Abstract: A stator assembly 28 for a gas turbine engine 10 is disclosed. The stator assembly includes an inner stator structure 54 and an outer stator structure 52. A plurality of tensioned members 50 extend radially between the structures to stiffen the structures against deflection and to restrain the structures against relative movement. In one embodiment, the inner stator structure is an engine casing 54, the outer stator structure 42 is a fan casing, and the radially extending members are a plurality of guide vanes 50.

Abstract: A control valve assembly 10 having a pair of axially opposed seats 54, 56 is disclosed. A poppet 66 is disposed in a control chamber 58 between the seats. The poppet is movable between the seats to establish an average pressure in the control chamber. The poppet is a portion of an armature 28. In one embodiment, the armature is urged in a first direction by a solenoid and in the opposite direction by a spring 76 which extends between the armature and a housing of the valve. In another embodiment, means 310, such as diaphragms 312 or 314 or the slidable engagement 318, 320 between the housing 224 and the first end 251 of the armature are provided for radially positioning the armature as the armature is moved between the seats. In still another embodiment, the armature 228 is formed of a first section 416 and a second section 418 which are jointed by a shaft 434 which is slidable with respect to the first section.

Abstract: A stator assembly 18 for a gas turbine engine is disclosed. Various construction details relating to the mounting of a stator vane 42 in the engine are developed. In one embodiment, the vane is: bolted at a downstream flange 112 of the vane to an inner support 54; radially splined to a support such as the outer support 56 at an upstream flange 125 which is spaced axially from the downstream flange; and, is adapted to slidably engage the outer support to provide sealing contact between the vane and the remainder of the engine.

Abstract: A circumferentially extending structure 30 for containing particles having an axial component and a radial component of velocity is disclosed. The apparatus is comprised of a support structure 46 and a fabric 44 wrapped under tension about the support structure such that the installed length of the fabric is greater than the free length of the fabric. In one particular embodiment the fabric is coated with a layer of epoxy resin such that the resin penetrates only the top layer of the fabric to form a shield 95 which protects the containment fabric from injury. A method for forming the circumferentially extending structure is disclosed which includes the steps of forming a support structure and wrapping a fabric about the support structure under a preload to cause an elongation of the fabric and tension in the fabric in the installed condition.

Abstract: A ternary alloy catalyst for the electrochemical reduction of oxygen is disclosed. Various methods of making the catalyst are developed. The catalyst has an ordered structure which improves stability and the specific activity of the catalyst.

Abstract: A coolable stator assembly formed of wall segments 36 for bounding a working medium flow path 14 is disclosed. The wall segments extend circumferentially about the working medium flow path and are circumferentially spaced leaving a clearance gap G therebetween. A duct 148 for cooling air is formed by the facing sides 144, 146 of the wall segments and a pair of radially spaced seal elements such as an inner seal plate 134 and an outer air seal plate 136. In one embodiment, a primary flow path for cooling air extends radially outwardly of the wall segments and the working medium flow path extends radially inwardly of the wall segments. The duct is pressurized with cooling air from an adjacent location at an intermediate pressure between the primary flow path 32 and the working medium flow path 14.

Abstract: Components of a rotor assembly which is capable of long term reliable operation in an axial flow gas turbine engine environment are disclosed. Various construction details enabling good low cycle fatigue life by reducing stress concentrations in the rotor disk are disclosed. Rotor disk and blade features are combined to provide a seal land on the rotor assembly without the need of disk sideplates.

Abstract: A rotor assembly 22 for a gas turbine engine is disclosed. The engine has a compression section 12 and a turbine section 16. Various construction details which enable the modular disassembly of the turbine section are developed. The rotor assembly includes a rotor shaft 42 extending between the compression section and the turbine section. An annular shaft 66 engages a bearing 64, is joined to a rotor blade assembly 74, and rotatably supports the rotor shaft 42.

Abstract: An electrical apparatus, such as a solenoid assembly 10, and a method for making the solenoid assembly are disclosed. Various construction details which improve the integrity of the solenoid assembly against the leakage of fluids are disclosed. In one embodiment, the solenoid assembly has a first wall, such as a flange 14, which is substantially fused about the wall to a second wall, such as an encapsulating casing 18.

