Abstract: A compressor has: a rotor and a shroud having a internal and external sides and an air outlet; an annular case mounted to the external side and enclosing a plenum, the annular case having inner and outer sides and defining an aperture; a valve mounted to the annular case at the aperture and having: a support secured to the annular case and defining a seat surrounding a bleed passage, the seat located on the outer side, the support defining a guiding aperture, and a valve member having a head and a stem slidably received within the guiding aperture, the valve member having a closed position and an open position, the head abutting the valve seat in the closed position and offset from the valve seat in the open position; and an actuator engaged to the valve member for moving the valve member between the closed position and the open position.

Abstract: An apparatus is provided for an aircraft propulsion system. This apparatus includes a duct structure, and the duct structure includes a transition duct, an inlet duct and a bypass duct. The duct structure is configured as a monolithic body. The transition duct includes an inlet, a first outlet and a second outlet. The transition duct extends longitudinally along a longitudinal centerline from the inlet to the second outlet. The first outlet is arranged longitudinally along the longitudinal centerline between the inlet and the second outlet. A centerline axis of the first outlet is angularly offset from the longitudinal centerline. The inlet duct extends longitudinally along the longitudinal centerline to the inlet. The bypass duct extends longitudinally along the longitudinal centerline from the second outlet.

Abstract: A surge control system includes a rotor system with at least one compressor section and at least one turbine section operably coupled to a shaft. The surge control system also includes sensors configured to collect sensor data from the rotor system, an electric motor operably coupled to the rotor system, and a controller. The controller is operable to detect surge event from the sensor data, determine an amount of power to apply to the rotor system, and increase the amount of power provided to the rotor system to recover from the surge event.

Abstract: A compressor bleed apparatus includes: a compressor comprising one or more rotors mounted for rotation about a central axis and enclosed in a compressor casing; a bleed slot passing through the compressor casing; an outer wall defining, in cooperation with the compressor casing, a plenum surrounding the compressor casing; at least one offtake pipe communicating with the plenum; and wherein at least one of the plenum and the bleed slot has a non-axisymmetric structure.

Abstract: A gas turbine engine comprising a housing coupled to an upstream source of hot gas and superheated water droplets, the housing having a centerline, an annular bay section positioned radially away from the centerline and protruding in an upstream direction, a rotatable shaft positioned along the centerline, a fluid mover coupled to the rotating shaft and positioned to receive the hot gas and superheated water droplets from the upstream source and to move the hot gas and superheated water droplets radially toward the annular bay section of the housing, a separator plate that is fixedly coupled to the housing; and an extractive turbine assembly positioned downstream from the separator plate and the annular bay section. The superheated water droplets mix thoroughly with the hot gas inside the annular bay section causing the water droplets to covert to steam, and the steam flows to the extractive turbine, increasing an efficiency of turbine rotation.

Abstract: A cylinder head assembly for an internal combustion engine includes a cast cylinder head and a turbocharger housing integrally cast with the cylinder head and having an integrally cast wastegate housing. The turbocharger housing is configured to receive a turbocharger cartridge rotatably supporting a shaft coupled between a compressor wheel and a turbine wheel. The integrally cast wastegate housing defines a wastegate chamber configured to receive a wastegate valve, a flow of exhaust gas from the turbine wheel, and a flow of wastegate exhaust gas.

Abstract: A waste gate assembly for a turbocharger includes a valve member formed by a valve shaft and an arm attached to an end of the shaft, the arm defining a through bore, an inner surface of the through bore defining an arm groove therein. A poppet for the valve has a pin whose outer surface defines a pin groove. A generally polygonal retaining ring of elastically deformable wire is installed partially in the arm groove and partially in the pin groove to retain the poppet on the pin, thereby attaching the poppet to the arm of the valve member. An anti-rotation feature prevents relative rotation of the poppet about the pin axis. Vertices of the retaining ring are in the arm groove, while sides of the retaining ring are in the pin groove. Once the retaining ring is pre-installed in the arm groove of the arm, the arm can be assembled to the poppet by a push-to-connect process.

Abstract: A cooling arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, an offtake duct that has an offtake inlet coupled to a cooling source, the offtake duct defining a throat, and a valve downstream of the throat. The valve couples the offtake duct and a first cooling flow path. The valve is operable to selectively modulate flow through the offtake duct. A bleed passage includes a bleed inlet coupling the offtake duct and a second cooling flow path. The bleed inlet is defined at a location between the offtake inlet and the throat, inclusive.

