Abstract: A submersible pump (10) includes a casing (11) which houses a motor (13) and a pump assembly (14). A shaft (12) which carries the impeller (37) portion of the pump assembly (14) is driven by the motor (13) to draw fluid, in which the pump (10) is immersed, into the casing (11) through inlet ports (38) to be transferred to the pump assembly (14) and thereby pumped to a remote location. The shaft (12) has an axial bore (40) therein which is open at the bottom (41) to receive fluid. That fluid moves upwardly within the shaft (12) and passes out through radial bores (43) to join with the fluid received from the inlet ports (38). As such, internal fluid positioned in a chamber (23) is cooled by the fluid passing through the shaft (12) and that internal fluid in turn maintains the components in the casing (11) cool.

Abstract: A seal construction is provided for sealing a rotating pump shaft against passage of a fluid along its central axis. The seal construction includes front and rear sealing flanges mounted coaxially to and rotatable with the pump shaft. A temperature stabilized chamber is provided adjacent each sealing flange including means for recirculating and cooling fluid disposed therein so as to maintain the fluid between adjacent engaging members at a substantially constant temperature thereby maintaining a flatness of the sealing engagement between the sealing flange surfaces and the engaging members.

Abstract: An exhaust housing having an eductor is provided. The eductor includes an outer annular casing circumscribing an inner annular casing to define a flow path therebetween for receiving the exhaust gas from the turbine section of an engine. A plurality of struts are integral with both casings. The struts have passages that extend from the exterior of the outer casing to the interior of the inner casing. A non-oil lubricated bearing is mounted within the interior of the inner casing for journaling a rotating shaft. During operation, the kinetic energy of the high velocity exhaust gas flowing between the casings and into a tailpipe induces cooling airflow from the exterior of the exhaust section, through the passages, across the bearing, and then out to the tailpipe.

Abstract: An impeller displaces fluids without turbulence, thereby reducing noise and increasing efficiency. The impeller employs annular disks stacked on a shaft which may be rotatably mounted in a specially shaped housing. The disks cooperate with a complementary surface formed, e.g., by the interior of the impeller housing or by another impeller, so as to use a combination of surface friction, centrifugal forces, and a venturi effect to propel fluids tangentially without turbulence. The impeller is well suited for use with a heat exchange device because the flat disks present a large surface area providing good heat exchange with fluids flowing past the disks. A heat pipe or other suitable heat transfer mechanism may be provided in the shaft of the impeller to form a heat transfer system integral with the impeller for heating or cooling purposes.

Abstract: A cooling enhancement for a gas turbine engine blade outer air seal is made up of a plurality of arcuate seal segments, and each one has one or more internal cooling passages. Each segment has a supply surface opposite and in spaced relation to a sealing surface, and first and second end surfaces extending from the sealing surface to the supply surface. Each of the end surfaces includes a substantially planar perpendicular surface and a substantially planar canted surface intersecting at an included angle of between 100 degrees and 140 degrees, and the supply surface has a plurality of cooling orifices adjacent the second end surface. At least one cooling passage extends from the first end surface towards the second end surface, and each cooling passage intersects the first end surface and terminates short of the second end surface. Each cooling passage communicates with the supply surface through at least one of the cooling orifices.

Abstract: Cooling apparatus for removing heat generated by friction between machine parts located within a liquid confining enclosure, for example, a seal surrounding the drive shaft of a motor driven pump used for below-ground pumping of sewage, the apparatus comprising a baffled chamber of novel construction which may be mounted on the pump motor housing and cooperates with a tubular heat exchanger, for automatic circulation, in closed circuit, of hot cooling liquid from the seal to the chamber, where it circulates in an orbital motion by virtue of the baffle arrangement, then passes to the tubular heat exchanger, and from there to the seal to cool it.

