Abstract: An invention is disclosed for positioning an object wherein three point supports provide three contact points which define a first plane. Three additional point supports provide three additional contact points which are not coplanar with the first plane and which define a second plane. The first and second planes are nonperpendicular. The point supports accurately and repeatably position the object for optical measurement of a dimension of the object. The invention can be used in connection with the quality control testing of weldments which attach blade tips to gas turbine engine blades.

Abstract: The invention comprises a system for cooling a component in a gas turbine engine, and, in particular, for cooling an engine electronic control thereof. The cooling system includes a housing for mounting the control having a plurality of heat transfer fins extending outwardly therefrom. The housing is mounted in the engine upstream of a compressor and to a front frame having an aperture through which the fins extend. The front frame defines a flowpath to the compressor and the fins extend into the flowpath without adversely affecting the aerodynamic airflow pattern thereof. In a preferred embodiment, the fins extend substantially only to an inner surface of the front frame, and the housing includes temperature and pressure sensors disposed below root sections of the fins.

Abstract: In the present invention, fuel flow in an aircraft is modulated automatically in order to maintain a preselected altitude.

Abstract: A hollow composite airfoil with an integral internal support rib of fluoroelastomer rubber is formed by bracketing the rib between two silicone rubber mandrels to form a core assembly having a desired aerodynamic shape, then building up on opposite sides of the core assembly separate stacks of laminae of a composite material of graphite (or carbon) and glass fibers impregnated with an epoxy resin, with the two stacks overlapping adjacent to the leading and trailing edges of the core assembly. Heat and pressure are then applied to the core assembly with the laminae thereon to bond together the laminae of each stack, then to bond the two stacks together along the overlapping portions thereof and to bond the two stacks to the rib to form a continuous shell around the core assembly. The mandrels are then removed. One open end of the resulting hollow airfoil is plugged and that end is inserted into a recess in a mounting platform with a predetermined clearance space therebetween.

Abstract: Disclosed is a bladed disk assembly having a new and improved rotor blade. The blade includes a shank and dovetail extending from an airfoil portion thereof. The shank includes a pocket extending therein from an end surface thereof. The shank pocket allows for reduced weight of the blade while maintaining acceptable bending stiffness thereof. In an exemplary embodiment of the invention, the bladed disk assembly is effective for being interchangeable with a blisk assembly having an inlet hub radius ratio of about less than about 0.5 and a root solidity of greater than about 2.2.

Abstract: An improved exhaust system including a lobed mixer and an improved exhaust centerbody is provided. The improved exhaust centerbody includes means for cooperating with the lobed mixer to increase mixing effectiveness of the exhaust system without substantially increasing pressure losses attributable thereto. In a preferred embodiment of the invention, the cooperating means include a plurality of circumferentially spaced elongated deformations, such as grooves and ridges, which deformations extend radially with respect to a reference surface of the exhaust centerbody and which deformations are aligned in an axial direction substantially parallel to a longitudinal axis of the centerbody.

Abstract: An improved blade tip with an abrasive coating is disclosed. The blade tip is included in a rotor blade which is rotatable with respect to a stationary surface. The tip has a contour which is effective for producing a normal loading component on the coating if the tip contacts the surface while rotating. In a specific form of the present invention, the tip comprises an end wall extending radially outwardly from the perimeter of the outer end of the rotor blade and a concave surface bounded by the end walls and extending radially inwardly therefrom.

Abstract: The invention comprises a blade for a gas turbine engine including an airfoil portion having a non-linear stacking axis intersecting a reference radial axis that is effective for generating a compressive component of bending stress due to centrifugal force acting on the blade. The compressive component of bending stress is provided in a life-limiting section of the blade, which, for example, includes trailing and leading edges of the blade. Inasmuch as the stacking axis, which represents the locus of centers of gravity of transverse sections of an airfoil portion of the blade, is non-linear, an increased amount of a compressive, component of bending stress can be generated at a life-limiting section between a root and tip of the blade without substantially increasing bending stress at the root of the blade due to the non-linear stacking.

