Abstract: The scavenge oil system disclosing the invention has a scavenge oil outlet located at the bottom of a blower housing whereby lubricating oil can flow thereto by gravity in most attitudinal positions of the housing. When the blower housing is in an attitude that a portion thereof, such as the rear, is at a level lower than the scavenge oil outlet, a scavenge pump, having an impeller driven by the blower shaft, is rendered effectively operable by having an inlet beneath the level of oil at the rear of the housing and the scavenge pump pumps the oil to a higher level whereby it may flow from the housing by gravity through either the scavenge oil outlet of the housing or through other passages.

Abstract: A flow machine, especially a gas turbine equipped with means for separating an oil/air mixture and for returning centrifuged oil droplets to a circulation having oil consuming devices such as bearing places and with a vent line leading from the center toward the outside; the separating means includes a porous air-permeable element built into the hollow main shaft between two oil-impermeable walls whereby radially outer feed openings for the oil/air mixture are arranged in the upstream wall which correspond to openings in the main shaft while an air discharge opening is arranged in the downstream wall in its center which is in communication with the vent line.

Abstract: A fluid seal arrangement for use in a turbomachine, having first and second adjacent sets of turbine blades arranged for relative rotation about a common machine axis. A main fluid flowpath is established across the blades. Parts of at least one set of blades form a clearance opening which communicates between the main fluid flowpath and an outside region. An annular arm projects over the clearance opening into the outside region to form with an outer periphery of the other set of blades an annular passage communicating with the clearance opening. An annular cavity on the other blades receives a buffer fluid. Jet openings from the cavity direct a pressurized supply of the buffer fluid into the annular passage, to induce a sealing fluid flow from the outside region through the clearance opening and into the main fluid flowpath to prevent leakage of fluid from the main fluid flowpath through the clearance opening.

Abstract: The turbine vanes of a gas turbine engine immediately downstream of the combustor are maintained at a cool temperature by judiciously directing cooling air at the stagnation point ahead of the vane's leading edge at the juncture of the vane's airfoil section and platform.

Abstract: A pump seal oil system for a reactor pump wherein seal oil is provided at a pre-determined rate of flow without changing the rate of flow in response to pressure differences between the seal oil in the pump and the reactor pressure. Seal oil is provided at a first rate when the reactor pump is in operation and at a second higher rate when the reactor pump is not in operation.

Abstract: A vacuum pump with a seal structure for a pump unit of the vacuum pump and a driving mechanism for rotating a rotor in the pump stages of the pump is disclosed. The seal structure is provided with a narrow gap sealing arrangement formed by a stationary member which is opposed to the portion of a shaft of the driving mechanism which is between the pump unit and an upper bearing supporting the same shaft, which narrow gap sealing arrangement comprises first, second and third seal portions; a mechanism for supplying a discharge gas to the first seal portion; and a mechanism for supplying a purge gas to the second and third seal portions. Owing to these parts, the feed rate of the purge gas can be minimized, and the entry of the oil mist, which occurs during the lubrication of the bearing, into the interior of the pump unit can be prevented. This enables the interior of the pump unit to be kept clean.

Abstract: A liquid scavenging pump system for scavenging oil or the like from a blower, an engine or the like. A casing is provided for housing the blower and defining an oil receiving cavity. A dual pump is mounted in the casing and has first and second pumps in communication with the casing cavity for conjoint rotation. A first inlet is provided from the casing cavity to the first pump, and a first outlet is provided from the first pump for delivering oil from the cavity to a pump or the like. A second inlet is provided from the casing cavity, remote from the first inlet, to the second pump. The second outlet from the second pump is in communication with the first inlet to the first pump to facilitate operating the pump at various attitudes. The dual pump is of the radial-vaned impeller type, but includes two sets of axially spaced impeller vanes separated by a common barrier and including a sleeve for mounting on a common drive shaft.

Abstract: A manifold (20) includes a plurality of separate, identical flow channels (28) separated by flow dividers (46). The flow dividers (46) include a thickened boss section (54) for receiving a mounting bolt (50), and are skewed adjacent the manifold outlet for forming a plurality of tangentially directed nozzles (18).

