Abstract: An airfoil and nozzle assembly including an outer shroud having a plurality of vane members attached to an inner surface and having a cantilevered end. The assembly further includes a inner shroud being formed by a plurality of segments. Each of the segments having a first end and a second end and having a recess positioned in each of the ends. The cantilevered end of the vane member being positioned in the recess. The airfoil and nozzle assembly being made from a material having a lower rate of thermal expansion than that of the components to which the airfoil and nozzle assembly is attached.

Abstract: The present volume monitoring device (40) includes a cylindrical portion (66) having a piston assembly (100) therein. The cylindrical portion (66) having a measuring device (48) attached thereto at one end (46) and a readout gage (44) attached thereto at an other end (50). The measuring device (48) including a plurality of plungers (181) which when the volume displacement monitoring device (40) is positioned within an opening activates a flow of fluid to move the piston assembly (100) and establishes a readout on the readout gage (44). The volume displacement monitoring device (40) provides an economical way of monitoring the size of an opening. Furthermore, the volume displacement monitoring device (40) can be used in the field and does not require additional environmental protection to remain within safety standards.

Abstract: A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes an outer shroud and an inner shroud having a plurality of horizontally segmented vanes therebetween being positioned by a connecting member positioning segmented vanes in functional relationship one to another. The turbine nozzle vane assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the other component.

Abstract: Cooling air delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by better utilizing the cooling air bled from the compressor section of the gas turbine engine. For example, a flow of cooling air is directed to a plurality of airfoils having a leading edge and includes a cooling path therein each of the plurality of blades in which is positioned a device which causes the cooling air to swirl and more effectively absorb heat and cool the leading edge of the airfoil.

Abstract: The present air conditioning system bleeds high pressure, hot, compressed air from the compressor section of a gas turbine engine and passes the high pressure flow of air directly through a single heat exchanger, through a flow control valve, is used to drive a supersonic turbine device, exits the supersonic turbine device as a low pressure, cooled flow of air and passes through a water separator prior to being used to cool the cabin zone. The primary advantages of the improved air conditioning system includes the elimination of the necessity for pressure regulation and only one heat exchanger is required. Furthermore, the improved air conditioning system is modulely designed and allows for a more flexibility, enabling the components to be more selectively located. Furthermore, the system is considerably smaller and lighter in weight.

Abstract: A premix fuel injection nozzle includes a first mixing chamber having a preestablished cross-sectional area and a second mixing chamber having a preestablished cross-sectional areal being larger than the preestablished cross-sectional area of the first mixing chamber. The first mixing chamber and the second mixing chamber are in communication with each other.

Abstract: An axial flow turbine's nozzle/nozzle support structure having a cantilevered nozzle outer structure including an outer shroud and airfoil vanes extending radially inwardly therefrom, an inner shroud radially adjacent the inner end of the airfoil vanes and cooperatively disposed relative to the outer shroud to provide an annular fluid flow path, an inner and an outer support ring respectively arranged radially inside the inner shroud and axially adjacent a portion of the outer shroud, and pins extending through such portion and into the outer support ring. The inner support ring or inner shroud has a groove therein bounded by end walls for receiving and being axially abuttable with a locating projection from the adjacent airfoil vane, inner shroud, or inner support ring.

Abstract: A turbine nozzle and shroud assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes a plurality of segmented vane defining a first vane segment and a second vane segment. Each of the first and second vane segments having a vertical portion. Each of the first vane segments and the second vane segments being positioned in functional relationship one to another within a recess formed within an outer shroud and an inner shroud. The turbine nozzle and shroud assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the other component.

Abstract: A turbine blade having a preestablished rate of thermal expansion is attached to a turbine flange having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade. The turbine flange includes a first upstanding flange and a second upstanding flange having a groove formed therebetween. The turbine flange further includes a recess. Each of the first and second upstanding flanges have a plurality of bores therein. A turbine blade has a first member and a second member positioned in one of the groove and the recess. Each of the first member and the second member have a plurality of bores therein. And, a pin is positioned in respective ones of the plurality of bores in the first and second upstanding members and the first and second members and attach the blade to the turbine flange. The pin has a preestablished rate of thermal expansion being substantially equal to the rate of thermal expansion of the blade.

Abstract: A method and apparatus are provided for producing a temperature profile of a part operating within a machine is provided. The machine is operated with the part for a predetermined period of time. The part is placed in a light box in which a camera produces an image of the part. The image is compared with a standard set of colors and the standard color most closely corresponding to each pixel of the image is selected.

Abstract: Prior art recuperators or heat exchangers have been restricted in use to only part speed and power application when adapted for use with high pressure gas turbine engine. The present recuperator or heat exchanger has been adapted for use with a high pressure ratio gas turbine engine. The recuperator includes a plurality of air cells being formed by a plurality of primary surface sheets. The primary surface sheets define a first surface and a second surface and has a plurality of corrugations formed therein. Each of the plurality of corrugations has a crest and a root extending from the respective first surface and second surface a preestablished axial distance. The preestablished axial distance from the crest to the first surface being unequal to that of the preestablished axial distance from the root to the second surface.

