Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a flexible supplemental seal is disposed between the support ring and inner band of the nozzle segment radially inwardly of the chordal hinge seal. To minimize or prevent leakage flow across the chordal hinge seal, the flexible seal extends between the inner rail and the sealing surface of the support ring radially inwardly of the chordal hinge seal. A first margin of the flexible seal engages in a linear groove carried by the inner rail. The opposite margin extends arcuately in sealing engagement with the nozzle support ring.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of each nozzle segment radially inwardly of the chordal hinge seal. To minimize or prevent leakage flow across the chordal hinge seal, the seal is formed of flexible sheet metal which extends between the inner rail and a seat projecting from the annular sealing surface of the support ring radially inwardly of the chordal hinge seal. A first margin of the flexible seal engages in an arcuate groove carried by the inner rail. The opposite margin extends arcuately in sealing engagement along the seat carried by the nozzle support ring.

Abstract: The invention relates to a guide vane (17) for a turbomachine (1), in particular a gas turbine guide vane, in which the platform (48) has a separating region (50), which is embodied as a separate component. This has, in particular, advantages with respect to the simplification of cast blade/vane (17) in terms of manufacturing technology, with respect to the variability of a material selection, the quality of a protective coating to be applied and efficient cooling.

Abstract: An axial flow compressor and a method for mounting the stator blades in the compressor. The compressor is comprised of a stator casing having a rotor axially positioned therein. The casing has internal circumferential grooves into which the stator blades are equally spaced therein. Resilient spacers, e.g. leaf spring, are positioned within any spaces which might exist in the groove after all of the blades have been properly spaced around the groove.

Abstract: A steam turbine of the type which incorporates a turbine case defining a plurality of passages having outlets opening through an inside end wall of the turbine case in a direction generally parallel to the turbine shaft, with nozzles positioned over the outlets to direct steam against the periphery of the turbine wheel, can be modified to a higher efficiency design. To perform the modification, the nozzles are removed, an arcuately shaped housing is positioned in covering relationship with the outlets, and an arcuately shaped louver is positioned so as to form an end wall of the housing. The louver has a plurality of vanes to direct the steam against the periphery of the turbine wheel to cause rotation of the turbine shaft and the housing forms a confined steam flow path from the outlets to the louver. The downstream turbine blading can be modified if desired.

Abstract: The present invention provides a seal for a gas turbine engine, comprising an annular ring with an L-shaped cross-section having a radially extending leg and an axially extending leg. A plurality of corrugations are formed in the axial leg so as to make it compliant in the circumferential direction.

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

Abstract: A compliant woven tubular seal is provided in an arcuate cavity opening through an axial face of a plurality of shroud segments in opposition to a nozzle retaining ring. The annular composite tubular woven compliant seal includes a stainless steel inner metal core surrounded by an annular layer of silica fiber. Surrounding the silica fiber is a metal foil which prevents flow past the supplemental seal. An outer wear-resistant braiding serves as a protective covering and wear surface.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a pair of sheet metal shims overlaid by a woven metallic cloth. A bracket and a portion of the supplemental seal are received in a groove along a radial inward facing surface of the inner rail. The projecting margin of the cloth seal bears against the annular sealing surface of the nozzle support ring. The shims of the distal margin of the supplemental seal are slit and staggered in a chord-wise direction relative to one another to provide flexibility and effective sealing engagement with the nozzle support ring.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a pair of sheet metal shims overlaid by a woven metallic cloth supported by a bracket secured to a back side surface of the inner rail. The radially inner end of the cloth seal bears against the annular sealing surface of the nozzle support ring. The shims of the legs of the supplemental seal are slit along their distal margin and staggered in a chord-wise direction relative to one another to provide flexibility and effective sealing engagement with the nozzle support ring.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner band of the nozzle segment on a lower pressure side of the chordal hinge seal. The supplemental seal includes a flexible sheet metal seal having a margin secured in a groove of the inner rail of the nozzle segments with a bent-over edge to form a seal therewith. The opposite margin has an edge which bears against the axially opposed sealing surface of the nozzle support ring. Leakage flow past the chordal hinge seal exerts sealing pressure against the preloaded flexible seal to maintain the seal between the sealing surfaces of the support ring and segments. The supplemental seal extends circumferentially and spans the joint between adjacent nozzle segments.

