General Electric Company

Other

Rafael Jose Ruiz

Robert Joseph Albers

Marcia Boyle

Christopher Charles Glynn

William Lee Herron

Scott Anthony Estridge

John Erik Hershey

Robert Proctor

Michael Terry Bucaro

Samhita Dasgupta

Brock Estel Osborn

Donald Lee Gardner

Roger Francis Wartner

Kevin Stephen Hansell

Ryan Michael Urbassik

A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.

Aircraft gas turbine engine blade tip clearance control

A multi sensor clearance probe with at least longitudinally and transversely spaced apart first and second sensors operable to measure first and second distances respectively between the sensors and a longitudinally spaced apart rotating rotor. The sensors being operable to measure blade tip clearances between radially outer turbine blade tips and an annular stator shroud circumscribing the blade tips. The blade tips may be squealer tips and the sensors operable to measure the distances between the sensors and tops of squealer tip walls and outwardly facing walls within cavities of the squealer tips. The probe may be operably connected to a controller for sending signals to the controller indicating the first and second distances for controlling an air valve used for active clearance control. Two or more of the probe may be used to determine rotor centerline offset.

Multi sensor clearance probe

A method for operating a gas turbine engine is provided. The gas turbine engine includes a fan, a high pressure turbine coupled downstream from the fan, and a low pressure turbine downstream from the high pressure turbine. The method includes channeling a portion of air discharged from the fan through a clearance control system including an inlet assembly that includes a plurality of louvers, and directing air from the inlet assembly into a first pipe and second pipe coupled to the inlet assembly such that pressure losses associated with the airflow are facilitated to be reduced.

Method and apparatus for operating gas turbine engines

A gas turbine engine thermal control apparatus includes at least one annular spray tube having spray holes oriented to impinge thermal control air onto a fillet between an outer casing and a forward thermal control ring and, in a more particular embodiment, into a center of the fillet. The apparatus may include an annular segmented stator shroud attached to the outer casing and circumscribing radial outer blade tips of turbine blades of a turbine rotor. A thermal air distribution manifold encircling a portion of the outer casing includes an annular supply tube connected in fluid supply relationship to plenums of header assemblies. The annular spray tube is connected to at least one of the plenums and may be elongated radially inwardly and axially. Baffles attached to radially outwardly facing surfaces of the panels may be contoured to form exhaust passages having exhaust passage inlets and outlets between the baffles and the panels.

Thermal control of gas turbine engine rings for active clearance control

A portable battery charger that is powered by a gasoline, diesel, or propane engine. The portable device incorporates a recoil or electric starter and an engine throttle lever that can be used to vary the RPM of the engine and therefore the voltage/current output of the charger. The charger uses a permanent magnet alternator equipped with a belt tension adjustor arm and a heavy duty diode rectifier. The components of the charger (the engine and the alternator) are positioned on a wheeled, heavy-gauge steel, roll around cart that makes the charger easily portable. The two-wheeled cart includes an extended handle, allowing the user to move and steer the charger into position for use. Positioned on this handle is a control box with an anti-spark keyed switch that blocks any charging current from traveling through the charging cables until the switch is thrown. This control facilitates the safe hook-up of the charging clamps while the charger (engine) is running. The charger includes heavy duty cables between the alternator and the anti-spark control box, and additionally out from the control box to insulated clamps that are used to connect to the batteries. The control box additionally includes an ammeter and a voltmeter to indicate the charging current and voltage. The portable charger structured in this manner can be used to charge a non-specific number of batteries in parallel, typically in less than 2-4 hours depending on the size and state of the existing battery charge. The charger may also be used in the process of equalizing a bank of batteries to facilitate a reduction in stratification and sulfation.

Portable battery charger powered by internal combustion engine

A turbine engine stator assembly in juxtaposition across a radial gap with a rotary blading assembly includes a radially movable shroud and a gap control member made of at least one shape memory alloy (SMA). The SMA is selected and preconditioned to deform pre-selected amounts to change the radial length of the gap during engine operation responsive to temperature about the SMA. A fluid flow means delivers fluid to the SMA at pre-selected temperatures during engine operation.

Turbine engine stator including shape memory alloy and clearance control method

A method of operating a gas turbine engine is provided. The gas turbine engine includes at least one engine casing and at least one rotor assembly. The method includes directing airflow through a supply pipe and into a heat exchanger, lowering the temperature of the airflow in the heat exchanger, and directing the cooled airflow into the engine casing to cool the casing.

Methods and apparatus for maintaining rotor assembly tip clearances

A method for controlling fluid leakage between a first pressure region and a second pressure region within a gas turbine engine using a first sealing member and a second sealing member. The first sealing member is movably coupled to a portion of the gas turbine engine, and a space defined generally between a portion of the first sealing member and a portion of the second sealing member fluidly couples the first pressure region to the second pressure region. The method includes moving the first sealing member towards the second sealing member using fluid pressure within a portion of the engine, and, using the first and second sealing members, substantially controlling fluid leakage between the first pressure area and the second pressure area through the space generally without contacting the first sealing member with the second sealing member.

Growing community of inventors

Liberty Township, OH, United States of America

Rafael Jose Ruiz