Abstract: Prior to dry-in of a building, constructing an outer frame within an external opening of the building by attaching a top piece to a top, attaching a first side piece to a first side, attaching a second side piece to a second side, and attaching a bottom piece to a bottom of the building opening. After constructing the outer frame within the external opening of the building, the method includes mounting glass to glass receiving surfaces of the top piece, the first side piece, the second side piece, and the bottom piece. After dry-in and interior wall finishing of the building, the method includes attaching a plurality of inner base caps to an interior of the outer frame. After dry-in and exterior wall finishing of the building, the method includes attaching a plurality of outer base caps to an exterior of the outer frame.

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Abstract: A case is provided for a gas turbine engine. The case includes a wall defining a through-hole. The case also includes first and second pockets adjacent to, and on opposite sides, of the through hole. A method of reducing stress in a case of a gas turbine engine is also provided that includes reducing stress about a through-hole by providing a concavity on each side of the through-hole.

Abstract: Aspects of the disclosure are directed to a system for an engine having an axial centerline, comprising: a diffuser case, a turbine case, and a turbine vane support, where the diffuser case and the turbine case are coupled to one another via a substantially radially oriented flange, where the turbine vane support includes a heat shield for the flange, and where the turbine vane support includes a radially outward projecting tab that couples to the turbine case via a radial interference fit.

Abstract: A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.

Abstract: A flange heat shield is provided. The flange heat shield may comprise an annular body having a forward end opposite an aft end. The forward end of the flange heat shield may comprise a radial snap configured to interface with an inner surface of an engine case. The inner surface of the engine case may comprise an airflow ramp forward of the radial snap. The aft end of the flange heat shield may comprise a plurality of notches defining voids on the aft end. The aft end of the flange heat shield may also comprise mounting tabs configured to couple the flange heat shield to the engine case.

Abstract: Methods and systems are disclosed for generating more random data or ensuring more random data than provided by single sources. Entropy is gathered among multiple random or pseudo-random sources at different frequencies. The entropy is pushed, pulled, or otherwise presented to a pseudo-random number generator when there is enough entropy. The determination of enough entropy can be through a modified Hamming distance. The frequencies of polling for entropy from the entropy sources can be jittered by a random amount.

Abstract: A vertically and laterally adjustable frame for a mine ventilation structure having two or more pairs of adjustable height support columns, and a plurality of adjustable length support beams, each support beam mounted to and spanning between a pair of the support columns. A mine overcast and a method of assembling an overcast in an intersection within a mine are also provided, with the overcast including a vertically and laterally adjustable frame, and a plurality of side and ceiling panels mounted to the frame.

Abstract: A temperature control system for controlling a water heater to adjust the temperature of water in a water storage tank, the control system including a first temperature sensor coupled to the storage tank and configured to measure a first temperature of the water at a first location within the storage tank, a second temperature sensor coupled to the storage tank and configured to measure a second temperature of the water at a second location within the storage tank, and a controller coupled to the first and second temperature sensors and configured to turn ON the water heater when the measured first and second temperatures are below a first setpoint temperature, and to turn OFF the water heater when the measured first and second temperatures are at or above a second setpoint temperature.

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Abstract: A pre-diffuser of an inner diffuser case of a gas turbine engine may comprise an annular outer wall and an annular inner wall radially inside of the annular outer wall to define a passage for primary airflow therebetween. The pre-diffuser may further comprise at least one strut extending radially between the annular inner wall and the annular outer wall and at least one aperture formed in the strut that extends radially through the strut, the annular inner wall, and the annular outer wall. The pre-diffuser may further comprise at least one hollow cavity formed in the strut, and the hollow cavity may be separate from the aperture.

Abstract: An inner casing for a diffuser-combustor assembly of a gas turbine engine is disclosed. The inner casing may include an outer-ring, an inner-ring circumscribed by the outer-ring, and a strut having a body extending between the inner-ring and the outer-ring. In addition, the inner casing may include a reinforcing-pad.