Abstract: A guide vane stage of a compressor comprising an outer ring and an inner ring, both of which are concentric and preferably circular is provided. The rings are connected to each other via a series of fixed vanes, characterized in that at least one of the rings is provided with a series of holes or apertures which allow the vanes to pass through these holes or apertures. The fixed vanes also have, at at least one of their ends, an aperture to allow at least one locking element to pass through, making it possible to simultaneously securely fasten all the present in the guide vane stage, on the non-functional side of the ring. The end of the fixed vanes through which the locking element passes is buried in an elastomeric element.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a pair of sheet metal shims overlaid by a woven metallic cloth supported by a bracket secured to a back side surface of the inner rail. The radially inner end of the cloth seal bears against the annular sealing surface of the nozzle support ring. The shims of the legs of the supplemental seal are slit along their distal margin and staggered in a chord-wise direction relative to one another to provide flexibility and effective sealing engagement with the nozzle support ring.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner band of the nozzle segment on a lower pressure side of the chordal hinge seal. The supplemental seal includes a flexible sheet metal seal having a margin secured in a groove of the inner rail of the nozzle segments with a bent-over edge to form a seal therewith. The opposite margin has an edge which bears against the axially opposed sealing surface of the nozzle support ring. Leakage flow past the chordal hinge seal exerts sealing pressure against the preloaded flexible seal to maintain the seal between the sealing surfaces of the support ring and segments. The supplemental seal extends circumferentially and spans the joint between adjacent nozzle segments.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a pair of sheet metal shims overlaid by a woven metallic cloth. A bracket and a portion of the supplemental seal are received in a groove along a radial inward facing surface of the inner rail. The projecting margin of the cloth seal bears against the annular sealing surface of the nozzle support ring. The shims of the distal margin of the supplemental seal are slit and staggered in a chord-wise direction relative to one another to provide flexibility and effective sealing engagement with the nozzle support ring.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner bands of the nozzle segments on a lower pressure side of the chordal hinge seals. To minimize or prevent leakage flow across the chordal hinge seals, a generally U-shaped supplemental seal having reversely folded U-shaped marginal portions is received in a cavity formed in the axially extending sealing surface of the inner rail of the nozzle segment. At operating conditions, the marginal portions seal against the base of the cavity and the annular sealing surface of the nozzle support ring to prevent leakage flow past the chordal hinge seal from entering the hot gas path.

Abstract: A turbine nozzle includes segments of outer and inner bands supporting corresponding vane pairs. The bands adjoin each other at corresponding ends along splitlines, with each band having a forward land, an opposite aft land, and a middle land extending therebetween. The forward lands have a nominal aft-facing step, the aft lands have a nominal forward-facing step and the middle lands are nominally flush.

Abstract: An inner shell of a steam turbine has discrete arcuate steam outlet ports through an axial face. In axial opposition is a nozzle ring including a pair of nozzle ring segments joined at a horizontal midline. At the midline joint, split partitions are employed to provide a full 360° discharge through the nozzle ring. The split partitions are split in an axial direction to define discrete partition portions in each of the nozzle ring segments adjacent the midline joint.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment. The supplemental seal is formed of a preloaded flexible sheet metal seal having a first margin secured in a linear groove extending in a tangential direction along the inner rail of the nozzle segments with a bent-over edge to form a seal therewith. The opposite second margin has an edge which bears against the axially opposed sealing surface of the nozzle support ring. Sealing pressure against the preloaded flexible seal from a high pressure region maintains the seal between the sealing surfaces of the support ring and segments. The supplemental seal extends tangentially and end edges thereof overlap one another to form a seal between adjacent nozzle segments.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner band of the nozzle segment on a lower pressure side of the chordal hinge seal. To minimize or prevent leakage flow across the chordal hinge seal, a generally U-shaped portion seals between radially opposed surfaces of the nozzle support ring and inner band, the legs of the U-shaped portion engaging those surfaces. In a further embodiment, an arcuate sheet metal supplemental seal having a sinuous shape is disposed and seals between the radially opposed surfaces of the nozzle support ring and inner band, respectively.

Abstract: A system for supporting bolted upper and lower diaphragms to one another in an outer housing of a turbine includes support screws threaded into bores adjacent opposite sides of the lower shell. The head of each support screw has a threaded bore receiving a set screw. The set screw has a length equal to the depth of the slot in which the head resides in the lower shell, minus a small clearance. With the diaphragms supported by the engagement of the set screw at the lower end with an abutment at the bottom of the slot, the clearance enables the diaphragms to move vertically upwardly, limited by the clearance distance.

Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a sheet metal seal supported by a bracket secured to the back side and radial inner surfaces of the inner rail. The sheet metal seal has a flexible margin which is preloaded and bears against the annular sealing surface of the nozzle support ring. The bracket is bolted or welded to the inner rail with the sheet metal seal therebetween inhibiting or precluding leakage past the back side of the supplemental seal.

