Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of stepped first ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Each stepped first ridge has a first portion proximal the substrate surface with a pair of first opposed lateral walls terminating in a plateau, and a second portion terminating in a ridge tip. These ridge or rib embodiments have first lower and second upper wear zones. The lower zone, which at and below first portion height, optimizes engine airflow characteristics, while the upper zone, between the plateau and the second portion ridge is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.

Abstract: A compressor is disclosed herein. The compressor may include a shroud cavity. The compressor also may include a flow directing device positioned within the shroud cavity. The flow directing device may be configured to direct a flow within the shroud cavity.

Abstract: A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path. Further included is at least one strut operatively coupling the inner structure to the outer structure. Yet further included is at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut.

Abstract: A method and system for controlling clearance between the tips of blades of a turbine rotor in a gas turbine airplane engine and a turbine ring of a casing surrounding the blades. A valve is controlled to act on a flow rate and/or a temperature of air directed against the casing. The valve is of the on/off type for switching between an open state and a closed state in a determined reaction time, the valve control module including a corrector for determining a first binary control signal that can take a first value corresponding to an open state and a second value corresponding to a closed state of the valve. The corrector includes a time-delay module for determining a binary control signal, with the duration between two successive changes of state in the control signal being not less than the reaction time of the valve.

Abstract: Gas Pressure Reduction Generator (GPRG) systems and methods for implementing a GPRG system are provided, where the GPRG systems comprise a gas inlet configured to receive a pressurized gas flow, at least one expander in gas flow receiving communication with the gas inlet wherein the expander is operable to convert the pressurized gas flow into mechanical energy and a depressurized gas flow, and a generator configured to convert the mechanical energy into electrical energy.

Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.

Abstract: A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine. The method comprising the steps of performing a first run of the gas turbine engine, shutting down the gas turbine engine and starting the gas turbine engine for a second run. The method further comprises measuring at least one performance parameter during or after the first engine run but before a time selected at which air within the gas turbine engine, soaked to the approximate temperature of one or more surrounding engine components, is substantially displaced as a consequence of the second run. The thermal condition of at least part of the engine in accordance with the measured performance parameters is then recorded. Finally the recorded thermal condition is retrieved and the temperature of the casing is controlled during at least part of the second run in a manner dependent on it.

Abstract: A demand-based load balancing function may be provided by one or more drive controllers that takes advantage of the affinity laws to linearize the control of the variable of interest (e.g., flow, pressure, etc.). Each drive controller may be set up by the user simply inputting a few values into the drive controller. Based on the inputs, the drive controllers may interpolate control points using an assumed linear relationship between the variable to be controlled (e.g., pressure) and the current driven to the pump. Feedback data from the system may be used to continually update the drive controllers so as to potentially allow them to better balance power usage to each pump.

Abstract: An embodiment of a gas turbine engine having a liner and casing is disclosed. The liner is disposed between the casing and a rotatable turbomachinery component. In one form, the rotatable turbomachinery component is a turbofan engine. The liner can be thin relative to a distance between the liner and the casing. Protrusions can be used between the liner and the casing. The protrusions can be a rib and can extend from the casing or the liner. An insert, such as an abradable surface, can be used with the liner. A filler can be used in the space between the liner and the casing.

Abstract: A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn.

Abstract: An apparatus and method for cooling a dual, walled component is disclosed herein. An augmented cooling system according to the present disclosure includes transporting a cooling fluid through one wall of a cooling pathway formed between two opposing spaced apart walls of the dual walled component. The cooling fluid can be deflected away from one wall of the cooling pathway with a first trip strip as the cooling fluid traverses along the cooling pathway. The cooling fluid can be deflected away from the opposing wall of the cooling pathway with a second trip strip as the cooling fluid continues traversing along the cooling pathway. The cooling fluid can then be discharged from the cooling pathway through the opposing wall of the dual walled component.

