Abstract: The cooling-air ducting of the axial flow gas turbine runs in the area of the last blading stage (9+14) radially inwards of the heat-accumulation segments (23, 24) inside the outer boundary of the rotor (4) and through blade root channels (21) in the blade roots of the last moving blade ring (9) and finally through a cooling-air blade ring (28) fixed to the rotor into the diffuser into which the cooling-air flow enters with a velocity vector which essentially corresponds to the average velocity vector of the exhaust-gas flow entering into the diffuser. This avoids the flow losses which occur when the cooling-air flow passes out into the exhaust-gas flow in the area of the last stage or stages. At the same time, the temperature difference between the rotor circumference and the last rotor disk (4), likewise cooled by tapped air from the compressor, is in this way reduced, as a result of which the thermal stresses in the rotor are also reduced.

Abstract: A side-channel compressor includes a rotor having transport blades, and an injection nozzle for introducing a cooling liquid into a transport section of the compressor. Damage to the transport blades by droplets of liquid can be avoided by the providing the injection nozzle at the part of the compressor housing forming the side channel. The injection nozzle directs the coolant into a side channel space which is free of the transport blades.

Abstract: Apparatus and method for reducing the effects of draft tube pressure fluctuations acting on a runner in a hydraulic reaction turbine or the effects of suction tube pre-rotation acting on the impeller in a centrifugal pump. A closed surge suppression chamber is mounted about the exterior of the turbine draft tube or pump suction tube. A plurality of openings are provided about the exterior of the draft tube or pump suction tube communicating with both the interior of the draft tube or pump suction tube and the interior of the chamber near its bottom thereof. An air inlet is provided leading into the chamber at the top thereof. In operation, and during operation of the turbine or pump where a rotating helical vortex of water has formed in the draft tube or pump suction tube, water flows from the draft tube or pump suction tube through the openings and into the bottom of the chamber while air is injected into the top of the chamber.

Abstract: A cavitating centrifugal pump which includes a housing defining a pumping chamber. An impeller is rotatable in the pumping chamber and includes a plurality of impeller blades designed for forming trailing vapor cavities within a liquid in the chamber to generate low pressure regions behind the blades upon rotation of the impeller. A fluid inlet is provided to the chamber radially inwardly of the low pressure regions and in communication therewith. A fluid outlet is provided from the chamber radially outwardly of the fluid inlet and in an area of the chamber whereby the fluid can be pumped from the chamber. Liquid inlets are provided to the chamber in the area of the impeller blades for flushing the low pressure regions behind the blades.

Abstract: A aromatizing device for an air compressor which is mounted either in the compressor inlet or the feed tube between the compressor tank and pneumatic machinery. The air flows through a solid or liquid aromatizing agent in a chamber so that the agent is entrained therein to mask odors. The flow passage may be in parallel to the main passage and controlled to pass air and entrain agent for a predetermined time only following operation of the compressor.

Abstract: The invention concerns a method and an apparatus for the mixing of liquid or gas into pulp stock. In the method the pulp is fed into a centrifugal pump, into which, at the same time, the material to be mixed is fed into the zone between the center and the outer circumference of the rotor wheel. The apparatus is preferably provided with rotor blades consisting of two parts and with feed pins extending into the gap between the said parts.

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: An axial-admission steam turbine, includes a steam inflow region, guide vane rings including a first guide vane ring, guide vanes of the first guide vane ring having radially inner ends, a shaft being rotatable in a given direction, an annular shaft shield being connected to the radially inner ends of the guide vanes of the first guide vane ring and being disposed in vicinity of the steam inflow region, the annular shaft shield surrounding the shaft at a distance defining a ring canal therebetween, the annular shaft shield having nozzles formed therein for discharging into the ring canal tangentially relative to the shaft as seen in the given direction of rotation of the shaft.

Abstract: A method and apparatus for determining when to initiate the cleaning of the turbine blades of a turbocharger is disclosed. The performance of the compressor portion of the turbocharger is monitored and upon a degradation in performance being detected it is indicated that fouling of the turbine blades has occurred. In response to this indication a water injection system is energized for supplying atomized water under high pressure to the exhaust gas powering the turbocharger to effectively clean the turbine blades. Means are provided for decreasing the speed of the turbocharger during the cleaning cycle to allow for an effective cleaning operation.

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: The invention relates to a method of improving the part-load behavior of a turbo machine operating with a rotor 13 having fixed vanes 14. Such method uses the feature of applying auxiliary fluid injection nozzles 18 near the inlet 11 of the rotor for adding a small amount of fluid to the main fluid flow.The additional amount of fluid is projected in direction such that a substantial velocity component of the movement of this additional fluid is directed tangentially with respect to the rotation of the rotor 13.

Abstract: An open circuit liquid cooled gas turbine in which a coolant passes through the turbine blades and is expelled at the tips thereof. The coolant is recaptured by providing ports in the turbine casing in radial alignment with the turbine blades whereby fluid expelled radially is received by the ports. A trough is provided in the turbine casing axially displaced downstream from the turbine blades to recapture coolant that is blown by the ports due to the differential pressure in the turbine.

