Abstract: A high pressure floating ring assembly includes a floating ring having a sealing surface thereon closely fit with respect to the outer diameter of a cylindrical shaft and wherein relative motion occurs between the inside diameter of the floating ring and the outside diameter of the shaft. Passages are provided to produce a high differential pressure across the sides of the seal and a side thrust reaction pin is located in each of a plurality of circumferentially spaced openings formed in the seal housing and in the body of the seal thereby to define a close tolerance seal to housing gap which permits the floating ring to readily reposition while the shaft is radially shifted with respect to the seal either by misalignment or eccentric shaft motion.
Abstract: A gas turbine engine has an internal drive shaft including one end connected to a driven load and an opposite end connected to a turbine wheel and wherein the shaft has an in situ adjustable balance system near the critical center of a bearing span for the shaft including two 360.degree. rings piloted on the outer diameter of the shaft at a point accessible through an internal engine panel; each of the rings has a small amount of material removed from its periphery whereby both of the rings are precisely unbalanced an equivalent amount; the rings are locked circumferentially together by radial serrations thereon; numbered tangs on the outside diameter of each ring identify the circumferential location of unbalance once the rings are locked together; an aft ring of the pair of rings has a spline on its inside diameter that mates with a like spline on the shaft to lock the entire assembly together.
Abstract: An accessory transmission mechanism for causing the lance of a soot blower of the well-known IK long travel type to oscillate about its longitudinal axis, rather than rotating continuously in the conventional manner during its projecting travel and during its retracting travel, and which also drives the lance longitudinally, consists of a conversion transmission assembly adapted to be installed in the carriage of the blower. The conversion assembly includes a tubular idler shaft fitted on and rotatable independently of a solid inner shaft which is mounted in the blower carriage as a simple replacement for a corresondingly mounted shaft of the standard blower carriage. The tubular shaft drives a Scotch yoke mechanism and also drives the walking pinions which drive the carriage along the beam to actuate the lance longitudinally.
Abstract: A bearing sleeve extractor assembly includes a movable workpiece support on a stand having an overhead circular spray head to receive a multi-surfaced elongated bearing sleeve connected to a support member and wherein the spray head includes a perforated inner wall and an insulated outer wall having a heated vapor chamber therebetween connected to a heat source for directing heated vapor into the spray head for distribution therefrom to produce even convection heating of the bearing sleeve continuously circumferentially therearound so as to produce a non-mechanical thermal release of the bearing sleeve from its support member.
Abstract: A gas turbine engine having variable geometry flow controllers therein for controlling mass flow in accordance with engine operation includes a rotor with a wide variation in thrust forces thereon during different phases of engine operation countered by a variable axial load integrating device having a rotating hydraulic thrust compensating piston mounted forwardly of the rotor in association with a rotor thrust bearing and further including means for generating a centrifugal head in accordance with engine speed by means of rotating oil trapped between the rotating piston and a nonrotating counter piston; depth of rotating oil is automatically regulated by an integral, flow regulator having flow area therethrough varied in accordance with axial position of a thrust bearing carriage that has the variable rotor thrust loading imposed thereon.
Abstract: An industrial gas turbine engine includes an inclined annular combustor made up of a plurality of support segments each including inner and outer walls of trapezoidally configured planar configuration extents and including side flanges thereon interconnected by means of air cooled connector bolt assemblies to form a continuous annular combustion chamber therebetween and wherein an air fuel mixing chamber is formed at one end of the support segments including means for directing and mixing fuel within a plenum and a perforated header plate for directing streams of air and fuel mixture into the combustion chamber; each of the outer and inner walls of each of the support segments having a ribbed lattice with tracks slidably supporting porous laminated replaceable panels and including pores therein for distributing combustion air into the combustion chamber while cooling the inner surface of each of the panels by transpiration cooling thereof.
