Abstract: A turbine for a turbomachine includes an annular row (20) of moving blades (20a) surrounded by a support ring (26) of abradable material (24) carried by a housing (10). The turbine also includes a distributor (30) mounted downstream of the moving blades (20a) and having an attachment mechanism with a radially outer spoiler (38) coming to bear radially inwards on a cylindrical wall (12) connected to housing (10). An annular wall (14) extends radially inwards from the cylindrical wall (12) and engages at its radially inner end in an annular groove (28) of the support ring (26), and in which a free annular space (40) is formed between a radially outer face (26b) of the ring (26) and the cylindrical wall (12).

Abstract: A flow control device for constraining fluid flow between axial flow turbomachines in series has a flow constrainer which constrains the fluid flow downstream of the first turbomachine in the series to the blades region of the second turbomachine, preventing fluid flow from impacting the hub or nosecone of the second turbomachine and providing more uniform fluid flow to the second turbomachine. The flow control device includes connective elements for positioning between the downstream region of the first turbomachine and the upstream region of the second turbomachine. The device may be equipped with stator vanes having a variety of optional configurations to further improve the uniformity of the fluid flow load on the second turbomachine.

Abstract: A motor includes a rotor rotatable about a center axis extending vertically, a stator to rotate the rotor, and a housing covering the rotor and the stator from a radially outer side. The housing includes a first housing located on a first side in the axial direction, and a second housing located on a second side in the axial direction. The first housing includes a first opposing surface opposing the second housing in the axial direction, and a first wall portion extending from the first opposing surface to the second side in the axial direction. The second housing includes a second opposing surface opposing the first housing in the axial direction, a second wall portion extending from the second opposing surface to the first side in the axial direction, and a base portion holding the stator. The first wall portion and the second wall portion oppose each other in a radial direction.

Abstract: Provided is a vacuum pump regarding which compression can be improved at low costs. Included is a plurality of Siegbahn exhaust mechanisms in which a helical groove is provided to a stator disc. The Siegbahn exhaust mechanisms are provided on both faces of an upstream side and a downstream side of the stator disc. An end portion of the helical groove provided on the upstream side and a start portion of the helical groove provided on the downstream side are situated at least partially overlapping in a circumferential direction. A width of a channel of a switchback portion of the upstream side and the downstream side is equivalent or less than a depth of a channel of the Siegbahn exhaust mechanisms.

Abstract: In one aspect, the present disclosure is directed a gas turbine engine including a compressor, a combustor, and a turbine in a serial flow arrangement. The compressor includes a casing having an inner wall and an outer wall. The inner wall defines a passageway for airflow through the compressor. The casing defines a bleed cavity between the inner wall and the outer wall. The inner wall has an opening. The casing defining a channel between the opening and the bleed cavity to direct airflow into the bleed cavity. The channel is defined by a first wall and a second wall of the casing. The second wall being downstream of the first wall. A surface of the first wall has a pattern to reduce flow separation in the channel.

Abstract: A vacuum pump includes a housing, a rotatable shaft extending in an axial direction within the housing, a first pumping arrangement including a first stator arrangement and a first rotor arrangement, and a second pumping arrangement including a second stator arrangement and a second rotor arrangement. The vacuum pump further includes a spacer arranged between the first pumping arrangement and the second pumping arrangement. The spacer is coupled between the first stator arrangement and the second stator arrangement and is configured to provide a defined elasticity in the axial direction allowing an elastic deformation of the spacer in the axial direction.

Abstract: An example compressor bleed slot apparatus includes an annular compressor casing, a blade row mounted for rotation about a centerline axis inside the compressor casing, a bleed slot passing through the forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row, an array of struts interconnecting the inboard and outboard walls, and an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange includes a necked-down portion adjacent the forward section of the compressor casing, the necked-down portion positioned axially between an inlet of the bleed slot and an outlet of the bleed slot.

