Honeywell International Inc.

Deanna Pinar Chase

Amandine Miner

Richard Bryce Fox

Paul Kurlak

Stephen Frederic Yates

Russell W Johnson

Harry Lester Kington

Peter M Michalakos

David K Jan

Mike S Koerner

Bijan F Hagh

Anthony Martinez

Jason Smoke

Don Mittendorf

David R Waldman

Michael Kahrs

Lorenzo Crosatti

Ed Zurmehly

Brent Ludwig

Greg Ockenfels

Gregory Ockenfels

Alonso Peralta-Duran

Mike Koerner

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

Methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities

A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.

Diverging-converging cooling passage for a turbine blade

Dual alloy bladed rotors are provided, as are methods for manufacturing dual alloy bladed rotors. In one embodiment, the method includes arranging bladed pieces in a ring formation such that contiguous bladed pieces contact along shank-to-shank bonding interfaces. The ring formation is positioned around a hub disk, which is contacted by the bladed pieces along a shank-to-hub bonding interface. A metallic sealing material is deposited between contiguous bladed pieces utilizing, for example, a laser welding process to produce an annular seal around the ring formation. A hermetic cavity is then formed, which is circumferentially bounded by the annular seal and which encloses the shank-to-shank and shank-to-hub bonding interface. Afterwards, a Hot Isostatic Pressing process is performed during which the ring formation and the hub disk are exposed to elevated pressures external to the hermetic cavity sufficient to diffusion bond the shank-to-shank and shank-to-hub bonding interface.

Dual alloy bladed rotors suitable for usage in gas turbine engines and methods for the manufacture thereof

Compliant coupling systems and methods are provided for coupling a shroud to an engine casing. The complaint coupling system includes a retaining ring adapted to be positioned adjacent to the shroud and adapted to be coupled to the engine casing. The retaining ring defines a coupling channel about a circumference of the retaining ring and at least one notch that interrupts the coupling channel. The complaint coupling system also includes a first clip received within the coupling channel. The first clip has a biasing portion that extends into a space defined by the at least one notch, and the biasing portion is adapted to contact the shroud. The complaint coupling system includes a second clip received within the coupling channel. The second clip has a bumper portion that extends into the spaced defined by the at least one notch, and the bumper portion is adapted to contact the shroud.

Compliant coupling systems and methods for shrouds

An Environmental Control System includes a sensor, an air purification subsystem, and a controller in communication with the sensor and air purification subsystem. The sensor detects a contaminant in the air and generates a contaminant signal. The controller compares the contaminant signal to a predicted sensory response threshold. When the contaminant signal reaches the predicted sensory response threshold, the controller commands the air purification subsystem to alter a condition in the air.

Human factors approach to control contaminant concentrations in aircraft supply air from engine and APU bleed air and ground air sources, and in recirculated air being delivered to aircraft cabins for the optimization of user experience and energy consumption

An environmental control system (ECS) having particulates in air therein includes a sensor, an air purification subsystem, and a controller in communication with the sensor and air purification subsystem. The sensor detects particulates in the air, and generates a particulate concentration signal. The controller: compares the particulate concentration signal to a predicted particulate concentration threshold that is based on one of a probability of odor detection, a probability of sensory irritancy detection, and a combination thereof. When the particulate concentration signal reaches the predicted particulate concentration threshold, the controller commands the air purification subsystem to alter a condition in the air containing the particulates.

Method to use ultrafine particulate matter detection and measurement to control air supply system contaminant delivery to the aircraft cabin environment

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Tempe, AZ, United States of America

Deanna Pinar Chase