Abstract: An air sprayable, fluid, non-metallic coating mixture to provide an article coating having the ability to reflect at least 75% of heat energy in the frequency range of up to 2.6 microns comprises the combination of two different alpha alumina powders. A first powder predominantly is in a particle size range of less than about 1 micron; a second powder is of a particle size greater than 7 times the particle size of the first powder. The mixture includes a glass powder having a melting point of at least about 1400° F. and of a particle size less than about 45 microns. The mixture includes a binder that will form up to about 80% of its weight in silica when heated to a temperature of at least the melting point of the glass powder. In the article coating, provided by air spraying the mixture onto an article and heating to a temperature sufficient to melt the glass powder and to form the silica from the binder, the glass and silica form a matrix about and binding together the alumina powder.

Abstract: A method of removing a diffusion aluminide coating on a component designed for use in a hostile environment, such as superalloy turbine, combustor and augmentor components of a gas turbine engine. The method selectively removes an aluminide coating by stripping aluminum from the coating without causing excessive attack, alloy depletion and gross thinning of the underlying superalloy substrate. Processing steps generally include contacting the coating with a mixture that contains a halogen-containing activator and a metallic powder containing an aluminide-forming metal constituent, such as by pack cementation-type process. The mixture is then heated to a temperature sufficient to vaporize the halogen-containing activator and for a duration sufficient to cause the halogen-containing activator to provide a transfer mechanism for the removal of aluminum from at least a portion of the diffusion aluminide coating, while the metallic powder absorbs the removed aluminum.

Abstract: A turbine airfoil includes first and second sidewalls joined together at leading and trailing edges, and spaced apart to define first and second cavities separated by a septum therebetween. An aft bridge extends along the first cavity and includes a row of outlet holes therein. The septum includes a row of inlet holes. And, turbulators are disposed in rows inside the first cavity, and extend from the first sidewall toward the second sidewall. The turbulators are aligned with the inlet holes for multiple impingement cooling thereof.

Abstract: A method of removing hot corrosion products from the surface of a component exposed to corrosive conditions at elevated temperatures, as is the case with turbine, combustor or augmentor components of gas turbine engines. The method is particularly suited for the removal of hot corrosion products from components protected with a diffusion aluminide coating, either as an environmental coating or as a bond coat for a thermal barrier coating (TBC). The processing steps of the method include immersing the component in a heated liquid solution containing acetic acid, and then agitating the surfaces of the component while the component remains immersed in the solution. In this manner, hot corrosion products on the surfaces of the component are removed without damaging or removing the diffusion aluminide coating. As a result, regions of the component from which the hot corrosion products were removed can then be repaired by a suitable aluminizing process.

Abstract: An intermediary device is provided between an eddy current bolt hole inspection machine and an associated eddy current probe to positionally align the probe in each bolt hole to be inspected. A first end of the device is attachable to the eddy current bolt hole inspection machine, and a second end, having a tightening bolt, is attachable to the eddy current probe. A collet associated with the second end of the device secures the probe to the device when the tightening bolt is tightened subsequent to the second end accepting the eddy current probe. An adjustable flange component has a first portion separated from a second portion via a spring wave washer to allow the second portion to move left to right and front to back, relative to the first portion.

Abstract: A turbine blade including an airfoil having a plurality of trailing edge slots and a plurality of trailing edge openings for use in a turbine engine is described. The trailing edge slots extend along a pressure side wall to the trailing edge at an upper portion of the blade. The trailing edge openings extend through the trailing edge at a lower portion of the blade. The trailing edge at the upper portion of the airfoil is relatively thin in comparison to the trailing edge at the lower portion of the airfoil, which allows for high aerodynamic efficiency and cooling of the airfoil.

Abstract: A shaft assembly for movement of an array of adjustable members comprises a hollow shaft body including a shaft body wall with a wall outer surface. A plurality of spaced apart clevises, secured with the shaft body wall on the wall outer surface, each includes connection means disposed away from the wall outer surface for connection with an actuator for movement of the adjustable members.

Abstract: Corrosion is avoided in variable stator vanes through the use of an outer trunnion bushing that eliminates the galvanic corrosion potential of conventional bushings. The bushing has a plurality of layers arranged concentrically so as to include an innermost layer and an outermost layer. The innermost layer is made of a braided graphite composite laminate material, and the outermost layer is made of a non-galvanic material.

Abstract: A method for repair welding a titanium compressor blisk using laser twist welding. A blisk assembly has damaged portions removed. The surface to be repaired is provided with a predetermined geometry. The portions to be repaired are surrounded by a fixture which contains a laser nozzle. The fixture can provide a protective atmosphere to the area under repair while also shielding adjacent areas from damage resulting form welding. The welding is accomplished using preprogrammed patterns. The welding within the fixture is monitored remotely and is adjusted when stand-off between the weld nozzle and the molten metal are not within a predetermined range.