Abstract: An apparatus for propelling a continuous gas mixture stream of an inert carrier gas and an aggressive doping gas, includes an electric motor having a motor housing filled with pure carrier gas and a shaft with a shaft extension, a radial blower having an impeller mounted directly on the shaft extension and a blower housing filled with the gas mixture and coupled to the motor housing, a gas ring of pure carrier gas being continuously fed and maintained in a ring space for sealing the blower housing against the motor housing in an operating state, and a hollow sealing ring being inflated with compressed gas for sealing the blower housing from the motor housing when the blower is stopped.

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 turbine provided with at least an annular array of rotary aerofoil blades has a casing, the radially inwardly facing surface of which is provided with a plurality of grooves. The grooves are adjacent the radially outer tips of the aerofoil blades and are so arranged that they direct the gas flow between the blade tips and the casing along the absolute ideal flow path in the region of the blade tips. This ensures that at least some of the momentum of the gases flowing between the blade tips and the casing is transformed into rotating energy as vortices form in the grooves. This energy is subsequently imparted to the tips of the aerofoil blades.

Abstract: An assembly for producing wet compression of gas being compressed in a centrifugal-type, multistage gas compressor having an impeller, a diffuser "downstream" of the impeller, and a cross-over channel connected to the downstream end of the diffuser includes a plurality of liquid jets for injecting a vaporizable liquid such as water into a gas stream undergoing compression. The liquid jets are positioned axisymmetrically about the longitudinal axis of the compressor shaft and are adapted to inject liquid into the diffuser substantially upstream of the cross-over channel, and, in a preferred embodiment, have a radial spacing from such axis of about 1.05 to 1.1 times the maximum radius of the compressor impeller. The invention attains a marked increase in vaporization of the injected liquid, providing better compressor performance and reduced wear of compressor internal parts.

Abstract: A ferrofluid seal for a bearing application with a stationary shaft about which a hub rotates. The seal consists of a permanent magnet and one or more annular pole pieces which form a magnetic circuit with the bearing shaft. The magnetic circuit includes an annular gap between the shaft and the pole pieces in which the magnetic flux traps a magnetic fluid which bridges the gap to form a seal. The shaft is tapered in the gap area to form a wedge-shaped gap which accommodates changes in the magnetic fluid volume due to temperature variations while holding the fluid within the magnetic field to maintain the seal. The pole piece which forms the gap has a straight annular face located at a constant radial distance from the shaft axis. At high operating temperatures expansion of the magnetic fluid causes the fluid to fill the taper of the shaft, but, since the shaft is stationary, fluid spash is eliminated. The straight surface of the pole piece controls fluid splash caused by centrifugal force.

Abstract: The blade has an aerofoil body 10 having a leading edge surface 11 which is cooled by air passing through a helical first passage 12 having first portions passing close to said leading edge surface and alternating with second portions passing through a more nearly central part of the blade section remote from said leading edge. A spanwise but straight second passage 15 extends through the blade in a position within the helical passage and closer to the second than the first portions thereof. Heat abstracted from the leading edge by air flow in said first portions is transferred by the flow to the second portions and from there through the blade material to the flow in the straight passage.

Abstract: A stator structure 34 for supporting an outer air seal 46 is disclosed. Various construction details which adapt the stator structure to evenly move inward and outward in response to the impingement of cooling air are developed. In one embodiment an upstream support ring and a downstream support ring for the outer air seal are attached together.

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: In a turbine engine (8) having a shaft (60) with turbine blades (24, 24', . . . 24.sup.N) thereon which rotate in a chamber (12) of the engine housing (10) to produce thrust in response to an operator input. A pneumatic sensor system (30) connected to said housing (10) for maintaining the space relationship between the tip (26, 26', . . . 26.sup.N) of the blades (24, 24', . . . 24.sup.N) and the wall (28) of housing 10 within set limits under varying operational conditions experienced by the turbine engine (8).

Abstract: An axial flow liquid pump comprises an outer tube, a smaller diameter inner tube, and a driven shaft journaled near the top of the inner tube. An upwardly opening cup-shaped rotor is secured in the lower end of the shaft such that a cylindrical sidewall is at least partially spaced between the inner tube and the outer tube. A helical flange is secured to the outer surface of the cylindrical sidewall. Radial passages are provided in said rotor below the helical flange. The passages are arranged to be above the lower end of the inner tube. A baffle plate having passages therein is secured just above the rotor.

Abstract: A glandless submersible electrical dynamo operative at high temperatures comprising a casing containing a stator and a rotor and a metal alloy filling the space within the casing. The metal alloy is liquid at the operating temperatures of the pump and is an alloy of bismuth, preferably with lead or tin. The bismuth is present in an amount of between 40-60% and the alloy has the property of substantially no volume change upon solidification.