Abstract: A shroud assembly for a gas turbine engine consists of a housing having a boundary wall and a gas contacting skin, the wall and skin being in segmented form. The skin consists of a thin metal sheet attached to the boundary wall, and a ceramic gas contacting coating. The skin is impingement cooled by cooling air flowing through apertures in the boundary wall, and the cooling air exhausts into the gas flow through passages.The use of a thin metal sheet with a ceramic coating promotes favorable temperature gradients in the skin enabling the coating to run at optimum conditions for maximum cooling effect.

Abstract: The blade has an aerofoil portion (16) having a first (23), a second (24), a third (25) and a fourth (26) internal spanwise passage for cooling air arranged in chordwise succession with the first passage being at the leading edge wall (17) of the blade. The first and third passages are connected to respective a cooling air supplies (14A,14B) at the root end (11) of the blade. At the tip (28) of the blade the third passage is connected to the second passage to introduce air, warmed on passing through the third passage, into the second passage and ameliorate undue cooling of the internal walls (19,20) between the first, second and third passages. The third passage is also connected to the fourth passage for supply of cooling air to the trailing region of the blade. The second passage has outlets (24A) to the exterior of the blade whereby the flow through the second passage is controllable independently of the air supply to the fourth passage, i.e. to the trailing region of the blade.

Abstract: An annular sleeve surrounds a turbine rotor and is fixed with respect to the turbine casing, the sleeve being elastically deformable in a radial direction. A wear ring is carried by the sleeve, the wear ring being composed of segments arranged end-to-end circumferentially. The adjacent ends of the segments are spaced apart when the turbine is cold or idling. The thermal expansions of the turbine rotor and of the sleeve and ring are so related that in one operating temperature range of the turbine the spaces between the adjacent ends of the ring segments close and the segment ends engage each other, and in a higher operating temperature range of the turbine the sleeve expands. Air leaving the compressor is directed against the sleeve and the stationary part carrying the sleeve. The wear ring and portion carrying the sleeve may be insulated. The sleeve may be mounted on a combustion chamber surrounding the turbine.

Abstract: An annular sleeve surrounds a turbine rotor and is fixed to a stationary part, the sleeve being elastically deformable in a radial direction. A wear ring is carried by the sleeve, the wear ring being composed of segments arranged end-to-end circumferentially. The adjacent ends of the segments are spaced apart at all operating conditions of the turbine. The thermal expansions of the turbine rotor and of the sleeve and ring are so related that under operating conditions of the turbine, when the engine of which it forms a part is running, the sleeve thermally expands radially. The rate of thermal expansion of the stationary part is directly related to the rate of thermal expansion of the turbine rotor. Air leaving the compressor is directed against the sleeve and the stationary part carrying the sleeve. The wear ring and portion carrying the sleeve may be insulated. The sleeve may be mounted on a combustion chamber surrounding the turbine.

Abstract: A gas turbine in which hot gas is directed only over a portion or preselected number of the turbine blades and means are provided for directing a flow of a cooling gas over another portion or different preselected number of blades. In accordance with a preferred embodiment, the means for providing cooling gas comprises a compressor means located adjacent the turbine. Preferably the gas turbine comprises a plurality of alternating compressor means and turbine stages wherein the direction of flow of cooling gas is countercurrent to that of the hot gas flowing through the turbine stages.

Abstract: A full admission radial impulse turbine and turbines with full admission radial impulse stages. The last-mentioned turbines are of the single shaft, dual pressure type. Provision is made for utilizing working fluid exhausted from the high pressure section, in which the radial impulse stage(s) are located, in the low pressure section which contains axial flow turbine stages. The (or each) radial impulse stage in the dual pressure turbine has a rotor or wheel with buckets or pockets oriented transversely to the direction of wheel rotation and opening onto the periphery of the wheel. Working fluid is supplied to the buckets via nozzles formed in, or supported from, a nozzle ring surrounding the turbine wheel and aligned with the entrance ends of the buckets.

Abstract: A gas turbine engine has a turbine which includes an annular array of rotary aerofoil blades surrounded by an annular shroud member. All or a major portion of the annular shroud member is constituted by a heat pipe. A distance measuring device is provided to measure the clearance between the tips of the rotary aerofoil blades and the shroud member and its output is monitored by a control unit. The control unit is adapted to control a valve which regulates the flow rate of cooling air directed onto the heat pipe. The arrangement is such that the temperature of the heat pipe is maintained at a level which is consistent with the clearance between the rotary aerofoil blade tips and the annular shroud member being within a predetermined range of values.

Abstract: A temperature sensing assembly which continuously senses the temperature of a constituent stream, of a flow of a gaseous medium; and, as a result of such sensing, generates pneumatic servo-pressure to drive air valves, which control the flow of the constituent stream, to open and shut in accordance with specific requirements.

Abstract: A device for controlling the clearance between the blade tips of a gas turbine engine turbine rotor and associated segmented shrouds comprises a control ring which is secured to the engine casing by a plurality of dowels. The control ring is supplied with cooling fluid to its hollow interior and is covered with a thermally insulating layer, whereby the rate of movement of the shroud segments can be maintained substantially equal to that of the adjacent turbine rotor.

