Abstract: A gas turbine stationary blade unit in which two stationary blades are formed in a single segment by divided shrouds functions to lessen the occurrence of cracks. Two stationary blades 1a, 1b are fixed to an outer shroud and an inner shroud, respectively. Each shroud is divided into two sections 2a, 2b and 3a, 3b. Flanges 4a, 4b are provided to connect the section together by bolts via boltholes 7. Likewise, flanges 5a, 5b are provided to form a similar connection or joint. If the two stationary blades 1a, 1b are fixed in a single segment by the shrouds which are not divided, a restraining force becomes larger, local stress occurs due to thermal stress and the frequency of crack occurrence increases. However, since the shrouds are divided respectively into two parts and jointed together by bolts, the crack occurrence is lessened. Also, pinholes are provided in opposing faces at the divided portion of the shrouds.

Abstract: A sealing element seals a gap which may be formed between two components that are movable thermally relative to one another. Each component has a component groove located one opposite the other. The sealing element is directed along a center line, in a cross-section essentially perpendicular to a main line, and has a first end, a second end located opposite the first end and a toothed middle region located between the ends. The sealing element is suitable in particular for sealing off a gap between guide blades at high temperatures in a gas turbine plant for the purpose of preventing a gas flow out of a cooling-gas region into a hot-gas region. A gas turbine plant is provided with the sealing element for sealing the gap.

Abstract: The present invention relates to a seal interposed between platforms of blades for a fan in an axial gas turbine engine. Modern impact resistant fan blades have larger interplatform gaps. As a result, the interplatform seals have to seal a large gap. The seal is stiffened such that it can withstand centrifugal forces due to fan operation. In addition, various construction details are developed for the stiffened seal.

Abstract: An exhaust gas turbine for an exhaust gas turbocharger has a nozzle ring having an inner ring and an outer ring supporting a plurality of guide vanes. The nozzle ring is diagonally supported between a covering ring and the inlet casing, with the outer ring bearing against the covering ring and the inner ring bearing against the inlet casing. The outer ring provides an axial expansion gap with gas inlet casing and a radial expansion gap with the gas outlet casing. The nozzle ring is free to expand into the axial and radial gaps as a result of thermal expansion, without causing stress to the adjacent components.

Abstract: The present invention relates to a seal interposed between platforms of blades for a fan in an axial gas turbine engine. Modern impact resistant fan blades have larger interplatform gaps. As a result, the interplatform seals have to seal a large gap. The seal is stiffened such that it can withstand centrifugal forces due to fan operation. In addition, various construction derails are developed for the stiffened seal.

Abstract: In order to create an adjusting ring for the synchronous alteration of the angle of pitch of guide vanes of a compressor having several bearing points for mounting on a compressor housing of the compressor, which can be manufactured at least partially from materials with a low coefficient of thermal expansion and is, nevertheless, compatible with a metallic compressor housing with respect to temperature, it is suggested that the adjusting ring comprise curved ring segments each arranged between two adjacent bearing points, the curvature of the ring segments decreasing during an increase in the temperature of the ring segments so that the bearing points between the ring segments are displaced outwards in a radial direction.

Abstract: An improved heat insulation assembly for a thermal turbo-engine having hollow spaces, is provided with the assembly including a heat-insulating material enclosed within a heat-resistant cover that is formed such that it permits an increase in the inner volume, and the heat-insulating material being a heat-insulating material which increases its volume upon heating to such an extent that the cover is expandable until contact with the inner side of a corresponding hollow space.

Abstract: A turbine nozzle includes a circumferentially continuous annular outer band, and a plurality of circumferentially spaced apart vanes extending radially inwardly therefrom. A circumferentially segmented inner band is joined to the vanes and is disposed coaxially with the outer band. The inner band includes a plurality of circumferentially adjoining arcuate segments, adjacent ones of which have circumferentially facing end faces spaced apart to define a gap therebetween. In an exemplary embodiment, strip seals are inserted in corresponding slots formed in the end faces to seal leakage therebetween.

Abstract: A turbine shroud hanger is supported from an annular outer casing and includes an annular radial flange and integral forward and aft legs at a radially inner end thereof. The legs extend axially oppositely to each other and include respective distal ends configured for supporting a plurality of arcuate shroud panels radially above a plurality of turbine rotor blades to define a tip clearance therebetween. The legs include circumferentially spaced apart forward and aft slots extending axially from the distal ends thereof toward the radial flange, and completely radially therethrough to bifurcate the legs into circumferential segments for reducing transient thermal expansion of the hanger to reduce in turn expansion of the tip clearance.

