Abstract: A system for cleaning a gas turbine engine may generally include a wash stand having a base frame and a plurality of fluid injection nozzles configured to be supported by the base frame relative to the gas turbine engine. The nozzles may be configured to inject a cleaning fluid through an inlet of the fan casing of the engine as the fan blades are being rotated in a rotational direction such that the cleaning fluid is directed past the rotating fan blades and into a compressor inlet of the engine. Additionally, each nozzle may be oriented at a positive tangential angle defined relative to the rotational direction of the plurality of fan blades. The system may also include a fluid source in flow communication with the wash stand for supplying the cleaning fluid to the plurality of fluid injection nozzles.

Abstract: A system for cleaning a gas turbine engine may generally include a wash stand having a base frame and a plurality of fluid injection nozzles configured to be supported by the base frame relative to the gas turbine engine. The nozzles may be configured to inject a cleaning fluid through an inlet of the fan casing of the engine as the fan blades are being rotated in a rotational direction such that the cleaning fluid is directed past the rotating fan blades and into a compressor inlet of the engine. Additionally, each nozzle may be oriented at a positive tangential angle defined relative to the rotational direction of the plurality of fan blades. The system may also include a fluid source in flow communication with the wash stand for supplying the cleaning fluid to the plurality of fluid injection nozzles.

Abstract: A system for cleaning a gas turbine engine may generally include a wash stand having a base frame and a plurality of fluid injection nozzles configured to be supported by the base frame relative to the gas turbine engine. The nozzles may be configured to inject a cleaning fluid through an inlet of the fan casing of the engine as the fan blades are being rotated in a rotational direction such that the cleaning fluid is directed past the rotating fan blades and into a compressor inlet of the engine. Additionally, each nozzle may be oriented at a positive tangential angle defined relative to the rotational direction of the plurality of fan blades. The system may also include a fluid source in flow communication with the wash stand for supplying the cleaning fluid to the plurality of fluid injection nozzles.

Abstract: A system for cleaning a gas turbine engine may generally include a wash stand having a base frame and a plurality of fluid injection nozzles configured to be supported by the base frame relative to the gas turbine engine. The nozzles may be configured to inject a cleaning fluid through an inlet of the fan casing of the engine as the fan blades are being rotated in a rotational direction such that the cleaning fluid is directed past the rotating fan blades and into a compressor inlet of the engine. Additionally, each nozzle may be oriented at a positive tangential angle defined relative to the rotational direction of the plurality of fan blades. The system may also include a fluid source in flow communication with the wash stand for supplying the cleaning fluid to the plurality of fluid injection nozzles.

Abstract: Bolted together first and second flanges include bolts disposed through first bolt holes in the first flange. The bolts extend at least partially through second holes in the second flange. Bolt include bolt heads, threads, and shanks therebetween. Crushable spacers disposed around the shanks of a first plurality of the bolts and contacting and axially extending between the bolt heads and the first flange. Bushings disposed around a second plurality of the bolts and contacting and axially extending between the bolt heads and the second flange. A shank outer diameter may be smaller than a thread diameter and heat shrink tubing may be disposed around the bolt shanks of at least some of the spacers. First bolt holes may extend into an open annular slot on first flange and second holes may extend partially through a forward extending annular rail of second flange with rail received within slot.

Abstract: Bolted together first and second flanges include bolts disposed through first bolt holes in the first flange. The bolts extend at least partially through second holes in the second flange. Bolt include bolt heads, threads, and shanks therebetween. Crushable spacers disposed around the shanks of a first plurality of the bolts and contacting and axially extending between the bolt heads and the first flange. Bushings disposed around a second plurality of the bolts and contacting and axially extending between the bolt heads and the second flange. A shank outer diameter may be smaller than a thread diameter and heat shrink tubing may be disposed around the bolt shanks of at least some of the spacers. First bolt holes may extend into an open annular slot on first flange and second holes may extend partially through a forward extending annular rail of second flange with rail received within slot.

Abstract: A method enables a thrust link including a clevis to be coupled to a mounting lug including a spherical bearing. The method comprises positioning the spherical bearing within the thrust link clevis, and coupling the thrust link to the mounting lug by inserting a fastener through the clevis such that the fastener extends from one side of the clevis through the spherical bearing to the other side of the clevis, and such that fuse element included with at least one of the fastener and the clevis is positioned within a structural load path defined between the clevis and the thrust link, wherein the fuse element is configured to fail when subjected to a predetermined load.

