General Electric Company

General Electric Technology Gmbh

Thomas Earnest Moldenhauer

Thomas James Batzinger

Keith Cletus Belsom

Francis Alexander Reed

Robert William Bergman

Sivaramanivas Ramaswamy

Gareth William David Lewis

Daniel Lawrence Banowetz

Bouria Mohamed Faqihi

James Frederik Den Outer

Michael John Lynch

Sheng Jia Zheng

Prasad Thapa

Richard Preston Epley

Michael Charles Freda

Steven C Castellaw

Diego Quinones

Abdul Khaliq

Manoj Kumar Km

The present application provides a cooling hole location system for locating a cooling hole in a gas turbine component, wherein the cooling hole is covered by a thermal barrier coating. The cooling hole location system may include a light source positioned on a first side of the gas turbine component and an optical detector positioned on a second side of the gas turbine component. The optical detector detects light from the light source visible through the thermal barrier coating covering the cooling hole.

Systems and methods of locating cooling features in a gas turbine component under thermal barrier coatings

Various aspects include methods of inspecting a substantially round hole in a material. One method can include: feeding a probe axially into the substantially round hole until the probe completely passes through the substantially round hole while the probe is activated; rotating the probe at least ninety degrees around a primary axis of the substantially round hole after feeding the probe completely through the substantially round hole; removing the probe axially from the substantially round hole after rotating the probe at least ninety degrees while the probe is activated; and compiling at least one of eddy current data or ultrasound data about the hole from the feeding of the probe axially into the substantially round hole and the removing of the probe axially from the substantially round hole.

Inspection methods with probe for substantially round hole

A method for detecting leakage at a fluid connection for a gas turbine fuel supply system is disclosed herein. The method includes closing a flow control valve at an upstream end of the fuel supply system and pressurizing the fuel supply system with a compressed medium via a compressed medium supply to a target pressure. The target pressure is less than a pressure threshold of a check valve that is disposed downstream from the compressed medium supply and upstream from a corresponding combustor of the gas turbine. The method further includes pointing a receiver portion of an ultrasonic detection device proximate to at least one tube fitting of the fuel supply system located between the flow control valve and a combustor which is fluidly coupled to the fuel supply system. Detection of an increase in sound level and/or the sound of popping at the tube fitting is indicative of a leak at the tube fitting.

Method for detecting leaks in a fuel circuit of a gas turbine fuel supply system

A method for inspecting a wye ring in a generator includes the steps of dismantling the generator to gain access to the wye ring and at least a portion of a rotor, applying a test signal to the rotor and measuring an inductive voltage at two or more locations near the wye ring. A comparing step compares results from the measuring step to determine if a fault exists in the wye ring. A predetermined difference in inductive voltage measurements indicates presence of the fault.

Method for inspecting wye ring

An apparatus is provided for inspecting a component of a turbomachine in-situ. The apparatus includes an end effector having a frame defining a stable platform with a curved surface of the component, a spring loaded suspension attached to the frame, and a probe connected to a wedge member, where the probe and wedge member are connected to the spring loaded suspension. The probe is configured to inspect the component by passing signals through the wedge.

Apparatus for inspecting turbomachine components in-situ

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Burnt Hills, NY, United States of America

Thomas Earnest Moldenhauer