Abstract: A locking member for engaging a shield 40 which is disposed during processing about an airfoil 24 of a flow directing assembly 10, such as a stator vane or rotor blade, is disclosed. Various details are developed for the construction of the locking member. In one embodiment, the locking member is separate from the shield and has projections 112, 116 that each engage an opening 36a, 36b in the airfoil and tabs 114, 118 which engage an opening 78, 84 in the shield. In another embodiment, the shield has a projection 106a which is attached to the shield.

Abstract: A coolable airfoil structure having internal heat transfer features through which cooling air is flowed under operative conditions is disclosed. Various construction details and features are developed which affect the castability and core strength during manufacture and strength and cooling effectiveness of the airfoil after manufacture. In one particular embodiment, the airfoil has a plurality of heat transfer members disposed in the rearmost section of the trailing edge region which comprises a single impingement rib, a single row of pedestals and a single row of chordwisely extending flow dividers.

Abstract: A tool 12 for disposing laser blocking material 52 on the interior of an airfoil 10 is disclosed. Various construction details are developed which speed the process. In one detailed embodiment, the tool has reciprocatable jaws 92, 94 which open and close to urge a mask 78 into engagement with the airfoil.

Abstract: A method for forming a rotor assembly for guiding motion of one circumferentially extending structure with respect to a second structure is disclosed. Various steps of the method are developed and include forming a pin for receiving a rotatable element for the roller assembly. In one particular embodiment the method includes forming the pin with a one-piece head and trapping the rotatable element between the pin and support structure for the pin.

Abstract: A method for forming a stator assembly 28 of a rotary machine 10 which includes masking the stator assembly during a machining operation on a seal member 70 is disclosed. Various detailed steps of the method are disclosed which decrease the cost of the method. In one embodiment of the method, the method includes disposing a shield assembly 98 about the stator assembly 28 to such an extent that individual members of the stator assembly need not be disassembled for cleaning.

Abstract: A coolable airfoil structure having internal heat transfer features through which cooling air is flowed under operative conditions is disclosed. Various construction details and features are developed which affect the castability and core effectiveness of the airfoil after manufacture. In one particular embodiment, the airfoil has a plurality of heat transfer members disposed in the rearmost section of the trailing edge region which comprises a single impingement rib, a single row of pedestals and a single row of chordwisely extending flow dividers.

Abstract: A method for orienting an airfoil 10 during filling of an airfoil with laser blocking material 52 prior to a laser machining operation is provide and includes making a mask 78 for the airfoil.

Abstract: A method and assembly useful in metal joining processes is disclosed which blocks the deposition of molten metal in openings. The method and assembly employs mica material with a binder to block the flow of molten metal. In one detailed embodiment, the mica material supports elements of the articles being brazed.

Abstract: A method for assembling a rotary machine, such as a gas turbine engine, having rotor elements and associated seal lands. Various details of the method are developed for facilitating assembly of the rotary machine that are, in one embodiment, applicable to installing fan blades to a fan rotor disk while rotating the rotor disk by hand. In one embodiment, a lubricant is applied to a seal land to reduce friction between the rotor element and the seal land during assembly.

Abstract: A fixture 56 for disposing laser blocking material 52 on the interior of an airfoil 10 is disclosed. Various construction details are developed which allow for the repetitive disposition of the laser blocking material in one airfoil after another. In one embodiment, the fixture includes a sprue plate 62 and locating block 126 which are spanwisely spaced and engage the ends 14, 18 of the airfoil.

Abstract: A shield 40 for use in processing a flow directing assembly 10, such as a stator vane or rotor blade, is disclosed. Various construction details are developed for the shield. The shield has two sides 52, 56 and at least two tabs 56, 58 which each extend from one of the sides and through the other side.

Abstract: A shield assembly 98 is disclosed which has one or more shield elements 102, 104, 106 which block, during machining of a seal member 70 for a rotary machine 10, seal particles from entering a vane cluster 58. Various construction details are developed which increase the effectiveness of the shield assembly. In one embodiment, the shield assembly has an upper shield element 102 having a U-shaped cross sectional shape which fits over a stator assembly 28 that includes the seal member.

Abstract: A roller assembly for guiding the motion of a circumferentially extending ring in a gas turbine engine, where the roller assembly has a pin and a collar. The pin has a head which engages a rotatable element, which in turn adapts the roller assembly to engage a track and which adapts the roller assembly to receive an external force from the track under operative conditions, causing a reactive force on the rotatable element to resist the external force. A gap formed between a shank of the pin and the collar decreases the bending stresses in the shank in comparison to forces acting on the pin at an end of the collar which engages a support.

Abstract: An apparatus 28 for forming at least a portion of the edge 12,14 of airfoil 10 using a tool assembly 68 is disclosed. The tool assembly has a tool 164 with a cutting face 202 having a shape which is like the shape of the finished edge of the airfoil. Various construction details of the apparatus are developed which enable the tool to incrementally remove material while accommodating wave-like variations in the airfoil edge. In one embodiment, the apparatus has a probe assembly 166 attached to the tool which is moveable with respect to a reference surface R.sub.s on the airfoil to guide the tool.

Abstract: A compact heat exchanger system 52 for a duct 32 of a gas turbine engine 10 is disclosed, the heat exchanger system being disposed between two locations having an adverse pressure gradient. Various construction details which reduce the impact of the system 52 on engine efficiency, provide acceptable levels of drag, and reduce the possibility of foreign object damage are developed. In one embodiment the system has a low profile inlet 58 adjacent the inner wall 36 of a fan duct and has a flow path 56 extending from the inlet 58 to the outlet 62 which is continuous under all operating conditions of the engine.

Abstract: A housing assembly for a turbine engine has a housing which is adapted to cooperate with an adjacent valve ring assembly. The housing has a plurality of passages for working medium gases which extend radially through the housing and are circumferentially spaced in the housing. The valve ring modulates the flow through the passages. A plurality of flanges extend axially and circumferentially from the housing. Each flange has a track opening which receives a liner and a roller assembly having a bearing surface. The roller assembly in combination with the liner guides the valve ring assembly. The liner and the housing have different physical characteristics, such as a different rate of thermal expansion and different spring rate characteristics which accommodate differences in thermal growth between the liner and the housing.

Abstract: A stator assembly of an axial flow rotary machine has a compressor bleed system. The compressor bleed system includes an axially translating valve ring. The valve ring is movable between an open and closed position and includes guide roller and guide track having guide walls which urge the valve ring axially against resilient seal members. The track is contoured to provide a mechanical advantage when the valve ring is moved to the closed position. A liner is adapted to engage the stator assembly to form the track.

Abstract: A fixture 14 for use in applying a material to a face 16,18 of a rotor blade 10 is disclosed. Various construction details are developed which reduce rework of the rotor blade and facilitate application of the material are developed. In one embodiment, a pad 48 has a surface 50 which blocks the flow of molten material to the flow path surface 42 of the shroud 12 of the rotor blade.

Abstract: A rotatable seal element 38 is formed of at least two circumferentially continuous rings 48,50. The rings have decreased thickness T.sub.2, T.sub.3 in the outward direction. Various construction details are developed which effect the level of cyclic fatigue life. In one particular embodiment, the seal element has a flat surface 74 extending inwardly from the sides at the interface between the rings.

Abstract: An inlet-outlet module 108 having both an inlet 58 and an outlet 62 for a heat exchanger system 52 is disclosed. Various construction details which improve the stiffness to weight ratio and the aerodynamic smoothness are developed. In one embodiment, the module 108 is formed of a one piece casting having a lobed mixer 94 at the outlet.