Abstract: Two stages of relatively rotatable guide vanes (22,24) are arranged in tandem. Shroud portions (42,46) on the vanes overlap in loose engagement, until an associated gas turbine engine starts operating. Gas loads then act on the downstream vane stage (24) and move it in a downstream direction until the opposing flanks of radially opposing lands (44,48) on respective shrouds (42,46) engage, whereupon, gas leakage via the overlap onto the turbine casing (40) is at least substantially reduced.

Abstract: A turbomolecular pump capable of maintaining a maximum discharge rate even in a higher pressure has rotor blades or stator blades formed such that surface angles on a first surface of the blades facing the direction of rotation differ between an inlet port side of the blades and an outlet port side. The surface closer to the inlet port has a larger angle than on a side closer to the outlet port. One side of the blades has a plurality of surface portions each with different angles. The angles of the surfaces are in the range of 20° to 50° on the inlet port side, 10° to 40° on an intermediate portion, and 10° to 90° on the outlet port side. The angles of the first and second surface portions are larger than that of the intermediate surface portion.

Abstract: Two stages of relatively rotatable guide vanes (22,24) are arranged in tandem. Shroud portions (42,46) on the vanes overlap in loose engagement, until an associated gas turbine engine starts operating. Gas loads then act on the downstream vane stage (24) and move it in a downstream direction until the opposing flanks of radially opposing lands (44,48) on respective shrouds (42,46) engage, whereupon, gas leakage via the overlap onto the turbine casing (40) is at least substantially reduced.

Abstract: A combination airflow straightener and finger guard straightens airflow and minimize the chance of fingers or other objects coming into contact with rotating blades of a fan, and includes a plurality of vanes that extend radially outward from a hub to an outer frame of the combination airflow straightener and finger guard. Each vane can be considered as having three portions. The first portion is closest to the fan and is parallel to the airflow leaving the fan. The second portion is farthest from the fan and is aligned with the axis of rotation of the fan (or some other desired exhaust vector). The third portion is curved to link the first portion to the second portion to straighten the airflow to the desired exhaust vector, with the space between each pair of vanes forming a plenum that straightens the airflow by removing the rotational components from the airflow.

Abstract: A gas turbine has circumferential arrays of nozzles and shrouds and a plurality of combustors for flowing hot gases of combustion through respective sets of adjacent nozzles and shrouds. First and second nozzles of each set of nozzles are subject to different known inlet conditions of the hot gases of combustion flowing from the associated combustor and transition piece. The first nozzle in each set is preferentially located relative to the second nozzle of that set at a circumferential location relative to the associated combustor based on the known different inlet conditions. The first and second nozzles are therefore qualitatively different from one another dependent on those different inlet conditions. Similarly, the shrouds are subject to different inlet conditions and are preferentially designed and located based on those known inlet conditions.

Abstract: A compressor stator includes an outer casing supporting a row of stator vanes extending radially inwardly therefrom. Each vane includes pressure and suction sides extending axially between leading and trailing edges and radially between a root and a tip. The root and tip are twisted relative to a pitch section disposed therebetween. Each vane tip is radially convex adjacent a leading edge for defining an axially concave outer flowpath in the casing for reducing peak velocity of airflow for enhanced efficiency.

Abstract: A fan tray apparatus and method includes a mounting body portion having a length and a width. The mounting body portion further includes first and second longitudinal sides and first and second lateral sides. A plurality of fans is operatively attached to the mounting body portion. The plurality of fans includes a first set of fans, a second set of fans, and a third set of fans. The first set of fans is positioned along the first lateral side. The second set of fans is positioned along the second lateral side. The third set of fans is positioned between the first set of fans and the second set of fans, the third set of fans positioned on a middle portion of mounting body portion.

Abstract: The pressure ratio &Dgr;P4S of a final stage moving blade is reduced. As a result, the Mach number in the final stage moving blade can be suppressed, and in the gas turbine operating at a pressure ratio of 20 or more, therefore, decline of turbine efficiency due to shock wave loss can be prevented securely.

Abstract: A turbine includes three rows of airfoils which receive in sequence hot combustion gases during operation. The third row airfoils are clocked circumferentially relative to the first row airfoils for bathing the third row airfoils with relatively cool wakes discharged from the first row airfoils during the hottest running condition of the gas turbine engine being powered. The third row airfoils therefore avoid the hottest temperature of the combustion gases for reducing the cooling requirements thereof.

Abstract: A method of positioning arrays of stages of a turbine, particularly for aircraft engines; the turbine having an axis and a first, a second and a third array of blades arranged consecutively, and of which the first and third array have a relative velocity about the axis with respect to the second array; the method including the steps of determining the paths of wakes moving inside gaps defined by the blades in the second array and towards the third array; distinguishing, for each wake, a first and at least one second zone differing from each other; selecting one of the first and second zone; and regulating the position of the third array with respect to the first array by aligning the leading edges of the blades in the third array with the paths of the selected wake zones.