Abstract: Stator vane retaining means such as may be used in a compressor of a gas turbine engine is disclosed. The compressor is the type including a casing with first and second annular members and a plurality of vanes, each vane having a vane axis and a root end for mounting to the casing. The stator vane retaining means comprise a first flange extending radially outwardly from the first member and a second flange extending radially outwardly from the second member. The second flange includes a plurality of radially extending recesses. The flanges are adapted to mate so that the first flange encloses the recesses thereby forming a plurality of radially extending holes. Each of the holes is adapted to receive one of the root ends. The stator vane retaining means may also include a plurality of bolts extending through the flanges and intersecting a cut-out portion of each of the root ends of the vanes. In this manner, radial retention of each of the vanes is provided.

Abstract: A carburetion assembly including flow control means is provided for controlling a discharge spray angle of a fuel and air mixture thereof. According to one embodiment of the present invention, the flow control means can comprise a plurality of circumferentially spaced apertures in a shroud member which are effective for providing a control portion of compressor airflow in a downstream, axial direction from a swirler stage of the swirler assembly. The apertures provide a predetermined amount of airflow circumferentially about the fuel and air mixture for constraining the mixture and controlling the discharge spray angle thereof.

Abstract: In one form of the present invention, the thrust of a gas turbine engine is inferred. If a droop in thrust is predicted, components of the engine are modulated in response to restore thrust.

Abstract: A turbomachine seal for reducing fluid flow through the gap between circumferentially adjacent blade platforms is disclosed. The seal comprises a pair of radially inwardly extending elastomeric members. Each member has an inwardly extending first face and is bonded at a second face to respective ones of adjacent platforms. Each elastomeric member is circumferentially deflectable under a centrifugal load so that respective first faces meet.

Abstract: An assembly is disclosed for automatically balancing thrust on the rotor of a gas turbine engine. An annular chamber axially positioned relative to the rotor is adapted to receive pressurized hydraulic fluid and apply it to the rotor. The force thereby applied to the rotor is regulated by sensing changes in axial rotor thrust and delivering hydraulic fluid to the chamber at a pressure sufficient to balance axial forces acting on the rotor.

Abstract: The present invention utilizes a wire wool slug packed inside a helical coil of an aircraft engine sensor in order to reduce vibration damage to the coil.

Abstract: The diffuser of the present invention comprises a plurality of passages which intersect at radially inner ends thereof to define a quasi-vaneless annular inlet for receiving accelerated gases from an impeller of a centrifugal compressor. Each of the passages includes a throat portion having a quadrilateral cross section, including two subtantially parallel linear sidewalls and two substantially arcuate opposing sidewalls, effective for reducing the length of and thereby pressure losses from the annular inlet. The linearity and regularity of the diffuser passages enables the diffuser to be manufactured to close tolerances by electric discharge milling an annular plate utilizing a single tool. This assures uniformity and consistency between diffusers.

Abstract: A fluid-cooled article, such as a turbomachinery blading member, is provided with a fluid passage by a method of depositing a first material on a work surface of a mandrel by low pressure plasma deposition. A first member thus generated is separated from the mandrel. In one form, an inner surface of the first member is provided with a surface groove. After depositing a sacrificial material in the groove, a cover material is applied to entrap the sacrificial material. Removal of the sacrificial material provides the fluid passage.

Abstract: Means for reducing gas flow in the space between first and second relatively moveable members. The means include a support bracket which is attached to the first member and a seal plate which is hinged to the support bracket. One end of the seal plate is in slideable contact with the second member. The means also includes a flexible membrane which is fixedly attached to the support bracket of the seal plate to prevent leakage of gas through the hinge.

Abstract: A multiple-impingement cooled structure, such as for use as a turbine shroud assembly. The structure includes a plurality of baffles which define with an element to be cooled, such as a shroud, a plurality of cavities. Impingement cooling air is directed through holes in one of the baffles to impinge upon only the portion of the shroud in a first cavity. That cooling air is then directed to impinge again upon the portion of the shroud in a second cavity.

Abstract: The present invention includes a pair of cantilevered probes. A first fastening means is fastened to a first of the probes and is loosely journaled about the second probe. A second fastening means is fastened to the second probe and is loosely journaled about the first probe. The invention provides improved resistance to the harmful effects of vibration.

Abstract: An invention is disclosed in which a fluidic counter generates fluidic switching signals in response to a fluidic oscillator for sequentially activating a plurality of fluidically activated electrical switches for multiplexing a plurality of electrical conductors into a single conductor.