Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

Bryan J Hackett

Eli Cole Warren

Daniel J Boudreau

Charles W Haldeman

Edward F Dreger, Iii

William W Rice

Michael F Sabol

Alan E Ingram

Michael J Saitta

Douglas H Thomesen

Patrick M Harrington

Ryan C Smith

David Dodds

Hunter Tomick

Adam Swagger

Alfred F Covino

Richard C Hendricks

Kyle Hardwick

Nicholas O'Gara

An optical system is provided that includes a conduit fitting, a first connector, a first conduit, a first ferrule and a first nut. The conduit fitting includes a receptacle. The first connector is disposed within the receptacle. The first connector includes a first bore, a first counterbore and a first port radially outboard of the first bore. The first conduit includes a first optics line and a first fluid passage. The first conduit projects longitudinally into the first counterbore and is attached to the first connector. The first optics line projects longitudinally into the first bore. The first fluid passage is fluidly coupled with the first port. The first ferrule circumscribes the first connector. The first nut is threaded onto the conduit fitting and is configured to wedge the first ferrule radially between the first connector and the conduit fitting.

Coupling optical fibers and cooling fluid passages

A lead cooling assembly includes a cooling jacket including a tubular section having an exterior portion and an interior portion, where the interior portion is proportioned to surround a probe lead and provide space for a flow of a gaseous coolant. The lead cooling assembly also includes an intake configured to admit the gaseous coolant into the interior portion of the cooling jacket. The lead cooling assembly further includes a collar configured to fit over the exterior portion of the cooling jacket, where the collar includes one or more exit holes configured to pass the gaseous coolant out of the interior portion of the cooling jacket.

Blade tip clearance probe/lead cooling jacket

A measurement system is provided that includes a probe assembly. The probe assembly includes a capacitance probe and an optical probe. The capacitance probe includes a capacitance sensor that forms a sensor face of the probe assembly. An aperture projects axially through the capacitance sensor to the sensor face. The optical probe is configured with an optical line of sight through the aperture into a volume adjacent the sensor face.

Measurement system having a capacitance probe and an optical probe

A probe adapter includes an adapter body including a probe aperture and a slot. The probe adapter further includes a driver slidably mounted within the slot and slidable between a first position and a second position. The driver includes a first end and a second end opposite the first end. The first end includes a ramped recess extending in a direction from the first end toward the second end. The probe adapter further includes a threaded fastener configured to contact the second end of the driver so as to retain the driver in the first position.

Probe adapter for a blade outer air seal and method for using same

A measurement system for determining an angular position of a component of a gas turbine engine includes one or more proximity sensors positioned at a fixed structure of the gas turbine engine and one or more sensor targets positioned at a rotatable component of the gas turbine engine. Each sensor target of the one or more sensor targets includes a target surface having a variable distance between the target surface and the proximity sensor with rotation of the rotatable component about a component axis of rotation. A measurement of distance between the proximity sensor and the target surface as measured by the proximity sensor is indicative of an angular position of the rotatable component relative to the component axis of rotation.

Proximity vane angle measurement

A variable alignment aerodynamic probe may comprise a probe body having a leading edge and extending radially into a vane case, a sensor element proximate the leading edge, and a bearing coupled to the probe body and the vane case. The probe body may be configured to rotate in response to a turned flow within the vane case. The rotation of the probe body may be configured to maintain an angle of attack of the leading edge with respect to the turned flow between 0&#xb0; and 15&#xb0;.

Systems and methods for variable alignment aerodynamic probes

A performance measurement system of an inlet of a gas turbine engine includes a probe strut configured for installation to a case strut of an inlet case of a gas turbine engine. The probe strut includes one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes, a first attachment point configured to secure the probe strut to a hub portion of the inlet case, and a second attachment point configured to secure the probe strut to an outer case portion of the inlet case. A data acquisition module is located at a central longitudinal axis of the inlet and is operably connected to the probe to collect sensed data therefrom. The probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

Inlet performance measurement system for gas turbine engine

Growing community of inventors

Newington, CT, United States of America

Bryan J Hackett