Abstract: A method enables a thrust link including a clevis to be coupled to a mounting lug including a spherical bearing. The method comprises positioning the spherical bearing within the thrust link clevis, and coupling the thrust link to the mounting lug by inserting a fastener through the clevis such that the fastener extends from one side of the clevis through the spherical bearing to the other side of the clevis, and such that fuse element included with at least one of the fastener and the clevis is positioned within a structural load path defined between the clevis and the thrust link, wherein the fuse element is configured to fail when subjected to a predetermined load.

Abstract: A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000° F.

Abstract: An airfoil for a gas turbine engine including an inflection that facilitates enhancing film cooling of the airfoil, without adversely affecting aerodynamic efficiency of airfoil is described. The airfoil includes a generally concave first sidewall and a generally convex second sidewall joined at a leading edge and at a trailing edge of the airfoil. A plurality of cooling openings extend between an internal cooling chamber and an external surface of the first sidewall. One cooling opening extends from the cooling chamber into the inflection at a relatively shallow injection angle with respect the airfoil external surface.

Abstract: The present invention provides for a method to reduce the strength of the honeycomb of a jet turbine stator, increasing its machinability, with a resultant reduction in measured peak tooth temperature, while maintaining or even improving its high temperature capability, so as not to limit its operating environment. The air seal functionality is unaffected, and even improved in some instances. The machinability of the honeycomb is increased by using a light element diffused into the honeycomb ribbon to produce the effect of reducing its strength and ductility while maintaining the environmental resistance needed. The present invention also includes the stator honeycomb produced by the foregoing method.

Abstract: A turbine cooling circuit includes a flow sleeve having an aft end for adjoining the rim of a turbine disk. A seal rotor is spaced from the aft end adjacent a row of inlet holes. An inducer has an outlet disposed radially outwardly from the sleeve inlet holes. And, a seal stator surrounds the seal rotor to define a rotary seal disposed radially inwardly from the inducer outlet.

Abstract: An airfoil for a gas turbine engine including an inflection that facilitates enhancing film cooling of the airfoil, without adversely affecting aerodynamic efficiency of airfoil is described. The airfoil includes a generally concave first sidewall and a generally convex second sidewall joined at a leading edge and at a trailing edge of the airfoil. A plurality of cooling openings extend between an internal cooling chamber and an external surface of the first sidewall.

Abstract: A turbine cooling circuit includes a flow sleeve having an aft end for adjoining the rim of a turbine disk. A seal rotor is spaced from the aft end adjacent a row of inlet holes. An inducer has an outlet disposed radially outwardly from the sleeve inlet holes. And, a seal stator surrounds the seal rotor to define a rotary seal disposed radially inwardly from the inducer outlet.

Abstract: The present invention provides for a method to reduce the strength of the honeycomb of a jet turbine stator, increasing its machinability, with a resultant reduction in measured peak tooth temperature, while maintaining or even improving its high temperature capability, so as not to limit its operating environment. The air seal functionality is unaffected, and even improved in some instances. The machinability of the honeycomb is increased by using a light element diffused into the honeycomb ribbon to produce the effect of reducing its strength and ductility while maintaining the environmental resistance needed. The present invention also includes the stator honeycomb produced by the foregoing method.

Abstract: A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000° F.

Abstract: A web-based method and system for monitoring and managing program performance in a real-time manner enhances business reflex. Elements of program performance and structure are maintained and updated on the information platform, and accessible by management and others requiring the information. The information platform is a combination of desktop and spreadsheet technologies that raise the decision making abilities of the business entity. The information platform collects and integrates data from multiple users. The collected and integrated data can be stored, and is retrievable for observation, analysis, and updating by subsequent users.

Abstract: A gas turbine engine rotor assembly includes a plurality of aerodynamic devices to direct airflow radially inward. The gas turbine engine rotor assembly includes a rotor shaft that includes a plurality of openings. The aerodynamic devices include a pair of vane segments and a pair of sidewalls. A contoured outer surface includes an opening and permits the aerodynamic device to be positioned against an inner surface of the rotor shaft, and a flange ring defines a pocket. The aerodynamic device fits within the pocket to concentrically align the openings.