Abstract: A unique anti-icing management system for a gas turbine engine is disclosed according to which, at all times, only the required amount of heat is applied to inlet surfaces of the engine to prevent the formation of ice. Heated air is bled from the compressor discharge for this purpose and the amount of flow of the heated air is adjusted by a uniquely operated solenoid valve under the direction of an electronic control responsive to any one of a variety of meaningful conditions including, but not necessarily limited to, temperature of an anti-iced surface at the inlet to the engine, rotational speed of the engine, and the presence of an ice producing meteorological condition. The solenoid valve assumes only two operable positions, namely, a fully open position and a fully closed position, and is operated in a pulsed fashion to control flow on a time basis, rather than on a percentage-of-opening basis which is the conventional mode of operation.

Abstract: A segmented combustor wall panel for a gas turbine engine is retained by a clip secured to a post extending radially from the segmented panel. This post passes through a hole in the outer wall support structure and is machined to have a square cross section at a region spaced from its end. A double looped spring clip composed of spring sheet metal is received on the post and has its free opposed ends provided with cutouts to conform to the shape of the square cross section portion of the post to thereby prevent rotation of the clip on the post. The double looped arrangement of the clip provides a fail safe feature in that the clip will retain the post even in the event half the clip should fail.

Abstract: A gas turbine engine having a turbine casing with a contoured entry. The contoured entry is located upon the housing such that upon assembly of the engine the contoured entry is located relatively directly prior to the turbine blades. The contoured entry is positioned relatively directly prior to a spacing between the tips of the turbine blades and the housing such that gases are directionally restricted away from the spacing and into the turbine blades.

Abstract: A combustion chamber liner has three layers; a first ceramic layer, a second filamentary steel wool type layer and a third metallic layer. The interior of the liner is cooled by passages in the third layer and emergency or failure activated cooling occurs in a damaged area in the first layer. Sensor means can be placed in the liner or externally of the liner to detect changes in the coolant flow or pressure and thereby detect a failure in the liner.

Abstract: A combustion chamber liner having a layer of refractory material, a layer of metallic material, means to adaptably fix the layer of refractory material to the layer of metallic material and a means for internally cooling the liner. The means to adaptably fix the layer of refractory material to the layer of metallic material allows both layers to expand and contract separately without risk of damaging the liner because of different thermal expansion rates. The means for internally cooling the liner allows the liner to operate at higher temperatures and increases the useful life of the liner.

Abstract: An improved deburring brush is presented which is useful in processing aerospace parts of considerable length and surface complexity. The brush includes a cylindrical hub for providing support during use. A multiplicity of brush elements of the channel strip type are attached at regular intervals around the periphery of the hub. Attachment is typically by use of retaining strips which hold the brush strips in lengthwise channels cut in the hub surface. Each brush element includes a longitudinal metal strip bent into a generally U-shape to form a rear wall and two converging sidewalls. Bristle fibers are then laid side by side in a row, then collectively folded at their middles around a core wire for insertion into the U-shaped channel which is then compressed so that the sidewalls press against the multiplicity of protruding bristles. Each bristle is flexible and has impregnated therein a plurality of abrasive particles. The outwardly extending ends of each bristle readily flex in the plane of rotation.

Abstract: An apparatus is provided for use in a gas turbine engine to achieve an efficient atomization of fuel over a wide range of fuel flow rates and engine operating conditions. The apparatus comprises a valve to selectively block the flow of fuel directed to the fuel injector of the engine during the start-up conditions of the engine. The valve, however, will permit the fuel to flow through a mixing apparatus during start-up conditions. The mixing apparatus includes a nozzle into which the fuel is directed. The mixing apparatus also is in communication with a supply of air. The pressure drop created as the fuel passes through the nozzle will draw air into the apparatus and effect mixing of fuel and air. Subsequent passage of the fuel/air mixture through the relatively large passages of the conventional fuel injector will effect good atomization even at low fuel flow rates associated with start-up conditions.