Abstract: An exhaust system for a front mounted, transverse engine includes an exhaust pipe and tailpipe assembly having an interposed low profile gas converter therebetween supported by a pair of pedestal type suspension assemblies and a converter support bar directed transversely below the converter and wherein each of the suspension assemblies includes a resiliently yieldable insulator of elastomeric material vertically compressed by the supported exhaust system and including a cylindrical hollow end slidably fitted over a converter bar end to vertically support the bar on a vehicle frame and further including a thin web segment that readily bends on either side of the at rest vertical axis of the insulator to accommodate fore and aft engine induced roll movements while serving to isolate inherent exhaust noise transmission from the exhaust system to the vehicle frame or body.
Abstract: A vehicle drive system includes a gas turbine engine having a compressor inlet control to reduce total engine air flow to between two and three percent of normal air flow during periods where fuel flow to the gas turbine engine combustor is terminated. An auxiliary flywheel is mounted between a power turbine output shaft and engine reduction gear for power transfer to the rear differential of a road vehicle. The auxiliary flywheel is driven at high speed of rotation of the power shaft to store energy which is used to start the engine following off modes of operation wherein air flow to the compressor is severely restricted and fuel flow to the combustor is terminated.
Abstract: A clutch assembly for use between a combiner box and a vertical take-off, shaft driven variable pitch lift cruise fan is self contained and is positively engaged and disengaged without spline tooth interference upon pilot demand and wherein means are provided so that no clutch slip occurs following engagement and wherein further means are provided to maintain clutch engagement in the event of oil pressure loss during the engaged mode of operation.
Abstract: A rotary disc, regenerative type automotive gas turbine engine has a water cooled block for supplying hot water to a cab heater core and for supporting a gasifier spool and a power turbine spool within a core section of the block which receives high pressure air from a rotary regenerator matrix disc for flow to a combustor for supplying motive fluid to a gasifier turbine and power turbine with exhaust flow directed from the core section through the regenerator matrix disc and wherein the water cooled block includes an integral planar surface thereon defining a reference plane for the rotary regenerator matrix with the high pressure inlet air and low pressure exhaust gas being directed therethrough for heating the inlet air and wherein the block further includes a water coolant filled passage therethrough in surrounding relationship to the power turbine to act as a containment mass therearound; the water coolant filled passage being located in close proximity to the planar surface defining the reference plane
Abstract: A method for manufacturing a turbine rotor assembly from dissimilar materials includes the step of preforming a turbine disc of powdered metal by direct hot isostatic pressing; machining the OD of the disc rim to an exact dimension; prefabricating a ring of airfoil elements having a circular rim with a machined ID therein fit to the OD of the turbine disc; sealing joint lines on side surfaces of the joined parts to create a vacuum at the interface with a high melt temperature sealant; thereafter diffusion bonding the joined and sealed parts by hot isostatically pressing them at temperatures in excess of 1500.degree. F. and under fluid pressure directly applied to the parts in excess of 1000 psi to press the ring ID into intimate contact with the OD of the disc until the dissimilar materials are diffusion bonded to form a high strength butt joint therebetween.
Abstract: A gas turbine engine includes a compressor having a plurality of fixed diffuser passages therein each including a gate and associated cam ring control means for operating each of the gates either open or closed to vary the gas flow through the compressor diffuser for turbine engine control; the gas turbine engine further includes a turbine section having a plurality of turbine nozzle passages each having a separate gate therein selectively operated under the control of cam ring means to vary the amount of motive fluid to the turbine in accordance with desired engine operation and wherein each of the gates are operative with respect to either the diffuser or the nozzle passages to change the area of gas flow therethrough by blocking some or all of the channels without resultant change in incident angle of the gas flow with respect to the inlet of each of the passages.
Abstract: A regenerator assembly for a gas turbine engine includes a center driven, rotatable disc type ceramic core with a hub and drive shaft including a chain driven sprocket fixedly secured thereto and wherein damper means including first and second relatively movable parts are connected between the sprocket and hub and a resiliently yieldable slipper is located in the hub and compressible to accept hub loads without taking a permanent set; the damper means and slipper combining to damp oscillations in said matrix disc drive shaft during operation of the regenerator assembly and further operative to isolate frangible material of the core from shocks imposed thereon by the drive thereto.