Abstract: An axial blower has a blower motor and a blower wheel. The blower motor includes a motor shaft; a motor housing; a front and a rear bearing cover attached to the motor housing; ventilating openings provided in the front bearing cover; and air outlet openings provided in the rear bearing cover. The blower wheel includes a hollow hub surrounding the rear side of the motor housing; a plurality of impellers affixed to the exterior of the hub and projecting therefrom; a plurality of vane-like ribs carried by the hub at the interior thereof for generating a cooling air stream flowing between the hub and the motor housing; a bell-shaped part forming an axial continuation of the hub and surrounding the front side of the motor housing, a bottom portion, a central opening in the bottom portion and a plurality of ventilating openings provided in the bottom portion. The ventilating openings are arranged in a circular array concentrically with the central opening.

Abstract: An interstage thermal shield assembly for a gas turbine engine. The assembly includes an axially-extending thermal shield positioned between first and second stage disks to form a seal therebetween. The thermal shield includes complementary hook members shaped to engage slotted hook members formed on the first stage disk to form a bayonet connection, and complementary lip members for engaging lobe members formed on the second stage disk by means of split rings, thereby eliminating the need for a bolted connection between the thermal shield and disks and facilitating attachment and removal of the thermal shield. The thermal shield includes an annular impeller which is positioned rearwardly of the first stage disk, the impeller including bayonet connection with the disk which restrains the impeller from axial deflection, but permits radial deflection in response to thermal changes.

Abstract: A cylindrical support portion is provided on a wafer pump case to surround a rotary shaft, and a cylindrically formed power transmitting rotary wheel surrounding the support portion is integrally coupled to an outer end of the rotary shaft which protrudes outwardly from the support portion. A bearing means is interposed between an inner surface of the power transmitting rotary wheel and an outer surface of the support portion. A plurality of sealing members disposed concentrically with the bearing means are interposed between the rotary shaft and an inner surface of the cylindrical support portion at a location axially outwardly spaced from the mechanical seal, and a grease is filled between the sealing members. The water pump structure not only improves the sealing property of the sealing members by providing the sealing members at a location in which the deflection of the rotary shaft is smallest, but also increases the retaining property for the grease between the plurality of sealing members.

Abstract: A thermal shielding apparatus for use in the low pressure stage of a turbine engine having a plurality of tubular honeycomb cells which are axially aligned and arranged perpendicularly to a radially outwardly directed heat flux. The cells are layered and are housed by an inner and outer liner. The outer liner and an outer casing form a space between them, the outer casing being located radially outward from the outer liner. The layers of honeycomb cells reduce radiant heat flow to the outer casing.

Abstract: The disclosure relates to a fully integrated single stage centrifugal air compression system that exhibits a relatively high flow rate at relatively low pressure. The air compression system comprises a single impeller that is driven through a belt drive by a conventional electric motor. A novel parallel wall axially split diffuser converts the high kinetic energy of air leaving the impeller into pressure energy. Cooling of the air compressor is achieved by an integral fan on the motor pulley which draws filtered ambient air into a plenum. Plenum air is ducted through a novel system of heat exchangers which draw heat from the compressor bearings. A passage through the center of the compressor drive shaft conducts pressurized air from the plenum through the drive shaft to cool the bearings, resulting in a bearing running temperature slightly above ambient.

Abstract: A submersible centrifugal pump is disclosed. It includes a housing with a linear stack of axially mounted pumping units therein. Each unit is constructed as a module with at least a first and a second impeller mounted to a central shaft. A diffuser forms an outer casing which is provided for each impeller. A thrust bearing, lubricated and cooled by the fluid being pumped is supported from and to the outer casing and is arranged to receive axial force from the upstream impellers in each modular unit. A plurality of impellers and diffusers can form a single modular unit.