Abstract: A welding power supply having an adjustable cover is disclosed. The welding power supply includes an enclosure housing an engine, a porous radiator thermally coupled to the engine, and a fan configured to propel air through the radiator. A ventilation opening is in fluid communication with the fan and radiator. The fan is configured to move heated air along an air path and out of the ventilation opening. The air may be heated by the welding power supply components (e.g. engine, radiator, charge air cooler, oil cooler, compressor, generator, weld circuitry, and/or other components), for example. The adjustable cover is positioned over the ventilation when in a fully closed and/or partially open/closed position. The adjustable cover may be moved between fully closed, partially open/closed, and fully open positions. The amount of air that is allowed to exit the enclosure, and the amount of air that is recirculated within the enclosure, may be altered by adjusting the position of the adjustable cover.

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Abstract: Methods and systems are disclosed for generating more random data or ensuring more random data than provided by single sources. Entropy is gathered among multiple random or pseudo-random sources at different frequencies. The entropy is pushed, pulled, or otherwise presented to a pseudo-random number generator when there is enough entropy. The determination of enough entropy can be through a modified Hamming distance. The frequencies of polling for entropy from the entropy sources can be jittered by a random amount.

Abstract: A pre-diffuser and exit guide vane (EGV) system for a gas turbine engine includes an annular EGV assembly containing a number of guide vanes and having an annular opening bounded by a radially inner annular sealing surface at a first radius and a radially outer annular sealing surface at a second radius. First and second seals substantially matching the first and second radii respectively join the EGV assembly to an annular pre-diffuser having an annular opening bounded by radially inner and outer annular sealing surfaces at substantially the first and second radii. The seals seal the inner sealing surface of the EGV assembly to the inner sealing surface of the pre-diffuser and the second seal seals the outer sealing surface of the EGV assembly to the outer sealing surface of the pre-diffuser, such that the EGV assembly annular opening is in fluid communication with the annular opening of the pre-diffuser.

Abstract: Methods and systems are disclosed for generating more random data or ensuring more random data than provided by single sources. Entropy is gathered among multiple random or pseudo-random sources at different frequencies. The entropy is pushed, pulled, or otherwise presented to a pseudo-random number generator when there is enough entropy. The determination of enough entropy can be through a modified Hamming distance. The frequencies of polling for entropy from the entropy sources can be jittered by a random amount.

Abstract: A thermal valve for controlling a flow of fluid includes a housing having an inlet and an outlet configured to permit the flow of fluid through an interior of the housing, an actuator including heat-sensitive material configured to contract or expand based on a temperature of the fluid, a rod fixedly coupled to the housing and partially inside the actuator, the rod being configured to move relative to the actuator as the heat-sensitive material contracts or expands, a chamber inside the housing and fixedly coupled to the housing, the chamber being configured to accommodate the actuator, a first compressive resilient element configured to movably couple the actuator to the chamber, and a disc movably coupled to the chamber via a second compression element, and configured to permit flow of the fluid from the inlet to the outlet and to reduce flow of water from the outlet to the inlet.

Abstract: A hydrostatic seal and vibration damping apparatus for a gas turbine engine adapted to reduce vibrations during cold engine start-ups is disclosed. In one disclosed configuration, the vibration damping apparatus is comprised of a temperature sensitive control ring having a relatively high coefficient of thermal expansion adapted to expand quickly at relatively low temperatures to protect the hydrostatic seal during such gas turbine engine startups. At operational temperatures, the control ring is adapted to become separated from the hydrostatic sea.

Abstract: An outer diffuser case of a diffuser case assembly for use in a gas turbine engine may have a housing orientated about an engine axis, a forward flange projecting radially outward from the housing, a mid-flange spaced axially aft of the forward flange and projecting radially inward from the housing, and an aft flange projecting radially outward from the housing. The mid flange is spaced axially between the forward and aft flanges and is configured to detachably engage an inner diffuser case of the case assembly. The forward flange is configured to detachably engage a high pressure compressor and the aft flange is configured to detachably engage a high pressure turbine of the engine.