Abstract: A combustor assembly for an automotive gas turbine engine includes a continuously ignited, pilot flame tube supported on a combustor dome immediately downstream of an inlet fuel nozzle and air swirler assembly. The pilot flame tube has an air swirler and fuel nozzle supported on an interior bulkhead and air is supplied upstream of the bulkhead and through a double-walled porous tube assembly for cooling wall portions of the flame tube exposed to the flame front within the combustor and wall portions thereof exposed to a pilot flame formed within the flame tube.
Abstract: A short length afterburner assembly for a jet propulsion engine having a fan bypass includes cold and hot air cross-over passages and a plurality of flame stabilization swirler vanes associated with a balanced load controller for positioning the vanes parallel to hot gas stream flow from a jet engine core when the afterburner is off and in an inclined position to such gas stream flow when fuel is injected therein during afterburner operation thereby to produce flame spread within the afterburner core by a combination of translatory and swirling motions; and wherein atomized fuel for afterburner combustion is injected into hot gases ducted through hot air cross-over passages from the jet engine core to produce premix and prevaporization of fuel upstream of fixed flameholders and wherein cold fan bypass air cross-over passages have movable turbulator grids positioned during afterburner operation for mixing cold air flow with the bypassed hot core gas at the fixed flameholders during afterburner operation and wh
October 25, 1977
Date of Patent:
January 16, 1979
General Motors Corporation
Arthur H. Lefebvre, Samuel B. Reider, Jerry G. Tomlinson
Abstract: A gas turbine engine coupling assembly includes a radially outwardly located diaphragm coupling having a pair of thin relatively flexible diaphragms mounted between two rotating members to permit torque transfer therebetween and to compensate for angular misalignment and axial position compensation therebetween; and wherein the diaphragm coupling further includes a pair of high backlash, non-contacting spline elements located approximately in the plane of the diaphragms including a male splined part secured to one of the rotating members and a female splined part attached to the other member centered radially by the pair of diaphragms to preclude splined members from contacting one another during normal operation and wherein the splined parts back up the diaphragms by contact to directly couple the two rotating parts together to prevent engine overspeed in the event of diaphragm failure.
Abstract: A pressure control valve assembly includes a valve housing having a spring loaded, resilient valve element with reversely curved conical surfaces thereon one of which is seated on a fixed, annular pressure relief seat by a first spring element and the other of which is seated against a spring biased ball check valve that controls flow through a central opening in the valve element defining a vacuum relief path.
Abstract: Combustion apparatus for a gas turbine engine includes two separate combustion zones; one having a first air flow thereto defined by a plurality of holes in combustion apparatus liner; the second zone has air flow thereto through a second plurality of holes in the combustion apparatus liner. Parallel fuel injectors supply fuel into the respective zones and include a wide angle fuel flow nozzle that supplies fuel to the pilot zone of combustion and a narrow cone fuel injector that directs fuel through the pilot zone without combustion and into a downstream main combustion region where the fuel is then burned with air flow though the second plurality of holes to produce a staged combustion of air fuel in the combustion apparatus to achieve high combustion efficiency over a broad ange of fuel/air ratios as well as more uniform combustor outlet temperatures and low smoke output.
Abstract: An inducer for a high speed centrifugal pump includes a shaft located upstream of the inlet eye of the centrifugal pump concentrically within an inlet bore; and further includes a plurality of axial blades on an inducer shaft for producing a boost pressure to the inlet of the centrifugal pump and wherein means are included to direct a spray of fuel in a direction radially of the longitudinal axis of the shaft immediately upstream of the blades to reduce the amount of fuel flow across the inducer with a resultant lowered pressure rise than would otherwise occur.
Abstract: A gas turbine engine has a turbine vane case, an outer combustion case and inner vane case along with an air seal located in circumferential surrounding relationship to a circumferential row of stator vanes defining a turbine nozzle assembly upstream of a high pressure turbine stage. Individual stator vanes can be replaced without removing the high pressure turbine stage by configuring an index vane to be removably secured to an inner support band by means of a spring loaded pin and configuring each of the remaining vanes in the vane row to have a side slotted base secured to the inner band and removable therefrom by rotation of each of the individual vanes in a direction opposite to the tangential gas load thereon.