Williams International Co., L.l.c.

Caterpillar Inc.

Mark E Suchezky

Thomas J Williams

Gregg G Williams

Robert S Thompson, Jr

David W Jarrell

James B Drobnis

Curtis E Lynch

Richard E Annati

Craig Miller

Lisa M Simpkins

A sacrificial outer sleeve of a self-eroding single-use gas-turbine-engine igniter contains a main pyrotechnic composition and an initiator embedded therein proximate to a distal portion of the sacrificial outer sleeve. The sacrificial outer sleeve extends within a combustion chamber of the gas-turbine engine when operatively coupled thereto so as to provide for igniting a fuel/air mixture therein. The sacrificial outer sleeve is constructed of a material that is consumable either responsive to combustion of the main pyrotechnic composition responsive to activation of the initiator responsive to an actuation signal communicated via an associated signal conduit, or, responsive to a subsequent operation of said gas-turbine engine to which the igniter is operatively coupled, when operatively coupled thereto.

Self-eroding single-use gas-turbine-engine igniter

A fluid-conduit collector spans across a plurality of collector-inlet interface structures and at least one fluidic diode element. A branch inlet portion of at least one collector-inlet interface structure, in fluid communication with a corresponding fluid-conduit runner portion, provides for receiving exhaust gases from a corresponding separate exhaust port of an intermittent-combustion internal combustion engine. A main inlet portion of the collector-inlet interface structure in fluid communication with an outlet portion thereof defines a portion of the fluid conduit of the collector. The branch inlet portion is in fluid communication with the outlet portion via a collector inlet port that is at least partially bounded by a relatively-sharp-edged junction with the fluid conduit of the collector. The fluidic-diode element located coincident with, or downstream of, the collector inlet port provides for a relatively-higher coefficient of discharge for exhaust gases flowing towards an outlet of the collector, than for an associated reverse-directed bulk flow or acoustic pressure wave flowing in a reverse direction.

Valvular-conduit exhaust manifold

A fluid-conduit collector () spans across a plurality of collector-inlet interface structures (&#x2033;) and at least one fluidic diode element (&#x2033;). A branch inlet portion ('&#x2033;) of at least one collector-inlet interface structure (&#x2033;), in fluid communication with a corresponding fluid-conduit runner portion (), provides for receiving fluid from a source of fluid (). A main inlet portion (&#x2032;) of the collector-inlet interface structure in fluid communication with an outlet portion (&#x2033;) thereof defines a portion of the fluid conduit of the collector (). The branch inlet portion (&#x2032;&#x2033;) is in fluid communication with the outlet portion (&#x2033;) via a collector inlet port () that is at least partially bounded by a relatively-sharp-edged junction () with the fluid conduit of the collector (). The fluidic-diode element (&#x2033;) located coincident with, or downstream of, the collector inlet port () provides for a relatively-higher coefficient of discharge for fluid flowing () towards () an outlet () of the collector (), than for fluid flowing () in a reverse direction ().

Valvular-conduit manifold

A turbocharger is provided that includes a turbine, a compressor and a bearing housing disposed and connected between the turbine and the compressor. A shaft is rotatably disposed within the bearing housing and extending into the turbine and the compressor. A bearing arrangement is disposed between the shaft and the bearing housing and includes a inner bearing race element and an outer bearing race element. The compressor wheel includes a hub having a collar portion with a bore therein for receiving an end of the shaft. An end portion of the inner bearing race element is arranged to engage an outer circumferential surface of the collar portion.

Turbocharger with bearing piloted compressor wheel

Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with corresponding aft hollow interior portions of each blade. A radially-extending central rib within each blade partitions the hollow interior thereof into aft and forward hollow interior portions that are in fluid communication through an associated opening in the central rib and through a radially-extending gap between the central rib and the interior surface of the blade. A blade outlet duct provides for fluid communication between the forward hollow interior portion and a forward cavity of the bladed rotor, and a rotor outlet duct provides for discharging the fuel from a radially-inboard portion of the forward cavity.

Fuel-cooled bladed rotor of a gas turbine engine

An aftwardly-extending internally-threaded boss of a boreless-hub compressor rotor of a turbocharger engages a corresponding externally-threaded forward end portion of an associated rotor shaft of the turbocharger, wherein an internal surface of an inner race of an associated rolling-element bearing of the turbocharger is in engagement with both an external surface of the rotor shaft and an external surface of the internally-threaded boss of the boreless-hub compressor rotor, wherein the rotor shaft extends through the inner race of the rolling-element bearing.

Turbocharger compressor rotor alignment system

Fuel () is supplied to a rotatable portion () of a gas turbine engine () comprising a rotor () and at least one blade () operatively coupled thereto, so as to provide for cooling at least one of the rotor () or the at least one blade () by transforming the fuel () to a vapor or gaseous state. The fuel () is discharged in a vapor or gaseous state from the rotatable portion () directly into a combustion chamber () of the gas turbine engine ().

Gas turbine engine cooling system and method

A first trailing edge portion of a scarfed jet engine exhaust nozzle aft of a second trailing edge portion relative to a central axis of an associated exhaust duct causes an automatic nozzle-pressure-ratio responsive transverse deflection of the associated exhaust flow away from the first trailing edge portion. When offset from both the center of gravity (CG) and the central longitudinal axis of an aircraft, at a relatively low nozzle pressure ratio, e.g. during takeoff, the thrust vector from the exhaust flow acts relatively close to the CG, whereas at a relatively high nozzle pressure ratio, e.g. during relatively high-speed cruise, the scarfed exhaust nozzle deflects the exhaust flow so that the resulting thrust vector is relatively parallel to the path of the aircraft. With the final portion of the exhaust duct skewed, the primary axis of the jet engine can be relatively parallel to the path of the aircraft.

Jet engine exhaust nozzle and associated system and method of use

A turbine nozzle is constructed from a plurality of associated circumferential turbine nozzle segments each of which incorporates at least one pre-formed annular-segment passage bounded at a first azimuthal boundary by a first portion of a first bounding nozzle vane, and at a second azimuthal boundary by a second portion of a second bounding nozzle vane, with the at least one pre-formed annular-segment passage therebetween, wherein when assembled in the turbine nozzle, a first portion of a first bounding nozzle vane of one circumferential turbine nozzle segment is joined to a second portion of a second bounding nozzle vane of another adjacent circumferential turbine nozzle segment so as to form therebetween a nozzle vane of the turbine nozzle, wherein the minimum through-flow area of the associated at least one pre-formed annular-segment passage is substantially unaffected by the assembly of the circumferential turbine nozzle segments to form the turbine nozzle.

Turbine nozzle apparatus and associated method of manufacture

A bearing housing of a rotor shaft support assembly of a turbocharger core mounts to and closes a forward end of a cavity that both receives and discharges exhaust gases of an internal combustion engine. A turbine rotor operatively coupled to a rotor shaft and a compressor rotor of an associated turbocharger rotor assembly rotates within a turbine rotor shroud portion of an associated turbine nozzle cartridge assembly, wherein the rotor shaft is rotationally supported by at least one bearing within the bearing housing. The turbine nozzle cartridge assembly provides for directing exhaust gases from the cavity through a peripheral inlet leading to a plurality of vanes between forward and aft walls, through the turbine rotor shroud portion, and then through a nozzle exhaust portion incorporating an external sealing surface on an aft portion thereof that cooperates with a sealing element where the exhaust gases are discharged from the cavity.

Growing community of inventors

South Lyon, MI, United States of America

Mark E Suchezky