Abstract: A method and device for detecting conditions conducive to the onset of pumping that can affect a low-pressure compressor of an aircraft turbine engine. The turbine engine including a high-pressure compressor. The method including measuring a speed variation of the aircraft and measuring a speed variation of the high-pressure compressor. The method including a preliminary step of measuring an altitude of the aircraft. The conditions conducive to the onset of pumping being detected when the following conditions are jointly obtained: (a) the speed variation measured over a predetermined time interval corresponds to an acceleration greater than a first positive threshold, (b) the measured speed variation corresponds to a deceleration less than a second negative threshold, and (c) the altitude is greater than a third predetermined threshold.

Abstract: An improved stator assembly is disclosed. The stator assembly may comprise an exit guide vane, an OD ring, and an ID ring. The exit guide vane may couple at one end to the OD ring and at an opposite end to the ID ring. The exit guide vane may comprise a leading edge opposite of a trailing edge. The OD ring and the ID ring may couple to a diffuser assembly of a gas turbine engine. The stator assembly may further comprise an aft OD seal, a forward OD seal, an ID seal, and a diffuser assembly seal to reduce airflow leaks around the stator assembly.

Abstract: A centrifugal compressor is equipped with a housing including a suction passage which accommodates an impeller. The suction passage is provided with a first opening portion formed at a position facing the impeller, a second opening portion formed on an upstream side of the first opening portion, a circulation flow path which allows the first opening portion and the second opening portion to communicate with each other and extends in an annular shape around a rotational axis of the impeller, and a plurality of guide vanes disposed in the circulation flow path. The circulation flow path includes a first region in which a plurality of guide vanes is disposed at intervals in a circumferential direction, and a second region in which no guide vane is disposed. The second region extends over a wider range in the circumferential direction than the interval between the guide vanes in the first region.

Abstract: A turbomachine component or collection of components includes a first blade and a second blade and a platform from which the blades extend. The platform, between the pressure face of the first blade and the suction face of the second blade, has a non-axisymmetric surface defining a plurality of fins of substantially triangular section extending downstream of a leading edge of each of the blades. Each fin is associated with a leading position and a trailing position on the surface, between which positions the fin extends, such that the leading position is situated at between 5% and 35% length relative to a chord of the blade extending from a leading edge to a trailing edge of the blade. The further a fin is from the suction face of the second blade, the further the leading position of the fin is axially from the leading edge of the blades.

Abstract: A gas turbine stage, in particular to an aircraft gas turbine. This gas turbine includes at least one casing having at least one bleed duct and at least one bore, and further includes at least one variable guide vane having a trunnion, a rotary plate, and a guide vane airfoil. The trunnion is disposed in the bore, and the guide vane airfoil is integrally formed with the rotary plate. The guide vane airfoil integrally formed with the rotary plate extends beyond this rotary plate in such a way that, viewed in the direction of flow of the gas path of the gas turbine, a flag corner of the guide vane airfoil, which corner faces the bleed duct and/or is in particular a virtual one, is located downstream of the beginning of the inlet opening of the bleed duct.

Abstract: A diffuser for an air cycle machine defines airflow both to a compressor rotor from the inlet and from the compressor rotor through a plurality of vanes that define radially extending airflow passages. The size and shape of both the inlet and the vanes of the diffuser define and tailor the character of airflow presented to and leaving the compressor rotor to provide a desired change in air flow.

Abstract: A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed.

Abstract: An annular seal flange is formed at an inner peripheral edge portion of an upstream-side seal ring. The seal flange projects in a downstream direction. When seal rings are viewed from radially inside, the seal flange of the upstream-side seal ring is designed to at least partially occlude an end gap of the downstream-side (the most downstream-side) seal ring.

Abstract: A blade cascade for a turbomachine having a plurality of blades arranged next to one another in the peripheral direction, at least two blades having a variation for generating an asymmetric outflow in the rear area, as well as a turbomachine having an asymmetric blade cascade, which is connected upstream from another blade cascade, are disclosed.