Abstract: A two stage jointed stationary blade of a high pressure or intermediate pressure steam turbine is formed with a bolt joint in place of a welded joint so as to make detachment and disassembly possible, and thereby facilitating maintenance and inspection work and reducing assembling man-hours. A stationary blade (front stage)(2), outer ring front portion (1) and inner ring front portion (3) are welded into an integral structure. A stationary blade (rear stage) 22, outer ring rear portion (21) and inner ring rear portion (23) are also welded into an integral structure. The outer ring front portion 1, outer ring center portion 10 and the outer ring rear portion 21 are mutually engaged via engaging portions (4, 11 and 12, 24) with precise positioning and then jointed together integrally by bolt (30).

Abstract: To reduce the number of stages of a turbine and, associated therewith, the overall length and the costs, blading having high stage-specific enthalpy transfer is to be used. In this case, the disadvantages of conventional highly loaded blading, such as increased secondary flow losses due to blades of large chord length and comparatively small height and the design of the turbine in the complicated chamber type of construction, are to be avoided. Resulting from these requirements is a highly loaded slim blade type of construction having considerable deflection. A turbine having blading according to the invention is characterized by a loading parameter RBL, which in the HRBL blading according to the invention, in contrast to conventional types of construction, is greater than 1.

Abstract: A fan guard has a function of supercharging a fan in addition to supporting a rotor device is disclosed. The fan guard is to be mounted beside the rotor device for supporting the rotor device, and additionally, the fan guard interacts with an airflow generated by the revolution of the rotor blades to supercharge the fan. The fan guard essentially includes a main frame, and a set of guard blades radially arranged inside the main frame and fixed onto an inner surface of the main frame by each one end thereof. Each of the guard blades is preferred to have a shape similar to the shape of the rotor blades, and the set of guard blades can be arranged either upstream or downstream of the rotor blades.

Abstract: A stator device for an axial flow fan has a plurality of first stator elements and a corresponding plurality of second stator elements, the first stator elements being disposed axially rearwardly of the second stator elements so as to define an air flow slot therebetween.

Abstract: An axial flow compressor for use in a gas turbine or other industrial application having an improved efficiency is provided through modification of the blade shape and profile of the blades subject to a subsonic high velocity inlet flow so as to avoid shock losses in the blade rows, and improve the total efficiency. The curvature distribution on the suction surface of the stator blade rows or rotor blade rows of the axial flow compressor is adapted to have a local minimum in a region toward the leading edge of the blade, and then a local maximum. Thereby, an excessive increment in velocity on the suction surface from the leading edge to the position of the maximum velocity can be suppressed, and the occurrence of a shock wave can be avoided so as to minimize pressure loss in the blade rows, thus increasing the total efficiency of the axial compressor.

Abstract: Power generation turbines having different power outputs for different power grid frequency applications have modular second and third stages, rotors, bucket wheels for all stages and other ancillary parts. The first and second turbines have sizes not geometrically scaled according to speed. Four-stage turbines having different outputs for different power grid frequencies not geometrically scaled have an identical annulus through the first, second and third stages, different geometry in the first and fourth stages, and identical geometry in the second and third stages.

Abstract: In a radial-axial inlet housing of rotating thermal machines, a flow divider is disposed in the turbine or compressor inlet, in front of the inlet and opposite the first turbine guide vane row or the compressor ribs. The flow divider in this case is disposed in the central lower stagnation point of the housing flow. It has a thick-headed profile with a straight median line. The rear side of the flow divider, seen in the direction of flow, is disposed perpendicularly to the rotary shaft at a distance from the first guide vane row or the ribs. There is a gap between the radially inner side of the flow divider and the housing wall, and the chord length of the flow divider decreases radially outwardly. The leading edge of the flow divider, seen in the direction of flow, is inclined like a straightened potential line relative to the housing wall.

Abstract: A booster-compressor for a high flow coefficient turboprop aircraft engine increases engine thrust by supercharging the air into the inlet of the gas generating core engine. The flow of supercharged air from the booster-compressor is split between the core engine and the ambient to allow for the use of standard size rotor blades and stator blades and to provide supplemental thrust. The rotor blades are designed as impulse rotors and the stator vanes are arranged in an axially converging annular flowpath in order to limit to a minimum any increase in the static pressure of the supercharged air.

Abstract: An airfoil for a compression section 12 of a rotary machine 10 is disclosed. Various construction details are developed to increase the efficiency of the compression section 12. In one detailed embodiment, the airfoil has a spanwise axis 52 or stacking line which extends in a generally radial direction. The stacking line or spanwise axis 52 is straight over the mid-section of the airfoil and is angled circumferentially toward the radial direction in the end wall regions 58, 66 of the airfoil.

