General Electric Company

Anthony Constantine Thermos

Ronald Ralph Cairo

Mehmet Demiroglu

Fadi Elias Rahal

Weiping Wang

Charles Erklin Seeley

Hsin-Pang Wang

Stephen Paul Wassynger

Marc Edward Blohm

Joseph Anthony Weber

Carl Gerard Schott

Charles Van Buchan

Nitin Bhate

Max Robert Farson

Govindarajan Rengarajan

Ajay Gangadhar Patil

Martel Alexander McCallum

Carlos Alberto Collado

William John Miller

Venkata Siva Chaluvadi

Kahwai Gachago Muriithi

Nitin Narayan Bhate

Ramanath Iyer Ramakrishnan

James Patrick Claeys

Scott Yiming Yu

Cj Silver

Simon Shadbolt

Nick Podmore

Stephen J Jordan

A rotor blade and blade retention key assembly includes: a radially outer airfoil, a shank and a radially inner attachment dovetail. The attachment dovetail has a radially innermost surface formed with a notch at one axial end thereof, and a retention key is received in the notch, and rotatable from a retracted position where a retention key portion is substantially flush with the radially innermost surface, to an extended position where the retention key portion projects inwardly from said radially innermost surface and into a recess or pocket formed in a rotor wheel slot to prevent axial movement of the blade within the slot.

Gas turbine compressor last stage rotor blades with axial retention

A fixture assembly and inspection method by which the internal diameter and/or concentricity of a segmented annular seal can be readily inspected and optionally measured prior to final installation. The fixture assembly has at least two fixture segments supported on a base, by which an annular fixture housing is defined having an outer rim and a groove with a cross-sectional shape corresponding to a cross-sectional shape of the annular seal. The fixture assembly further includes a device or apparatus for assessing at least one dimensional characteristic of the annular seal when installed in the groove of the fixture housing and as the assessing device/apparatus travels along the interior circumference of the fixture housing.

Fixture and inspection method for an annular seal

Several physical features on an inlet guide vane (IGV) ensure proper orientation of the IGV within a compressor during assembly. A gear with several teeth removed results in a flat surface on the gear which inhibits the gear from rotating on the rack of the compressor inlet casing. An orientation pin is located in the internal bore of the gear. The cylindrical IGV spindle has a portion formed as a flat surface and the orientation pin engages this flat surface. These features are applicable to both a one-piece IGV where the jackshaft is integrated with the IGV stem and a two-piece IGV in which the jackshaft is separate from the IGV stem. A feature applicable to a two-piece IGV is a shaped boss on the IGV stem that allows the jackshaft to be located on the IGV stem in only one orientation.

Features to properly orient inlet guide vanes

An inlet guide vane having a nominal profile substantially in accordance with Cartesian coordinate values of x, y, and z set forth in TABLE 1 reduces vibration of engine components at various operating conditions. A scaling factor can be applied to the values to make the airfoil larger or smaller. The TABLE 1 x and y values are distances in inches within a tolerance which, when connected by smooth curves, define airfoil profile sections at each distance z in inches, the profile sections being joined smoothly to form a complete airfoil shape. The tolerance in an embodiment is up to about 0.16 inches.

Inlet guide vane

A method of manufacturing a turbine blade includes (a) supporting a turbine blade internal core support at opposite ends such that radially inner and outer ends of the turbine blade remain open during casting; (b) casting the blade including the airfoil portion, wherein the radially outer edge of the airfoil portion is inclined relative to horizontal; (c) machining the radially outer edge of the airfoil portion to form a peripheral shoulder about a radially outer opening in the airfoil portion; and (d) seating a tip cap on the peripheral shoulder and fixing the tip cap to the airfoil portion of the blade.

Turbine blade tip cap

A method for controlling distortion of a turbine case (&ldquo;case&rdquo;) includes measuring a temperature distribution for the case that includes thermal gradients. The method further includes modeling thermal stresses on the case induced by the thermal gradients, calculating an out of roundness index (&ldquo;index&rdquo;) resulting from the thermal stresses, and comparing the index with at least one distortion limit to determine whether the case has a satisfactory or an unsatisfactory index. The temperature distribution is controlled for an unsatisfactory index to produce the satisfactory index. A system for controlling distortion of the turbine case includes a thermal measurement system, for measuring the temperature distribution, and a computer configured for modeling the thermal stresses, calculating and comparing the index with the distortion limit, and controlling the temperature distribution for an unsatisfactory index to produce the satisfactory index.

Method and system for controlling distortion of turbine case due to thermal variations

A quill for locating a measuring device in proximity to a rotor surface includes a body portion having a bore oriented at an acute angle relative to horizontal, the bore adapted to receive a forward end of the measuring device; and a mounting flange portion for securing the quill to a machine component.

Mounting block for a proximity probe used for measuring axial movement of a rotor

A tool for removal of star-washers from a bore includes a handle; and a tool secured to the handle, the tool component having a distal end with an elongated slot extending from the distal end rearwardly toward the handle, and a plurality of hooks circumferentially equally spaced about the distal end.

Tool for removal and installation of star-washers

A thermocouple assembly includes a thermocouple; a plurality of lead wires extending from the thermocouple; an insulating jacket extending along and enclosing the plurality of leads; and at least one internally sealed area within the insulating jacket to prevent fluid leakage along and within the insulating jacket. The invention also provides a method of preventing leakage of a fluid along and through an insulating jacket of a thermocouple including the steps of a) attaching a plurality of lead wires to a thermocouple; b) adding a heat sensitive pseudo-wire to extend along the plurality of lead wires; c) enclosing the lead wires and pseudo-wire inside an insulating jacket; d) locally heating axially spaced portions of the insulating jacket to a temperature which melts the pseudo-wire and fuses it with an interior surface of the jacket.

Thermocouple assembly

Method of preventing leakage of a fluid along and through an insulating jacket of a thermocouple

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Greer, SC, United States of America

Anthony Constantine Thermos