Abstract: The subject invention relates to insecticidal toxin complex (“TC”) fusion proteins and to polynucleotides that encode these fusion proteins. In some embodiments, the invention provides a fusion protein comprising a Class A protein, a Class B protein, and a Class C TC protein fused together to form a single protein. In some other embodiments, the invention provides a fusion protein comprising a Class B and a Class C TC proteins fused together. In the latter embodiments, the BC or CB fusion protein can be used to enhance or potentiate the anti-insect activity of a “Toxin A” or Class A protein. The subject invention also includes plants, cells (bacterial and plant cells for example), and seeds that comprise the polynucleotides. The subject invention also includes methods of controlling pests (preferably insects and other plant pests) with fusion proteins of the subject invention.

Abstract: This invention encompasses the identification and isolation of genes that confer disease control properties in plants, as well as plants comprising such genes. These genes are derived from the following sources: Nicotiana benthamiana, Oryzae sativa (var. Indica IR7), Papaver rhoeas, Saccharomyces cerevisiae and Trichoderma harzianum (Rifai 1295-22). The control conferred is against the one or more of the following phytopathogens: Aspergillus flavus, Cercospora zeae-maydis, Fusarium monilforme, Fusarium graminearum, Helminthosporium maydis, Phoma lingam, Phomopsis helianthi, Phytopthera infestans, Pyricularia oryzae, Pythium ultimum, Rhizoctonia solani, Sclerotinia sclerotiorum, Ustilago maydis, and Verticillium dahliae. Further, this invention encompasses other homologous and heterologous sequences with a high degree of functional similarity.

Abstract: A balance weight for a turbine rotor includes: (a) a block-like centerbody; (b) a pair of resilient spring arms extending laterally from opposite sides of the centerbody, the centerbody and the spring arms collectively defining an arcuate shape; and (c) at least one locating structure extending from a radially outer surface of the balance weight.

Abstract: The subject invention provides exciting new sources for surprising, new types of toxin complex (“TC”) proteins. The subject invention includes these new classes and types of TC proteins. The subject invention also includes polynucleotides that encode the subject proteins. The subject invention further provides vectors and cells comprising these polynucleotides. The subject invention also provides novel methods of controlling insects. The subject invention relates in part to the surprising discovery that new types of TC proteins can be obtained from a widely diverse phylogenetic spectrum of organisms including, most notably and surprisingly, eukaryotic fungus.

Abstract: A gas turbine engine centrifugal compressor axial forward thrust apparatus bleeds impeller tip aft bleed flow from between an annular centrifugal compressor impeller of a high pressure rotor and a diffuser directly downstream of the impeller. The apparatus then uses the aft bleed flow to pressurize an annular cavity extending radially between an inner combustor casing and the rotor and extending axially between forward and aft thrust balance seals. Forward and aft thrust balance lands are in sealing engagement with the forward and aft thrust balance seals on the high pressure rotor respectively. An annular stator plenum in fluid communication with the annular cavity is bounded in part by a forward end wall having conical diffusion holes therethrough which may be axially or circumferentially or axially and circumferentially angled. The forward thrust balance seal may be on an aft conical arm of the impeller.

Abstract: The subject invention relates to insecticidal toxin complex (“TC”) fusion proteins and to polynucleotides that encode these fusion proteins. In some embodiments, the invention provides a fusion protein comprising a Class A protein, a Class B protein, and a Class C TC protein fused together to form a single protein. In some other embodiments, the invention provides a fusion protein comprising a Class B and a Class C TC proteins fused together. In the latter embodiments, the BC or CB fusion protein can be used to enhance or potentiate the anti-insect activity of a “Toxin A” or Class A protein. The subject invention also includes plants, cells (bacterial and plant cells for example), and seeds that comprise the polynucleotides. The subject invention also includes methods of controlling pests (preferably insects and other plant pests) with fusion proteins of the subject invention.

Abstract: This invention encompasses the identification and isolation of genes that confer disease control properties in plants, as well as plants comprising such genes. These genes are derived from the following sources: Nicotiana benthamiana, Oryzae sativa (var. Indica IR7), Papaver rhoeas, Saccharomyces cerevisiae and Trichoderma harzianum (Rifai 1295-22). The control conferred is against the one or more of the following phytopathogens: Aspergillus flavus, Cercospora zeae-maydis, Fusarium monilforme, Fusarium graminearum, Helminthosporium maydis, Phoma lingam, Phomopsis helianthi, Phytopthera infestans, Pyricularia oryzae, Pythium ultimum, Rhizoctonia solani, Sclerotinia sclerotiorum, Ustilago maydis, and Verticillium dahlias. Further, this invention encompasses other homologous and heterologous sequences with a high degree of functional similarity.

Abstract: The subject invention relates to insecticidal toxin complex (“TC”) fusion proteins and to polynucleotides that encode these fusion proteins. In some embodiments, the invention provide a fusion protein comprising a Class A protein, a Class B protein, and a Class C TC protein fused together to form a single protein. In some other embodiments, the invention provides a fusion protein compromising a Class B and a Class C TC proteins fused together. In the latter embodiments, the BC and CB fusion protein can be used to enhance or potentate the anti-insect activity of a “Toxin A” or Class A protein. The subject invention also includes plants, cells (bacterial and plant cells for example) and seeds that comprise the polynueleotides. The subject invention also includes methods of controlling pests (preferably insects and other plant pests) with fusion proteins of the subject invention.