Abstract: A turbine cylinder is in contact at its outer surface with split rings which are held in place in annular slots in a cylindrically extending ring holder. The rings, while remaining in contact with the outer surface of the cylinder, are allowed to expand and contract within their respective slots. Notches are constructed at the inner circumference of the rings to form a labyrinth type cooling passage in conjunction with the outer surface of the turbine cylinder.

Abstract: A gas turbine engine is disclosed in which a particularly efficient use of cooling air is made. In this engine, at least part of the cooling of the turbine blades is effected by a bleed of air from one of the compressors. This bleed air is ducted to flow between the shanks of adjacent rotor blades to cool them, and the used bleed air then rejoins the main gas flow of the engine upstream of the turbine rotor.

Abstract: A stationary air-cooled shroud or cylinder forming a portion of a turbine asembly includes an inner ring having a matrix of grooves formed therein, and an outer restraining ring covering the matrix so as to form a labyrinth of passageways for the flow of cooling air therethrough. A suspension ring cooperates with the inner ring and the restraint ring to define an entry flow path for the cooling air, and also a plenum chamber having an auxiliary outlet to provide film cooling air to the clearance spacing between the inner ring and the rotor blade tips. The fow of cool air through the labyrinth is operative to reduce the level and gradient of the metal tempertures in the shroud in order to obtain improved turbine blade tip clearance control.

Abstract: An improved floating seal is provided to minimize leakage around the ends of a variable area turbine stator nozzle for use in cooperation with a circumscribing shroud. The seal is contoured to float within a pocket formed in the end of the nozzle vane which extends to the vane trailing edge. The forward end of the seal is forced into engagement with the shroud by the pressure of cooling air from within the vane. A seal surface attached to the trailing edge of the seal and projecting laterally of the vane utilizes the differential pressure across the vane airfoil surfaces to hold the trailing edge of the seal into engagement with the shroud. The improved floating seal reduces vane end leakage experienced by prior art floating seals.

Abstract: A turbine vane for use in a gas turbine engine having high turbine inlet temperatures is disclosed. Film cooling is provided at the leading edge of the vane airfoil by cooling air which flows through leading edge holes from a hollow cavity in the airfoil section. Film cooling air is also provided through wall holes along the suction and pressure sides of the airfoil. A U-shaped insert having a pressure leg and a suction leg is disposed within the hollow cavity to isolate the leading edge holes from the wall holes. When the cavity is pressurized, the legs are each urged against corresponding seal ribs which extend from the cavity wall to effectively isolate the leading edge holes.

Abstract: A duct wall embracing the turbine of a gas turbine engine is cooled by impingement of air jets on to the outside of the wall. For control of the air flow the wall is surrounded by a chamber divided into inlet and outlet regions by a partition having spaced apart portions projecting towards the wall. The air jets emerge from nozzle openings in the free ends of the projections. Air rebounding from the wall enters the spaces between the projections and so does not interfere with the flow of fresh air thereby raising the efficiency of the heat exchange.

Abstract: A coolable shroud surrounding the tips of the turbine blades of a gas turbine engine is disclosed. The shroud comprises a plurality of arcuate segments which are supported by the turbine case concentrically about the axis of the engine in end to end relationship. Each segment is adapted to receive and distribute cooling air about the walls of the shroud which are exposed to the hot working medium gases flowing through the turbine during operation of the engine. A combination of impingement cooling and transpiration cooling techniques maximize the cooling effectiveness of the air supplied.

Abstract: Means for preventing the wasteful leakage of cooling air within the turbine section of a gas turbine engine is disclosed. A segmented shroud radially separates the flow path for the working medium gases from cooling air supply chambers which are disposed radially outward of the flow path. Rotatable vanes penetrate the shroud and extend into the medium flow path to control the flow of medium gases through the turbine. A ring, which is split, is urged against the vane and the adjacent shroud segments in operative response to a spring member to prevent the excess leakage of cooling air therebetween.

Abstract: A coolable shroud having a sealing surface surrounding the tips of the turbine blades of a gas turbine engine is disclosed. The shroud comprises a plurality of arcuate segments which are supported by the turbine case in end to end relationship concentrically about the axis of the engine. Each segment is adapted to receive and distribute cooling air about the walls of the shroud which are exposed to the hot working medium gases flowing through the turbine during operation of the engine. Cooling air is flowable to the gap between adjacent shroud segments to maintain continuity of the sealing surface across the gap.

Abstract: A device for automatically regulating the clearance between the tips of the otor blades of a turbine, particularly of a gas turbine, and the adjacent wall of a turbine stator, comprising means for directing a gaseous flow against the said wall to regulate its temperature. This gaseous flow is obtained from a proportioner including at least two inlet passages connected to sources of gas at different temperatures and controlled by the thermal expansion of an obturator responsive to the temperature of fluid passing through the turbine, so as to reduce the temperature of the said gaseous flow as the obturator expands, in order to cool the stator in stable conditions and to heat it in transitory conditions.