Abstract: Systems and methods for making a material composition are disclosed. The method includes mixing a thermoset polymer, a petroleum distillate, a release agent, and a catalyst to form an admixture. A cellulosic material is mixed with the admixture to form a generally homogenous furnish. The system includes a mixing chamber, a feeding chamber, and a die. The die includes a pressing chamber, which has a volume formed by first and second platens. The platens are in facing opposition to one another and have a length extending continuously from an entrance to an exit of the die. The platens have a plurality of orifices and heating elements disposed along the length. The platens are disposed in first and second positions. The first position forms a first volume and the second position forms a second volume.

Abstract: Systems and methods for making a material composition are disclosed. The method includes mixing a thermoset polymer, a petroleum distillate, a release agent, and a catalyst to form an admixture. A cellulosic material is mixed with the admixture to form a generally homogenous furnish. The system includes a mixing chamber, a feeding chamber, and a die. The die includes a pressing chamber, which has a volume formed by first and second platens. The platens are in facing opposition to one another and have a length extending continuously from an entrance to an exit of the die. The platens have a plurality of orifices and heating elements disposed along the length. The platens are disposed in first and second positions. The first position forms a first volume and the second position forms a second volume.

Abstract: A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and the second platform leg is configured to be retained by a second retainer coupled to a second adjacent rotor blade. A method of assembling a blade assembly that includes a removable platform, a rotor assembly including the removable platform, and a gas turbine engine assembly including the removable platform, are also described herein.

Abstract: A rotor blade assembly includes a shank, an airfoil that is formed integrally with the shank, and a removable platform coupled between said shank and said airfoil via a friction fit. A method of assembling a gas turbine engine rotor blade assembly that includes a removable platform, and a gas turbine engine rotor assembly including the removable platform are also described herein.

Abstract: Systems and methods for making a material composition are disclosed. The method includes mixing a thermoset polymer, a petroleum distillate, a release agent, and a catalyst to form an admixture. A cellulosic material is mixed with the admixture to form a generally homogenous furnish. The system includes a mixing chamber, a feeding chamber, and a die. The die includes a pressing chamber, which has a volume formed by first and second platens. The platens are in facing opposition to one another and have a length extending continuously from an entrance to an exit of the die. The platens have a plurality of orifices and heating elements disposed along the length. The platens are disposed in first and second positions. The first position forms a first volume and the second position forms a second volume.

Abstract: A coating process and TBC system suitable for protecting the surface of a component subjected to a hostile thermal environment. The TBC system has a first layer with a columnar microstructure, and a second layer on the first layer and with a microstructure characterized by irregular flattened grains. According to one aspect, the first layer is present and the second layer is not present on a first surface portion of the component, and the first and second layers are both present on a second surface portion of the component. According to another aspect, the first and second layers contain the same base ceramic compound.

Abstract: A method for fabricating a turbine rotor blade includes casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, and an airfoil, and forming a plurality of openings between the platform inner surface and the platform outer surface to facilitate cooling an exterior surface of the platform.

Abstract: A method for fabricating a turbine rotor blade includes casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, and an airfoil, and forming a plurality of openings between the platform inner surface and the platform outer surface to facilitate cooling an exterior surface of the platform.

Abstract: A method for fabricating a rotor blade includes casting the turbine rotor blade to include a shank, and a platform having an upper surface and a lower surface, and coupling a first component to the rotor blade such that a first substantially hollow plenum is defined between the first component, the shank, and the platform lower surface.

Abstract: A method facilitates fabricating a rotor assembly for a gas turbine engine. The method comprises providing a plurality of rotor blades that each include an airfoil, a dovetail, a shank, and a platform, wherein the platform extends between the shank and the airfoil, and wherein the dovetail extends outwardly from the shank, and forming a cooling circuit within a portion of the shank to supply cooling air to the rotor blade for supplying cooling air to the rotor blade for impingement cooling a portion of the rotor blade and for supplying cooling air to the rotor blade for purging a cavity defined downstream from the rotor blade.

Abstract: Systems and methods for making a material composition are disclosed. The method includes mixing a thermoset polymer, a petroleum distillate, a release agent, and a catalyst to form an admixture. A cellulosic material is mixed with the admixture to form a generally homogenous furnish. The system includes a mixing chamber, a feeding chamber, and a die. The die includes a pressing chamber, which has a volume formed by first and second platens. The platens are in facing opposition to one another and have a length extending continuously from an entrance to an exit of the die. The platens have a plurality of orifices and heating elements disposed along the length. The platens are disposed in first and second positions. The first position forms a first volume and the second position forms a second volume.

Abstract: A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The suction side wall has a selectively reduced thickness, which allows shortened trailing edge slots, improving trailing edge cooling.

Abstract: The invention generally relates to sending data (e.g. print data or a document), in a network environment, to a port monitor, and to upload the data to an upload manager for storing in a database. Relevant data may be sent from a print spooler to the port monitor invoking an upload manger to convey (e.g. securely or non-securely) print data to a web server. A version manager determines whether the print driver being used to print data is authentic, and data are written to a web server as packets of information and sent to a database for storage. Additionally, a system, method and recordable medium are recognized whereby a pass through (e.g. a port monitor filter) is inserted between a print spooler and a port monitor in order to detach the port monitor from the print spooler such that object code can be upgraded for future versions of software.

Abstract: A turbine includes a row of blades each having an integral airfoil, platform, and dovetail. Each platform has opposite first and second side edges corresponding with the opposite pressure and suction sides of the airfoil. The platform first side edge is radially higher than the platform second side edge continuously between opposite forward and aft edges of the platform. In this way, adjacent platforms define a down step therebetween for preventing obstruction of combustion gases flowable downstream thereover.

Abstract: A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.

Abstract: A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.

Abstract: A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The airfoil trailing edge is selectively thickened in the root portion so as to allow shortened trailing edge slots, thereby improving trailing edge cooling and reducing mechanical and thermal stresses.

Abstract: A dovetail assembly including non-parallel relief faces that facilitates reduced pressure face brinelling in turbine engines. The assembly includes a plurality of rotor blades, each including a dovetail. Each dovetail includes at least a pair of blade tangs including blade relief faces. The dovetail assembly also includes a rotor disk including a plurality of dovetail slots, each sized to receive a dovetail. Each dovetail slot is defined by at least one pair of opposing disk tangs including disk relief faces. The disk relief faces are non-parallel to the blade relief faces when the dovetail is mounted in the dovetail slot.

Abstract: A turbine includes a row of blades each having an integral airfoil, platform, and dovetail. Each platform has opposite first and second side edges corresponding with the opposite pressure and suction sides of the airfoil. The platform first side edge is radially higher than the platform second side edge continuously between opposite forward and aft edges of the platform. In this way, adjacent platforms define a down step therebetween for preventing obstruction of combustion gases flowable downstream thereover.