Abstract: A gas turbine compression system (1) comprising a gas channel (5), a low pressure compressor section (8) and a high pressure compressor section (9) for compression of the gas in the channel and a compressor structure (14) arranged between the low pressure compressor section (8) and the high pressure compressor section (9). The compressor structure (14) is designed to conduct a gas flow in the gas channel and comprises a plurality of radial struts (15,16,21,24,25) for transmission of load, wherein at least one of the struts (15,16,21,24,25) is hollow for housing service components. The compressor structure (14) is arranged directly downstream of a last rotor (10) in the low pressure compressor section (8) and designed for substantially turning a swirling gas flow from the rotor (10) by a plurality of the struts (15,16,21,24,25) having a cambered shape.

Abstract: A diaphragm for a steam turbine is disclosed that has at least one arc of admission. The arc of admission has a plurality of nozzles arranged about the circumference of the diaphragm and are configured to eject a working fluid at succeeding rotor blades axially-spaced from the diaphragm. The flow area of the first few nozzle vanes in the arc of admission is gradually increased along the arcuate length of the diaphragm, thereby mitigating the load impulse absorbed by each rotor blade as it enters the arc of admission. The flow area of the last few nozzle vanes in the arc of admission is gradually decreased so that each rotor blade does not suddenly go from full load impulse to zero and thereby contribute to the fatigue of the rotor blade and create unwanted noise.

Abstract: A guide blade ring (1) arranged downstream of the fan in the bypass duct of a turbofan engine for untwisting the airflow generated by the fan includes guide stator vane support struts (3) integrated into the guide blade ring at regular intervals respectively in place of a guide stator vane, the guide stator vane support struts (3) having a larger thickness and chord length than the guide stator vanes (2). A flow channel (4), respectively defined between a suction side (7) of the guide stator vane support strut and a guide stator vane (2.1) adjacent thereto on the suction side, is expanded by a geometric modification of the guide stator vane (2.1) with respect to the remaining guide stator vanes (2) in accordance with the respective configuration of the guide stator vane support strut.

Abstract: A system includes a rotary machine including, a stator, a rotor configured to rotate relative to the stator, a plurality of axial grooves disposed along a circumference of the stator or the rotor, a plurality of blade segments disposed along the circumference, wherein each blade segment of the plurality of blade segments comprises a blade coupled to a mounting base supported in a respective axial groove of the plurality of axial grooves, and the plurality of blades has a non-uniform blade spacing about the circumference.

Abstract: A system, including a rotary machine including: a stator, a rotor configured to rotate relative to the stator, wherein the rotor comprises a plurality of blades having a non-uniform spacing about a circumference of the rotor.

Abstract: Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.

Abstract: Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.

Abstract: A method of manufacturing a compressor section includes the steps of defining a compressor section having a number of blades, and having one or more stator sections, each with numbers of vanes. Each stator section has at least two sections wherein the spacing between the vanes in a first of the sections is not equal to a spacing between the vanes in a second of the sections. The number of blades, and the number of vanes where all of the sections are selected to achieve acoustic cutoff.

Abstract: In exemplary embodiments, a nozzle can include a first flow wall, a second flow wall and a vane disposed between the first and second flow walls, wherein the vane is mechanically coupled to the first flow wall and in contact with the second flow wall.

Abstract: An exemplary control stage of a steam turbine is disclosed, which includes plural staging valves circumferentially distributed around the turbine for regulating steam admission flow so as to control the loading of the turbine. Nozzle chambers are connected to a downstream end of each staging valve. An arc of admission forms the downstream portion of each nozzle chamber, and control stage nozzles in the arcs of admission define the downstream end of the nozzle chamber. Each nozzle chamber has at least two arcs of admission, each with a different circumferential dimension.

Abstract: A method of operating an axial turbine, having a stage including stationary blades and moving blades, each stationary blade having a radial height of an outlet thereof higher than the radial height of an inlet thereof, each moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, the moving blades being constructed such that a moving blade front-end peripheral velocity Mach number exceeds 1.0, the method including restraining a radial velocity component of a working fluid flowing through an outer peripheral portion of the stationary blade from the stationary blade inlet to the stationary blade outlet, whereby the working fluid having passed through the stationary blade flows substantially parallel to the central axis of the turbine from the stationary blade outlet to the moving blade inlet.