Abstract: A turbine stator includes a partition plate including an inner ring that extends along a circumferential direction, an outer ring that is disposed on an outer side of the inner ring in a radial direction, and extends in the circumferential direction, a plurality of nozzles that are disposed in the circumferential direction between the inner ring and the outer ring, and are configured to guide a fluid from an upstream side toward a downstream side in an axial direction, and an annular protruding portion, protrudes from the outer ring to the downstream side in the axial direction, and extends along the outer ring in the circumferential direction, and a casing surrounding the partition plate from the outer side in the radial direction, and having a contact support surface that is in contact with the annular protruding portion from the downstream side in the axial direction.

Abstract: A steam turbine includes a guide member that is disposed between a first rotor blade row and a second stator vane row to guide a fluid from the first rotor blade row toward the second stator vane row. When seen in a circumferential direction, an outer peripheral surface of an inner ring of the second stator vane row is disposed farther to an inner side in a radial direction than an outer peripheral surface of a platform of the first rotor blade row. The guide member has a guide surface that extends from an outer peripheral surface of a shroud of the first rotor blade row toward an inner peripheral surface of an outer ring of the second stator vane row so as to be inclined toward the inner side in the radial direction as the guide surface approaches a second side from a first side in an axial direction.

Abstract: A turbo-molecular pump comprises multiple stages of rotor blades and multiple stages of stator blades. When m is a positive real number equal to or less than a total number of stages of the rotor blades and greater than one and K is a natural number which is not a multiple of m in a case where m is a natural number and is a natural number in a case where m is not the natural number, the multiple stages of the rotor blades include a rotor blade at an inter-blade angle ?1, and a rotor blade of which reference position is phase-shifted from a reference position of the rotor blade at the inter-blade angle ?1 by an angle ?1·K/m.

Abstract: A gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.

Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.

Abstract: This disclosure provides a cross key anti rotation spacer for use in a gas turbine engine. A compressor disk assembly can have a cross key ring having a plurality of keys, teeth, or castellations, alternating with a plurality of gaps to form a cross key surface. The keys or teeth of the cross key surface can mesh with corresponding teeth formed on a spacer of a compressor rotor assembly. The spacer teeth, in connection with the teeth or keys of the cross key ring can prevent rotation between the spacer and compressor disk. This is particularly beneficial during transient operations, such as startup and shutdown of the gas turbine engine.

Abstract: An assembly includes a one-piece bladed disk, at least one low-pressure compressor rotor, and a low-pressure compressor shaft. The bladed disk and the low-pressure compressor rotor are both adapted to be shrunk onto the low-pressure compressor shaft and mechanically attached to it by sets of splines. At least one clamping member blocks axially the different collars with respect to the shaft.

Abstract: A compressor of a gas turbine engine is described which includes a rotor and a stator located immediately downstream of the rotor. The stator comprises a plurality of stator vanes each having an airfoil extending along a generally radial span between a root and a tip of the airfoil. The radially inner portion has aerodynamic forward sweep at the leading edge, the forward sweep having a maximum forward sweep that is more forward than a sweep at the leading edge in the intermediate portion.

Abstract: Disclosed is a turbomachine including a stator, a rotor rotatable about an axis of rotation, and an annulus for carrying a core flow, the annulus having a side wall on the stator and a side wall on the rotor, at least one airfoil array having a plurality of airfoils being disposed in the annulus. In a departure from an ideal aerodynamic annulus contour, a radial annulus enlargement begins upstream of the airfoils and extends downstream up to an aft portion of the airfoil array that follows the ideal aerodynamic annulus contour. Also disclosed is an airfoil for such a turbomachine.

Abstract: When a compressor vane or blade for an engine is used in an environment containing abundant foreign substances, deposits originated from the foreign substances are likely to deposit on surfaces of the vane or blade. The compressor vane or blade according to the present disclosure has a base body of the compressor vane or blade; and a coating covering the base body, which consists essentially of one or more selected from the group of molybdenum disulfide and tungsten disulfide.