Abstract: A turbine blade damper in the form of a sheet metal body includes a concave notch along one edge thereof, and a projecting side tab along an opposite edge thereof.

Abstract: A thermal barrier coating system and a method for forming the coating system on a component designed for use in a hostile thermal environment, such as superalloy turbine, combustor and augmentor components of a gas turbine engine. The coating system includes a diffusion aluminide bond coat whose oxide growth rate is significantly reduced to improve the spallation resistance of a thermal barrier layer by forming the bond coat to include a dispersion of aluminum, chromium, nickel, cobalt and/or platinum group metal oxides. The oxides preferably constitute about 5 to about 20 volume percent of the bond coat. A preferred method of forming the bond coat is to initiate a diffusion aluminizing process in the absence of oxygen to deposit a base layer of diffusion aluminide, and then intermittently introduce an oxygen-containing gas into the diffusion aluminizing process to form within the bond coat the desired dispersion of oxides.

Abstract: A turbine blade includes an airfoil having a leading edge flow chamber disposed behind a leading edge in flow communication with an isolation flow channel disposed therebehind. The isolation channel is bounded on opposite sides by a pair of side flow channels.

Abstract: An interface seal for a turbine engine including a rotor shroud hanger including at least one opening, an outer band including an aft rail, and a seal spring mounted in the opening and extending over an interface between the outer band and the shroud hanger, is described. The seal provides a barrier that prevents the leakage of high pressure cooling air through the interface into the combustion gas flowpath bypassing turbine engine components, and thus forces the high pressure cooling air through the necessary turbine engine components.

Abstract: A method of forming a multilayer ceramic coating system on a substrate that requires thermal protection from a hostile thermal environment. The method generally entails forming at least one tape that contains ceramic particles dispersed in an organic constituent, such as a binder and/or plasticizer. If a single tape is used, the tape is formed of multiple layers of different compositions and applied as a unit to the substrate, thereby forming at least an innermost layer and an outermost layer on the substrate. If multiple tapes are used, a first tape is applied to the substrate to form the innermost layer, and a second tape is applied to form the outermost layer. The tape/tapes are then sintered to form innermost and outermost ceramic layers, respectively, on the substrate.

Abstract: A fastening system includes a tool for fastening a threaded stud having external first threads. The tool includes a longitudinally extending casing having a cavity with an open first end and an aperture mount connected to the casing at a second end of the cavity and spaced apart a first distance from the open end. A threaded first aperture having internal second threads is disposed within the mount and has a centerline that passes through the open end and is threaded to receive the stud through an open aperture first end and to receive a threaded shank through an open aperture second end. A stop is provided for stopping the threaded shank from threading more than a predetermined first distance into the first aperture so that the stud protrudes a predetermined height from the part it is screwed into.

Abstract: A turbine blade includes a hollow airfoil having a squealer tip rib extending outboard from a tip cap enclosing the airfoil. An impingement baffle is spaced inboard from the tip cap to define a tip plenum therebetween. Impingement holes extend through the baffle and are directed at the junction of the rib and cap for impinging a coolant jet thereagainst.

Abstract: A turbine airfoil includes first and second sidewalls joined together at leading and trailing edges, and extending longitudinally from root to tip. An internal cooling circuit is disposed between the sidewalls for channeling a coolant therein. A column of longitudinally spaced apart ejection slots extend through the first sidewall along the trailing edge, and are disposed in flow communication with the cooling circuit for discharging the coolant toward the trailing edge. Some of the slots are disposed between a pitchline and the tip and are inclined at different ejection angles longitudinally outwardly from the pitchline. And, some of the slots are disposed between the pitchline and root and extend at least parallel with the pitchline without longitudinally inward inclination.

Abstract: A method of making a hollow airfoil includes machining first and second parts to produce internal features thereof. The parts are then co-machined simultaneously at complementary joining surfaces. The parts are then bonded together at the co-machined joining surfaces.

Abstract: A turbine engine includes a gear driven booster connected to a high pressure shaft of the engine. A gear assembly connects the booster to the high pressure shaft. The booster is a high speed orthogonal booster that includes a plurality of rotor blades and a plurality of stator vanes. The booster rotates in a direction that is opposite to a direction the high pressure shaft rotates.

Abstract: A gas turbine blade includes an airfoil, platform, and dovetail. The blade is cast with a chamfer along one edge of the platform thereof. The platform edge is then machined to truncate the chamfer in a simple and precise method.