United Technologies Corporation

Raytheon Technologies Corporation

Darren M Wind

Eli Cole Warren

John E Paul

Ian F Agoos

Sebastian Martinez

Alan E Ingram

Michael J Saitta

Robert Kujawa

Corey A Benoit

William W Rice

Kevin Andrew Ford

Michael F Sabol

Patrick M Harrington

Charles Kniffin

Steven D Mitchell

Ian Alexander Fielder Agoos

Mark A Davidson

An optical probe includes an optical housing, a transmitting lens and a receiving lens. The optical housing extends from a proximate end to an opposing distal end. The transmitting lens is disposed at the distal end and is configured to output a first transmitted signal beams having a first transmission axis and a second transmitted beam having a second transmission axis that is different from the first transmission axis. The receiving lens is disposed at the distal end and configured to receive the first and second reflected signal beams corresponding respectively to the first and second transmitted signal beams. The optical housing has formed therein a transmitting optical channel configured to communicate an input optical signal from the proximate end to the transmitting lens. A receiving optical channel separated from the transmitting optical channel communicates the first and second reflected signal beams to the proximate end.

Optical time of arrival airfoil measurement probe

An axial location of a time of arrival probe may be determined by attaching a wedge comprising a distal surface to a blade. A first edge of the distal surface and a second edge of the distal surface may form an angle. The axial location of the probe may be determined based on the angle and a distance extending from the first edge of the wedge to the blade.

Determining axial location of time of arrival probe

A low profile un-lensed non-intrusive stress measurement system probe may comprise a housing comprising a first channel and an optical face, a first hypotube disposed within the first channel and coupled at a sensing aperture in the optical face, and a plurality of optical fibers disposed within the first hypotube, wherein the first hypotube executes a bend between 45&#xb0; and 90&#xb0; within the housing.

Low profile embedded non-intrusive stress measurement system probe

In combination a wear indicator and a component of a gas turbine engine is provided. The wear indicator is secured to a surface of the component of the gas turbine engine. The wear indicator comprising: a first side delaminates when impacted by a blade of the gas turbine engine; a second side parallel to the first side, the second side being secured to a surface of the component of the gas turbine engine; a mid-section interposed between the first side and the second side; and a reference dimension remains constant when the first side delaminates.

Wear indicator for determining wear on a component of a gas turbine engine

Disclosed is a first transmitter that transmits a first optical signal towards a target, a plurality of receivers that receive the first optical signal after the first optical signal is reflected by the target and each provides a respective received optical signal, at least one photodetector that receives the received optical signals and provides at least a first electrical signal, and a processor that receives the first electrical signal to compute a position of the target relative to a baseline position based on: a first position of a first receiver of the plurality of receivers, a second position of a second receiver of the plurality of receivers, the first electrical signal. The processor computes a clearance between the target and a component based on a third position of a third receiver, a fourth position of a fourth receiver and a second electrical signal.

Determination of a clearance and a position of a target

A system and method for performing stress measurement on rotating parts is disclosed. The system may include a laser assembly configured to emit a plurality of laser beams having different wavelengths, and a probe assembly mounted proximal to a rotatable part in a device. The probe assembly may be configured to output a reflected laser beam onto a first target on the rotatable part. The probe assembly may be configured to output another reflected laser beam onto a second target on the rotatable part. The probe assembly may include a redirector, and a lens assembly mounted proximal to the redirector and configured to converge the laser beams. The redirector may be configured to change the direction of each emitted laser beam.

Multiple laser time of arrival probe

A turbine section according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including an edge and a probe positioned a distance from the airfoil. The probe is configured to detect radiation emitted from a radiation source. A sensor is operatively coupled to the probe and is configured to generate a signal utilized to determine when the edge of the airfoil extends into a line-of-sight between the probe and the radiation source.

Background radiation measurement system

A system and method for performing stress measurement on rotating parts is disclosed. The system may include a laser assembly configured to emit a laser beam, and a probe assembly mounted proximal to a rotatable part in a device. The probe assembly may be configured to output a reflected laser beam onto a first target on the rotatable part. The probe assembly may further be configured to move the reflected laser beam from the first target to a second target on the rotatable part. The probe assembly may include a redirector moveable from a first position to a second position, and a lens mounted proximal to the redirector and configured to focus the laser beam. The redirector may be configured to change the laser beam direction from a first direction to a second direction when moved from the first position to the second position.

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Glastonbury, CT, United States of America

Darren M Wind