Abstract: This invention encompasses the identification and isolation of genes that confer disease control properties in plants, as well as plants comprising such genes. These genes are derived from the following sources: Nicotiana benthamiana, Oryzae sativa (var. Indica IR7), Papaver rhoeas, Saccharomyces cerevisiae and Trichoderma harzianum (Rifai 1295-22). The control conferred is against the one or more of the following phytopathogens: Aspergillus flavus, Cercospora zeae-maydis, Fusarium monilforme, Fusarium graminearum, Helminthosporium maydis, Phoma lingam, Phomopsis helianthi, Phytopthera infestans, Pyricularia oryzae, Pythium ultimum, Rhizoctonia solani, Sclerotinia sclerotiorum, Ustilago maydis, and Verticillium dahliae. Further, this invention encompasses other homologous and heterologous sequences with a high degree of functional similarity.

Abstract: Methods for repairing and manufacturing a gas turbine blade, and the gas turbine blade repaired and manufactured with such methods are presented with, for example, the repair method comprising providing a gas turbine blade, the blade comprising a blade tip and a blade body; removing at least one portion of the blade tip; providing at least one freestanding tip insert; and disposing the at least one tip insert onto the gas turbine blade body such that the at least one tip insert replaces the at least one removed portion of the blade tip.

Abstract: Methods for repairing and manufacturing a gas turbine airfoil, and the airfoil repaired and manufactured with such methods are presented with, for example, the repair method comprising providing an airfoil having specified nominal dimensions, the airfoil comprising a first material, the first material having a creep life and a fatigue life, the airfoil further comprising a leading edge section and a trailing edge section; removing at least one portion of at least one section of the airfoil to create at least one deficit of material for the airfoil relative to the specified nominal dimensions, the at least one section selected from the group consisting of the leading edge section and the trailing edge section; providing at least one insert comprising a second material, the second material having a creep life that is at least substantially equal to the creep life of the first material, and a fatigue life that is at least substantially equal to the fatigue life of the first material; and disposing the at least o

Abstract: Methods for repairing and manufacturing a gas turbine blade, and the gas turbine blade repaired and manufactured with such methods are presented with, for example, the repair method comprising providing a gas turbine blade, the blade comprising a blade tip and a blade body; removing at least one portion of the blade tip; providing at least one freestanding tip insert; and disposing the at least one tip insert onto the gas turbine blade body such that the at least one tip insert replaces the at least one removed portion of the blade tip.

Abstract: Methods for repairing and manufacturing a gas turbine airfoil, and the airfoil repaired and manufactured with such methods are presented with, for example, the repair method comprising providing an airfoil having specified nominal dimensions, the airfoil comprising a first material, the first material having a creep life and a fatigue life, the airfoil further comprising a leading edge section and a trailing edge section; removing at least one portion of at least one section of the airfoil to create at least one deficit of material for the airfoil relative to the specified nominal dimensions, the at least one section selected from the group consisting of the leading edge section and the trailing edge section; providing at least one insert comprising a second material, the second material having a creep life that is at least substantially equal to the creep life of the first material, and a fatigue life that is at least substantially equal to the fatigue life of the first material; and disposing the at least o

Abstract: A composition comprises cobalt; chromium; carbon; boron; zirconium; aluminum; at least one refractory material; and nickel. The composition is used as a repair material for repairing superalloy articles in a repair process.

Abstract: A gas turbine component can be refurbished and/or repaired with an arc welding process that is used in conjunction with a 6-axis robot, a camera and a robot controller/vision processor. Applied to a wire fed plasma welding process, the vision system identifies the part, constructs a weld path based on the part's individual contour, and calculates a trajectory (with or without sinusoidal oscillation) for the robot arm to follow.

Abstract: A solid-solution strengthened superalloy weld composition, includes: about 10 to about 15 wt % Co; about 18 to about 22 wt % Cr; about 0.5 to about 1.3 wt % Al; about 3.5 to about 4.5 wt % Ta; about 1 to about 2 wt % Mo; about 13.5 to about 17.0 wt % W, up to about 0.08 wt % C; up to about 0.06 wt % Zr; up to about 0.015 wt % B; about 0.4 to about 1.2 wt % Mn; about 0.1 to about 0.3 wt % Si; and balance Ni.

Abstract: A solid-solution strengthened superalloy weld composition, includes: about 0 to about 10 wt % Co; about 18 to about 22 wt % Cr; about 0.2 to about 0.7 wt % Al; about 15 to about 28 wt % of the sum of refractory elements; up to about 0.09 wt % C; up to about 0.06 wt % Zr; up to about 0.015 wt % B; about 0.4 to about 1.2 wt % Mn; about 0.2 to about 0.45 wt % Si; and balance Ni.

Abstract: A composition comprises cobalt; chromium; carbon; boron; zirconium; aluminum; at least one refractory material; and nickel. The composition is used as a repair material for repairing superalloy articles in a repair process.

Abstract: A method of applying a wear-resistant hardface material (alloy) to a portion of a turbine blade, typically a wear surface on a shrouded turbine blade. A thin foil of brazing alloy (which in the preferred embodiment is a nickel-based alloy) is placed over said wear surface, and a hardface alloy of a greater than desired thickness (which in the preferred embodiment is a cobalt-based alloy) is placed thereover, thereby sandwiching the foil therebetween. The wear surface, foil, and hardface material are heated for a period sufficient to melt the foil and cause bonding of the hardface alloy to the wear surface. The hardface material is thereafter machined to bring the wear surface to design tolerances. A turbine blade, and a method of rebuilding a portion of a turbine blade, are also disclosed.