Abstract: A turbine comprising at least one stage (20) having a diaphragm (1) which is split in two along a diametrical plane and which includes an outer ring (3) and an inner ring (6) interconnected by virtue of (10 and 11) serving to guide the turbine fluid, the downstream face (14) of the outer ring (3) being pressed against a ring (19) of the turbine stator (4), the diaphragm (1) being provided with sealing (17) providing sealing between the outer ring (3) and the stator (4), the turbine being characterized in that the sealing (17) are disposed on the outer edge (15) of the outer ring (3), in that the downstream face (14) of the outer ring (3) is provided with a land (18) at a distance from the outer edge (15) and bearing against the ring (19) of the stator (4), and in that communication (22, 27, 27') are provided for providing communication between the space (25) situated between the land (18) and the sealing (17), and a space downstream from the diaphragm (1) with the pressure in the space being less than the pre

Abstract: A turbine engine operates at high pressure and at relatively low temperatures and revolutions per minute through the use of special carburetion, compressor, combustion unit, and turbine arrangements. The system is characterized by the use of water which is vaporized and concurrently reduces the temperature of the vaporized fuel and air mixture as compression occurs, and is not physically intermixed with the combustion gases until after initial combustion takes place. The compressor includes a pair of back-to-back, four stage composite compressors to which synchronized dual carburetion or meter-flow arrangements separately supply water and gasoline or other fuel, along with air. The water absorbs heat from the compression of both of the two compressors, and the resultant vaporous product gases are routed to the jacket of a combustion chamber in which the compressed fuel and air mixture is burned.

Abstract: Turbine apparatus that includes a tubular housing, a rotor assembly drivingly mounted on a shaft and having a hub and a plurality of circumferentially spaced, generally V-shaped blades extending radially outwardly of the rotor hub, each rotor blade having first and second leg portions oppositely inclined relative to a plane perpendicular to the shaft that passes through the vertex of the blade, first and second stator assemblies on axially opposite sides of the rotor assembly that have a plurality of circumferential spaced blades that are respectively inclined relative to said plane at about the same angle as the adjacent set of the first and second leg portions, at least one stator assembly having the shaft rotatably extended therethrough, whereby the rotor assembly will be driven in the same direction whether fluid passes through the housing in one axial direction or the opposite axial direction. More than one set of first and second stator and rotor assemblies may be provided in the housing.

Abstract: An axial flow, reversible fan for use as a plug unit in a heat treating furnace comprises a shaft, an impeller having opposing faces mounted on an end of the shaft and comprising a tankhead and a plurality of flat blades disposed about and extending radially therefrom, a first set of fixed concavo-convex vanes disposed about and extending radially from the shaft adjacent a face of the impeller, a second set of fixed concavo-convex vanes disposed about and extending radially from the shaft adjacent the opposite face of the impeller, and a driving means for rotating the impeller which is attached to the shaft.

Abstract: A locking system for locking in position the blades in the stator case of an axial compressor, wherein all of the blades are subjected exactly to the same locking load and can rapidly be assembled and disassembled when necessary. The system is especially suited for axial compressors which are required to operate in a dusty environment.

Abstract: A power-generating wind-driven turbine is disclosed which offers the advantage that it is compact and lightweight and is capable of producing a substantially greater output than a conventional windmill with a comparable size rotor. The turbine comprises an outer shroud and a nose cone which provide a streamlined wind collecting inlet designed so that the air stream is contracted to increase its velocity through the turbine blades, plus an exit section designed to exhaust the air stream with a minimum of turbulence.

Abstract: This invention relates to a vane assembly for a split-shaft gas turbine engine. The invention relates to a vane assembly which is placed in the hot gas stream to control diffusion and to deflect the hot gas just prior to passage through the blades of the power wheel. The vane assembly is characterized by having each controlling and deflecting blade constructed in two cooperating parts, a forward portion of the vane which is hollow and stationary to control diffusion and a trailing portion which is allowed to pivot through a small angle to control deflection. The vane assembly is constructed in sections to have two complete vanes per section and the sections are fitted into circumferential slots in the casing of the turbine. The vane tip actuators are passed through the turbine casing and are fitted to the trailing portions of each vane so that the trailing portions of the entire assembly move as a unit by a single control mechanism.

Abstract: A turbomachine having a stationary housing and a rotatable rotor mounted therein and including a series of rotor blade rings carried by the rotor and a series of guide vane rings carried by the housing, the guide vane rings and the rotor blade rings being disposed in mutually alternating relationship, further includes means defining an annular space located forward of the first rotor blade ring of the series of rotor blade rings, flow medium supply means communicating with the annular space for supplying flow medium thereto, the annular space extending radially outwardly and along the entire periphery of the turbomachine for producing a torsional flow of the flow medium, the rotor having a shaft formed with a collar, and the series of rotor blade rings including a first blade ring mounted on the collar directly behind the annular space and having a diameter greater than that of the succeeding blade rings of the series, whereby the flow medium supplied to the annular space axially impinges directly on the firs