General Electric Company

Michael Adelbert Sullivan

Mark Andrew Cournoyer

Bhalchandra Arun Desai

Huong Van Vu

Eric Milton Lafontaine

Gary Michael Itzel

Richard William Albrecht, Jr

Larry W Plemmons

Xiuzhang James Zhang

Scott Edmond Ellis

Fred W Staub

Adam John Fredmonski

Robert Harold Weisgerber

Harold P Rieck, Jr

Felipe Roman-Morales

R Paul Chiu

Sergio Daniel Marques Amaral

Richard Mallory Davis

Ariel C Jacala

Yang Liu

Avnit Singh

Dale W Ladoon

Ferruccio Candela

Armando J Quinones

Mahesh Madhukar Athavale

Embodiments of the present disclosure include an oil degradation byproducts removal system. The oil degradation byproducts removal system includes a plurality of electrostatically-charged drum assemblies configured to pass through an oil flow. The oil degradation byproducts removal system is configured to be disposed within an accessory module of a turbine engine system.

Rotary oil degradation byproducts removal system

A gas turbine inlet heat exchange coil assembly includes a gas turbine inlet housing formed to include an inlet and an outlet and a flow path therebetween. A plurality of adjacent coils are located in proximity to the inlet, and moveable between a closed operative position where the coils are aligned substantially in a plane so as to maximize resistance to flow along the flow path, and an open inoperative position where said coils are individually rotated substantially 90&#xb0; such that the coils lie in individual, parallel planes so as to minimize resistance to flow along the flow path.

Retractable gas turbine inlet coils

A system for conditioning air flow to a gas turbine includes a filter housing and a conditioning media inside the filter housing to adjust the temperature of the air flowing through the filter housing. At least one of a depth or a density of the conditioning media varies across the filter housing. A method for conditioning air flow to a gas turbine includes flowing air through a filter housing connected to the gas turbine and flowing the air across a conditioning media in the filter housing. The method further includes conditioning the air flow to reduce the temperature difference of the air exiting the filter housing across a dimension of the filter housing.

System and method for conditioning air flow to a gas turbine

A blade tip of a turbine rotor blade for a gas turbine engine, the turbine rotor blade including an airfoil and a root portion for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge, the pressure sidewall and suction sidewall extending from the root portion to the blade tip, and a squealer tip cavity formed at the blade tip, the blade tip comprising: a trailing edge trench originating at the squealer tip cavity, wherein the trailing edge trench generally extends toward the trailing edge of the blade tip.

Rotor blades for turbine engines

A turbine bucket for a turbomachine includes a main body portion having a base portion and an airfoil portion, the base portion includes a bucket cavity forward region and a shank cavity. The turbine bucket also includes a cooling channel that extends through the main body portion. At least one flow passage extends between one of the cooling channel and the shank cavity, toward the bucket cavity forward region. The at least one flow passage delivers a flow of cooling gas toward the bucket cavity forward region. The flow of cooling gas limits ingestion of hot gases into the bucket cavity forward region.

Turbine bucket for a turbomachine and method of reducing bow wave effects at a turbine bucket

The first stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and R set forth in Tables I and II, respectively, and second stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values set forth in Tables III and IV, respectively. The X, Y and R values are in millimeters. R represents distances along a radius from an axis of rotation of the turbine. For each airfoil, X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius at each distance R. The profile sections at the R distances for each airfoil are joined smoothly with one another to form the airfoil shape. The airfoil shapes given by the X, Y and R distances lie within envelopes of &#xb1;4.064 millimeters in a direction normal to any airfoil surface location therealong.

First and second stage turbine airfoil shapes

In a gas turbine bucket having a shank portion, a radial tip portion and an airfoil having leading and trailing edges and pressure and suction surfaces, and an internal fluid cooling circuit, an improvement wherein the internal fluid cooling circuit has a serpentine configuration including plural radial outflow passages and plural radial inflow passages. The radial outflow passages, in one example, are shaped to have aspect ratios of about 3.3 to 1 and Buoyancy Numbers of &lt;0.15 or &gt;0.80. A method of determining a configuration for steam cooling passages for a bucket stage in a gas turbine is also provided which includes, in one example, the steps of:

Closed circuit steam cooled bucket

A turbine disk cooling system for a gas turbine engine of a type having a compressor section including first and second disks connected by a seal and defining a compressor interstage volume, a turbine section including first and second stage disks connected by a seal and defining a turbine inner stage volume, and a compressor shaft interconnecting the compressor disks with the turbine disks including orifices located in the compressor seal for allowing air in the compressor section to enter the compressor interstage volume, and a radial inflow impeller for guiding the compressor air towards the compressor shaft. The impeller including a plurality of radially-extending conduits suspended in the compressor interstage volume, the conduits having a plurality of interior, radially-extending passages for conveying the compressor air from the orifice to the compressor shaft. The cooling system further including ducts concentric with the engine centerline for conveying air from the compressor interstage volume to the turbine section, wherein the first stage turbine disk includes an aft shaft having a plurality of openings therethrough allowing the flow of air from the ducts into the turbine interstage volume. The tubular conduit elements having a radially outer portion divided into a plurality of spaced longitudinal segments and a radially inner portion protruding from the conduit element and including a peripheral flange shaped to engage the peripheral flange of the conduit elements.

Turbine disk cooling system

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Woodstock, GA, United States of America

Michael Adelbert Sullivan