Abstract: A high specific modulus shaft for use in a dynamic assembly such as a gas turbine engine is constructed having a metal outer tubular shaft to transmit the torque and an interior shaft constructed of a metal and high modulus filament composite material bonded to the inner diameter of the outer shaft. The outer shaft may be constructed of steel or titanium or superalloy such as Inconel 718. The inner shaft may be constructed of an aluminum matrix in which multiple boron filaments are embedded in axial alignment or of a titanium matrix in which boron filaments coated with silicon carbide or boron carbide are similarly embedded.

Abstract: A unique anti-icing management system for a gas turbine engine is disclosed according to which, at all times, only the required amount of heat is applied to inlet surfaces of the engine to prevent the formation of ice. Heated air is bled from the compressor discharge for this purpose and the amount of flow of the heated air is adjusted by a uniquely operated solenoid valve under the direction of an electronic control responsive to any one of a variety of meaningful conditions including, but not necessarily limited to, temperature of an anti-iced surface at the inlet to the engine, rotational speed of the engine, and the presence of an ice producing meteorological condition. The solenoid valve assumes only two operable positions, namely, a fully open position and a fully closed position, and is operated in a pulsed fashion to control flow on a time basis, rather than on a percentage-of-opening basis which is the conventional mode of operation.

Abstract: The invention is directed to a quadridge antenna situated within a quadri-fluted module. The tips of the ridge elements are recessed a distance below the surface of the window aperture.

Abstract: A self-aligning bearing assembly for use with a frame and a shaft. The assembly comprises bearings such that the shaft can move relative to the frame and a spring and a friction surface for repositionably mounting the bearings relative to the frame. The spring and friction surface for repositionably mounting the bearings can frictionally hold the bearings in a first position relative to the frame and can allow the bearings to move to a second position relative to the frame and be frictionally held in the second position when repositioned thereto without affecting the critical speed of the shaft system.

Abstract: A method and apparatus for accurately positioning successive turbine blades in a fixture in preparation for grinding of the root form and/or of the shroud thereof. The leading edge of the airfoil portion of each blade is supported by a vee block at first and second pairs of spaced locations and the concave surface of the blade is additionally supported adjacent its trailing edge by means of a pad member having a planar surface so oriented that the entire surface thereof coextensive with the concave surface is substantially contiguous therewith. The pad member is also so positioned relative to the vee block to assure a proper chord angle when the turbine blade is mounted on the rotational disk of the engine. In this manner, the stacking axis of each blade is substantially aligned with a predetermined axis within a tolerance range which is always less than the difference in size between a minimum contour and a maximum contour of the airfoil portion.

Abstract: An improved design for a structure such as a turbine vane or blade subjected to extreme temperature levels and/or gradients resulting in extreme deformation stresses within the structure. The present structures comprise an interior skeletal support having a plurality of spaced, flexible support legs which extend out and are attached to spaced areas of a flexible outer surface skin which is subjected to extreme temperature levels or temperature gradients during use. The extreme stresses normally developed by the expansion of the surface skin are avoided by the ability of the skin to move minutely and flex the spaced support legs to variable extents and in predetermined directions.

Abstract: An assembly of stacked rings is provided to form the cylindrical section of a combustor such as used in a gas turbine engine. Each ring is force-fitted into its adjacent ring and joined to it, as by brazing, to form a unitary structure. The rings are configured to assure proper alignment when fitted together and provide a space for holding brazing material immediately adjacent to the mating surfaces to be joined so that the brazing material, when fused in a vacuum furnace, flows evenly between the surfaces. To assure proper distribution of the brazing material when fused, one of the mating surfaces may be upset, as by knurling, to a dimension assuring a light force-fit of the parts to be joined. Each ring also includes a shaped portion projecting into the interior of the assembly for directing cooling air, introduced through the side walls of the rings, along the interior surfaces of the assembly to protect it from high temperature gases generated by combustion of fuel within the combustor.