Abstract: A rotor disk assembly comprises a first rotor disk with a plurality of circumferentially distributed first throughbores. A second rotor disk comprises a connection portion projecting at least partially axially, a plurality of circumferentially distributed second throughbores being provided in the connection portion in cooperative distribution relative to the first rotor disk for the first and second throughbores to be in register with one another in the rotor disk assembly. Connector bolts each have an elongated body with a flange between its ends, a head at its first end and a removable head at its second end, the head at the first end spaced apart from the flange for the connector bolt to be secured to one of the rotor disks at a respective throughbore, the removable head at the second end being spaced apart from the flange for the second end to project.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable of one another about an engine axis. The LP spool comprises an LP turbine, an LP compressor and an LP shaft. The HP pressure spool comprises an HP turbine, an HP compressor and an HP shaft. The LP turbine is in fluid flow communication with the HP turbine and disposed downstream therefrom. The HP compressor is in fluid flow communication with the LP compressor and disposed downstream therefrom. The LP shaft has an upstream shaft portion extending upstream of the LP turbine to a location upstream of the LP compressor to provide a first power take-off at an upstream end of the engine and a downstream shaft portion extending downstream of the LP turbine to provide a second power take-off at a downstream end of the engine, thereby allowing mounting of a reduction gear box at either end of the engine.

Abstract: A pump for a fluid which can be blood has a stator housing and a rotor hub with leading and trailing portions and an intermediate portion disposed therebetween. At least one impeller blade at the leading portion drives circumferential and axial components of a flow into a pump annulus or intermediate pathway portion. At least one stator blade extends radially inward from the stator housing within the intermediate pathway portion and is configured to reduce a circumferential component of the flow.

Abstract: The present application relates to a stator for a low-pressure compressor of an axial turbine engine. The stator includes an annular row of stator vanes with connection vanes, and support vanes which are grouped into vaned casings. The casings include internal platforms and external platforms, and are integrally produced by means of additive production based on titanium powder. The stator has a circular internal shroud which is formed by the internal platforms of the vanes of the casings and internal shroud segments which are fixed to the connection vanes. The internal platforms include pairs of contact surfaces in order to interlock the shroud segments therein by moving into abutment and sliding against the contact surfaces. The contact surfaces are perpendicular to the rotation axis and form axial stops.

Abstract: A thrust generating apparatus for controlling an attitude of a movable body includes an outer shell body, a first inner shell body and a second inner shell body, a first fan rotating body and a second fan rotating body, an intermediate shell body, and a driving unit. A outer surface of the intermediate shell body has a shape such that an air flow sent from an opening end inside of any one of the first inner shell body and the second inner shell body is accommodated and flowed out to an outer flow path . When the first fan rotating body is rotated, the air flow suctioned from the outside in the axial direction of the first inner shell body passes through the outer flow path defined by the second inner shell body to be jetted from a second opening end of the outer shell body.

Abstract: Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.

Abstract: A rotor disk for a gas turbine engine is disclosed and formed to enable operation at high rotational speeds in a high temperature environment. The rotor disk is formed to include a bore, a live rim diameter and an outer diameter related to each other according to defined relationships.

Abstract: The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).

Abstract: An axial-flow exhaust turbine is capable of discharging water drops collected from a steam passage. The axial-flow exhaust turbine includes: a steam passage in which rotor blades and stator blades are arranged in rows; an exhaust chamber for discharging steam from the steam passage in a turbine axial direction, the exhaust chamber being positioned at a downstream side of the steam passage; a casing including the steam passage and the exhaust chamber inside the casing; an inner partition wall positioned on an inner circumferential side of the casing so as to face the exhaust chamber; and a drain flow channel defined between the casing and the inner partition wall. The water drops collected from the steam passage can pass through the drain flow channel.

Abstract: A disc turbine engine includes a multi disc engine in which each disc engine includes a turbine blade, and low-pressure compressor blade, a high-pressure compressor blade and a bearing that runs the disc engine freely around a shaft. Each disc engine has its own cooling system, the compressor's blades act as cooling fins for the turbine blade, and air bleeding from the high-pressure compressor to the lower pressure compressor through a hollow turbine blade. Cooling the nozzle is by attaching the nozzle to the guide fan and by air bleeding through the hollow body. There is no stator in between the disc engine and no large shaft is required because the power produced by each turbine blade is consumed by its own compressor. The weight and cost of this engine will be less than other engines at the same thrust output.

Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.

Abstract: A turbomachine includes an annular flow path section between a plurality of radially extending stator vanes and a plurality of radially extending rotor blades. At least a first portion of the flow path section has a circumferentially varying outer periphery which includes a recess circumferentially alternating with axisymmetric surfaces.

Abstract: A fan assembly includes a first fan including a first frame, a second fan including a second frame, the first frame of the first fan has a first jointing surface, and the second frame of the second fan has a second jointing surface. A first concave structure and a first flange are formed along two ends of a first direction of the first jointing surface of the first fan, and a first concave structure and a first flange are formed along two ends of a first direction of the second jointing surface of the second fan respectively. The first flange of the first fan moves relatively to the second jointing surface of the second fan, and is embedded in the first concave structure of the second fan.

Abstract: Flow control devices and structures designed and configured to improve the performance of a turbomachine. Exemplary flow control devices may include various flow guiding channels, ribs, diffuser passage-width reductions, and other treatments and may be located on one or both of a shroud and hub side of a machine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.

Abstract: A clamping and support system for a turbine is disclosed. The clamping and support system may include a support bar coupled with a lower diaphragm portion of the turbine. The support bar may have a protuberance extending from a first end portion thereof that may at least partially extend into a slot formed in the lower diaphragm portion of the turbine. The clamping and support system may also include a clamping bar coupled with a second end portion of the support bar. The clamping bar may at least partially extend into a slot formed in an upper diaphragm portion of the turbine such that at least a portion of the lower diaphragm portion and at least a portion of the upper diaphragm portion are interposed between the clamping bar and the protuberance of the support bar, thereby coupling the lower diaphragm portion with the upper diaphragm portion.

Abstract: A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.

Abstract: Drill bits having flushing channels and surface features that cooperate to evacuate cuttings. The surface features can be provided as flutes, fins, and/or ribs defined in a body portion of the bits. Optionally, the surface features can define back-cutting edges the permit back reaming.

Abstract: A rotary vacuum pump includes a first set of pumping stages having rotor discs with a first diameter and a second set of pumping stages having rotor discs with a second different diameter and further comprising an intermediate pumping stage that is particularly adapted for matching the change in the diameter of the pump rotor discs. According to the invention, the intermediate pumping stage comprises a rotor disc having an outer portion in the radial direction that is axially tapered from its inner diameter to its outer diameter and a corresponding stator stage including a spacer ring that is axially tapered from its periphery toward its center.

Abstract: A rotor (10) of a rotary machine (T1) according to the invention includes a plurality of rotor members (20, 30, and 40) which are joined to each other in the axial direction in which the axis (P) extends, and among the plurality of rotor members (20, 30 and 40), the first rotor member (30) in hydraulic fluid injection portions (3a and 3b) of a passageway (3) is formed of Ni-based alloy so that the inside thereof is hollow throughout the entire length in the axial direction.

Abstract: A series fan includes a first fan and a second fan. The first fan has a first frame, a second frame and a first flow passage. The second fan has a third frame, a fourth frame and a second flow passage. A first static blade is disposed at the first frame, while a second static blade is disposed at the fourth frame. A first dynamic blade assembly is disposed in the first flow passage, while a second dynamic blade assembly is disposed in the second flow passage. The second frame is assembled with the third frame. The first and second static blades serve to enhance the support strength and protection effect for the series fan. In addition, the first and second dynamic blade assemblies can be designed with an increased aerodynamic volume.

Abstract: A hydraulic bearing is provided for a stationary gas turbine that has an oil sump with an outflow for hydraulic oil, wherein the outflow has an outflow opening which is arranged in the oil sump and an outflow line which is connected to the outflow opening. The hydraulic bearing is adapted to bring about an annular flow with a central air column when hydraulic oil flows out in the outflow line.

Abstract: A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides.

Abstract: A turbine engine includes an airfoil made of an aluminum-rare earth element alloy.

