Honeywell International Inc.

Vibrant Corporation

Robert Hogan

Surendra Singh

Andy Kinney

Frederick William Vensel

Mark C Morris

Donald G Godfrey

James Hall

Vincent Chung

Jim Ohm

Gregory Weaver

Jack Saunders

Randal Easterwood

The disclosed embodiments generally relate to non-destructive evaluation methods. In an embodiment, a method for non-destructive evaluation of a aerospace component includes positioning a first plurality of sensors in the region of interest, positioning a second plurality of sensors in the region of interest, inducing a vibration in the region of interest using the first plurality of sensors and receiving a resonance frequency spectra using the second plurality of sensors, and comparing the received resonance frequency spectra against a reference spectra to determine the presence of an anomaly in the region of interest.

Non-destructive evaluation methods for aerospace components

Thermal Acoustic Imaging (TAI) methods and systems are provided for detecting defects in an object. The TAI system may include a plurality of acoustic wave transceivers (AWTs), which are positioned around the object at different locations, and a broadband frequency signal generator, which is coupled to each of the AWTs. The system may further include an acoustic processor configured to utilize the AWTs to gather acoustic data pertaining to the object, process the acoustic data to generate spectral response data, and then process the spectral response data to determine an optimized setup. The optimized setup may include optimized excitation frequencies and optimized inspection positions for positioning a plurality of infrared imaging devices at different locations around the object. A plurality of infrared imaging devices may then be selectively positioned with respect to the object at the optimized inspection positions and utilized to further inspect the object for defects.

Thermal acoustic imaging methods, systems, and apparatus for detecting defects in an object

The disclosed embodiments generally relate to non-destructive evaluation methods. More particularly, the disclosed embodiments relate to ultrasonic non-destructive evaluation methods for the evaluation of friction welded bladed discs ('blisks'). In an embodiment, a method for non-destructive evaluation of a bladed disc structure includes identifying a region of interest on the bladed disc structure; positioning an ultrasonic transducer and receiver in the region of interest; scanning the region of interest using the ultrasonic transducer and receiver to produce a scan image; and comparing the scan image against a reference image to determine the presence of an anomaly in the region of interest.

Ultrasonic non-destructive evaluation methods for friction-welded blisks

A welding system is provided for welding a first work piece to a second work piece at a joint having a weld face and a root face. The welding system includes a weld face sensor configured to determine first joint characteristics at the weld face; a root face sensor configured to determine second joint characteristics at the root face; a controller coupled to the weld face sensor and the root face sensor and configured to generate positioning signals based on the first joint characteristics and the second joint characteristics; and a welding gun coupled to the controller and positioned proximate to the weld face, the welding gun configured to generate a welding beam for welding the joint based on the positioning signals from the controller.

Welding systems and methods

A method and apparatus is provided to analyze a dual wall structure having at least one hollow core therein and having the same unknown material sound velocities in walls and in post as well. A transducer is located in at least two different positions with respect to the structure, whereby the transducer propagates an ultrasonic wave toward the dual wall structure. A portion of the ultrasonic wave is reflected back to the transducer. One wave traverses a portion of the dual wall structure that has a core filled with a medium having a known material acoustic property. A second wave traverses a portion of the post that has an unknown material sound velocity. From time of flight measurements of the above mentioned waves, the wall thickness and core shift, if any, can be determined.

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Chandler, AZ, United States of America

Robert Hogan