Abstract: A ternary alloy catalyst for the electrochemical reduction of oxygen is disclosed. Various methods of making the catalyst are developed. The catalyst has an ordered structure which improves stability and the specific activity of the catalyst.

Abstract: A ferric hydrous oxide of a character that retards the deposition of iron based compounds on the walls of a conduit is prepared by flowing an aqueous solution containing iron-based compounds including magnetite into a vented chamber, and boiling the solution at atmospheric pressure.

Abstract: A method for making a carbon-graphite component of the type adapted for use in an electrochemical cell is disclosed. The precursor sheet structure for the component contains cellulose and purified graphite powder which provides certain advantages during processing and in the final products.

Abstract: A stator assembly 18 for a gas turbine engine is disclosed. The stator assembly includes an engine case 24 and a wall 26, such as a wall that includes an array of stator vanes 42. A high pressure region 74 (cooling chambers) extends between the wall and the engine case. The cooling chambers 74 are in flow communication through a leak path with a working medium flow path 14. An annular outer support 56 bounding the chambers beneath the vanes forms with the vanes an intermediate chamber 132 through which the leak path for cooling fluid passes. The annular support further includes a plurality of orifices 94 for diverting flow away from the leak path to lower the pressure of the intermediate chamber. In one embodiment, the chamber is formed in part by an annular groove 84 in the support and a plurality of flanges 124 associated with the vanes. The flanges are urged rearwardly into sealing contact with the annular support.

Abstract: A porous plate for an electrochemical cell, such as plates 22, 24 having a sealing material disposed in an edge region 41 of the plate is disclosed. Various construction details including a method for making the plate are disclosed which increase the cross pressure material the plate can withstand. In one embodiment, the seal region 41 is impregnated with powder having a low structure and predetermined particle size using a pressurized liquid carrier.

Abstract: A coolable seal assembly, such as the outer air seal 26, for a gas turbine engine 10 is disclosed. The seal assembly is formed of a plurality of arcuate seal segments 24 which extend circumferentially about an axis of the engine. The seal segments 24 are spaced apart leaving a clearance gap G therebetween. An orifice plate, such as the orifice plate 94, is disposed in the gap. The orifice plate has an opening, such as the orifice 106, for ducting cooling fluid into the gap G. In one embodiment, the orifice plate is integral with one of the arcuate seal segments and forms a shoulder 128 on the seal segment. Flow through the orifice plate is variably restricted by a device, such as the adjacent seal segment 24b, so that the restriction is responsive to the size of the gap G under certain operative conditions of the engine.

Abstract: A coolable seal assembly, having a ceramic facing material 76, such as an outer air seal 26, for a gas turbine engine is disclosed. The seal assembly is formed of an array of arcuate seal segments 24. Various construction details which enhance the ability of the seal segment to sustain a thermal shock are disclosed. The seal segment is mountable by conventional means in a rotary machine and includes circumferentially extending flanges 30, 32. The longitudinal continuity of the flanges is interrupted to decrease the effect of the flanges on the overall effective thickness and the local effective thickness of the substrate.

Abstract: A rotor blade 14 having a spar 138 and shell 134 is disclosed. Various construction details are developed for efficiently transferring rotational loads on the rotor blade to the root section 28 of the spar. The spar has a projection 139 over which extends a portion 100 of the shell and a platform 36 of the rotor blade.

Abstract: A cooling system 46 for a turbofan gas turbine 10 is disclosed. Various construction details which increase the effectiveness of a heat exchanger 48 located in the secondary flow path 24 are developed. In one embodiment, the cooled air is used for protecting a bearing compartment.

Abstract: A stator structure 34 for supporting an outer air seal 46 is disclosed. Various construction details which adapt the stator structure to evenly move inward and outward in response to the impingement of cooling air are developed. In one embodiment an upstream support ring and a downstream support ring for the outer air seal are attached together.

Abstract: A coolable stator assembly 16 for a gas turbine engine 10 is disclosed. The stator assembly includes an outer air seal 26 and an upstream support 32 and a downstream support 34 supporting the outer air seal about a flow path 14 for working medium gases. Various construction details are developed which enable impingement cooling of the outer air seal at a first location with cooling air and enable ducting a portion of the collected cooling air through the support for impingement cooling of the outer air seal at a second location. In one embodiment, metering holes 112 extend through the supports for directing the cooling air against the edge region of the outer air seal.