Abstract: A coupling for feeding a heat-exchange fluid between a stationary supply and a rotating body comprises a tubular rotor shaft fixed to the rotating body and rotatable about and centered on an axis and a nonrotatable housing fixed stationarily adjacent and surrounding the body. This housing is provided with an inlet connected to the supply and is formed with a passage permitting fluid communication between the supply and the body through the shaft. At least one roller bearing rotationally supports the shaft in the housing and outer and inner seals axially flanking the bearing define an annular substantially closed chamber containing the bearing and each seal between the housing and the shaft. The inner seal has an inner side exposed to the fluid and the outer seal has an outer side exposed to the surrounding atmosphere. A coolant is circulated through the chamber.

Abstract: A heat-dissipating coupling securing first and second shaft sections together for co-rotation and inhibiting heat transfer between the shaft sections. In an exemplary embodiment, the coupling includes a first coupling half secured to the first shaft section, and a second coupling half secured to the second shaft section. A plurality of air ducts extending generally transversely of the rotational axis of the shafts are formed between the first and second coupling halves. The ducts may be formed by grooves in the first coupling half, which are closed by a planar surface of the second coupling half. The ducts extend generally radially, and may be straight, or curved concavely or convexly with respect to the direction of the rotation of the shaft sections. Air may be supplied to the air ducts by providing one of the shaft sections as a hollow shaft in fluid communication with the coupling. Alternatively, air may be supplied to the ducts via a plurality of air inlet holes formed in the coupling itself.

Abstract: A submersible centrifugal pump is disclosed. It includes a housing with a linear stack of axially mounted pumping units therein. Each unit constructed as a module with at least a first and a second impeller mounted to a central shaft. A diffuser forms an outer casing which is provided for each impeller. A thrust bearing, lubricated and cooled by the fluid being pumped is supported from and to the outer casing and is arranged to receive axial force from the upstream impellers in each modular unit. A plurality of impellers and diffusers can form a single modular unit.

Abstract: A method of treating a surface of a machine element to permit the outer layers thereof to freely expand when repeatedly subjected to sudden temperature variations without thermal stressing the inner layers thereof.

Abstract: Method and apparatus for cooling shaft seals of a turbine-generator system which includes a hydrogen inner-cooled generator having a stator with a cylindrical core and a rotor mounted for rotation on a shaft within the cylindrical core, a turbine coupled to the shaft at one end of the generator, an exciter coupled to the shaft at the other end of the generator, and a pair of seals each of which surround the shaft at both ends of the generator for substantially minimizing a leakage of hydrogen therefrom. Each of the seals includes a seal ring with a hydrogen side and an air side, and a closed loop oil supply is provided for each such side. One closed loop oil supply supplies oil to the hydrogen side of each of the seals, and another closed loop oil supply supplies oil to the air side of each of the seals, and both oil supplies are coupled within a heat exchanger for exchanging heat between the two closed loop oil supplies.

Abstract: The turbo-compressor air supply system of the present invention supplies air to a paint spray system or the like at an elevated pressure. The turbo-compressor includes a housing and a rotatable, vertically-disposed drive shaft centrally disposed within the housing, and a bearing housing which houses a concentrically disposed bearing. The system comprises a rotatable section centrally disposed about the shaft. The section includes a first rotor and a second rotor. Each rotor comprises a first series of blades spirally arrayed about the center of the shaft. The first series of blades are sandwiched between a first pair of plates. The rotors are rotatably driven in the same direction as the shaft, as air is directed onto and through the blades. The rotors are coaxial with the shaft. The rotatable section also includes a tubular sleeve which is mounted about the shaft. The sleeve separates the rotors, and the sleeve is rotatable with the rotors and the shaft in the same direction as the rotors and the shaft.