Abstract: A stator for a turbomachine. The stator includes a plurality of nozzle vanes, with the distance between each of the plurality of nozzle vanes varying circumferentially around the stator in a repeating pattern configured to distribute a vibration energy over a plurality of side band vibration frequencies around a nominal passing frequency in a rotor.

Abstract: A turbine reduces variations in mass flow at throats even when the flow rate of fluid is low or high. The turbine includes a turbine rotor having turbine blades; a turbine housing accommodating the turbine rotor 80 and whose cross-sectional area of a scroll portion formed between the turbine housing and the turbine rotor gradually decreases; a plurality of fixed vanes fixed along a curved line dividing the scroll portion into an inner scroll part and an outer scroll part; throats formed between the adjacent fixed vanes and communicate between the inner scroll part and the outer scroll part; and a switch valve which switches a flow path in the turbine housing either to the inner scroll part or to both the inner scroll part and the outer scroll part, in which flow path areas of the throats are reduced in a downstream direction of the scroll portion.

Abstract: A compressor which includes: an inner casing arranged so as to cover a rotor shaft; an outer casing arranged so as to cover the inner casing and forming a fluid flow path around the rotor shaft; and a plurality of struts mounted in the entrance of the fluid flow path and between the inner casing and the outer casing; in which the plurality of struts are arranged in a radial pattern centered on the rotor shaft, and the spacings between the adjacent struts in the circumferential direction of the rotor shaft are unequal.

Abstract: A fluid flow engine (1), in particular a turbo engine, has at least one guide vane row (5) with a plurality of guide vanes (6) and at least one rotor blade row (7) with a plurality of rotor blades (8). One guide vane row (5) and one rotor blade row (7) that follows the former directly downstream with respect to a working gas flow (11), together form a stage (10) of the fluid flow engine (1).

Abstract: In the invention, stator blades are arranged in such a manner that respective intervals between the adjacent stator blades (SV) become unequal at least partly. If the stator blades are arranged as mentioned above, there are formed wave fronts having different moving directions and phases, and these wave fronts are interfered with each other so as to be attenuated. Accordingly, an interference noise is reduced. Therefore, in accordance with the invention, it is possible to reduce an interference noise without enlarging a rotor stator blade interval as well as reducing a used amount of a sound absorption material.

Abstract: A fan includes a fan blade wheel and a fan frame. A fan wheel seat is disposed at the center of the air outlet of the fan frame and the air outlet faces a heat generating component. An air inlet of the fan frame is disposed opposite to the air outlet. The fan wheel has a hub with first blades and projections extending radially from the circumferential side of the hub. The projections are disposed between every two of the first blades alternately such that it is auxiliary for guiding airflow outward the fan smoothly. Hence, air pressure at the air outlet increases greatly for enhancing effect of heat dissipation effectively.

Abstract: A fluid pump assembly includes a rotatable component that can be rotated about an axis and a static vane assembly located adjacent to the rotatable component. The static vane assembly includes a circumferential surface axially spaced from the rotatable component, and one or more vanes extending from the circumferential surface toward the rotatable component. The one or more vanes are configured to produce a radial load on the rotatable component when the rotatable component is rotating about the axis and a fluid is present between the static vane assembly and the rotatable component.

Abstract: A conveying member, especially a rotor or stator, for conveying a flowable, preferably gaseous medium, comprises a plurality of blades (S1-S7) arranged following each other with a circumferential distance in a circumferential direction (U) around a central axis (A). Either a first circumferential distance (a) or a second circumferential distance (b) differing from the first circumferential distance (a) is provided between a blade and a respective blade following it in the circumferential direction (U) in a group of blades directly following each other in a circumferential direction (U), which the group comprises at least some of the blades (S1-S7). The first circumferential distance (a) is provided between at least two blades (S1-S7) located directly adjacent to one another, and the second circumferential distance is provided between at least two blades (S1-S7) located directly adjacent to one another.

