Abstract: A compressor blade having an airfoil that comprises oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, a forward-most nose of the airfoil located at the leading edge and having a profile, a blade tip, and an erosion-resistant coating. The coating is present on the concave surface near the trailing edge, optionally present on the nose, optionally present on the convex surface, wherein the convex surface is free of the erosion resistant coating within at least 20% of the chord length from the nose. The thickness of the coating on the concave surface, the convex surface, and the nose is such that, if the gas turbine engine is exposed to an erosive environment, deterioration of the concave surface, the convex surface and the leading edge does not form a pronounced cusp at an intersection of the convex surface and leading edge.

Abstract: An antenna of the present disclosure has a housing having a shallow cavity in the housing and a flat, disk-shaped radiating element disposed in the shallow cavity, the radiating element having an arc shape slot. In addition, the antenna has a substantially circular parasitic element disposed in the shallow cavity on the bottom of the housing. The antenna operates as a half-wave antenna at a frequency range of 450 MHz to 470 MHz and as a full-wave antenna at a frequency range of 902 MHz to 928 MHz.

Abstract: An antenna of the present disclosure has a housing having a shallow cavity in a top of the housing and a shallow cavity in a bottom of the housing. The antenna further has a substantially circular radiating element disposed in the shallow cavity on the top of the housing, the radiating element having an arc shape slot. In addition, the antenna has a substantially circular parasitic element disposed in the shallow cavity on the bottom of the housing.

Abstract: An antenna of the present disclosure has a housing having a shallow cavity in a top of the housing and a shallow cavity in a bottom of the housing. The antenna further has a substantially circular radiating element disposed in the shallow cavity on the top of the housing, the radiating element having an arc shape slot. In addition, the antenna has a substantially circular parasitic element disposed in the shallow cavity on the bottom of the housing.

Abstract: An antenna of the present disclosure has a housing having a shallow cavity in the housing and a flat, disk-shaped radiating element disposed in the shallow cavity, the radiating element having an arc shape slot. In addition, the antenna has a substantially circular parasitic element disposed in the shallow cavity on the bottom of the housing. The antenna operates as a half-wave antenna at a frequency range of 450 MHz to 470 MHz and as a full-wave antenna at a frequency range of 902 MHz to 928 MHz.

Abstract: An antenna of the present disclosure has a housing having a shallow cavity in a top of the housing and a shallow cavity in a bottom of the housing. The antenna further has a substantially circular radiating element disposed in the shallow cavity on the top of the housing, the radiating element having an arc shape slot. In addition, the antenna has a substantially circular parasitic element disposed in the shallow cavity on the bottom of the housing.

Abstract: A process for depositing coatings, and particularly erosion-resistant coatings suitable for protecting surfaces subjected to collisions with particles, such as a compressor blade of a gas turbine engine. The blade has an airfoil comprising oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, and a blade tip. An erosion-resistant coating is present on at least the concave surface, but not on the convex surface within at least 20% of the chord length from the leading edge.

Abstract: A gas turbine engine airfoil is repaired by machining away airfoil material along at least a portion of at least one of leading and trailing edges and a radially outer tip forming at least one cut-back area and forming a weldment by welding successive beads of welding material into the cut-back area. Desired finished dimensions of the repaired airfoil are obtained by machining away some of the weld bead material in the weldment and then deep compressive residual stresses are imparted in a pre-stressed region extending into and encompassing the weldment and a portion of the airfoil adjacent the weldment. The compressive residual stresses may be are imparted after either rough machining or final finishing thereafter of the weldment. The cut-back area may extend up to about 90% of the airfoil's span and have a maximum cut-back depth up to about 0.22 inches.

Abstract: A method enables a variable vane assembly for a gas turbine engine including a casing and an inner shroud to be assembled. The method comprises providing at least one variable vane including a radially inner spindle that has a substantially circular cross-sectional shape, and coupling the variable vane radially between the casing and the inner shroud such that the radially inner spindle is rotatably coupled within an opening extending through the inner shroud, wherein the opening has a non-circular cross-sectional profile.

Abstract: A method for assembling a vane sector for a gas turbine engine, the vane sector including an airfoil vane and a platform includes depositing a wear coating material onto a selected area of the platform, positioning the platform adjacent to the airfoil vane, and executing a brazing operation such that the airfoil vane is permanently coupled to the platform portion and such that the wear coating material is bonded across a predefined area of the platform.

Abstract: A gas turbine engine blade is laser shock peened by laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and shot peening a portion of the airfoil to counter the laser shock induced twist in the airfoil. The shot peening may be performed before or after the laser shock peening. The shot peening may be applied over a laser shock peened surface formed by the laser shock peening. The shot peening may be performed asymmetrically on asymmetrically shot peened pressure and suction side areas of pressure and suction sides, respectively, of the airfoil. A shot peened patch near a blade tip may be formed on one of pressure and suction sides of the airfoil wherein the airfoil extends radially outwardly from a blade platform to the blade tip of the blade.

Abstract: A method for laser shock peening a gas turbine engine blade includes laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and altering a root of the blade to counter the laser shock induced twist in the airfoil. The altering may be done after the laser shock peening. The altering may be done before the laser shock peening during casting or forging of the blade or during a machining or broaching procedure which cuts a shape of the root. One embodiment of the altering includes forming the root with an altered root centerline having an altered centerline angle with respect to a predetermined root centerline designed for a non-laser shock peened airfoil of the blade.

Abstract: A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.

Abstract: A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.

Abstract: The present invention discloses solventless composition suitable for application as a hot melt to a substrate, said composition comprising a mixture or alloy of resins, selected such that the averaged glass transition temperature (Tg) of the combined unreacted resins is greater than -30.degree. and less than +60.degree. C. The melt viscosity of the unreacted resins are selected so that the combined resin mix has a melt viscosity of from about 0.05 to 25 Poise when measured at 180.degree. C. and at a shear rate of 10,000 Hz.

Abstract: The method for making a reduced fat foodstuff entails replacing at least a portion of the fat and/or oil in the foodstuff with a high amylose starch hydrolysate having an apparent amylose content above about 40% and a DE greater than 5 and less than 15.0. A high amylose corn starch is the preferred starch base.

Abstract: An audible enrichment bleed warning device, for fuel-injected engines having an enrichment bleed, emits an audible warning that the enrichment bleed is open and extra fuel is being delivered to the engine, reminding the operator to close it after the engine has warmed. The warning device may be a horn or a whistle.

Abstract: A flexible bicycle rim strip has two free ends and a securing hole near each end. The free ends insert through a rectangular valve stem hole in the rim, and are secured to adjacent spoke nipples.

Abstract: A two-position bicycle pedal having heel stops at different distances from the spindle, such that either the arch or ball of the foot is positioned over the spindle. A heel step is provided, for support of the heel, when the arch of the foot is over the spindle.