Abstract: A new and improved air motor operated rotary earth drilling tool for use with a source of high pressure, high volume compressed air has a circulation control housing, a motor housing, a reduction gear housing, and a bearing housing connected longitudinally in series. The circulation control housing is connected to high pressure, high volume, compressed air and has an outlet opening into the motor housing, and an exhaust opening for discharge of compressed air for flushing cuttings and debris from a bore hole which is controlled by longitudinal movement of an inlet tube. The motor housing has a motor chamber and a sliding vane rotor with a rotary shaft extending into the reduction gear housing. A planetary reduction gear receives the rotor shaft and has a low speed, high torque output shaft extending into the bearing housing. A passageway conducts compressed air around the planetary reduction gear for cooling.

Abstract: A submersible centrifugal pump is disclosed. It includes a housing with a linear stack of axially mounted pumping units therein. Each unit constructed as a module with at least a first and a second impeller mounted to a central shaft. A diffuser forms an outer casing which is provided for each impeller. A thrust bearing, lubricated and cooled by the fluid being pumped is supported from and to the outer casing and is arranged to receive axial force from the upstream impellers in each modular unit. A plurality of impellers and diffusers can form a single modular unit.

Abstract: A gas turbine jet propulsion unit of multi-shaft-double-flow construction in which a front compressor or fan supplies compressed air into a secondary channel arranged coaxially to the propulsion unit axis and formed between outer and inner wall structures, from which a secondary air component is taken and blown out against the turbine housing structures for purposes of turbine component cooling; the secondary air channel extends essentially over the entire propulsion unit length or at least up to the area near the turbine housing structure while the secondary air component is taken off from the secondary flow by way of openings in the inner wall structure which are arranged in direct proximity of the respective turbine housing structure.

Abstract: A rotor bearing on the turbine side of a gas turbine is surrounded by a concentric cavity through which fuel is routed from its source to the turbine combustion chamber. The fuel of the gas turbine is used as the coolant for the rotor bearing and at the same time the concentric cavity surrounding the bearing forms a hydraulic "compression" film damping device.

Abstract: A gas turbine engine cooling system has cooling air cooling in order, the first stage disk (50) and blades (22), the second stage vanes (24), and the second stage air seal (82). Air passes to the second stage vane from the rotor through a reaction nozzle (62) effecting a reaction stage adding energy to the rotor and cooling the air.

Abstract: A coolant system uses a first quantity of high temperature air at cruise power and a second larger quantity of cooler air at high power. Relatively high rotating clearances are achieved at high power and low clearance achieved at cruise power.

Abstract: Apparatus for cooling and thermally isolating turbocompressor foil bearings. The bearing journal includes a hollow shaft through which gas is positively circulated to cool the shaft. A slinger at one end of the shaft develops a centrifugal pumping action during operation of the turbocompressor by virtue of a plurality of radially directed gas passages. Pressurized gas may be introduced from the compressor into the interior of the hollow shaft and, after traversing the shaft, returned to the compressor. The invention includes arrangements for protecting the bearing against combustion products which may leak past turbine wheel seals by removing such combustion products before they can reach the bearing.

Abstract: A turbo-compressor air supply system for supplying air at relatively low pressure and high volume to a paint spray system or the like. The air supply system comprises a drive motor including a casing, a drive shaft projecting from the casing and air intake means in fluid communication with the casing. A turbo-compressor is provided which includes a housing, a drive shaft having first and second projecting ends, a bearing housing projecting from the compressor housing and disposed concentrically around and spaced from a projecting end of the drive shaft and a bearing disposed concentrically around the projecting end. A drive train couples the compressor drive shaft with the other projecting end of the drive motor drive shaft to enable the motor to drive the turbo-compressor. Means are provided for placing the bearing housing in fluid communication with a drive motor casing and associated air intake means to provide cooling for the bearing.

Abstract: A pump having a heat exchanger including a rotating baffle sleeve secured to the pump shaft. A seal baffle on the rotating baffle sleeve extends over the pump seal assembly cartridge. A cooling cylinder containing circulating component cooling water is suspended within the rotating baffle sleeve and defines a flow passageway therein for cooling heated product water, before the product water contacts the shaft seal. A seal injector distributor ring uniformly distributes seal injection water to the seal. A thermal shield in the heat exchanger reduces thermal stresses in the heat exchanger. A slotted keyway spacer ring facilitates replacement and alignment of a hydrostatic bearing.