Abstract: A compressor or pump employs principles of unsteady delayed stall to enhance the head increase produced by the compressor or pump. Plural airfoil-shaped lifting elements are spaced from each other in a cascade and the fluid is directed into the cascade by a device that varies a parameter of the flow relative to each lifting element in repeating cycles to cause the flow relative to each lifting element to begin to separate from the lifting element and then reattach thereto during each cycle. The cascade can comprise an axial flow impeller with plural impeller blades arranged around a hub capable of rotating on an axis. The device for varying the flow parameter can be a stator with a plurality of stator blades upstream of the impeller, or a second, counter-rotating axial flow impeller. In either case, the parameter is a flow angle at which the flow is directed to the downstream impeller.

Abstract: A stator vane assembly for a turbomachine comprising a plurality of circumferentially arranged stator vanes (32), the axial position of the stator vanes (32) and/or the pitch angle circumferentially between adjacent stator vanes (32) is varied circumferentially around the stator vane assembly. The stator vane assembly reduces the pressure distortion upstream of the fan outlet stator vanes (32), reduces the circumferential pressure variation and this reduces blade forced response excitation, noise generation and aerodynamic losses.

Abstract: A gas turbine engine turbine stage has an annular row of turbine airfoils including a first plurality of first airfoils having a first chord length and a second plurality of second airfoils having a second chord length shorter than the first chord length. At least one of the second airfoils is circumferentially disposed between each adjacent pair of the first airfoils. A second leading edges of the second airfoils are located downstream of first leading edges of the first airfoils. The first and second airfoils have different first and second temperature capabilities respectively and the first temperature capability is greater than the second temperature capability. The first and second airfoils may be made from different alloys and/or the second airfoils may be constructed to use lower amounts of cooling airflow than the first airfoils. More than one of the second airfoils may be disposed between each pair of the first airfoils.

Abstract: A method of assembling a gas turbine engine includes coupling an inner engine casing to an outer engine casing such that an annular flow path is defined therebetween, coupling a plurality of circumferentially-spaced support struts between the inner and outer casings, and coupling a plurality of circumferentially-spaced outlet guide vanes within the flow path upstream from the support struts, such that a first circumferential spacing is defined between a first guide vane and a second guide vane, and a second circumferential spacing is defined between the second guide vane and a third guide vane. The guide vanes are arranged such that the second guide vane is between the first and third guide vanes and the second circumferential spacing is different from the first circumferential spacing.

Abstract: A stator includes a row of airfoils extending inwardly from a casing. The airfoils are spaced apart circumferentially from each other at a spacing varying in turn around the perimeter of the casing for reducing vibratory excitation of a downstream rotor stage.

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: The present invention is intended to implement a high-temperature, high-pressure, high-output, high/low-pressure integrated steam turbine provided with a turbine rotor formed as an integral rotor member. It is provided with a high-pressure turbine (3) to which primary steam (20) is supplied, a low-pressure turbine (5) having last-stage turbine rotor blades (47), a turbine rotor (2) formed of an integral rotor member, an integral casing (6), and a downward-exhaust type of exhaust chamber (15); it has a rated power of at least 100 MW; the last-stage turbine rotor blades are rotor blades of an effective blade length of at least 36 inches rotating at 3000 rpm, or are rotor blades of an effective blade length of at least 33.

Abstract: In a centrifugal blower in which the outer periphery of an intake opening is arranged outside of the inner edge of a main blade, a large number of sub blades are provided in the intake opening at a location corresponding to the main blade. The sub blades lead the secondary air flowing from an outside area of the intake opening to a rotating direction of a centrifugal multi blade fan. Thus, the secondary air flows from the sub blade to the main blade smoothly, thereby increasing a secondary air flow amount and reducing air flow noise.

Abstract: This invention relates to an axial fan housing having a metallic shielding grating covering an air passage opening, wherein the grating is formed with a series of vane-like guide bars arranged in two or more concentric circular series. The number of guide bars in each circular concentric series increases from the radially inner series to the radially outer series of guide bars.

