Openshaw & Co

A system includes at least one component of a turbine section (22). The at least one component includes a fuel port (56) formed into a wall (111) of the at least one component, which is configured to inject fuel (52) into a chamber (94) of the turbine section. The at least one component also includes an inert gas port (57) formed into the wall upstream of the fuel port. The inert gas port is configured to inject an inert gas (54) to flow at least partially around the injected fuel in a buffer region (228) downstream from the fuel port. The presence of the inert gas in the buffer region may mitigate an ignition of the fuel near the surface of the wall downstream of the fuel port (e.g., flame anchoring) and/or help to lift the flame from the ignited fuel into the hot gas flow path.

A three-dimensional woven fabric (400, 500, 600, 700) for a composite airfoil (300) for a turbine engine (100) and methods of manufacturing such a fabric. The method includes forming, during weaving a plurality of reinforcing fiber tows (202), a spar section (410) of the woven fabric (400, 500, 600, 700). The method also includes forming, during weaving the plurality of reinforcing fiber tows (202), a first edge section (420, 440) integrally woven with the spar section (410) and extending in a second direction therefrom and forming, during weaving the plurality of reinforcing fiber tows (202), a second edge section (430, 450) integrally woven with the spar section (410) and extending in the second direction therefrom, the second edge section (430, 450) being positioned opposite the first edge section (420, 440) with a gap (462, 464) formed therebetween.

A HGP segment, such as a nozzle or shroud, for a GT system includes a body. A seal slot is defined in the face of side edge(s) of the body. Each seal slot has radial inner and outer walls, an inner sidewall between the radially inner and outer walls, and receives part of a sealing member extending between the seal slots of adjacent segments. Groove(s) are defined in one or both of the radial inner and outer walls of the seal slot and extend transverse to the slot. The groove(s) extend between the inner sidewall of the respective seal slot and the face of the respective side edge. A cooling passage is defined in the body and has an outlet defined in the inner sidewall within the at least one groove of the slot and an inlet in fluid communication with an inner coolant source defined in the body.

Ceramic matrix composite (CMC) fasteners and fastener systems, as well as methods of forming CMC fasteners and fastener systems, are provided. For example, a CMC fastener includes a CMC material forming a body portion having a first plurality of continuous fibers disposed in a first matrix, and a thread portion having a second plurality of continuous fibers disposed in a second matrix. The body portion has a body length in an axial direction. The thread portion is wound in a helix about the body portion such that the second plurality of continuous fibers wrap about the first plurality of continuous fibers along the axial direction. A CMC fastener system can include the CMC fastener and a CMC threaded nut.

An auto-visual data processing and insight generation system (100) for an aircraft engine includes a processor (720) and a memory (730) including processor executable instructions that cause the system to: perform video processing on image frames (501, 502), wherein the video processing includes selecting frames of the image frames as key frames based upon feature criteria including a change in pixels, a trend change in graphs, or a specified filter in the frames; perform an extraction of a feature included in the key frames, wherein the feature is extracted from a two-dimensional image to generate a three-dimensional model; identify an insight regarding the feature based on the three-dimensional model to predict performance of a component of the aircraft engine; verify an analytical or physical growth model based on the identified insight; and tune a design of the aircraft engine based on a verification of the analytical or physical growth model.

A combustor dome assembly (100, 150, 200) includes an inner liner (102, 206), an outer liner (104, 204), a dome (116, 152, 202) disposed on the inner liner (102, 206) and the outer liner (104, 204), and a cowl (112) connected to the inner liner (102, 206) and to the outer liner (104, 204), wherein the dome (116, 152, 202) is disconnected from the cowl (112) and defines an annular surface facing the cowl (112), the annular surface extending from an outer diameter (124) of the dome (116, 152, 202) to an inner diameter (126) of the dome (116, 152, 202).

Systems, apparatus, articles of manufacture, and methods are disclosed for reference markers for engine components. An example turbine engine (100) includes a substrate (118, 142) and a blade (164, 168, 172, 176, 706, 708) coupled to the substrate (118, 142), the blade (164, 168, 172, 176, 706, 708) including a first side having an external surface (214) and a reference marker (216, 218, 302, 402, 502, 602, 604, 606, 722, 724) provided on the external surface (214), the reference marker (216, 218, 302, 402, 502, 602, 604, 606, 722, 724) including spatial marking features having predetermined dimensions, the spatial marking features including (a) a first spatial marking feature at a first location on the external surface (214) and (b) a second spatial marking feature at a second location on the external surface (214) that is different than the first location, wherein a combination of the first spatial marking feature and the second spatial marking feature provide a first measure of the blade (164, 168, 172, 176, 706, 708) based on the predetermined dimensions.

A method (200) of imaging a turbine engine component (68) with a thermographic sensor, the turbine engine component (68) having a first surface (86) and a second surface (89) spaced from the first surface (86), and a plurality of holes with inlets (94, 94a, 94b, 94c, 94d) formed in the second surface (89) and outlets (95, 95a, 95b, 95c, 95d) formed in the first surface (86). The method (200) including flowing air (202) through the turbine engine component (68) and obtaining, during the flowing of air (202), thermographic data (204) when the turbine engine component (68) and a thermograph sensor (126) are relatively orientated such that a viewing plane (140) and a centerline (110a, 110b, 100c, 110d) of the outlet (95, 95a, 95b, 95c, 95d) or a centerline (108a, 108b, 108c, 108d) of a cooling hole (92, 100, 100a, 100b, 100c, 100d) form and angle (152) in a range from 60° to 120°. A subset of the thermographic data is determined (206) and a flow score for the cooling hole (92, 100, 100a, 100b, 100c, 100d) is calculated (208), wherein the thermographic data subset, the flow score, or the thermographic data subset and the flow score are visually displayed (210).

Provided to approximate the sensation of actually writing on a writing medium when using a pen-type input device. An information processing system is configured to detect the speed and direction of movement of the pen tip of a pen-type input device on an operable surface as contact parameters, to calculate a feedback level corresponding to the current time based on a predetermined equation using the velocity at the current time for a case of a non-reversed state where the direction is not reversed between a predetermined time previous to the current time and the current time, to calculate the feedback level based on an equation into which the velocity at the current time is substituted as zero for a case of a reversed state where the direction is reversed between the predetermined time previous to the current time and the current time, and to drive a haptic reproduction unit in the pen-type input device based on the calculated feedback level.

A control circuit (105, 106) accesses (201) first time-dispersed output (202) from a first circuit (101, 103) and identifies a potential fault for that first circuit as a function, at least in part, of circuit output intermittency. These teachings will accommodate a variety of such circuits including, for example, a sensor (103) (such as an aircraft-mounted jet turbine engine sensor) as well as non-sensor circuits (101) (such as a full authority digital engine control).