Abstract: A compressor system includes an electric motor having a rotatable output shaft extending from either end thereof. The compressor system further includes multiple compression stages fluidly coupled to one another in series and mechanically connected to the output shaft. The first compressor stage includes two split impellers with each impeller discharging approximately one half of the fluid flow at a desired pressure to the second compressor stage.

Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, and a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow from the particulate.

Abstract: An electric propulsion unit (102) for an aircraft is shown. A fan (202) produces a pressured airflow (P) by raising the pressure of an incident airflow (I). An electric machine (201) is arranged to drive the fan and is located within a casing (204). A primary cooling circuit (205) is located within the casing, and includes the electric machine and a first pass of a fluid-fluid heat exchanger (208), thereby placing the electric machine and the fluid-fluid heat exchanger in thermal communication. A secondary cooling circuit includes a second pass of the fluid-fluid heat exchanger and an air-fluid heat exchanger (210) located within the pressurised airflow produced by the fan, thereby placing the fluid-fluid heat exchanger and the air-fluid heat exchanger in thermal communication.

Abstract: An air blower includes an impeller, a motor, a lead wire, and a casing. The impeller rotates around a central axis extending in a vertical direction. The motor rotates the impeller. The lead wire is connected to the motor. The casing houses the impeller and the motor. The casing includes a bottom plate portion, a side wall portion, and a top plate portion. The top plate portion is disposed axially above the impeller and is connected to the upper end of the side wall portion. The casing includes a lead-out port through which the lead wire is led out to the outside in the radial direction. The lead-out port includes a lower portion provided on the bottom plate portion and an upper portion provided on the side wall portion, and the lower and upper portions are defined by different members.

Abstract: A gas turbine includes a rotor that has a rotor disk at each of a plurality of stages and a plurality of blades fixed to the respective stages, a casing, a plurality of vanes fixed to the casing, and an annular member fixed to a radially inner side of each of the vanes. The rotor disk has a seal arm. The annular member has an outer opposing portion that is radially opposed to the seal arm. The gas turbine further includes a seal fin that protrudes from the outer opposing portion toward the seal arm, a first cavity that is defined in the annular member and extends in a circumferential direction to straddle at least two of the vanes, a second cavity that is on a radially inner side of the first cavity, and a plurality of compressed air discharge paths that connect the first cavity to the second cavity.

Abstract: There is provided a method for converting a turbofan engine, including the step of providing a turbofan engine and the step of converting the turbofan engine to provide a converted turbofan engine. The turbofan engine includes a core engine (including at least one high pressure spool assembly and a combustion chamber), and an unmodified fan configured for providing at least a bypass flow bypassing the core engine, the fan being mechanically coupled to a low pressure turbine that is in turn driven by the core engine.

Abstract: A compressor bleed slot apparatus includes: an annular compressor casing; a stator vane row disposed inside the compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing, axially downstream of the stator row; a bleed slot passing through the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot having an inlet positioned axially between the stator vane row and the blade row, 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 annular array of struts interconnecting the inboard and outboard walls; and an annular supplemental flange extending radially outward from the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot.

Abstract: A turbine housing includes: a housing body which includes a turbine housing part housing a turbine wheel, an inlet section forming an inlet flow passage for guiding exhaust gas to the turbine housing part, an outlet section forming an outlet flow passage for discharging the exhaust gas from the turbine housing part, and a waste-gate flow passage which brings the inlet flow passage and the outlet flow passage into communication so as to bypass the turbine housing part; and a sleeve disposed along an inner wall surface of the housing body forming the waste gate flow passage, at least on a downstream side of the waste-gate flow passage of the housing body with respect to a flow direction of the exhaust gas.

Abstract: A turbopump includes a slinger that has a first section and a second section. The first and second sections are disposed substantially radially in a fluid circuit. The second section is downstream of, and radially inward of, the first section. A housing is located downstream and adjacent to the first section of the slinger and radially outward of the second section of the slinger.

Abstract: A high pressure compressor section of a gas turbine engine including: an inner case separating a core flow path of the gas turbine engine and a plenum formed between the inner case and an outer case; a bleed port located on an inner surface of the inner case, the inner surface being proximate the core flow path; an outlet located on an outer surface of the inner case, the outer surface being proximate the plenum; and a bleed air passageway passing through the inner case to fluidly connect the bleed port to the outlet, wherein the bleed air passageway is fluidly connected to the core flow path through the bleed port and the bleed air passageway is fluidly connected to the plenum through the outlet.