Abstract: A rotary turbomachine, and particularly a turbojet engine, has a compressor stage that is especially adapted for operation in the transonic region. The compressor stage includes a rotor (1) having a hub (2) and a plurality of compressor blades (3) extending radially therefrom, and a stator having a plurality of compressor blades extending radially between a stator hub and a housing. The hub (2) of the rotor (1), and/or the hub of the stator, and/or the housing of the stator, have a circumferential surface contour that is not continuously rotationally symmetrical. Namely, a concave contour (K) is provided in the circumferential surface of the hub near the base of each blade (3) on the pressure side (PS) thereof, while the circumferential surface on the suction side (SS) of the base of each blade has a contour that is linear, slightly convex, convex/concave, or slightly concave to a lesser degree than the concave contour (K) on the pressure side of each blade.

Abstract: A tandem turbine-blade cascade for a turbine, turbo-engine or power engine includes at least two rows of blades disposed substantially directly in line with one another in the rotor or stator. The second row of blades has a larger number of blades than the first row of blades and the second row of blades are distributed nonuniformly. The spacing (s.sub.1) between two blades of the first row of blades is substantially equal to the sum (s.sub.2) of two successive blade spacings (s.sub.12, s.sub.22) in the second row of blades and the distribution quotient (s.sub.12 /s.sub.22) of the blade spacings in the second row is in the range between 0.4 and 1.0.

Abstract: A vacuum pump assembly which comprises at least two cylinders of different diameters and arranged coaxially relative to each other to define an annular space therebetween and a helical member positioned within the space to define a helical path between the cylinders. Rotation of the cylinders is effected relative to the helical member, or vice versa, about their longitudinal axis.

Abstract: A guide vane arrangement for axial fans, intended to translate the rotational component of the gas flow velocity after passage through the impeller (1) into a substantially axial velocity, including a ring (2) of guide vanes disposed downstream of the fan and in spaced relationship therewith. Alternate guide vanes are axially displaced with respect to the remaining ones, so that alternate guide vanes are at a first axial distance from the fan and the remainder are at a second axial distance from the fan. As an alternative, alternate guide vanes have a portion of the end part facing towards the fan removed, so that the forward edge of alternate guide vanes is at a first distance from the fan and the remaining guide vanes are at a second axial distance, and the guide vanes are non-uniformly distributed along the periphery of the ring.

Abstract: An axial flow fan includes blades mounted on a hub and extending radially outward to a shroud disposed around the hub. Pairs of stators are connected to the shroud at positions angularly spaced about the inner periphery of the shroud. Each pair of stators includes a trailing stator angularly spaced from a leading stator by a distance related to the number of blades of the cooling fan. A trailing stator of one pair is spaced from a leading stator of an adjacent pair by a distance different than the distance between leading and trailing stators of each pair.

Abstract: A system for deforming a turbine stator housing is disclosed which maintains a substantially uniform radial clearance between a stator and a rotor under all operating conditions of a turbojet engine. The system deforms the turbine stator housing so that its longitudinal axis is substantially conincident with the longitudinal axis of the rotor, particularly under transient conditions. Such deformation results in the attainment of equal radial clearance between the rotor and the stator around the periphery of the rotor. The deformation is achieved by heating or cooling a selected portion of the stator housing such that the temperature distribution, measured around a periphery of the stator housing, is non-uniform, such non-uniform temperature distribution causing the stator to radially deform such that is longitudinal axis is coincident with that of the rotor.

Abstract: An improved partial arc admission system for a high pressure steam turbine, the system having a plurality of nozzle blade groups the blade aspect ratio of blades in each group vary according to the maximum pressure drop across each nozzle blade group.

Abstract: In an axial fan whose fan wheel is retained in a tubular member by spokes, the blade edges of the individual fan blades which face the spokes are constructed geometrically different from one another.

Abstract: A gas turbine engine bearing support structure comprises a central hub which carries a bearing and which is supported by a plurality of spokes from a ring member. The majority of the spokes are radially extending so that each is perpendicular to an imaginary tangent at its point of intersection with the ring member. However, two of the spokes are not perpendicular but are inclined so that compressive loading on the spokes results in partial rotation of the central hub, thereby leading to compressive loads in the non-inclined spokes being partially relieved by localised bending.