The Boeing Company

Northrop Grumman Systems Corporation

Belur N Shivashankara

David W Foutch

Kevin O'Brien Gaw

Randy Jay Grove

David John Barene

Michael H Larson

Kory Shaffer

Jeston Lingelbach

Dylan E Jones

Dan John Clingman

James Henry Mabe

Charles A Parente

Leonard J Hebert

Noe Arcas

Ronald F Olsen

Wendell R Miller

Loyd D Jacobs

Samuel Joseph Cowan

Gene Woodard Stubbs

Fredrick M Hutto

Robert P Gerend

James W Ramsay

Kevin O'brien Gaw

Jesse Ian Follet

Zachariah Beach Vandemark

Dan J Clingman

James H Mabe

David William Foutch

A blocker door assembly for use in a gas turbine includes a panel, a core integrally formed with the panel, and a plurality of mounting structures extending from at least one of the panel and the core. The plurality of mounting structures are integrally formed with the core and the panel such that the panel, the core, and the mounting structures are co-molded from a thermoplastic material.

Blocker door assembly having a thermoplastic blocker door for use in a turbine engine

Sound-attenuating heat exchangers and methods of utilizing the same are disclosed herein. The sound-attenuating heat exchangers include an aerodynamically shaped layer, a base, an intermediate layer, and a cooled fluid containment body. The aerodynamically shaped layer defines an aerodynamically shaped surface, an opposed intermediate layer-facing surface, and a plurality of apertures. The intermediate layer defines a shaped layer-facing surface and an opposed base-facing surface. The base defines a base surface. The intermediate layer-facing surface at least partially defines a sound-attenuating volume. The base surface at least partially defines an elongate cooling conduit. The sound-attenuating volume is distinct from the elongate cooling conduit and the intermediate layer at least partially fluidly isolates the sound-attenuating volume from the elongate cooling conduit. The cooled fluid containment body at least partially defines a cooled fluid containment conduit. The methods include methods of utilizing the sound-attenuating heat exchangers.

Sound-attenuating heat exchangers and methods of utilizing the same

A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material.

Dendritic heat exchangers and methods of utilizing the same are disclosed herein. The dendritic heat exchangers include an elongate housing extending between a first end and a second end. The elongate housing defines a housing volume, a first fluid inlet, a first fluid outlet, a second fluid inlet, and a second fluid outlet. The dendritic heat exchangers also include a heat exchange structure extending within the housing volume. The heat exchange structure is configured to receive a second fluid inlet stream from the second fluid inlet and to provide a second fluid outlet stream to the second fluid outlet. The heat exchange structure includes a plurality of dendritic tubulars. Each dendritic tubular includes an inlet region, which defines an inlet conduit, and a branching region. The branching region defines a plurality of branch conduits that extends from the inlet conduit. The methods include methods of utilizing the dendritic heat exchangers.

Dendritic heat exchangers and methods of utilizing the same

In one embodiment, the disclosed vortex generator may include a flap, a bearing configured to be mounted on a surface, an axle retained in the bearing, the flap attached to the axle such that the flap rotates relative to the bearing about the axle, and an actuator made of a shape memory alloy attached to the flap and to a support, the actuator shaped to receive the axle therethrough, such that a change in temperature of the actuator causes the actuator to rotate the flap relative to the bearing.

Vortex generator using shape memory alloys

A device for measuring the acoustic absorption properties of materials such as liners for jet engines has a first housing, an acoustic driver configured to provide acoustic energy to the first housing, a second housing attached to the first housing, and an acoustic driver configured to provide acoustic energy to the second housing. Acoustic sensors are used to measure the acoustic energy emitted from the two housings and to measure the absorption of each of the housings.

Apparatus and method for measuring the acoustic properties of acoustic

An engine assembly comprising an engine having an unducted propeller mounted in a pusher configuration. The engine is supported by a mounting strut located upstream of the propeller. The trailing edge portion of the strut discharges air through a rearwardly facing slot to diminish discontinuity of airflow moving from the region of the strut to the propeller, so that load variations on the propeller are diminished, and also improves flow of the intersection of the strut and the fuselage.

Mounting assembly for unducted prop engine and method

A flush-dish microphone system for measuring aircraft flyover noise is disclosed. The system includes an acoustically hard base supporting a microphone. The base is configured along its periphery to define a plurality of outwardly extending tapered members. Each of the tapered members includes a pair of converging edges that are each at least in part curved. The curved edges produce a favorable progressive match of acoustic impedance at the ground/tapered member boundary that reduces edge diffraction contamination of the noise signal being measured by the microphone.

Acoustic reflector for ground plane microphone

A gas turbine engine combustion noise suppressor for a jet engine combustor assembly of the annular, cannular, or canannular variety includes a resonant cavity-type or bulk absorber-type noise suppressor. The inner wall of the combustor assembly is configured to couple combustion noise, generated within the burner cavity formed by the inner combustor wall, into the airflow duct formed between the inner and outer walls of the combustor assembly. The outer wall is perforated to, in turn, couple the combustion noise from the airflow duct into the resonant cavity-type or bulk absorber-type noise suppressor that is mounted on the portion of the outer wall that is adjacent the burner cavity. The inner combustor wall can include a large number of small acoustic openings and/or a smaller number of larger openings that include airflow barriers to couple the combustion noise into the combustor airflow duct while simultaneously minimizing air flow into the burner cavity from the combustor airflow duct. In other embodiments, a short burner cavity is employed that includes flutes or corrugations in the inner combustor wall to effect mixing of air and combustion products normally accomplished within the aft section of a conventional burner cavity. In each embodiment the structural relationship between the combustor and the noise suppressor modifies the combustion process occurring within a conventional combustor to generate less noise than a conventional combustor. The noise suppressor functions to further reduce the noise level.

Gas turbine engine combustion noise suppressor

Growing community of inventors

Bellevue, WA, United States of America

Belur N Shivashankara