Abstract: An air seal assembly 10 for a gas turbine engine comprising a full ring cover plate 20 and seal segment 14 attached to impingement boxes 18. The impingement boxes have counter mounted hooks 24, 26 that interlock with a turbine flange 22 and cover plate 20 to secure the seal assembly 10. Holes 36 in the impingement boxes 18 direct cooling air to the entire backside 38 of seal 14. Seals 14 are mounted to the impingement boxes 18 by pedestals 40 that are positioned to enhance seal flexibility since axial edges are unrestrained.

Abstract: Apparatus for cooling and thermally isolating turbocompressor foil bearings. The bearing journal includes a hollow shaft through which gas is positively circulated to cool the shaft. A slinger at one end of the shaft develops a centrifugal pumping action during operation of the turbocompressor by virtue of a plurality of radially directed gas passages. Pressurized gas may be introduced from the compressor into the interior of the hollow shaft and, after traversing the shaft, returned to the compressor. The invention includes arrangements for protecting the bearing against combustion products which may leak past turbine wheel seals by removing such combustion products before they can reach the bearing.

Abstract: The invention relates to a turbomolecular vacuum pump (1) with a rotor (6) and at least one antifriction bearing (17) for the rotor, the stationary ring (19) of the antifriction bearing being seated on the wall of a sleeve (21) which in turn is supported through at least two O-rings (26, 27) made from an elastic material on a casing section (13) of the pump. To improve the heat flow from the sleeve (21) to the casing (13) of the pump, the annular space (29) formed by two seal rings (26, 27), the sleeve (21) and the pump casing (13) is filled with a medium (31) promoting heat flow from the sleeve to the adjacent part of the casing.

Abstract: A multistage hydraulic machine includes a water chamber in a bottom ring of the highest-pressure stage. The water chamber supplies cooling water to seal gaps between rotary and stationary elements through a communication passage connected to the water chamber.

Abstract: A rotor including a disc requiring cooling, a drum, a cover surrounding the drum so as to provide an annular space, a radial cooling air supply line, and a deflection cascade in the supply line, which cascade deflects the cooling medium in the rotational direction of the rotor and accelerates the cooling medium to the peripheral velocity of the disc.

Abstract: A cooling system 46 for a turbofan gas turbine 10 is disclosed. Various construction details which increase the effectiveness of a heat exchanger 48 located in the secondary flow path 24 are developed. In one embodiment, the cooled air is used for protecting a bearing compartment.

Abstract: A coolable stator assembly 16 for a gas turbine engine 10 is disclosed. The stator assembly includes an outer air seal 26 and an upstream support 32 and a downstream support 34 supporting the outer air seal about a flow path 14 for working medium gases. Various construction details are developed which enable impingement cooling of the outer air seal at a first location with cooling air and enable ducting a portion of the collected cooling air through the support for impingement cooling of the outer air seal at a second location. In one embodiment, metering holes 112 extend through the supports for directing the cooling air against the edge region of the outer air seal.

Abstract: This invention relates to an improvement on material of a shroud for gas turbines. The material comprises 0.25-0.7 wt % C, 20-35 wt % Cr, 20-40 wt % Ni and balance Fe, and has an austenitic structure. The amount of the .sigma.-phase in this invention is less than 5% and Nv value (Electron Vacancy Number) is less than 2.8.

Abstract: An arrangement is provided for statically sealing between the inner shroud 12 of individual stator vanes of a gas turbine, and a seal housing 14 provided with a radially outwardly open channel 22 into which is received a plurality of outer seal segments 24, and which includes a radially outwardly open channel 33 throughout the length of each outer seal segment and with a plurality of inner seal segments received in the channel, with the outer seal segments being biased outwardly by the springs 36, and the inner seal segments 34 being biased outwardly into sealing contact with individual inner shrouds by the concentric inner compression springs 38 carried by the outer seal segments 24.