Abstract: A device and method for discharging sealing air in a turbofan engine includes a primary flow duct that extends through a core engine of the turbofan engine and a bypass duct. The device has at least one bearing chamber sealed by sealing air of the turbofan engine, said bearing chamber surrounding at least one oil-lubricated bearing element for mounting a mechanical component of the turbofan engine. At least one discharge path for escaping sealing air is provided, which extends up to the bypass duct of the turbofan engine.

Abstract: A compressor assembly that has a compressed air tank having a vibration absorption member. The vibration absorption member can exert a pressure on a portion of the compressed air tank. A method of controlling sound emitted from a compressor assembly, by using a vibration absorber which applies a force against the compressed gas tank. Controlling the sound level of the compressed gas tank is accomplished by absorbing vibration from the compressed gas tank by which exerting a pressure on a portion of the compressed gas tank.

Abstract: A facility, in particular a power plant, is provided having a steam turbine and a bypass station for diverting a working medium, as required, for the steam turbine around the steam turbine, wherein at least one resonance absorber is provided for the bypass station.

Abstract: An apparatus and method for controlling a clearance between the blades of a turbomachinery component and flow forming surface are disclosed herein, and includes controlling the clearance by moving the surface axially relative to the turbomachinery component. In one embodiment the apparatus includes an impeller rotatable about a first axis, a shroud encircling the impeller, and a first ring encircling the first axis. An actuator is operably engaged with the first ring to pivot the first ring about the first axis. The apparatus also includes at least one cam engaged with the first ring and at least one cam follower engaged with the shroud. Pivoting movement of the first ring about the first axis results in the at least one cam urging the at least one cam follower and the shroud along the first axis to vary a distance between the plurality of blades and the shroud.

Abstract: Certain embodiments of the invention may include systems, methods and apparatus for providing a labyrinth seal. In an example embodiment, a method is provided for sealing a flow path between a stationary element and a rotating element of a turbomachine. The method can include disposing at least one fixture on an inner surface of a stationary element associated with the turbomachine; disposing a packing ring linked via a spring element to the fixture wherein the packing ring comprises at least one bore; and disposing, according to a predetermined profile, a plurality of interdigitated packing ring teeth and rotor teeth intermediate to the packing ring and the rotating element; wherein the bore, packing ring teeth, and rotor teeth, cooperate to counter a moment associated with one or more axial forces.

Abstract: Turbine airflow is modulated to improve performance during part load operation in a turbomachine. The turbomachine includes a compressor, a turbine with a plurality of stages, and a diffuser. Modulating the airflow includes extracting airflow from an upstream component of the turbomachine, admitting the extracted airflow into a rear stage of the plurality of stages. Admitting airflow into the rear stage serves to increase rear stage loading and alter an energy distribution in the rear stage during part load operation.

Abstract: A centrifugal refrigerant compressor system includes an impeller connected to a shaft. A diffuser is arranged on a downstream side of the impeller and is configured to regulate refrigerant flow exiting the impeller. A magnetic bearing supports the shaft. A sensing element is configured to produce an output relating to a shaft condition. A controller is configured to receive the output and determine an undesired impeller operating condition based upon the shaft condition. The controller is configured to command the diffuser to a desired state in response to the undesired impeller operating condition.

Abstract: The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.

Abstract: An example variable vane scheduling method includes adjusting variable vanes from a position based on a first schedule to a position based on a different, second schedule in response to a control feature. An example method of controlling flow through a compressor of a turbomachine includes moving variable vanes to positions that allow more flow into the compressor in response to bleed air being communicated away from the compressor.

Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

Abstract: A turbine assembly for a turbocharger can include a C-shaped seal that includes an inner diameter, an outer diameter, an axis aligned parallel to a rotational axis of a turbine wheel, a lower lip that contacts a lower axial face of an outer surface of a shroud component along an annular portion of the shroud component, an upper lip that contacts a lower axial face of an inner surface of a turbine housing, and a wall portion that extends between the lower lip and the upper lip. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: An apparatus and method for controlling turbine blade tip clearance is disclosed herein. A blade track assembly can include a blade track carrier having a plurality of slots and rails defined by paths that vary in radial position as a function of circumferential location. An expansion ring can be operably coupled with the slots of the blade track carrier. A plurality of blade track segments can be operably coupled with the expansion ring and engageable with the rails of the blade track carrier such that expansion and contraction of the expansion ring causes radially outward movement and radially inward movement, respectively, of the blade track segments.

Abstract: A system for detecting airfoil clashing within a compressor comprises a compressor having a row of rotor blades and an adjacent row of stator vanes, an acoustic emission detection system that generates an acoustic emissions signal, a rotor blade monitoring system that generates a blade pass signal, and a processing unit that is in electronic communication with the acoustic emission detection system and the rotor blade monitoring system. The processing unit is configured to fuse the acoustic emissions signal with the blade pass signal to provide a combined signal that is indicative of an airfoil clashing event between the rotor blades and the adjacent row of stator vanes.

Abstract: Systems and methods are disclosed for a turbocharger compressor, the system comprising: an actuatable annular disk comprising choke slots therein; an outer annular disk comprising choke slots therein; and an actuator to rotate the actuatable annular disk relative to the outer annular disk to vary alignment of the choke slots of the actuatable annular disk and the outer annular disk. The actuator may be controlled by an engine controller responsive to operating conditions of the compressor and actuated to align choke slots. Alignment of the choke slots allows air to be drawn into the impeller effectively expanding the compressor flow capacity to prevent compressor choke.

Abstract: An improved bearing and shaft assembly for jet assemblies is disclosed. The improved bearing and shaft assembly includes a bearing assembly having an outer bearing member and an inner bearing member, and a shaft assembly having a shaft member, a shaft protection member, and a locking mechanism. Also, a jet assembly that includes the improved bearing and shaft assembly is disclosed. The jet assembly may be coupled to a motor assembly. The jet assembly further includes the housing that includes at least one inlet aperture and at least one outlet aperture, and an impeller positioned within a cavity of the housing. In addition, a pump comprising a motor assembly and a jet assembly that includes the improved bearing and shaft assembly is disclosed. Furthermore, a method for displacing a fluid using the improved bearing and shaft assembly is disclosed.

Abstract: A method of monitoring a gas turbine engine start system includes monitoring a pressure in a starter air duct in communication with a starter air valve which is in communication with an air turbine starter (ATS); identifying an expected transient pressure response in the starter air duct; and identifying the starter air valve as degraded if the expected transient pressure response does not occur after an open command to the starter air valve.

Abstract: An articulated erection structure is disclosed for use in mobilizing a wind energy extraction device. The wind turbine has blades capable of being disposed in side-by-side, parallel alignment for transportation. The erection structure has a mast that can be configured in a horizontal orientation for transportation with the turbine generator lowered, and reconfigured for power-generating operations in a vertical orientation with the turbine raised. The turbine generator may be mounted with an erection structure to a variety of transportation platforms, such as on a self-propelled vehicle, towed trailer, or transportation pallet. A hybrid system may integrate photovoltaic cells in addition to a wind energy extraction device.

Abstract: The present disclosure relates to shroud bleed in centrifugal compressors. An air-limiting component 130 may be located adjacent to a shroud 120. The shroud 120 may have a primary bleed slot 210, and the air-limiting component 130 may have a secondary bleed slot 310. The primary bleed slot 210 and the secondary bleed slot 310 may overlap at an effective bleed slot location. The air-limiting component 130 may rotate relative to the shroud 120, which may change a streamwise location of the effective bleed slot.

Abstract: An air conditioner for determining whether a human body exists in a sensing region using a plurality of heat sensors, as human body-detecting sensors, installed in the air conditioner and arranged at regular intervals. The air conditioner recognizing, when a human body has been detected, angles formed between the human body-detecting sensors and the human body, and calculating a distance from the human body-detecting sensors to the human body based on the recognized angles and a distance between the human body-detecting sensors, and adjusting a direction and speed of wind according to the calculated distance to the human body, and a control method of the air conditioner. Also, the air conditioner may be used as a security sensor when it does not operate.