Abstract: A removable inspection hole plug for sealing a plurality of inspection holes formed in a double-walled enclosure is disclosed in which individual sealing units are disposed in each of the inspection holes, with the individual sealing units linked together by a link rod pivotally attached to each of the sealing units. A seal is provided on each of the sealing units which slideably engages a wall defining the inspection hole and the link rod may be attached to the sealing units by a ball and socket swivel joint. One of the sealing units is attached to a housing which is, in turn, removably attached to the enclosure such that the sealing unit may undergo limited axial movement relative to the housing. This accommodates differential thermal expansion between the walls of the enclosures and also facilitates removal of the inspection hole plug by merely unfastening the housing from the enclosure and removing the housing along with the sealing units.

Abstract: An arrangement for sealing structural members particularly in the case of turbo-engines is provided. A structural member is to be divided along a first plane into segments, which can be moved relative to one another, and is to be movable in a second plane which is angularly offset with respect to the first plane. Projections of the segments sealingly engage in a groove of an additional structural member. Expansion gaps, which are arranged between abutting edges of the segments, are to be sealed off longitudinally and transversely with respect to the course of the gap by sealing plates. In this case, each expansion gap is to be sealed off between a sealing plate arranged transversely to the course of the gap and an opposing surface of the groove acting as a sealing surface by means of a V-shaped insert.

Abstract: A coolable outer air seal assembly for a gas turbine engine is disclosed. Various construction details are developed which provide an outer air seal assembly comprised of a plurality of seal segments including bumpers adapted to maintain adequate cooling fluid flow through the clearance gap between adjacent seal segments. In one particular embodiment, each seal segment includes a mating surface having a plurality of bumpers disposed adjacent to cooling fluid channel outlets and an axially extending ridge disposed along the radially outer edge of the mating surface. The bumpers extend circumferentially a distance H.sub.b to maintain a minimum opening G.sub.min between adjacent seal segments and extend a radial distance W.sub.b to restrict fluid from flowing axially through the clearance gap. The ridge extends radially outward to define in part a seal edge for engaging a feather seal.

Abstract: In a gas turbine engine tip clearance between rotor blades and an encircling shroud liner is controlled by moving the shroud liner radially to match the thermal and centrifugal growth of the rotor assembly. The shroud liner segments are suspended between two axially displaced control rings located in a passageway carrying air ducted from the compressor. One control ring responds very quickly to changes in gas temperature corresponding to centrifugal growth and blade thermal growth. The other ring responds very much more slowly and corresponds to the thermal growth of the disc. The shroud liner segments are suspended from the control rings to adopt a position that constitutes the average between the growth positions of the two control rings.

Abstract: A guide vane ring having guide vanes is provided on two rings which are arranged coaxially and radially at a distance from one another. These two rings are held on assigned housing sections which are subjected to thermally different expansions. One ring is rigidly connected with the guide vanes, and the other ring is connected with the free ends of the guide vanes by the compressive force of a tensioning element. In addition, the other ring is divided into several piston-ring-type elements which axially follow one another and which are each slotted approximately axially and form a cylindrical sliding surface for the whole free ends of the vanes. The tensioning element is arranged on the one group of assigned housing sections while forming a radial compressive force distributed uniformly on the elements.

Abstract: A compressor outlet guide vane (OGV) assembly includes inner and outer annular OGV walls, having outlet guide vanes mounted therebetween, are in abutting relationship with the corresponding leading edges of respective inner and outer diffuser casings and not welded to or otherwise supported by the leading edges of the diffuser casings as in the prior art. The OGV assembly is attached to an annular OGV support member that extends from a portion of a corresponding OGV wall circumscribing the thick section of the OGVs. This assembly decouples the inner and outer OGV annular walls from moments or thermally induced radial loads that may be transferred to the OGV walls due to the interface of the diffuser casings and OGV walls and which may in turn induce failure causing stresses in the OGV trailing edges.

Abstract: A multi-stage centrifugal pump wherein a casing surrounds an impeller and a fluid flow guiding insert in each pump stage. The casing is made of a ferritic material, and the inserts are made of an austenitic material. The casing defines with each insert a first clearance wherein a cylindrical surface of the casing is surrounded by a cylindrical surface of the respective insert so that the width of the clearance increases in response to heating of the inserts and of the casing at the respective first clearances. The casing further defines with each insert a second clearance which is disposed radially outwardly of the respective first clearance and wherein a frustoconical surface of the casing surrounds a complementary frustoconical surface of the respective insert so that the width of each second clearance decreases in response to heating of the casing and of the inserts at the respective second clearances.