Abstract: An axial flow turbine's nozzle/nozzle support structure having a cantilevered nozzle outer structure including an outer shroud and airfoil vanes extending radially inwardly therefrom, an inner shroud radially adjacent the inner end of the airfoil vanes and cooperatively disposed relative to the outer shroud to provide an annular fluid flow path, an inner and an outer support ring respectively arranged radially inside the inner shroud and axially adjacent a portion of the outer shroud, and pins extending through such portion and into the outer support ring. The inner support ring or inner shroud has a groove therein bounded by end walls for receiving and being axially abuttable with a locating projection from the adjacent airfoil vane, inner shroud, or inner support ring.

Abstract: Trim balancing of rotating components in the past has increased manufacturing cost. In many past applications, the time and energy required to trim balance rotating components required partial disassembly of an outer case or structure member. The present trim balancing system allows the gas turbine engine to be balanced with the outer case in situ. Access to a rotating component from the exterior of the case is made possible by a compressor air flow path and a pair of holes. The balancing can be accomplished by adding or removing weights or plugs to a band assembled on the rotating component.

Abstract: A nozzle guide vane assembly has ceramic components therein having a conventional thread thereon including a preestablished pitch and having a preestablished rate of thermal expansion. The nozzle guide vane assembly has a metallic components therein having a preestablished rate of thermal expansion being greater that the rate of thermal expansion of the ceramic components is positioned in a gas turbine engine. The metallic component, a nut, has a thread therein including a plurality of crests being spaced on a pitch equal to that of the ceramic component and has a pair of contacting surfaces extending from the plurality of crests. A notch spirally extends intermediate adjacent ones of the plurality of crests and has a preestablished depth which is at least twice the size of the conventional pitch. Furthermore, the pair of contacting surfaces are in contact with only a portion of the threaded surface of the ceramic components.

Abstract: Cooling air delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by better utilizing the cooling air bled from the compressor section of the gas turbine engine. For example, a flow of cooling air which is directed through internal passages of the engine and into a cavity and is used to cool the interface between a turbine disc and a plurality of turbine blades and further reduces ingestion of hot power gases into the internal portion of the gas turbine engine. The cavity has a generally tapered configuration and effectively cools the interface between the disc and the blade. Thus, increasing component life and increasing power and efficiencies of the engine.

Abstract: A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes an outer shroud and an inner shroud having a plurality of horizontally segmented vanes therebetween being positioned by a connecting member positioning segmented vanes in functional relationship one to another. The turbine nozzle vane assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the other component.

Abstract: A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes an outer shroud and an inner shroud having a plurality of vanes therebetween. Each of the plurality of vanes have a device for heating and cooling a portion of each of the plurality of vanes. Furthermore, the inner shroud has a plurality of bosses attached thereto. A cylindrical member has a plurality of grooves formed therein and each of the plurality of bosses are positioned in corresponding ones of the plurality of grooves.

Abstract: A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes an outer shroud having a mounting leg with an opening defined therein, a tip shoe ring having a mounting member with an opening defined therein, a nozzle support ring having a plurality of holes therein and a pin positioned in the corresponding opening in the outer shroud, opening in the tip shoe ring and the hole in the nozzle support ring. A rolling joint is provided between metallic components of the gas turbine engine and the nozzle guide vane assembly. The nozzle guide vane assembly is positioned radially about a central axis of the gas turbine engine and axially aligned with a combustor of the gas turbine engine.

Abstract: Past methods and apparatus for manufacturing a rotor assembly have been used to provide rotor assemblies for rotating electric machines. Many of these electric machines rotate at low speeds. The present method and apparatus for manufacturing a rotor assembly can be used to make a rotor assembly to be used at high speeds. The rotor assembly includes a shaft having a frustoconical mounting surface defined thereon and having a plurality of magnets attached to the frustoconical mounting surface. A cover having a frustoconical inner surface surrounds the magnets and compressively secures the magnets to the shaft. The compressive forces applied by the cover and the adhesive used to secure the magnets insuring that a positive contact pressure exists between the magnets and the shaft during operation of the electric machine.

Abstract: Past fuel injection nozzles have attempted to provide a structure to reduce tip temperatures. Such nozzles have failed to attain adequate reduction of tip temperatures without increasing the quantity of cooling air required. The present fuel injector structure has resulted in reduced tip temperatures without increasing the quantity of cooling air required. The structure includes a shell having an inner member positioned therein forming a first chamber therebetween, an end piece forming a second chamber between the inner member and the end piece. An inner body has a plurality of first angled passages formed therein and communicates between the second chamber and a passage. A flow of combustor air through the second chamber contacts an air side of the end piece resulting in a combustor side being cooled. The unique structure of the fuel injector nozzle provides improved tip cooling without increasing the quality of cooling air and improves the efficiency of the gas turbine engine.