Abstract: A centrifugal compressor for compressing a refrigerant vapour in a refrigeration cycle. The compressor comprises an impeller drive shaft (28) supported by first and second radial bearings (32) for rotation within the compressor housing and an impeller assembly including at least one centrifugal impeller wheel mounted on the impeller drive shaft to rotate with the impeller drive shaft. The first and second radial bearings are hydrodynamic fluid bearings in which the bearing fluid is the refrigerant vapour. The compressor further comprising a conduit (36) for supplying a portion of the refrigerant vapour from the impeller assembly to the first and second fluid bearings.

Abstract: An engine system having a compressor coupled to an engine and supplying air to an intake manifold, a throttle controlling the supply of air from the compressor to the intake manifold, a compressor recirculation valve (CRV) having a pneumatic control chamber, and a throttle aspirator having its motive section in fluid communication with an inlet of the throttle and its discharge section in fluid communication with an outlet of the throttle and its suction port in fluid communication with the pneumatic control chamber of the CRV. Such an engine system automatically minimizes surge during boost without a control system activating the CRV. Here, the CRV operates purely on the changes in pressure within the system forming a loop that resets itself. In another embodiment, a gate valve and a vacuum canister may be included rather than having the throttle aspirator directly connected to the CRV's pneumatic control chamber.

Abstract: Embodiments are disclosed that relate to controlling a compressor. In one example, method of controlling a compressor comprises regulating a discharge capacity of the compressor via a control current supplied to a control device, holding the control current supplied to the control device at substantially zero amperes for a first duration, and stepping the control current from substantially zero amperes to a sustainable current that provides a sustainable level of a performance parameter of the compressor.

Abstract: A method of assembling together titanium parts and steel parts by diffusion welding, the method interposing two thin layers of niobium or vanadium and copper respectively between a titanium part and a steel part, evacuating the assembly of parts and interposed metal layers, and subjecting the assembly to hot isostatic compression at a temperature lying in a range 900° C. to 950° C. and at a pressure lying in a range 1000 bars to 1500 bars for about two hours. The method can be applied to fabricating turbine shafts for turbomachines.

Abstract: A compressor control device includes an inlet guide vane opening degree control unit configured to control an opening degree of an inlet guide vane. The inlet guide vane opening degree control unit includes an inlet guide vane opening degree command value calculation unit configured to calculate an inlet guide vane opening degree command value based on an outlet pressure detection value and a plurality of inlet guide vane opening degree correction units each configured to correct the inlet guide vane opening degree command value based on the post-merger pressure detection value and a corresponding inlet flow rate detection value for each of a plurality of upstream-most compressor bodies.

Abstract: It is described a method and a turbine for expanding an organic operating fluid in a Rankine cycle, the method comprising the step of feeding the operating fluid to a turbine provided with a plurality of arrays of stator blades (S1-S4, AR) alternating with a plurality of arrays of rotor blades (R1-R5), to define corresponding turbine stages, constrained to a shaft which rotates on the respective rotation axis. The method comprises the further steps of: a) causing a first expansion of the operating fluid in one or more radial stages (S1-S3, R1-R3) of the turbine, b) diverting (AR) the operating fluid exiting from the radial stages in a direction axial and tangential with respect to the rotation axis, and c) causing a second fluid expansion in one or more axial stages (R4, S4, R5) of the turbine. Step b) corresponds to an enthalpy change of the operating fluid equal to at least 50% of the average enthalpy change provided for completing the fluid expansion in the turbine.