Abstract: A joint connection for abutting, circumferentially extending segments in a gas turbine engine, such as turbine nozzle segments, includes a sealing member which is insertable between longitudinally extending slots formed in the abutting side edges of two adjacent segments. The segments are each formed with a number of grooves which are longitudinally spaced along the length of the slots therein, and which extend beneath the sealing member carried within the slots. A cooling air flow path is thus formed extending from one side of the sealing member, into the longitudinal slot of each segment and then through the grooves to the opposite side of the sealing member so that the entire joint connection or seal region between the abutting side edges of the segments is cooled.

Abstract: A casing around a turbine and a casing around discharge nozzles have a concentrically arranged shell portion. The seal contains internal pressure while accommodating eccentric, expansion and axial travel. Arcuate seal segments have one leg sealing against a radial surface extending from the inner shell and the other leg against the outer shell. A linkage guides travel of the segments.

Abstract: To prevent overheating of the gaps between shroud segments circumferentially arranged about a high pressure turbine rotor, an improved seal is provided to block radial leakage flow of hot working gas through the gaps, as well as to restrict axial flow of working gas in the gaps. The seal includes a corrugated, axial fluid flow restricting element sandwiched between a pair of radially spaced, gap spanning shim sealing elements. Pressurized cooling air is admitted to the gap at locations between the shim sealing elements via passages through adjacent shroud segments to cool the gap and to further restrict working gas axial flow in the gap.

Abstract: A turbine support for reacting structural loads from a rotor bearing cage to a case of a gas turbine engine. The turbine support includes a homogeneous main casting and a rotor bearing cage. The main casting has concentrically arranged inner, intermediate and outer walls. The bearing cage is radially inboard and a rigid appendage of the inner wall. The inner and intermediate walls define therebetween a longitudinal segment of the annular hot gas flow path of the engine. The outer wall is bolted to the engine case. The inner wall is connected to the intermediate wall by a plurality of generally radially oriented, angularly separated inner load bearing struts of the main casting. The outer wall is connected to the intermediate wall by a plurality of radially oriented, angularly separated outer load bearing struts of the main casting.

Abstract: A turbine blade shroud assembly for a gas turbine engine includes a metal substrate ring on the engine, a continous ceramic barrier ring inside the substrate ring and exposed to hot gas in a hot gas flow path of the engine, and a wire mesh compliant ring between the barrier and substrate rings. The temperature of the barrier ring increases faster than the temperature of the substrate ring as the temperature in the hot gas flow path increases. The coefficient of thermal expansion of the substrate ring is less than the coefficient of thermal expansion of the barrier ring so that the barrier ring expands relative to the substrate ring with increasing temperature in the hot gas flow path and development of tensile hoop stress in the ceramic barrier ring is minimized.

Abstract: An improved lightweight frame for gas turbine engine is disclosed. The frame includes a hub and a radially spaced casing with two rows of circumferentially spaced tie rods extending between the hub and the casing. In a preferred embodiment, jam nuts are provided on the tie rods for accommodating compressive loads therein. The tie rods are pretensioned so that during operation in a gas turbine engine, for example, wherein the tie rods are heated by combustion gases, thermal expansion of the tie rods and resulting compressive stress will be accommodated by the pretension so that in a preferred embodiment the tie rods may operate nearly stress free at normal operation. The two rows of tie rods and jam nut pairs allow the frame to accommodate effectively blade-out loads channeled to the frame 30.

Abstract: The compact structural assembly comprises a gas generator, and two turbopumps for feeding the combustion chamber of a chamber of a rocket engine with propellants. A main structure which is essentially circularly symmetrical about the axes of rotation of the turbopumps and made of thermostructural composite materials surrounds the turbines and fixes together the body of the gas generator and the pump bodies of the turbopumps. Internal partitioning elements added to the main structure and likewise made of thermo-structural composite materials serve to divide the space inside the main structure into a plurality of intercommunicating cavities allowing hot gases from the gas generator to flow to the turbines, and also serving to collect the outlet gases from the turbines and exhaust them through a common exhaust duct.

