Abstract: Provided are sensors and methods of measuring the oxygen concentration of a fluid. An excitation light source is in optical communication with a transducer for transmitting an excitation light that is at least partially absorbed by the transducer. The transducer has a property of photoluminescence, and enters a higher energy state by at least partially absorbing the excitation light and enters a lower energy state through radiation of emitted light, thus producing spectral indicia. A light detection system, which is also in optical communication with the transducer, processes the spectral indicia to determine the concentration of oxygen in the fluid.

Abstract: Disclosed are propulsion systems 30 providing reduced fuel burn, weight and cost. A single gas generator core 38 drives multiple bladed propulsion elements 36 with a power train 48. The core 38 has a forward compressor 56 and a rearward turbine 40 and rotates about a longitudinal core axis 62. The bladed propulsion elements 36 rotate about bladed propulsion element axes 78 that are not coaxial with the core axis 62. The bladed propulsion elements 36 discharge an ambient air stream 50 rearward as a bypass stream 52 portion and a core stream 54 portion. The core stream 54 portion is directed to the compressor 56. The propulsion systems 30 mount inside a fuselage 22 of an airframe 20 or they are suspended beneath a wing 24 via pylons 32.

Abstract: In accordance with the present invention, there is provided a system for injecting a secondary fluid stream into a primary fluid stream with improved aerodynamic efficiency. The secondary fluid stream is injected into the primary fluid stream at a tangential angle and radial location that reduces both mixing and endwall losses. A platform borders the primary fluid stream and contains a trailing edge surface. A rail extends radially from the platform and one or more conduits enter the rail in a substantially radial direction. The conduits extend through the radial length of the rail, continue into the platform, and terminate at the trailing edge surface. The secondary fluid stream is conveyed by the conduits through the rail and the platform, to the trailing edge surface, for injecting into the primary fluid stream at an optimal angle and radial location.

Abstract: Provided is an accessory gearbox for a gas turbine engine that contributes minimally to engine weight and complexity. An accessory gearbox comprises a stationary frame that is circumferentially disposed about a central longitudinal axis of the engine. The frame includes a forward-directed axial face and a rearward-directed axial face for fastening the frame to the engine. A central bore accepts a rotational driving means and an outermost rim circumscribes the outer diameter of the frame. A compartment is located between the bore and the rim. At least one primary accessory is mounted to a face and proximate the compartment, remotely engaging the driving means and able to be driven concurrently therewith.

Abstract: In accordance with the present application, a fluid seal 30 and fluid sealing element 32, which are tolerant of fluid F direction reversals are provided. A sealing element 32 has at least two brush stages 50 to restrict leakage of the fluid F through a gap 38 between a component and a sealing surface. Each brush stage 50 includes a bristle arrangement 44 sandwiched between a back plate 48 and a common mid plate 46. A value allows 70 the fluid F to bypass a bristle arrangement 44 if the fluid pressure P1 or P2 varies between the chambers. Permanent damage to the sealing element 32 is avoided by allowing the higher pressure fluid F to bypass the upstream bristle arrangement 44 and a properly load the downstream bristle arrangement against a back plate 48.

Abstract: Disclosed is a structural frame for a gas turbine engine comprising an integral fluid reservoir and air/fluid heat exchanger. A central hub includes a reservoir for storing a fluid and an outer rim circumscribes the hub. A heat exchanger is fluidly coupled to the reservoir and is in simultaneous communication with the fluid and an air stream.

Abstract: Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.

Abstract: Provided are systems 10 and methods 100 for determining both the location and angular orientation of holes 12 with openings 14 on a surface 16 of an article 18 that are at least partially obstructed. In a method of the present invention, a scanning system 10 that includes a laser spot projector 40, a laser spot sensor 42, a memory device 48 and a processor 50 is provided. A laser beam 44 is projected onto the surface 16 of the article 18 in a region 24 containing at least one hole 12 and the spot sensor receives light reflections 46. A series of points 52 representing the scanned region is stored as a point cloud 54 in the memory device 48. The point cloud 54 is then manipulated to calculate the location and angular orientation of each hole in the region in relation to one or more pre-existing, article datums 22.

Abstract: A seal for restricting leakage of a fluid from a first chamber, through a gap between two components, to a second chamber is provided. A slot is formed in each of the two components. The slots face one another and are open to the gap. Each slot contains a longitudinal axis, an upstream surface proximate the first chamber and a downstream surface proximate the-second chamber. Disposed in the slots and spanning the gap is a bridging assembly comprising first and second bridging elements. Each bridging element contains a sectional profile, transverse to the longitudinal slot axis, that is wave shaped. The bridging elements further contain a crest portion disposed between two trough portions with the crest portions nesting together. When installed, the trough portions are disposed in the slots and the crest portions are disposed in the gap.