Abstract: A proportional moving air power transmission and energy collection and control system includes a fixed vertical spindle, a vertical rotational hub and a plurality of wings being supported around the vertical hub in 360°. Each of the wings has a blunt leading end and a pointy trailing end and defining an outer surface and an inner surface. In a fully opened position, the trailing end of each wing is moved away from the vertical hub to a diameter of the wing assembly to drive the vertical hub to rotate. In a fully closed position, the wings are overlapped with each other end-to-end to form a hollow cylinder-like structure to furl, such that the diameter of the wing assembly is minimized for facing the wind at all direction.

Abstract: A pump (1) for pumping highly viscous fluids is presented that includes a casing (3), an inlet (7), an outlet (8) and a closed impeller (5) rotatably arranged in the casing between the inlet and the outlet and that has a side room (6) between a shroud (4) of the impeller and the casing (3). In addition, the pump (1) includes a sealing element (7a, 7b, 8a, 8b) between the impeller (5) and the casing (3) each at an inlet side and at an outlet side of the impeller for restricting back flow through the side room (6) and for allowing the fluid contained in the side room to heat up, and an injection port (9) leading into the side room (6) for injecting a fluid into the side room for diminishing disk friction between the shroud (4) of the impeller and the casing (3).

Abstract: An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid.

Abstract: Embodiments of the present disclosure are directed towards a bearing of a rotor assembly having a first lubricant flow path configured to flow a first lubricant flow to a first bearing surface of the rotor assembly and a second lubricant flow path separate from the first lubricant flow path and configured to flow a second lubricant flow to a second bearing surface of the rotor assembly.

Abstract: A turbocharger assembly includes a compressor assembly, a turbine wheel, a shaft, a bearing assembly, and a cooling gas conduit. The compressor assembly includes a compressor impeller. The compressor impeller includes an outermost impeller edge and has a maximum cross-sectional dimension at the outermost impeller edge. The shaft interconnects the compressor impeller and the turbine wheel. The bearing assembly surrounds at least a portion of the shaft. The cooling gas conduit is disposed in fluid communication with the compressor assembly and the bearing assembly. At least a portion of the cooling gas conduit is disposed adjacent the outermost impeller edge such that the cooling gas conduit is configured to receive a portion of intake gases flowing along the outermost impeller edge and guide the portion of the intake gases toward the bearing assembly to cool the bearing assembly.

Abstract: Gas turbine inlet guide vane ice detection and control systems and methods that utilize active infra-red monitoring of inlet guide vanes, detection of ice formation on the guide vanes and elimination of the ice by altering properties of the gas turbine inlet intake airflow, such as by introducing compressed and/or heated air bled from the turbine. Ice has lower detectable emissivity intensity in the infra-red spectrum than ice-free inlet guide vane surfaces. Ice formation is inhibited by direct monitoring of inlet guide vane icing conditions, rather than by indirect empirical assumptions of ice formation based on atmospheric condition monitoring. Direct monitoring mitigates ice formation in real time without reliance on excessive use of gas turbine compressed or heated air bleed, which enhances turbine operational efficiency.

Abstract: The present invention relates to a method for providing a fluid flow to a compressor system of a first turbo machine, wherein the compressor system includes at least one compressor housing in which at least one impeller is arranged and through which a compressor flow flows. The method includes feeding a primary fluid flow to a mixing region of the compressor system. The method further includes feeding a secondary fluid flow from an outside region of the compressor housing to the mixing region so that the secondary fluid flow mixes at least in part with the primary fluid flow to form a resulting fluid flow so that between the primary fluid flow and the secondary fluid flow a momentum exchange takes place, and so that the secondary fluid flow is promoted by the primary fluid flow. The method further includes feeding the resulting fluid flow to the compressor flow upstream of the impeller in the direction of the impeller.