Abstract: A steam turbine 3 includes: a turbine rotor 4; a rotor blade 5 implanted to the turbine rotor 4; a stator blade 6 provided at an upstream side of the rotor blade 5; and a turbine casing 13 supporting the stator blade 6 and including the turbine rotor 4, the rotor blade 5 and the stator blade 6, and have a constitution in which a stage 7 is formed by a pair of the rotor blade 5 and the stator blade 6, and a steam passage 8 is formed by arranging plural stages 7 in an axial direction of the turbine rotor 4. A surface treatment to suppress an increase of a surface roughness caused by oxidation is performed for at least a part of a surface of the stator blade 6 and a surface of the rotor blade 5.

Abstract: An apparatus having reduced wear and friction between CMC-to-metal attachment and interface of the apparatus, including a CMC component having a surface. The CMC component surface is configured for sliding contact with a surface of a metal component, the sliding contact resulting in formation of debris along the contacting surfaces. The surface of the CMC component has an engineered surface feature formed therein to substantially prevent an accumulation of debris along the contacting surfaces.

Abstract: The invention relates to a helico-axial pump (1) for pumping a multi-phase mixture (M), said helico-axial pump (1) including a rotor (2) rotatably journalled in a pump housing (6) about a longitudinal axis (A), wherein the rotor (2) includes a compression stage (K) with a helico-axial impeller (3) and a stator (4) for the compression of the multi-phase mixture (M). In accordance with the invention a hydrodynamic stabilization element (7, 71, 72, 73) having a stabilization surface (700) is provided in the pump housing (6) and designed such that a stabilization gap (8) is formed upstream of the stabilization medium, so that in the operating state a hydrodynamic stabilization layer (S) can be formed from a stabilization medium in the stabilization gap (S). The invention further relates to a rotor (2) for a helico-axial pump (1), a method for the hydrodynamic journaling of a rotor (2) of a helico-axial pump (1) as well as to a hybrid pump with a rotor (2) for a helico-axial pump 1.

Abstract: The invention relates to a helico-axial pump (1) for conveying a multiphase mixture (M), which helico-axial pump (1) includes a rotor (2) rotatably journalled about a longitudinal axis (A) in a pump housing (6) and having a first part rotor (21) and a second part rotor (22), wherein the first part rotor (21) and the second part rotor (22) include a compression stage (K, K1E, K1A, K2E K2A) having a helico-axial impeller (3) and a stator (4) for the compression of the multiphase mixture (M). In accordance with the invention, a hydrodynamic stabilization bush (70) having a stabilization surface (700) is provided and formed between the first part rotor (21) and the second part rotor (22) such that a stabilization gap (8) is formed before the stabilization surface (700) so that a hydrodynamic stabilization layer (S) is formed from a stabilization medium (M) in the stabilization gap (8) in the operating state.

Abstract: A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end.

Abstract: A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configured as a full hoop. When the combustion section casing is detached from the engine and moved to a maintenance position to allow access to an interior of the engine, a positioning jig (98) is used to support the compressor section casing (83) and turbine section casing (87).

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.

Abstract: An inner diameter vane seal for a gas turbine engine comprises an annular, ring-like body having inner and outer diameter rims, forward and aft faces and an air passage. The outer diameter rim extends circumferentially for engaging inner diameter ends of stator vanes. The inner diameter rim extends circumferentially and is spaced radially from the inner outer diameter rim. The forward and aft faces extend radially between the outer diameter rim and the inner diameter rim. The air passage extends from the forward face to the aft face between the inner and outer diameter rims.

Abstract: Provided is a compressor that is capable of, with a simple configuration, facilitating the insertion operation of a compressor bundle by reliably preventing tilting thereof during insertion into a chamber; and that also makes it possible to reduce a roller size without increasing the contact pressure of rollers for sliding the compressor bundle. A small tilt sensor that detects a relative angle difference ? of the compressor bundle with respect to the bundle casing is provided at at least one location in the compressor bundle to be inserted into the chamber inside the bundle casing. In addition, the weight of the compressor bundle during the insertion into the chamber is supported by rollers provided at a bottom portion near the front end of the compressor bundle by making the rollers come in contact with an inner circumferential wall surface of the chamber.

Abstract: An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a number of stages in the low pressure turbine is from three to five.