Abstract: A turbocharger for a motor vehicle has a housing and a valve seat in the housing. The valve seat is retained in an interlocking manner in the housing by at least one elastic securing element.

Abstract: A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2?J/D?0.6 where D is the hydraulic diameter of an injection orifice.

Abstract: A submersible well pump assembly includes a pump driven by a motor. The pump has a number of stages, each stage including a diffuser having an annular diffuser inlet with an annular outer wall. Diffuser passages lead downstream and inward from the diffuser inlet. An impeller has a circumferential outer edge adjacent the outer wall of the diffuser inlet. Notches are formed in the circumferential outer edge, defining a serrated configuration.

Abstract: An axial compressor comprises a plurality of compressor stages positioned axially adjacent each other within a casing. Each of the plurality of compressor stages includes a rotor segment and a banded stator segment. An annulus is formed between the casing and an outer flowpath ring of the banded stator segment. A pathway may be provided that establishes an air flowpath between the annulus and another annulus formed by an adjacent stage.

Abstract: A wastegate sealing jig (13) includes a base (14) which is fixable to an exhaust portion (11) of a turbocharger (1), the base (14) including a wastegate valve (6), and a turbine hole (12) which discharges exhaust gas in a turbine chamber (4b), a protrusion (15) which is provided in the base (14) so as to extend toward the exhaust portion (11), a valve member (16) which is attached to a distal end of the protrusion (15). The wastegate (5) is closed by the valve member (16) by inserting the valve member (16) between the wastegate (5) and the wastegate valve (6) of the turbocharger (1) in a state in which the wastegate valve (6) is opened.

Abstract: Embodiments of a core-protecting fan module are provided, as are embodiments of a turbofan engine containing such a fan module. In an embodiment, the core-protecting fan module contains a nose member, a fan rotor downstream of the nose member, a full span stator downstream of the fan rotor, and a splitter structure downstream of the fan rotor. The fan rotor includes a plurality of fan blades, which extends from a rotor hub and which is angularly spaced about a rotational axis. Certain fundamental angular relationships are observed between the angles formed by rotational axis, the nose member, the fan rotor, and a leading edge of the splitter structure to reduce contaminant ingestion by the core flow path and to promote moisture shedding to reduce susceptibility to icing within the fan module, while further avoiding or minimizing negative impacts to other structural and functional aspects of the turbofan engine.

Abstract: A gas turbine includes an air cooler that subjects compressed air extracted from a compressor to heat exchange and supplies the cooled compressed air to a cooling system of a rotor system in a turbine; an air cooler bypass line that bypasses the compressed air introduced into the air cooler; an electric valve provided in the air cooler bypass line; and a control unit. The control unit controls opening and closing of the electric valve such that, during activation of a gas turbine, a degree of opening of the electric valve is set at or below a low-level degree of opening and such that, after the load of the gas turbine has been increased, the degree of opening of the electric valve is set to be larger than the low-level degree of opening.

Abstract: A gas turbine engine for an aircraft includes a fan section, a turbine section, a compressor section, and an engine bleed system. The compressor section includes a low compressor stage proximate to the fan section, a high compressor stage axially downstream from the low compressor stage and proximate to the turbine section, and a mid-compressor stage including variable vane assemblies distributed axially between the low and high compressor stage. The engine bleed system includes engine bleed taps with a mid-compressor bleed tap axially between two of the variable vane assemblies, at least one low stage bleed tap axially upstream from the mid-compressor bleed tap, and at least one high stage bleed tap axially downstream from the mid-compressor bleed tap. An external manifold is in pneumatic communication with the mid-compressor bleed tap. A valve system can select one engine bleed tap as a bleed air source for an aircraft use.

Abstract: A bleed air heat ejector includes a housing defining an inner passage extending in an axial direction from an inlet of the housing to an outlet of the housing, wherein the inlet is configured to channel ambient air into the housing, and wherein the outlet is configured to channel mixed heated and ambient air out of the housing. A dispenser is mounted in the housing between the inlet and the outlet. The dispenser includes an inner chamber configured to receive heated air from a bleed line. The dispenser includes a plurality of apertures therein for issuing heated air from the inner chamber into the inner passage of the housing to form a flow of mixed ambient and bleed air. The apertures of the inner chamber can be angled primary jets, vortex generators can be included, and/or secondary jets can be included to promote mixing of bleed and ambient air.