Abstract: A cryogenic turboexpander employing a rotor and a shaft fixed thereto including bearings rotatably supporting the shaft having a pressurized lubricating system. A labyrinth seal is positioned between the bearings and the rotor. A control valve is employed to sense differential pressure across a portion of the seal and regulate the pressure within a cavity between the seal and a near bearing.

Abstract: A machine for pumping liquid chlorine employs an upright shaft sump pump which is confined in a hermetically sealed housing and has a tubular supporting element surrounding the pump shaft. The latter is mounted in overhung position and is adjacent to a pressure pipe which conveys the pressurized liquid. The shaft seal is kept out of contact with the liquid by the housing as well as by a body of inert gas which is supplied to the interior of the housing and to the space between the shaft and the tubular element at a pressure depending on the pressure of inflowing liquid chlorine and being sufficiently high to prevent the inflow of liquid chlorine into the housing and/or tubular element when the pump is idle. The main impeller on the pump shaft is made integral with an auxiliary impeller which constitutes a hydrodynamic shaft seal and prevents the flow of conveyed liquid chlorine into the tubular element from below.

Abstract: Sealing device for the drive shaft (27) of a high pressure fluid pump comprising a system of seals (33, 34, 35) at least one of which (33) is a hydrostatic seal. Between this hydrostatic seal (33) and the interior of the volute (21) is disposed an auxiliary seal (45) of the mechanical type. The auxiliary seal (45) separates two chambers (46a) and (46b) which can be brought into communication or isolated by a system of pipes (47) on which a valve (48) is disposed. The invention is particularly applicable to the primary pumps of a pressurized water nuclear reactor.

Abstract: A turbine wheel for a hot gas turbine engine operable at relatively high peratures, e.g. above 2,000.degree. F., and high velocities, e.g. above 30,000 r.p.m. The blades are formed of temperature-resistant ceramic material. A special annular band of high tensile strength material is affixed to tip areas of the blades for translating centrifugal forces into compressive loadings on the blades. To compensate for differential thermal expansion of the band relative to the blades a localized cooling system is provided for selectively cooling the annular band without cooling the blades.

Abstract: The bore of the compressor for a gas turbine engine is heated by selectively bleeding compressor air from downstream stages so that heating only occurs at discreet times during the engine operating envelope. The bled air is admitted into the bore at the mid-stage station of the compressor wherein the compressor disks are scrubbed so as to expand and close the gap between the outer air seal and tips of the compressor blades during cruise of the aircraft and prevented from heating the disks during the high powered operations of the engine.

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: A sealing device is disclosed for maintaining a small positive clearance between packing segments and the turbine blade tips of a turbojet engine. The packing segments are connected to an inner ring which is, in turn, connected to an outer ring, all disposed within the turbojet casing. The coefficient of thermal expansion of the inner ring is greater than that of the outer ring such that, as air is directed onto the structure from the engine compressor, the differential expansion or contraction of the rings serves to move the packing segment in a radial direction to maintain the clearance between them and the turbine blade tips.

Abstract: Two rotationally symmetrically correlated components of a turbomachine, such as a gas turbine engine, define between them an air duct surrounding the axis of the components. A resilient band-like wall section extending radially from the first component bears resiliently in an axial direction against a wall section projecting radially from the second component to provide a seal for the duct. Another wall section of each component cooperate to form a radially extending tongue-in-groove joint, which may incorporate another seal for the duct, this joint permitting relative axial and radial movements between the two components. Means may be provided to maintain the fluid pressure within the duct higher than the pressure exterior thereto. The two components may be joined together by a bayonet-type connection. One of the components may comprise two members so that the member carrying part of the bayonet-type connection can be rotated with respect to the other member during assembly of the two components.

Abstract: A multi-stage hydraulic machine which includes a plurality of runner housings or chambers each having a runner positioned therein, a head cover and an intermediate speed ring, movable guide vanes at an outside portion of the runner housing or chamber of the highest pressure stage, each of the runners having a runner crown with an exhaust hole bored through it, each of the runner housings or chambers having an exhaust chamber formed at the exit portion of the exhaust hole and a device for sealing water at the radially outside portion of the exhaust chamber, and a plurality of exhaust paths provided in each of the exhaust chambers to the exterior of the machine respectively. Additionally, a method for operating the machine is disclosed.