Abstract: Disclosed are various embodiments of an EDM electrode dressing template comprising a body made of an electrically conductive material. Bonded to the body is a pad with an electrically conductive material with hardness greater than the body. An electrode with an eroded end is positioned proximate the pad and a DC current pulses between the eroded end and the pad. After a period of time, the eroded end is shaped into a dressed tip. Since the pad is less susceptible to spark erosion than the body, the electrode is more consistently dressed and the template is replaced less frequently.

Abstract: A tool for securing a clamp, such as a P clamp, to a mounting location, comprising: a first jaw; a second jaw; and an actuator to move the first jaw relative to the second jaw. The first jaw includes a retainer for a fastener. The method of attaching the clamp to the mounting location includes the steps of: placing a first fastener in the retainer; locating the clamp between the jaws; manipulating the actuator to tighten the clamp; and securing a second fastener to the first fastener.

Abstract: A rotor blade is provided that includes a root, a hollow airfoil, and a conduit disposed within the root. The hollow airfoil has a cavity defined by a suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage configuration is disposed within the cavity. The configuration includes a first radial passage, a second radial passage, a rib disposed between and separating the first radial passage and second radial passage, a plurality of crossover apertures disposed within the rib, and a plurality of trip strips disposed within the second radial passage. The trip strips are attached to an interior surface of one or both of the pressure side wall and the suction side wall. The trip strips are disposed within the first radial passage at an angle ? that is skewed relative to a cooling airflow direction within the first radial passage, and positioned such that each of the plurality of trip strips converges toward the rib.

Abstract: A rotor blade and a method for cooling a rotor blade are provided. The rotor blade includes a root and a hollow airfoil having a cavity defined by suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage configuration is disposed within the cavity. The configuration includes a serpentine passage having at least three radial segments connected to one another, an axially extending passage disposed between the tip and the serpentine passage, at least one aperture extending between the last radial segment and the axially extending passage, and one or more sink apertures disposed within one of the suction side wall or the pressure side wall of the last radial segment of the serpentine passage. At least one conduit is disposed within the root. The conduit is operable to permit airflow through the root and into the internal passage configuration.

Abstract: An anti-rotation lock for preventing circumferential movement of a stator segment in relation to a split case to which it is mounted is disclosed. A racetrack shaped pocket, disposed within the case and proximate the stator segment, is suitably sized to receive a lug and a spring pin. The lug is received in the pocket and protrudes radially inward from the case and is engagable by the stator segment, thus preventing circumferential movement with respect to the case. The spring pin is received adjacent to the lug and compressively retains the lug in the pocket.

Abstract: A gas turbine engine having a turbine section cooling system is disclosed which is able to cool the turbine section of the gas turbine engine to an optimal operating temperature range, while at the same time not substantially degrading engine performance. The disclosure provides a number of different structures for doing so including the provision of turning foils, turning holes, and turning grooves within a secondary air flow cavity which turns or directs cooling and parasitic leakage air into the turbine section in a direction in substantial alignment with a gas flow path through the turbine section.

Abstract: Provided is an aerodynamic profile for use in gas turbine airfoil and a turbine blade comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches. The R values are measured perpendicular to a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.

Abstract: Provided is an airfoil insert for discharging an increased volume of cooling air. The insert comprises a perforated, tubular-shaped body with a first end for introducing the cooling air. A second end located opposite the first end and discharges an increased volume of the cooling air for use in cooling inboard components. The second end approximates a castellated wall and comprises one or more tabs spaced about the periphery. Alternating between tabs are notches in the body for discharging the cooling air. Covers may be joined to opposing tabs by bridging across the second end, or opposing tabs themselves may be joined together by bridging across the second end.

Abstract: A rotor blade is provided having a hollow airfoil with a cavity and an attached root. The root has a leading edge conduit, at least one mid-body conduit, and a trailing edge conduit. Each conduit has a centerline. The leading edge conduit includes an inlet having a forward side, a suction side, and a pressure side that diverge from the centerline of the leading edge conduit, and an aft side. Each of the mid-body conduits includes an inlet having a suction side and a pressure side that diverge from the centerline of the mid-body conduit, and an aft side and a forward side. The trailing edge conduit includes an inlet having a suction side and a pressure side that diverge from the centerline of the trailing edge conduit. The trailing edge conduit inlet further includes a forward side and an aft side.

Abstract: A hole-drilling guide for directing a flexible hole-drilling instrument includes; a body made of an electrically insulating material, at least one inlet aperture penetrating a face of the body, at least one exit aperture penetrating a face of the body and a hollow, nonlinear raceway linking the inlet and exit apertures.