Abstract: A turbo machinery case includes a shell body extending circumferentially about a longitudinal axis and defining therein a main gas path. The shell body defines a first offtake opening and a second offtake opening that extend in a circumferential direction about the longitudinal axis. The first and second offtake openings are defined at a common axial location with respect to the longitudinal axis of the turbo machinery case.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a compressor section driven by the turbine section, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.

Abstract: An assembly can include a turbine housing that includes a bore, a wastegate seat, wastegate passages that extend to the wastegate seat and a divider wall disposed between the wastegate passages where the divider wall includes a divider wall surface; a rotatable wastegate shaft configured for receipt by the bore; a wastegate arm extending from the wastegate shaft; and a wastegate plug extending from the wastegate arm where the wastegate plug includes a contact portion that contacts the wastegate seat to cover the wastegate passages in a closed state and a mesh that contacts the divider wall surface in the closed state.

Abstract: A ram fan device includes a motor disposed in a housing that defines a motor cavity with a fan operatively connected to be driven by the motor and an outlet in fluid communication with the motor cavity. The housing includes a cooling inlet therethrough downstream of the fan and upstream of the motor, the cooling inlet being in fluid communication with the outlet through the motor cavity such that airflow can pass through the cooling inlet through the motor cavity and out the outlet.

Abstract: Methods and systems are provided for a variable inlet device of a compressor. In one example, a compressor may include a casing forming a recirculation passage surrounding an intake passage, an active casing treatment surrounding a wall separating the intake passage and the recirculation passage and adapted to selectively control a flow of gas through a plurality of ports disposed in the wall, and an impeller. Additionally, a variable inlet device may be position in the intake passage, upstream of the impeller, the variable inlet device including a plurality of adjacently arranged blades forming a ring, each of the blades being pivotable, about an axis arranged tangent to the ring, between the open and closed position.

Abstract: Methods and systems are provided for a variable inlet device of a compressor. In one example, a compressor may include an impeller rotatable about a central axis and an inlet conduit including a variable inlet device (VID) positioned upstream of the impeller and adjustable between and open position and a closed position that restricts and generates pre-swirl flow to the impeller. The VID may include a plurality of adjacently arranged blades forming a ring around the central axis with inner surfaces of the blades forming a flow passage through the VID, each of the blades being pivotable, about an axis arranged tangent to the ring, between the open and closed position.

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan delivering air into a bypass duct and into a core engine, a fan drive gear system having a gear carrier, and a fan shaft coupling the fan drive gear system to the fan. The core engine includes a low spool including a low pressure turbine and a low pressure shaft, and a high spool including a high pressure turbine, a compressor, and a high pressure shaft coupling the high pressure turbine to the compressor. A first bearing is forward of the fan drive gear system, and supporting said fan shaft and said fan drive gear system, and a second bearing is aft of the fan drive gear system, and supporting the fan drive gear system.

Abstract: An electric machine includes a rotor, a stator, and a winding. The rotor includes a rotor core and blades extending from the rotor core. Each blade is curved in an axial direction along the rotor core and is simultaneously configured as a pole that carries a magnetic flux of the electrical machine and as an airfoil that compresses a gas when the rotor is rotated. The gas flows axially between successive blades of the blades. The stator includes a stator core and teeth extending from the stator core toward the blades. Slots are defined between successive teeth. The winding is wound through at least two slots. The stator is mounted radially relative to the rotor so that a gap separates the blades from an exterior face of the teeth that is axially aligned along the stator core to follow an axial edge of a blade of the blades.

Abstract: In a control apparatus applied to an internal combustion engine in which when an opening degree of a valve body of a waste gate valve is less than the predetermined opening degree, the extension line intersects a wall surface of an exhaust passage located upstream of the upstream side end face of the exhaust gas purification catalyst, the control apparatus controls the waste gate valve so that at the time of execution of fuel cut off processing, when the temperature of the exhaust gas purification catalyst is less than a predetermined temperature, the valve body is fully closed, whereas when the temperature of the exhaust gas purification catalyst is not less than the predetermined temperature, the opening degree of the valve body is made to a deterioration suppression opening degree which is larger than when the valve body is fully closed and which is smaller than the predetermined opening degree.

Abstract: A compressor section for a gas turbine engine, the compressor section including a circumferential row of stator vanes, a circumferential row of rotor blades, and a casing arrangement. A row of bleed ports are provided in the casing arrangement. Each of the bleed ports extends radially and is curved such that an outlet of the port is rearward of and is circumferentially offset in a direction of rotation of the rotor blades from an inlet of the port.

Abstract: A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades. Each fan blade defines a hub radius (RHUB), which is the radius of the leading edge at the hub relative to a centerline of the fan, and a tip radius (RTIP), which is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than 0.25.