Abstract: A cooling system 46 for a turbofan gas turbine engine 10 is disclosed. Various construction details which increase the effectiveness of a heat exchanger 70, 76, 112 are disclosed. In one embodiment, a rotor shaft 98 is used to pressurize buffer air for a bearing compartment 40.

Abstract: In a medium-pressure steam turbine of single-flow chamber type design, for use as a ship's turbine, cooling steam is conveyed via holes in the wall of the inflow part for cooling the rotor surface and the first few rows of rotor blades. The cooling steam is guided by a baffle at the wall of the inflow part to annular spaces between the shaft seal of the guide vanes and the rotor surface and via axial cooling ducts in the rotor to the bases of the rotor blades. At each rotor blade of the rows connected by the axial cooling ducts, radial connecting canals are provided in the blade bases for guiding the cooling steam into axial canals which connect the annular spaces under the shaft seals of the adjacent guide vanes.

Abstract: A stress corrosion cracking proof steam turbine in which dry steam is blown into the gap between the hub portions of adjacent turbine discs, thereby preventing corrosion in the gap. A nozzle diaphragm is provided between the discs and has an inside circumferential face which straddles the gap. Labyrinthine packing is provided on the inside face of the nozzle diaphragm and comprises an upstream, an intermediate, and a downstream group of fins. A steam reservoir is located between the intermediate and downstream group of fins and straddles the gap. A steam supply means is located inside the nozzle diaphragm and provides dry steam (from inside or outside the turbine) to the reservoir and thus to the gap. To prevent leakage of high pressure wet steam into the reservoir, a steam leakage capturing means is provided between the upstream and the intermediate group of fins.

Abstract: A cooling system 46 for a turbofan gas turbine 10 is disclosed. Various construction details which increase the effectiveness of a heat exchanger 48 located in the secondary flow path 24 are developed. In one embodiment, the cooled air is used for protecting a bearing compartment.

Abstract: A multistage turbine construction in which the cooling flow to the turbine rotor is controlled by cooperating sealing elements carried respectively by the row of vanes and by the rotor with the sealing surface carried by the vanes, the stationary surface being an outwardly sealing surface and the fins cooperating therewith carried by the rotor extending radially inward such that as the turbine rotor cools down during reduced power operation the sealing effect will be increased to reduce the flow of cooling fluid over the rotor surface.

Abstract: An improved rotary labyrinth seal such as may be used in a gas turbine engine. The seal includes a rotor with at least one seal tooth and a stator with an abradable shroud and casing. The first and second members cooperate to inhibit the flow of fluid therebetween. The improvement comprises a conduit for conducting a portion of the fluid through the casing for heat transfer between the fluid and second member. In this manner, the thermal response of the stator is improved.

Abstract: A clearance control device in an inter-shaft turbojet engine bearing journal placed between a high pressure trunnion and a low pressure trunnion and including inserted between an inner ring and an outer ring, the high pressure trunnion including a series of longitudinal grooves and a series of longitudinal holes which are supplied with oil from an intake and an annular collector in the low pressure trunnion, from which the oil moves by centrifugation through radial holes into an annular recess in the downstream tightening nut of the outer ring, which in turn communicates with the grooves through holes formed in the nut. Clearance in the bearing journal is controlled by cooling the high pressure trunnion at the maximum operating speeds of the turbine via circulating oil. By virtue of an appropriate circuit, the oil supplied by the collector lubricates the bearing and cools the roller bearing journal.

