Andrew V Consiglio

20190189901, Jun 20, 2019

Dec 18, 2017

15/844711

- Farmington CT, US
Andrew Consiglio - Southbury CT, US

H01L 41/113
H01L 41/08
F01D 17/02

A sensor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a substrate layer formed on a localized surface of a rotatable gas turbine engine component, and at least one pair of transducers deposited on the substrate layer.

20150172565, Jun 18, 2015

Dec 4, 2014

14/560814

- Hartford CT, US
Andrew Consiglio - Southbury CT, US
Christopher J. Lehane - South Windsor CT, US
Mark F. Zelesky - Bolton CT, US

H04N 5/33
G06T 7/60
G06T 11/60

A method for thermally imaging a moving workpiece of a gas turbine engine comprises identifying a plurality of geometric features to construct a composite image. The geometric features include at least one integral thermal feature of the moving workpiece, and at least one artificial feature applied to the workpiece for diagnostic purposes. One of the plurality of geometric features is identified as a master feature, and the remainder of the plurality of geometric features are located relative to the master feature with relative actual coordinates. A pixel location of the master feature is identified or each image, and the remainder of the plurality of geometric features are located relative to the master feature with relative pixel coordinates. Offset, rotation, and scaling of the secondary images are varied to minimize a relative difference between the relative pixel coordinates and the relative actual coordinates. The offset, rotated, and scaled secondary images are combined with the reference image to form a composite image.

20150172566, Jun 18, 2015

Dec 4, 2014

14/560843

- Hartford CT, US
Andrew Consiglio - Southbury CT, US
Christopher J. Lehane - South Windsor CT, US
Mark F. Zelesky - Bolton CT, US

H04N 5/33
H04N 5/265
G06T 7/00

A method for thermally imaging a moving workpiece of a gas turbine engine using long wavelength infrared (LWIR) images of the workpiece captured during operation of the gas turbine engine. The method comprises determining average pixel intensity and pixel variation in intensity for each pixel across the plurality of LWIR images, determining average area intensity and area variation in intensity across a range of areas defined by increasing length scales about a selected pixel, and identifying as a critical length scale a length scale at which area variation in intensity is minimized as a function of length scale, for which the area intensity remains substantially the same as the average pixel intensity of the selected pixel. A composite image is built such that each pixel of the composite image has intensity equal to an average area intensity centered on that pixel, over the critical length scale.

20150160097, Jun 11, 2015

Dec 9, 2014

14/564774

- Hartford CT, US
Andrew Consiglio - Southbury CT, US
Mark F. Zelesky - Bolton CT, US
Joel H. Wagner - Wethersfield CT, US

G01M 15/14
G01J 5/00
F01D 21/00

A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.