Abstract: An anti-icing management system for a gas turbine engine according to which, at all times, only the required amount of heat is applied to inlet surfaces of the engine to prevent the formation of ice. Heated air is bled from the compressor discharge, or from some other suitable heat source, for this purpose. The amount of flow of the heated air is adjusted by an electronic control responsive to the temperature of the anti-iced engine inlet surfaces directly in the path of incoming air. The electronic control may be effective to admit flow of the heated air to the region to be heated when a separate ice detector determines the presence of ice and so informs the control.

Abstract: A bearing assembly is disclosed which is useful in mounting the cutter head of a lawn trimming implement to the tubular casing extending forward and downward from the power head. A flexible shaft housed within the tubular casing conveys rotary motion from the power head to the bearing assembly which comprises a short tubular bearing housing within which is a pair of spaced apart bearings. A central bore through the bearings is sized to accept the first end of a drive connector shaft. Within the tubular bearing housing and between the bearings is a lubricant holding annular felt ring. Adjacent the first end of the drive connector shaft is an annular slot which allows the shaft to be secured in the tubular bearing housing by a C-clip keeper. The midsection of the tubular bearing housing has an enlarged diameter as compared to the end sections which contain the bearings.

Abstract: A variable stator assembly is provided for a gas turbine engine. The assembly comprises at least one winglet disposed on the radially inner end of each variable stator blade and/or on the radially outer end of each variable stator blade. The assembly further comprises at least one shroud disposed substantially adjacent and parallel to the associated winglet and within the flow path relative to the winglet. In a preferred embodiment, the assembly comprises both inner and outer winglets and inner and outer shrouds, with the shrouds being disposed intermediate the pair of winglets. The downstream edge of the shroud is configured to be substantially adjacent to the upstream edge of each variable stator blade through the full range of movement of each variable stator blade. Additionally, the shroud extends into the flow path between adjacent variable stator blades.

Abstract: Erosion resistance is imparted to a metallic substrate without an attendant loss of fatigue life in the substrate in one embodiment by applying to the substrate a first ductile layer comprising a metal from Group VI to Group VIII elements as well as the noble metal group of elements, and a second hard erosion-resistant layer applied on the first layer comprising a boride, carbide, nitride or oxide of a metal selected from Group III to Group VI elements, the first layer capable of retaining substrate integrity and preventing diffusion of material from the second layer into the substrate. Another embodiment defines another layer of a substantially pure metal from Group III to Group VI between the first and second layers. Still another embodiment defines that in the second layer the content of either the carbide, nitride, boride or oxide is graded, i.e.

Abstract: Apparatus is disclosed which provides for the controlled deployment of a flexible samara blade used to orient and decelerate a submunition cannister which is dispensed at altitude and allowed to free fall to earth. Spin pins are anchored in and extend outwardly from the downstream end of the cannister. Placement of the pins is such that the flexible samara blade can be wrapped around the pins to place the blade in a stowed condition within the periphery of the cannister end prior to launch of the submunition. Caps on the pins are used to inhibit the stowed blade from slipping off the pins. The blade is wrapped around the pins in a direction opposite to the direction of rotation of the submunition during launch. Launching the submunition in a spinning state creates a centrifugal force in the weighted tip of the samara blade causing the wing to unwrap from the stowed to the deployed state. The pins keep tension in the unfolding wing and preclude erroneous twist-up of the flexible blade.

Abstract: An assembly for removing substantially all oil contamination from bleed air flowing at a temperature of the order to 600-650 degrees Fahrenheit from a bleed air port of a gas turbine aircraft engine to a duct leading to the cabin ventilation system of an aircraft. The assembly comprises a gas turbine engine and a catalytic converter interposed between and sealably coupled to the bleed air port of the engine and the ventilation duct, at a location near the engine. The catalytic converter comprises at least one catalytic converter matrix element through which the bleed air must flow at high temperature and at a mean velocity, each matrix element comprising a parallel array of slender tubules, which are coated internally with a catalytically active coating which produces oil-breakdown at the temperatures and residence time produced by the engine at continuous maximum thrust.