Abstract: A compressor for pressurizing a flow of air within an aircraft including an inlet providing the flow of air to the compressor. An outlet provides the flow of air, after pressurization by the compressor, to a chamber of the aircraft. A diffuser assembly is disposed between the inlet and the outlet. The diffuser assembly includes one or more vanes at least partially impeding the flow of air through the diffuser assembly. A backing plate is included having a surface adjacent to the one or more vanes. The surface includes a relief feature that enables air to bypass the one or more vanes. The relief feature has an axial depth of about 0.25% to 2.5% of a width of a flow path through the diffuser assembly or of about 0.5% to 5% of a thickness of a flange of the backing plate. A method of operating a compressor is also included.

Abstract: It is provided in the present invention a method for synchronously inhibiting subcritical vibrations of magnetic levitation molecular pump rotor, by means of synchronously sampling signals of subcritical vibrations of the rotor generated after the rotor of the magnetic levitation molecular pump touches down so as to obtain the amplitude and the phase of subcritical vibrations of the rotor, based on which outputting a compensation force for inhibiting subcritical vibrations of the rotor. Through using the present method, it is achieved of accurate synchronous for signals of subcritical vibrations and fast inhibition for subcritical vibrations of the rotor.

Abstract: A fluidics module rotatable about a rotational center includes first and second chambers and a compression chamber. First and second fluid channels are provided between the first and second chambers and the compression chamber, respectively. The flow resistance of the second fluid channel is smaller, for a flow of liquid from the compression chamber to the second chamber, than a flow resistance of the first fluid channel for a flow of liquid from the compression chamber to the first chamber. Upon rotation at a high rotational frequency, liquid is initially introduced from the first chamber into the compression chamber via the first fluid channel, so that a compressible medium is compressed within the compression chamber. Subsequently, the rotational frequency is reduced, so that the compressible medium within the compression chamber will expand and so that, thereby, liquid is driven into the second chamber via the second fluid channel.

Abstract: A wind turbine blade is configured such that the lift force from the blade airfoil is always normal, or nearly normal, to the shaft torque. This condition maximizes energy conversion. This objective may be achieved by a) having the airfoil chord always aligned to the actual wind direction (subject only to small angle of attack variations), and b) slowing the turbine rotation rate so that no blade twist is needed. As a result, blade tip speed due to shaft rotation is less than the wind speed, and preferably much less. This low tip speed eliminates any hazard to birds. The lift force from the blade airfoil directly drives the torque on the shaft, so the control problem simplifies to adjusting the blade angle of attack to keep the lift constant across varying wind speeds.

Abstract: The disclosure refers to a method and apparatus for checking the bearing alignment of a rotor of a gas turbine or steam turbine having a rotor with a radial offset and a radial offset surface and in a bearing shell, which supports the rotor, with a radial, at least in sections, end surface, wherein the radial offset surface and the radial end surface face the free end of the rotor. The radial offset is arranged in the bearing shell and offset towards the free end of the rotor. The degree of offset in the axial direction with regard to the rotor is measured at least two different circumferential positions around the rotor periphery in order to determine the alignment of the rotor. Differences in the degree of offset at different circumferential positions are used as measurement for the bearing alignment.

Abstract: The present application provides a steam turbine system. The steam turbine system may include a high pressure section, an intermediate pressure section, a shaft packing location positioned between the high pressure section and the intermediate pressure section, a source of steam, and a cooling system. The cooling system delivers a cooling steam extraction from the source of steam to the shaft packing location so as to cool the high pressure section and the intermediate pressure section.

Abstract: A clutch assembly includes a shaft, vent plug and oil guide sleeve. The shaft includes an internal cavity, first passages for allowing oil to lubricate clutch components, and second passages for allowing excess oil to drain from the internal cavity. The vent plug has a radial passage in communication with the internal cavity for venting the cavity with an external source of air. The oil guide sleeve directs oil into the internal cavity. A method for lubricating and venting an air turbine starter includes delivering lubricating oil to an internal cavity of a clutch via an oil guide sleeve. The oil guide sleeve prevents oil from exiting the cavity through excess oil drainage passages before it lubricates the clutch components. The method also includes draining excess oil from the cavity through excess oil drainage passages so that excess oil does not substantially impede air flow through a vent plug passage.