Abstract: A rotor shaft assembly for use in turbochargers includes a metal shaft having a generally cylindrical female cavity therein concentrically distributed about the axis thereof; and a solid hubbed ceramic turbine wheel having a male stub shaft insertable into the female cavity. The axis of the male stub shafted ceramic turbine is coextensive with the axis of the shaft and the stub shaft is mated with the female receptacle and joined by an adhesive. A turbocharger includes a rotor-shaft assembly of the above-described type, in which the metal to ceramic adhesive joint is located in the turbocharger center housing.

Abstract: An annular friction seal device to be disposed around the impeller of a turbine or high pressure compressor is disclosed. The turbine or compressor is of the type comprising, from the periphery inward, a support-ring surrounding the impeller, a first air-permeable annular layer fastened to the support-ring, and a second annular layer joined to the first layer and coming into immediate proximity with the impeller blade ends, and being abaradable by these ends. To simplify production of the annular seal device, it is provided with two annular layers provided within a single superalloy seal ring with channels bored through the entire seal ring. The channels are open to air in one zone and are closed in at least the upstream end of the other zone.

Abstract: A method of operating a water-turbine or a pump water turbine in which, when the runner is idling for phase modification running or stand-by running, the main machine is tripped by means of a main machine tripping circuit when the flow rate of cooling water supplied to the seal portions of the runner is maintained below a predetermined limit for a predetermined period of time. The main machine tripping circuit is excited to become operative only after the pressure around the runner comes down to a level approximating the water pressure in the draft pipe.

Abstract: A plurality of flow channels permit a controlled flow of compressed air to flow therein in contact with the flange of a gas turbine combustor transition piece to reduce the operational temperature of the flange and to thereby reduce stress creep distortion of the flange. The flow channels may be disposed in a surface of the flange facing a seal member or in a surface of the seal member facing the flange. In one embodiment, a longitudinal slot in the flange permits the entry of a sealing flange or seal plate. The flow channels may be disposed in the surface of the slot or in the surface of the flange or seal plate. In another embodiment of the invention, the seal member embraces the exterior of the flange and the flow channels may be disposed in either of the facing surfaces.

Abstract: A combination air and oil cooled seal housing is provided which also utilizes trapped stagnant air as an insulator. The combination prevents coking of the oil supplied as a lubricant to the bearings and seals in the hot section of a turbine engine. Pressurized air is introduced from the compressor into the inner structure support housing by means of hollow passages. The pressurized air absorbs heat as it traverses the passages in the structure. The oil supplied is connected to an annular shape cavity allowing the oil to be circulated therein and cool the seal support structure. Additional insulation is provided by cylindrically shaped trapped air shields surrounding the bearing package. Oil flowing through the structure can then properly lubricate the seals and bearings which support the turbine rotor stages within the housing assembly.

Abstract: Apparatus and method for minimizing and maintaining substantially constant the effective blade tip clearance between the outer free ends of rotor blades and an adjacent casing shroud of an axial-flow turbine of a gas turbine engine. The casing shroud includes a portion facing the hot gas stream and the outer rotor blade ends and a packing of high heat-resistance, high erosion-resistance ceramic elements secured to the shroud via a metal ring to face the blade tips. A heat insulator is interposed between the packing and the metal ring. A perforated conduit is mounted outside the metal ring for blowing cooling fluid against the metal ring on the side thereof remote from the insulator for equalizing the expansion of the metal ring to that of the turbine wheel. The ceramic packing includes projections facing the outer ends of the blades which are tapered so that they are easily broken off when coming into contact with the blades during running-in of the apparatus.

Abstract: Two concentric, partially overlapping annular plates mounted on a parallel support plate are provided for partly defining the gas flow path and for shielding bearings, etc. from hot combustion gases in a radial flow gas turbine. The radially outer plate is cooled by compressed air channeled past the plate surface opposite the combustion gases. The compressed air is metered to achieve a temperature distribution decreasing in the radially inward direction for providing sealing contact between the outer edge and the support plate. The radially inner plate is cooled by film cooling using the compressed air exiting the outer plate channel in the vicinity of the overlap.