Abstract: An anti-icing system for a rotating blunt nose bullet of a gas turbine engine uses a rotating thermosyphon effect to create a circulation within a chamber connected for rotation with the nose bullet which draws hot air from a downstream region of the engine forwards to impinge on the nose bullet over a small region close to the engine axis. This avoids complications with separate hot air supplies or electrical heaters. As shown in FIGS. 3 and 4 of the drawings, in one embodiment of the invention the chamber consists simply of a tube closed off by the nose bullet and in combination with an engine main shaft which extends to the turbine region of the engine to draw hot gas from this region. Alternatively, the chamber may extend only to the downstream end of the first compressor.

Abstract: A device is provided for efficiently directing nonrotating cooling air into a rotating turbine rotor. The device employs a nozzle to accelerate the cooling air in the direction of rotor rotation. A diffuser-deswirler then directs this air, with curved and expanding flow passages, into corresponding holes in the turbine rotor. With these elements, the device directs the cooling air into the rotating rotor section without significant pressure losses and with a lower resultant cooling air temperature.

Abstract: A liquid metal mechanical pump having therein a liquid metal free surface and a cover gas space over the liquid metal free surface and which is equipped with an emergency syphon system. This system has a syphon pipe and a liquid metal dump tank disposed outside the pump. The syphon pipe connects the pump and the dump tank so that the liquid metal in the tank flows out into the dump tank when the free surface of the liquid metal in the pump rises to a predetermined level higher than that of the normal operation of the pump.

Abstract: A hot gas centrifugal fan is constructed with a scroll part comprising spaced-apart walls 16 and 18 to define a hot gas passage 22 therebetween to which hot gas is conveyed when the fan is in a non-operating condition to hold the fan temperature sufficiently high to avoid unacceptable vibration brought on by thermal distortion of the fan wheel upon a re-start of the fan.

Abstract: A feather seal construction that interlocks a pair of feather seal elements that fit into intersecting slots. Each interlocking element is restrained axially but permits relative limited rotary motion. One of the elements is recessed with diametrically opposed slots forming an "H" shaped member and the other is apertured at one end which is then slotted, bent to allow it to fit into the diametrical slots and then joined in the original position. An extruding end adjacent one face of the interlocking element seals in an axial direction giving both radial and axial sealing characteristics.

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 liquid metal mechanical pump, having therein a liquid metal free surface and a cover gas space over the liquid metal free surface, is equipped with an emergency gas line shut-off system. This system can shut off a cover gas line by the solidification of liquid metal to thereby prevent the leakage of cover gas and the rise of the liquid metal level in the pump at the time of the failure of the cover gas line. The mechanical pump may further be equipped with an emergency syphon system which can discharge liquid metal when the liquid metal level in the pump exceeds a predetermined level.

Abstract: A seal between co-rotating, opposed annular surfaces of interconnected elements comprises a multi-filament wire rope disposed within an annular groove formed at the interface between the two surfaces, the groove being wedge-shaped in cross-section, one side of the wedge being formed by each element. The wire rope is forced into sealing relationship with the groove surfaces along its entire length by centrifugal forces. The multi-filament wire rope has improved sealing capability over solid, single filament wire seals of the prior art. The seal is particularly well suited for use in the hot turbine section of a gas turbine engine and is resistent to damage and failures due to multiple engine cycles.

Abstract: A cooling device for a steam turbine wherein a portion of boiler feedwater for cooling a casing of the turbine is supplied, after being heated by high pressure feedwater heaters, to a cooling fluid passage for the casing as a cooling fluid satisfying the temperature and pressure conditions necessary for effecting cooling of the casing, by a booster pump and a regenerating heat exchanger. After cooling the casing, the cooling fluid is returned to a boiler feedwater system following a heat exchange with a cooling fluid for cooling the casing.

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 invention pertains to improvements in a fluid handling system in which a working fluid passes through a rotor while undergoing a pressure change. A shaft extends longitudinally from and rotates with the rotor. A first seal surrounds the shaft in axially spaced relation to the rotor, and a lubricant having a minimum boiling point is injected into the first seal adjacent the shaft at a pressure sufficient to cause the lubricant to flow axially toward the rotor. A housing surrounds the rotor and shaft and defines a contact zone between the rotor and the first seal for receiving both lubricant and a contact fluid such as the working fluid or a seal buffer gas used to isolate the working fluid from the lubricant. The contact fluid has a maximum boiling point substantially less than the minimum boiling point of the lubricant.