Abstract: A nozzle lock for circumferentially securing a nozzle segment relative to the engine casing of a gas turbine engine. The nozzle lock includes a thickener pad joined to an outer surface of the engine casing and a locking member disposed in a notch located in the outer band of the nozzle segment. A pin formed on the locking member is press-fit into the casing and the thickener pad.

Abstract: A system for supporting bolted upper and lower diaphragms to one another in an outer housing of a turbine includes support screws threaded into bores adjacent opposite sides of the lower shell. The head of each support screw has a threaded bore receiving a set screw. The set screw has a length equal to the depth of the slot in which the head resides in the lower shell, minus a small clearance. With the diaphragms supported by the engagement of the set screw at the lower end with an abutment at the bottom of the slot, the clearance enables the diaphragms to move vertically upwardly, limited by the clearance distance.

Abstract: A segmented vane support structure for use in a gas turbine engine having an engine casing, includes a single piece inner ring and separated front outer and rear outer rings. The vane segments circumferentially abut to form a stator ring which is clamped at the respective opposed outer ends by the front outer and rear outer rings therebetween onto the inner ring. The front outer and rear outer rings are axially restrained to the engine casing by a retaining ring which is fitted in an inner annular groove of the engine casing. Each vane segment has a lug member at its outer diameter which radially and slidably engages in a slot of the engine casing to provide angular positioning of the vane segments within the engine casing and to transmit circumferential vane load into the engine casing. This support structure arrangement transmits circumferential loading to the engine casing and isolates radial loading from the engine casing caused by thermal growth changes of the vane segments.

Abstract: The invention concerns an apparatus for supporting blades of axial-flow machines, in particular turbojet propulsion units, which is distinguished by at least one pair of mutually oppositely disposed support rings (12, 14) which are supported adjustably relative to each other for assembly between guide or rotor blades of adjacent compressor or turbine stages.

Abstract: At least one airfoil shaped vane made of a low ductility material, for example a ceramic base material such as a ceramic matrix composite or an intermetallic material such as NiAl material, is releasably carried in a turbine vane assembly including inner and outer vane supports by at least one high temperature resistant compliant seal. The seal isolates the vane from at least one of the vane supports and allows independent thermal expansion and contraction of the vane in respect to the support.

Abstract: An airfoil for use in a gas turbine engine. The airfoil includes a body having an interior surface defining a hollow cavity in the airfoil having an inlet and an outlet. The airfoil also includes a partition within the cavity dividing the cavity into a first cooling passage and a second cooling passage. The first cooling passage communicates with the inlet for delivering cooling air to the first passage and the second cooling passage communicates with the outlet for exhausting cooling air from the second passage. The partition has a cooling hole therein extending between the first passage and the second passage permitting cooling air to pass from the first passage to the second passage. The cooling hole is sized and positioned with respect to the interior surface of the airfoil for directing cooling air toward a portion of the interior surface of the airfoil so the cooling air impinges upon the portion.

Abstract: A gas turbine engine nozzle includes outer and inner bands. Each of the bands includes segments circumferentially adjoining at corresponding splits. The splits of the inner band are circumferentially spaced from the splits of the outer band. A plurality of vanes are fixedly joined to the outer and inner segments which collectively define an accordion loadpath therethrough.

Abstract: A reversible nozzle (10), removably attached to a fluid emitting base, such as a half turbine casing (22). The reversible nozzle (10) has a nozzle body (16) and a nozzle tube (12), with the nozzle body (16) preferably forming a plurality of fastener receiving slots (18, 18a). The nozzle tube (12) is angled with respect to the nozzle body (16). An installed reversible nozzle (10) is reversed by removing fasteners (34) connecting the nozzle body (16) to the fluid emitting base (22), rotating the nozzle body (16) about a normal nozzle body axis X, and resecuring the reversible nozzle (10) to the fluid emitting base (22) with fasteners (34). To aid in the alignment of the reversible nozzle (10), one fastener receiving slot (18a) is preferably elongated.

Abstract: The present invention relates to an improved system for installing a vane in a gas turbine. The system includes a receptor pocket positioned within a first support structure and a boot attached to a first or inner end of a vane for insertion into the receptor pocket. In a first embodiment of the present invention, the receptor pocket is formed by machining it into the support structure. In a second embodiment of the present invention, the receptor pocket is formed by an insert which is installed into the support structure. In accordance with the present invention, the inner end of the vane having the boot is first inserted into the receptor pocket. After insertion has been completed, the vane is rotated until an outer base is brought into position against an outer support structure. The outer end of the vane is then secured to the outer support structure using studs and nuts.