Abstract: A fully-floating inlet flow guide for a double-flow steam turbine includes a pair of partially overlapping, generally cylindrical sealing rings circumscribing a turbine rotor adjacent a steam inlet with each of the bands being coupled to a respective one of a pair of first stage nozzle rings positioned on opposite sides of the inlet for directing steam into an axial flow path. The rings are provided with an annular seal at their overlapping portions such that axial expansion and contraction is accommodated without steam leakage through the seal. Radial expansion and contraction of the sealing rings is accommodated by attachment of each ring to a respective nozzle using a circumferential groove in a radially inner surface of each nozzle ring diaphragm and a tongue on each of the rings which fits into a respective groove. Each tongue has a plurality of circumferentially spaced slots and a block slidingly positioned in each of the slots.

Abstract: A split casing (10) of low, coefficient of expansion material, has internal upstream facing slots (12). A semicircular shroud ring (16), of high coefficient of expansion material, carries the vanes (18), and has a tongue (20) sliding within casing slot (12). Casing stop lugs (14) and shroud stop lugs (22) have mutually abuttable surfaces (70,72) to antirotate the shroud within the casing. The distance between abuttable surfaces of the casing is greater than the distance between abuttable surfaces of the shroud ring at room temperature, but the distance are the same at the long time operating temperature.

Abstract: A lightweight rigid turbine engine frame incorporates a one piece annular cast outer casing formed with a circumferential polygonal reinforcing section. The outer casing is separated and spaced from an inner ring by a plurality of radially extending spacer struts. The spacer struts are clamped in compression between the inner ring and outer casing by tensioning members such as bolts. A thermally free floating heat shield is mounted to the bolts in a manner which minimizes thermal stresses by avoiding all undesirable constraint of the heat shield by the engine frame.

Abstract: A stator assembly 20 for a rotary machine 10 includes an outer case 22 and an inner case 56 which is positioned from the outer case. The inner case is formed of segments 76 which overlap and which are relatively slidable in the circumferential direction. Various construction details are developed to keep the segments in an overlapping relationship. In one embodiment, a fastener 104 and slot 102 configuration are used to limit relative circumferential movement between the segments.

Abstract: Methods and apparatus for vane segment alignment and support in a combustion turbine. The vane segment alignment device is comprised of a rotatable, eccentric bushing and pin which is inserted into a slot of the vane segment. The eccentric bushing is further comprised of a cover plate which is peened to a splined torque plate thus holding the eccentric bushing in place against the vane segment but allowing for fine adjustments of the alignment of the vane segments. The vane segment support and alignment device provides for efficient and economical adjustment of the vane segments especially in electric generating plants where combustion turbines undergo high peak load operation. Additionally, the vane segment support and alignment device transfers torques and moments generated by aerodynamic flow from the vane segments to an inner cylinder thereby reducing the amount of misalignment due to aerodynamic drag.

Abstract: In an axial flow turbine having a casing disposed about a rotor, a liner also disposed about the rotor and in a radially spaced relationship with the casing, such that the spaced relationship defines an annular opening, and an annular row of stationary blades positioned within the annular opening, apparatus for maintaining the efficiency of said turbine is shown to include a sealing mechanism, connected to the stationary blades, for preventing motive fluid applied to the annular opening from circumventing the stationary blades so that the efficiency of the turbine is maintained. The sealing mechanism includes a pair of sealing bars disposed between the stationary blades, the casing and the liner.

Abstract: The invention is aimed at avoiding excessive wear of the tips of the turbine blades in deceleration of a gas turbine engine, and provides a control ring which is loosely supported by fixed structure. The control ring is made from a material which reacts more slowly to thermal changes than the support structure and firstly being loosely supported thereby, avoids the stresses which would be otherwise experienced by the fixed joining of differing materials for operation in varying temperatures. Secondly, on deceleration of the associated engine with consequent fall in operating temperature, the control ring contracts more slowly than the turbine assembly and so avoids engaging the shrouds abradable linings with the tips of the blades.

Abstract: A nozzle assembly for a turbine engine comprises an annular ceramic-matrix composite hub having integral radially outwardly extending vanes, and a pair of annular ceramic-matrix composite shrouds which interlockingly engage and secure the radially outermost ends of the vanes, whereby the hub is peripherally supported. The quasi-isotropic laminate structure of both hub and shroud materials generates like physical properties radially and circumferentially in the hub, and axially and circumferentially in the shrouds. Such quasi-isotropism in turn provides cooperative thermal expansion of the hub and shrouds during engine operation, whereby the radial, axial, and circumferential abutting surfaces of the ends of the vanes increasingly interlockingly engage with the correspondingly opposed surfaces of the shrouds to effect increased structural integrity of the nozzle assembly.

