middle section. The proximal section has a flat surface at a trailing edge of the blade. The trailing edge at the distal section is curved with an angle of curvature of about 10°. The trailing edge at the middle section is curved with an angle of curvature of about 36°. When the fan wheel is rotated by the electric motor at a constant speed, air pushed by each of the fan blades is propelled at a substantially same velocity and direction from the blade measured across a radial length of the blade.

Abstract: The invention relates to an axial flow fan for condenser in a refrigerator for enhancing efficiency and lowering noise, in which the number of blades is three, the diameter of a hub is 23.3±5% of the outside diameter of the axial flow fan and the width of each of the blades is 36.6±3% of the outside diameter of the axial flow fan.

Abstract: A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross.

Abstract: A gas compression apparatus and method according to which an impeller rotates to flow fluid through a casing, and a plurality of vanes are mounted on a plate in the casing. A series of cells are formed in the plate to form an array of acoustic resonators to attenuate acoustic energy generated by the impeller.

Abstract: Gas turbine engine components which are supplied with longitudinal ribs on the areas that are in contact with a gas flow, whereby the riblets have a length of at least 5 mm, a height of at least 0.02 mm and a width of at least 0.01 mm. Those riblets are applied using the High Velocity Oxyfuel Process (HVOF). Using this technique material in the form of a powder is applied at high velocity onto the substrate of the gas turbine engine components with the riblets created preferably by positioning a mask in front of the subject part. If necessary, prior to the application of the HVOF coating, a bondcoat can be applied on the subject parts.

Abstract: A device for a component to be cooled includes a baffle cooling plate with at least one leadthrough for the cooling agent, arranged in front of the component. The baffle cooling plate can be impinged upon with a cooling agent. A deviation channel for the cooling agent is provided next to the leadthrough for the cooling agent and between the baffle cooling plate and the component to be cooled. The cooling agent enters the deviation channel after the component has been baffle-cooled. The cooling agent is collected and deviated by way of the deviation channel and can be specifically sued for further cooling purposes. The inventive device provides more efficient baffle cooling.

Abstract: The object of this invention is to propose a variable capacity turbine, requiring neither adjustment process of the full-opening position and the perfect closing position nor the dedicated full position stopper, in which the adjustment works for setting up the full-opening position of the nozzle vanes are not required, and the accidents of damaging the turbine wheel caused by the nozzle vanes which opened excessively can be avoided. It has a plurality of joint members of the same number as the nozzle vanes, which connect a plurality of nozzle shafts for nozzle vanes and the nozzle driving member, and which rotate the nozzle shafts with a swing motion forced by the nozzle driving member. The nozzle angle regulator is provided with two full-opening stopper surfaces provided on at least two neighboring joint members to move the nozzle vanes towards the opening direction and stop the nozzle vanes at the full-opening position by contacting the two neighboring joint members to each other.

Abstract: A fluid-driven power generator having a turbine with several vanes, an exhaust chamber, a device for directing a first fluid towards the vanes of the turbine, a device for directing a second fluid through the generator housing assembly without contacting said turbine, a device for combining the first fluid and the second fluid in an exhaust chamber, and a device for creating a vacuum in the exhaust chamber.

Abstract: In order to create a rotor blade of hybrid design comprising a vane and a blade root, the vane having a first vane portion made of a metallic material and a second vane portion made of a lightweight material, provision is made for a rear edge of the rotor blade to be formed on the second vane portion, and for the second vane portion to be joined to the first vane portion in a single-section-type manner.

Abstract: The revolving fan impeller of a fan includes a fan blade ring, which is used to produce an air current, as well as a turbine blade ring, which is used to drive the impeller and which may be impinged upon by a pressurized fluid. The fan casing includes a feed channel for the pressurized fluid as well as several nozzles to carry the pressurized fluid from the feed channel to the turbine blade ring. The number of active nozzles may be varied. For this purpose, the nozzles are arranged on a stator ring, which may be rotated around the fan axis.

Abstract: A turbine nozzle assembly for a gas turbine engine, including: a plurality of segments joined together to form an outer band; a plurality of segments joined together to form an inner band; at least one airfoil positioned between the outer and inner bands; a leaf seal attached to each inner band segment by at least one pin member; and, a leaf seal attached to each outer band segment by at least one pin member. Each of the inner band segments includes a protrusion extending from a surface thereof so as to provide balanced support to the corresponding leaf seal in conjunction with the pin members. Each of the inner band segments further includes a first portion having a flange extending therefrom, a second portion opposite the first portion, a first end, and a second end opposite the first end, wherein the surface extends between the first and second ends and the first and second portions.

Abstract: A tip treatment assembly is provided including a tip treatment bar (16) and retaining means (24, 26) which cooperate with a retaining element (30, 32) to retain the tip treatment bar (16) with respect to support means (44) of the assembly. The retaining means (24, 26) may comprise a hole through the bar (16) through which the retaining element, in the form of wire 30, 32, extends. The tip treatment bars (16) can be formed by stamping from a sheet of material such as a suitable alloy.

Abstract: An axial flow fan wherein an impeller having a plurality of blades is supported rotatably in the cylindrical cavity portion of a venturi case so that an outer peripheral edge of each of the blades faces to an inner peripheral surface of the cavity portion with a small air gap. The outer peripheral edge of the blade is increased in thickness gradually toward a discharge port side of the venturi case from a suction port side of the venturi case. An peripheral edge portion of the blade at a suction port side of the venturi case is bent in the circumferential direction from a negative pressure surface side of the blade, so that the edge is small in thickness. An outer peripheral edge portion of the blade at a discharge port side of the venturi case has a portion extending circumferentially from a positive pressure surface side of the blade.

Abstract: A tip treatment bar (16) for a gas turbine engine has a damping coating (24) applied to one or more sides. The coating (24) may be a hard ceramic, for example Magnesia Alumina Spinel, and this may be plasma sprayed directly on to the bar (16) or applied to a substrate (26) which may then be applied to the bar (16).