Abstract: A leaf seal assembly is secured to the trailing edge of a shroud segment for sealing between the shroud segment and the leading edge side wall of a nozzle outer band. The leaf seal includes a circumferentially elongated seal plate biased by a pair of spring clips disposed in a groove along the trailing edge of the shroud segment to maintain the seal plate in engagement with the flange on the leading edge side wall of the nozzle outer band. The leaf seal plate and spring clips receive pins tack-welded to the shroud segment to secure the leaf seal assembly in place.

Abstract: A device for positioning of nozzles of a stator stage and for cooling of rotor discs in gas turbines, of the type including nozzle segments consisting of several airfoils. Each nozzle segment is connected at its top to an outer ring to define a chamber containing cooling air and is positioned at its base on an inner ring. The nozzle segments form a circumferential array about the axis of the gas turbine. In each airfoil of the nozzle segment, there is provided at least one tube, which is inserted in a corresponding duct inside the airfoil for delivering cooling air to the first and second stage discs.

Abstract: A nozzle stage segment includes inner and outer bands spaced radially one from the other with a nozzle vane therebetween. The outer band includes a wall defining a portion of the hot gas path flow through the turbine and an outer cover defining a chamber with the outer wall. The vane includes a vane extension integrally cast with the nozzle segment and extending into a vane extension on the cover. The cover mounts a forward hook for structurally mounting the nozzle segment to a fixed part of the turbine casing, thereby establishing a structural load path through the hook, the cover extension and the vane extension upon welding the extension to one another and the outer wall and cover to one another. Cavities in the vane open into the chamber to receive a cooling medium and which cavities and chamber form part of a closed circuit cooling path through the nozzle stage segment.

Abstract: A turbine diaphragm adapted to be supported in a lower turbine shell component includes a first diaphragm half portion having a pair of diametrically opposed horizontal joint surfaces and a second diaphragm half portion having a similar pair of diametrically opposed horizontal joint surfaces. The first and second diaphragm half portions are identical and interchangeable. Each diaphragm half portion is formed with mounting slots for receiving a support bar engageable with the lower turbine shell component, and with identical joint bolt holes to thereby insure interchangeability of the first and second diaphragm half portions.

Abstract: A support and locking device for nozzles of a high-pressure stage in gas turbines comprises a plurality of groups of stator vanes, which are associated with a plurality of outer sealing plates, for connection of the groups to the outer liner of the combustion chamber, and are associated with a plurality of inner sealing plates, for connection of the groups to the inner liner of the combustion chamber. Each of the groups of stator vanes is locked by an inner ring, and the ring has a first series of outer holes to reinforce this locking, and a second series, of inner, through holes, which are provided in an inner extension of the ring and are used to secure the ring itself to the structure of the gas turbine.

Abstract: A network switch for network communications includes at least one data port interface supporting a plurality of data ports transmitting and receiving data. A CPU interface is configured to communicate with a CPU, and an internal memory communicates with the at least one data port interface. A memory management unit is provided for communicating data from at least one data port interface and the memory. A communication channel is provided, for communicating data and messaging information between the at least one data port interface, the memory, and the memory management unit. The configuration of the network switch also includes a fast filtering process, with the fast filtering processor filtering packets coming into the at least one data port interface. Selective filter action is taken based upon a filtering result.

Abstract: An axial flow power tool turbine motor for operation with an elastic fluid, like pressured air, includes a housing (12), a rotor (11) rotatively journalled in the housing (12) and formed in one piece with drive blades (24) arranged in axially spaced circumferential rows (C, A, C, E, G, I, K), and a stator (10) in the form of a tubular body (22) which is immovably supported in the housing (12) and which carries internal guide vanes (23) arranged in circumferential rows (B, D, F, H, J), wherein the tubular stator body (22) is divided into three longitudinal sections (22a, 22b, 22c) with which the guide vanes (23) are integrally formed, and a retainer (27, 29) for fixing and mounting the longitudinal sections (22a, 22b, 22c) in accurately defined relative positions to form the tubular stator body (22).

Abstract: A diaphragm support bar for a turbine diaphragm comprising a vertical body portion having a support flange extending substantially perpendicularly from an upper end of the vertical body portion and adapted to be supported on a turbine shell component; and a dovetail extending substantially perpendicularly from a lower end of the vertical body portion and adapted to be received within a matching dovetail slot in the diaphragm.

