General Electric Company

Mohamed Sakami

Nirm Velumylum Nirmalan

Guanghua Wang

James Michael Storey

Fulton Jose Lopez

Jeremy Clyde Bailey

Shobhana Mani

Bernard Patrick Bewlay

William Albert Challener

Vinay Bhaskar Jammu

Jason Harris Karp

Robert Michael Zirin

Richard Scott Bourgeois

Thomas Charles Adcock

Naveenan Thiagarajan

Kristopher John Frutschy

James William Sears

Jason Edward Dees

James DeLancey

William Patrick Waters

Wontae Hwang

Christopher Dale Mathias

David Howard Syck

Hongmei Zhang

Ronald W Ferree, Jr

Jeffrey Jay Porubcan

Mao Leng

Aaton John Avagliano

A gas turbine engine having an optical imaging system with a housing configured for mounting to a wall of the turbine engine, a hollow probe extending from the housing and having a longitudinal axis, and an image receiving device at an end of the hollow probe configured to receive at least one of a perspective or image.

Optical imaging system for a gas turbine engine

An imaging system includes a sight tube extending along a longitudinal axis of the imaging system and configured to extend through an access port. The sight tube includes a wall extending about the longitudinal axis and defining a cavity. The imaging system also includes a plurality of cooling channels extending through the sight tube. The plurality of cooling channels are configured to direct cooling fluid through the sight tube for cooling the imaging system. The plurality of cooling channels are formed in the sight tube such that at least one cooling channel of the plurality of cooling channels extends in a direction oblique to the longitudinal axis.

Imaging system for inspecting components of turbomachines and method of assembly thereof

An apparatus for insertion through an opening in an outer casing of a gas turbine engine and inspection of internal turbine components at elevated temperatures having an optical sight tube configured to optically communicate with an interior of gas turbine engine via a distal end disposed at the interior and a proximal end disposed exterior of the internal turbine components and defined by a first longitudinal wall, at least one lens at the distal end of the optical sight tube adjacent to the longitudinal wall; and at least one longitudinal cooling groove in the longitudinal wall for flowing a cooling medium from a location external to the turbine to cool the optical sight tube at a location at least adjacent the distal end.

Optical apparatus and sight tube for inspecting turbine engine components

A system for optically monitoring a gas turbine engine includes an optical multiplexer configured to receive multiple images from respective viewports into the gas turbine engine. The optical multiplexer includes a movable reflective device configured to selectively direct at least a portion of each image toward a detector array, and the detector array is directed toward a fixed location on the optical multiplexer.

Optical monitoring system for a gas turbine engine

A system for an electronic device includes a housing having one or more walls that define an internal region. An outlet port is fluidically coupled to the internal region of the housing, which allows emission of a fluid from the internal region of the housing as a first flow at a first temperature. A merging element, fluidically coupled to the outlet port, merges the first flow with a second flow, which has a second temperature that is less than the first temperature.

Systems and methods to thermally manage electronic devices

A heat flux measurement device includes at least two thermocouples disposed within a front portion of the device at different axial distances from a front wall of the device. A correlation between the measured heat fluxes from the device over a period of time is used to estimate a fouling thickness on a wall, for example, a water wall of a radiant syngas cooler (RSC).

Heat flux measurement device for estimating fouling thickness

A temperature measurement device includes a first thermocouple mounted on a tubular body that is shielded from the effects of radiation by a radiation shield, and a second, unshielded thermocouple. A difference in the measured temperatures from the first and second thermocouples is compared with calculated temperatures using an iterative process to determine a corrected temperature of the gas stream that estimates and compensates for incident radiation.

Temperature measurement device that estimates and compensates for incident radiation

Growing community of inventors

West Chester, OH, United States of America

Mohamed Sakami