Abstract: A bell seal unit and retaining nut for use in the nozzle chamber unit of an elastic fluid turbine, such as the steam turbine used to drive electrical utility generators. The bell seal unit includes a radial flange with an end face sealing surface and a skirt portion with a lower skirt margin subdivided into a labryinth seal region and a guiding and wear resisting region. The labryinth seal region includes plural, spaced apart circumferential seal lands and grooves, and the guiding and wear resisting region includes plural axial lands and grooves. The ball seal unit is positioned for free but limited axial movement by a retaining nut which includes a smooth inner cylindrical surface, a shoulder surface and a lower flange surface. Plural slots extend between the shoulder and flange surfaces to facilitate fluid flow to the lower surface of the bell seal radial flange.

Abstract: A turbine housing in which a gas passage is divided into a plurality of gas paths and which can prevent stress concentration and admixture of divided gas flows upon thermal deformation.

Abstract: The invention comprises a mounting assembly for supporting the turbine outer casing duct adjacent to the turbine frame. Multiple support posts are mounted to the turbine frame and a roller means is rotatably attached to each support post. The roller means are aligned to rotate on a contact surface of the outer casing duct. Movement of the rollers on the contact surface is caused by the relative movement of the turbine frame and outer casing duct.

Abstract: A device for maintaining clearance between rotor blades and a surrounding housing is disclosed in which the device radially expands or contracts to match the expansion or contraction of the rotor blade tips. The expansion or contraction of the device is achieved by thermal transfer between the device and the gasses passing over the rotor blades. The device has several alternating segments having different thermal characteristics such that the expansion/contraction characteristics of the rotor blade can be accurately matched by the device.

Abstract: A floating expansion control ring (20) having a plurality of radially extending positioning lugs (18) is free to move eccentric to the axis of an enclosing engine (24) and within the confines of a spacer ring (14) rigidly mounted within said engine (24). This eccentric movement in a turbine engine permits slight eccentricities of a turbine rotor (11) in a turbine engine. This eccentric movement eliminates the need for abradable shrouds and abradable turbine blades.

Abstract: A turbo-engine constructed to maintain the radial gap between the rotor and casing. The casing of the engine includes an inner casing having shell-shaped parts with centering seats and adjacent parts are secured a given distance apart axially.Each shell-shaped part comprises a plurality of angular segments which are secured together by fasteners aligned in a plane extending perpendicularly to the axis of rotation of the rotor.

Abstract: A ceramic stator vane assembly for a gas turbine engine comprises a plurality of ceramic stator vane segments arranged in an annular array with each vane segment having integral concentric tip and root platform members. The tip and root platform members define continuous inner and outer surfaces for receiving inner and outer ceramic rings. Radial and axial housing members are provided for mounting the stator vane assembly within the engine, and thermal insulation means are provided between the ceramic vane assembly and the housing members.

Abstract: A turbine ring comprises an annular support in two parts and a ring of ceramic sectors for sealing purposes. The two parts of the support are interconnected by an axial groove and a sliding male part. Each part comprises an axial annular groove in which is engaged a respective axial edge portion of each sector. The cooperating internal radial faces respectively of the edge portion and of the groove are circumferential, while the radially outer radial face of each sector comprises at least one flat zone. The corresponding face of each groove may be polygonal.

Abstract: A load transference structure between a core engine and power turbine comprises a plurality of circumferentially spaced apart radially extending spoke members, each of which is attached at its radially inner extent to first and second axially spaced apart support panels. Each of the spoke members is provided with a circumferentially extending portion positioned adjacent the panels which are adapted to cooperate with a circumferentially adjacent spoke member in such a manner that radial but not circumferential load transfer is permitted to take place between them. The load transfer structure permits load transfer to take place between the core engine casing and the power turbine.

Abstract: An inner wall for a transition duct between the high pressure and low pressure turbines of a multirotor gas turbine engine in which the wall structure itself is made up of multiple aligned segments which are bolted to the inner shrouds of the vane clusters of the low pressure turbine and in which the segments are secured to forward and rearward cone elements with one of said elements bolted securely to the segments and the other cone having free axial and radial movement with respect to the segments with the cone elements supporting at their inner edges a seal element to cooperate with a rotating element on a low pressure rotor.