Abstract: This invention relates to a self-priming screw pump lubrication system. The system 10 includes a central feed tube which communicates at one end with lubricant in a reservoir or sump and at the other end to the central region of an assembly that includes a horizontally disposed rotating shaft. The shaft having thereon threaded portions of opposite pitch mounted within a pair of mating sleeves which sleeves are biased away from each other at the central region of the assembly. The other ends of the sleeves are in abutting relationship with the outer races of a pair of angular contact bearings to be lubricated. Each of the inner races of the bearings are mounted on the rotary shaft. Lubricant slingers are mounted on the rotating shaft at a point remote from the bearings and cooperate with the lubricant that has been drawn upward through the central feed tube and delivered to and past the bearings, whereupon the slingers propel the lubricant back to the reservoir for reuse.

Abstract: An anti-icing system for a rotating blunt nose bullet of a gas turbine engine uses a rotating thermosyphon effect to create a circulation within a chamber connected for rotation with the nose bullet which draws hot air from a downstream region of the engine forwards to impinge on the nose bullet over a small region close to the engine axis. This avoids complications with separate hot air supplies or electrical heaters. As shown in FIGS. 3 and 4 of the drawings, in one embodiment of the invention the chamber consists simply of a tube closed off by the nose bullet and in combination with an engine main shaft which extends to the turbine region of the engine to draw hot gas from this region. Alternatively, the chamber may extend only to the downstream end of the first compressor.

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 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: A shield for disposition between a lubricated bearing and a labyrinth seal in a gas turbine engine having a rotating member rotatable about a vertical axis, the shield preventing lubricant contamination of the seal. The shield includes an inner helical baffle on the rotating member between the bearing and the seal and an outer helical baffle on a stationary support between the inner baffle and the seal. The inner and outer baffles radially overlap to foreclose lubricant drip onto the seal and have corresponding helical leads so that the inner baffle can be threaded through the outer baffle when the rotating member is installed on the support.

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.

Abstract: Concentric, counterrotating shafts include means for bringing oil from within the inner shaft across an annular gap between the two shafts into oil scoops which rotate with the outer shaft. To minimize the splashing of oil as it travels across the annular gap between the two shafts a plurality of separate, circumferentially spaced apart oil compartments are disposed around the outer circumference of the inner shaft and rotate therewith. Oil from within the inner shaft travels radially outwardly through passageways in the shaft into the oil compartments whereupon the radial velocity of the oil is reduced to zero. The oil leaves the compartment through outlets and is slung across the gap between the shafts whereupon it is captured by oil scoops and is fed to its final destination, such as to a bearing race disposed radially outwardly of the outer shaft.

Abstract: A coolable rotor stage assembly 14 of the turbine 10 of an axial flow gas turbine engine is disclosed. A cavity 18 for purge air is adjacent the rotor disk 22. A nozzle 34 for metering the flow of cooling air through the rotor blade, for forming a jet of high velocity air and for directing the cooling air from the root of the rotor blade inhibits recirculation, retards formation of the radial pumping boundary layer, decreases the thickness t of the radial pumping boundary layer and does work on the rotor blade.

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 supply 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: A low collapse speed, self priming, lubricating oil pumping system for a turbomachine, operatively driven by the turbine main shaft, is disclosed. In a preferred form, the invention includes a permanent magnet generator operatively coupled to shaft of the turbine-generator or turbomachine being lubricated and driven thereby to produce an electrical output; an induction motor directly connected to the electrical output of the permanent magnet generator without intervening protective devices such as fuses, switches, and so forth; and a positive displacement pump located in or in proximity to an oil reservoir and driven by the induction motor to pump oil from the reservoir at a flow rate and pressure sufficient to supply oil to the turbine-generator or turbomachine during all operating phases thereof during which lubrication is required.

Abstract: The front portion (116) of the immersed turbo-generator bulb houses the alternator (5, 19). The intermediate portion (114) houses the gear box (26), and the rear portion has the turbine (122 projecting therefrom. The intermediate portion is of greater diameter than the front portion and they are interconnected by a flange (2). The external cooling is by tubes (7) through which cooling air flows, and having one end connected to orifices through the flange (2).