Abstract: An engine turbocharger includes a turbine inlet scroll for conducting exhaust gas from a laterally offset position to the annular inlet of a turbine wheel. An outer wall defines a generally S-shaped passage connecting an inlet flange with concentric annular outlet flanges aligned on laterally spaced parallel axes. An inner wall positioned near the outlet end of the turbine inlet duct defines an annular passage portion for distribution of exhaust gas to the turbine inlet. Three annularly spaced struts or vanes support the inner wall within the outer wall slightly upstream from the outlet flanges of the scroll. A straight vane is positioned on the central plane of the turbine inlet scroll to support the wall with the least possible interference with gas flow.

Abstract: A turbomachine stator vane set includes a ring of vanes having platforms arranged in a housing formed on an outer shell. The bottom of the housing has a non-planar surface which is spherical or cylindrical with a radius of curvature R, and the cooperating surface of the platforms has a corresponding non-planar surface which is spherical or cylindrical with a larger radius of curvature R+&Dgr;R prior to fitting and which is reduced to the radius R under stress, by the action of fastening rivets used to assemble the vane platforms with the outer shell.

Abstract: A seating spring is provided for a gas turbine engine compressor stator having a casing with a circumferential casing slot for mounting a plurality of vane sectors at outer bands thereof. The seating spring has at least one reaction tab configured to abut the casing at one side of the casing slot and a spring arm connected to the reaction tab and configured to abut a respective one of the outer bands to bias the outer band against the casing at a second side of the casing slot. A retention arm is connected to the reaction tab and engages the casing so as to be prevented from moving radially outward. The spring arm is thereby retained in contact with the outer band.

Abstract: A turbocharger includes a rotor having coaxial turbine and compressor wheels. In a preferred embodiment, a turbine inlet scroll conducts exhaust gas toward the turbine wheel and an exhaust duct carries exhaust gas away from the turbine wheel. A turbine nozzle ring coupled between the inlet scroll and the exhaust duct defines an annular passage including angled stator blades and vanes that direct gas angularly against energy converting blades of the turbine wheel. Ring seals at outer and inner edges of the nozzle ring inlet end seal the inlet end against loss of gas pressure. They may also form springs that axially bias the nozzle ring against a stop to fix the axial position of the nozzle ring. The nozzle ring is centered by radial guides at the outlet end which may include at least three radial keys on the nozzle ring engaging mating guide slots connected with the exhaust duct.

Abstract: A vane element adapted for assembly with a plurality of further vane elements to form a ring of vanes for a low pressure gas turbine. Each vane element has a vane blade with platforms at its outer and inner ends, the platform at the outer end being adapted for connection to a housing. Each platform has a flange integral with the vane blade and an outer wall spaced radially from the flange and joined thereto by a radial wall having a lateral projection. Opposite the projection, a recess is formed between the flange and the outer wall, the recess having a shape corresponding to that of the projection so that a plurality of the vane elements can be assembled to form the vane ring by engaging the projection of one vane element in the recess of an adjacent vane element. The projections are form-fit in the recesses so that the platforms of the vane elements are flush with one another.

Abstract: A low pressure-side first-stage compressor impeller and a high pressure-side second-stage compressor impeller are mounted respectively on opposite ends of a rotation shaft. A rotor of an electric motor for driving the two impellers is formed at a central portion of the rotation shaft. A stator of the motor is held by a motor casing. The motor casing, a first-stage compressor casing, which cooperates with the first-stage compressor impeller to form a first-stage compressor, and a second-stage compressor casing, which cooperates with the second-stage compressor impeller to form a second-stage compressor, are cast into an integral construction. This integral casing is further formed integrally with an intermediate cooler, disposed downstream of the first-stage compressor, and a discharge cooler disposed downstream of the second-stage compressor.

Abstract: Apparatus and method for directing a flow of fluid to a turbine via a nozzle box mountable to encircle a shaft. The nozzle box includes a housing having an inner wall spaced from an outer wall and joined therewith so as to form a chamber therein. The housing also includes at least one inlet and at least one outlet in which each is in fluid flow communication with the chamber. A plurality of radially projecting nozzles are positioned between the inner and outer walls and located upstream of the outlet for directing the flow of fluid through the outlet. A flow distributor is positioned between the inner and outer walls and located upstream of the nozzles for directing the flow of fluid through the chamber and to the nozzles. The flow distributor is configured to obtain a substantially uniform flow of fluid to the nozzles.

Abstract: A turbine nozzle includes a plurality of vanes joined at opposite ends to outer and inner bands. The inner band has a forward hook which is segmented to reduce thermal mismatch. And, in additional embodiments the vane includes an impingement baffle having preferential cooling.