Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A bearing assembly for supporting a rotating component of a rotary machine includes a bearing housing and a metallic clearance seal attached to the bearing housing. The metallic clearance seal having at least one tooth is configured to extend radially outward from the bearing housing spaced apart from the rotating component to define an envelope having a pre-determined cross-sectional shape. A non-metallic brush seal assembly is fixedly attached to the metallic clearance seal having a second pre-determined cross-sectional shape. The non-metallic brush seal assembly is adapted to the metallic clearance seal to extend through the envelope and terminate in substantially intimate contact with the rotating component. The non-metallic brush seal assembly comprises a plurality of fibers to substantially arrest leakage of a lubricant from the bearing housing to the envelope.

Abstract: A method for controlling distortion of a turbine case (“case”) 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 (“index”) 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.

Abstract: A method for controlling distortion of a turbine case (“case”) 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 (“index”) 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.

Abstract: A compression fitting for use in, for example, gas turbines includes a sleeve and an integrally formed key disposed partially along the length of the sleeve, a compressor body, a receiver body that threadably engages with the compressor body, and a seal. The seal is compressed against wires or instrumentation lines that pass through the fitting from the interior to the exterior of the gas turbine. The one part construction of the sleeve and key facilitates assembly of the compression fitting into the gas turbine. The key prevents the sleeve from rotating during and after compression of the fitting thereby protecting the wires or instrumentation lines passing through the fitting from being damaged or sheared off.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 9A 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.

Abstract: 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.