Abstract: A method can include applying a force to a control arm operatively coupled to a shaft; transmitting at least a portion of the force from the shaft, via an arm, to a plug positioned with respect to a wastegate seat of a turbine housing; maintaining an isostatic condition for relative positions of the shaft, the arm and the plug wherein contact exists between the plug and the wastegate seat; and in the isostatic condition, fixing the relative positions of the shaft, the arm and the plug via welding.

Abstract: A variable turbine geometry turbine turbocharger (1) includes a vane pack (50) disposed in the exhaust gas path upstream of the turbine wheel (12). The vane pack (50) includes vanes (30) that are rotatably supported between a pair of vane rings (34) and configured to adjustably control the flow of exhaust gas to the turbine wheel (12). In addition, a retainer (60, 160) secures the vane pack (50) to the bearing housing (16) in such a way that the vane pack (50) is mechanically decoupled from the turbine housing (4).

Abstract: There is provided a gas turbine system including: a compressing portion; a combustor generating a combustion operation by using first compressed air coming from the compressing portion; a turbine portion generating power by using a combustion gas coming from the combustor; a heat recoverer recovering a heat from a discharge gas of the turbine portion; and a compressed air supplier providing second compressed air to which the heat recovered by the heat recoverer is transferred, wherein at least a portion of the second compressed air to which the heat has been transferred is supplied to at least one of the combustor and the turbine portion.

Abstract: A compact flow control valve capable of providing long service life in a very hostile environment. The valve is a mono or dual coaxial slider valve capable of controlling two different functions sequentially, at least one of the functions being controlled progressively. The flow control valve controls the fluid connection between two volutes (6, 7) of a turbine housing (2) of a turbocharger as well as the fluid connection between the two volutes (6, 7) of the turbine housing (2) of the turbocharger and a waste gate port (9).

Abstract: A centrifugal compressor apparatus includes: an impeller mounted for rotation about a central longitudinal axis, the impeller including an impeller disk carrying an array of impeller blades around its periphery; a diffuser disposed downstream of the impeller, configured to diffuse and turn airflow discharged from the impeller; an extraction scoop disposed in fluid communication with the impeller and with a plenum disposed adjacent the impeller, and a dirt collector disposed in fluid communication with the plenum and configured to trap dirt therein.

Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.

Abstract: Airfoils for gas turbine engines are disclosed herein. The airfoils each include a pressure side and a suction side. Vortex-reduction passageways extend from the pressure side to the suction side.

Abstract: A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.

Abstract: A device for bleeding compressor air in a turbofan engine includes a low-pressure compressor of a primary duct, a fan stator arranged in a secondary duct downstream of a fan, and an arrangement for discharging compressor air from the low-pressure compressor into the secondary duct. The arrangement includes air guiding devices to guide compressor air into the secondary duct upstream of the fan stator relative to the flow direction in the secondary duct, past the stator vanes of the fan stator in a separate duct in the axial direction and is only mixed with the air of the secondary duct downstream of the fan stator. The separate duct is formed by a plurality of hollow structures extending in the longitudinal direction each between two adjacent stator vanes of the fan stator, with the hollow structures having a closed circumference in cross-section.

Abstract: A gas turbine compressor including a guide vane (1), a moving vane (2), in particular downstream, and a bleed channel (3) having an upstream channel wall (3.1), which merges into an annular space (5), an axially opposite downstream channel wall (3.2) having an inlet edge (3.3), which is rounded in particular, and a bleed channel outlet, the downstream channel wall enclosing with an axis of rotation of the compressor a first angle (?) which increases in the flow direction (x).

Abstract: A gas turbine engine comprising in axial flow series: a fan having a fan rotor; a series passages defined between adjacent outlet guide vanes for guiding flow from the fan; and a bifurcation. The gas turbine engine further comprises a substantially annular fluid passageway extending from the fan to the bifurcation, the outlet guide vanes being positioned within the passageway. The passageway includes a profiled region.

Abstract: An assembly for a turbine engine includes a plurality of vane segments. The vane segments are fastened together and form an adjustable stator vane that pivots about a variable vane axis. The adjustable stator vane includes a stator vane body, a shaft and a flange. The stator vane body extends axially between a first end and a second end, and includes an airfoil, a body surface and a cavity. The body surface is located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially at least partially around the inlet, and radially from the stator vane body. A first of the vane segments includes the flange. A second of the vane segments includes at least a portion of the airfoil.