Abstract: A stator assembly for a gas turbine engine is provided having novel means for securing it to the casing of the engine's compressor section. The stator assembly includes inner and outer shrouds secured, as by brazing, to a plurality of vanes and also includes a plurality of vane assemblies for clamping the shrouds and associated vanes to the casing of the compressor section. The vane of each vane assembly projects through but is not secured to the shrouds, the inner end of each vane of the vane assemblies having an integral plate engaging the interior of the inner shroud and means at its outer end for fastening the vane assembly to the casing by drawing the plate firmly into compression against the interior of the inner shroud. Since the vane assemblies are not secured to the shrouds, expansion of the casing during engine operation can be accommodated without imposing any destructive stresses on the shrouds, thereby protecting the structural integrity of the engine.

Abstract: A housing for a turbojet engine compressor is disclosed having inner and outer housing portions which may radially expand or contract as the compressor rotor wheel blades expand or contract, so as to maintain a minimum clearance between the housing and the rotor blade tips. A heat transfer manifold is applied about the outer periphery of the outer housing portion to rapidly expand the housing during transient operating conditions of the engine.

Abstract: Mated engaging grooves are formed at opposing surfaces of sections into which a turbine housing main body is divided with respect to the axial direction of a turbine. A partition wall is fitted in the mated engaging grooves, leaving a clearance in the radial direction. The end of the partition wall on the side of the gas inlet of the turbine housing main body is made into contact with the side surface or surfaces of a partition wall supporting member disposed at the gas inlet such that the partition wall supporting member is in coplanar relationship with a flange surface of the turbine housing main body, whereby thermal deformations in the direction of the gas flow at the gas inlet of the partition wall are permitted and the gas-tightness is ensured at the gas inlet of the turbine housing.

Abstract: A one-piece seal which surrounds the end of the burner duct to prevent leakage of high pressure air into the turbine inlet.

Abstract: Means for axially attaching a variable turbine vane array to a combustor in a gas turbine engine is disclosed. The attachment means are configured so that substantially all of the axial load on the array is transmitted through the walls of the combustor.

Abstract: A stator assembly 18 for a gas turbine engine is disclosed. The stator assembly includes an engine case 24 and a wall 26, such as a wall that includes an array of stator vanes 42. A high pressure region 74 (cooling chambers) extends between the wall and the engine case. The cooling chambers 74 are in flow communication through a leak path with a working medium flow path 14. An annular outer support 56 bounding the chambers beneath the vanes forms with the vanes an intermediate chamber 132 through which the leak path for cooling fluid passes. The annular support further includes a plurality of orifices 94 for diverting flow away from the leak path to lower the pressure of the intermediate chamber. In one embodiment, the chamber is formed in part by an annular groove 84 in the support and a plurality of flanges 124 associated with the vanes. The flanges are urged rearwardly into sealing contact with the annular support.

Abstract: A shroud for a gas turbine engine rotor stage is divided into a number of arcuate segments each of which is a trapezium. The segments are urged together by compression springs which attempts to make the assembly lengthen peripherally, by virtue of the chamfered ends 30 of the segments riding up each other. The completely circular shape of the shroud prevents that movement but as a result, a hoop load is generated which tends to move the segments radially outwards, thus achieving the same effect, along with a consequent increase in diameter. A cam ring and pins are used to control and reverse the movement, as desired. The shroud diameter can thus be altered to suit rotor expansion and contraction.

Abstract: A ceramic nozzle assembly for a gas turbine engine is provided. The assembly includes ceramic inner and outer shroud rings dimensioned to be concentrically disposed relative to one another. Recesses are provided in the outer circumferential surface of the inner shroud ring and apertures extend through the outer shroud ring in register with the recesses. Vanes extend through the apertures in the outer shroud ring and are engaged by the recesses in the inner shroud ring. A ceramic outer support ring slides over the outer shroud ring to securely retain the vanes. Slots or recesses are provided in both the inner and outer shroud ring to prevent rotation of the nozzle in the engine.

Abstract: A hollow thermally-conditioned turbine stator nozzle 12 is set forth to distribute and guide combustion gases from a forward inlet 15 to the turbine rotor blades 18. The nozzle includes a plurality of vanes 20 arranged annularly in the turbine. Each vane 20 has a body 22 to guide the fluid, the body being supported by outer and inner ends 34,64. The outer and inner ends each have a forward lug 44,74 and a rear lug 46,76. A floating support is provided for the vanes and includes forward shoulders 110,136 to engage the forward lugs and prevent rearward movement of the vanes and rear shoulders 114,142 having notches 116,144 to receive and confine the tangential movement of the vanes. Each vane also includes a hollow core 152 to pass a portion of fluid and reduce thermal stresses on the vane. The vane is preferably made of silicon nitride ceramic.