Abstract: In some embodiments, a computer system facilitates depth conflict mitigation for a virtual object that is in contact with one or more physical objects in a three-dimensional environment by changing visual properties of one or more portions of the virtual object. In some embodiments, a computer system facilitates depth conflict mitigation for a virtual object that is in contact with one or more physical objects in a three-dimensional environment by displaying the virtual object in a virtual environment within the three-dimensional environment. In some embodiments, a computer system facilitates depth conflict mitigation for a virtual object that is in contact with one or more physical objects in a three-dimensional environment by variably changing visual properties of one or more portions of the virtual object and/or by variably displaying the virtual object in a virtual environment based on one or more characteristics of the depth conflict.

Abstract: A method of repairing an integrally bladed rotor (IBR) may comprise: performing a vibratory analysis of a rotor module including a first inspected IBR with a potential repair shape for the IBR; determining an undesirable vibratory characteristic of a second inspected IBR in the rotor module; iterating the potential repair shape for the first IBR to eliminate the undesirable vibratory characteristic of the second inspected IBR; and repairing the first IBR with a selected repair shape based on determining the potential repair shape eliminates the undesirable vibratory characteristic.

Abstract: A method of repairing an integrally bladed rotor (IBR) may comprise: performing a vibratory analysis of a rotor module including a first inspected IBR with a potential repair shape for the IBR; determining an undesirable vibratory characteristic of a second inspected IBR in the rotor module; iterating the potential repair shape for the first IBR to eliminate the undesirable vibratory characteristic of the second inspected IBR; and repairing the first IBR with a selected repair shape based on determining the potential repair shape eliminates the undesirable vibratory characteristic.

Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: receiving, via the processor, one of a point cloud and a three-dimensional model for an inspected integrally bladed rotor (IBR) and a defect including a defect shape, a defect size, and a defect location; generating, via the processor, a first finite element model and a second finite element model based on the point cloud or the three-dimensional model, the first finite element model and the second finite element model; performing, via the processor, a structural analysis simulation with the first finite element model; performing, via the processor an aerodynamic analysis simulation with the second finite element model; iterating, via the processor, a repaired defect shape based on simulation data from the aerodynamic analysis simulation and the structural analysis simulation; an

Abstract: A method of projecting effects of blade modes onto rotor modes can comprise receiving, via a processor, a modal domain for an ideal bladed rotor and each blade of an inspected bladed rotor; determining, via the processor, whether a mode in the modal domain is at least one of an isolated mode and within a cluster of modes; analyzing, via the processor, the mode individually in response to the mode being isolated; and analyze, via the processor, the cluster of modes together in response to the mode being within the cluster of modes.

Abstract: A process for scheduling engine inspection for a gas turbine engine includes computing an expected damage increment based on aircraft usage data of a single flight, computing a cumulative expected damage by summing the expected damage increment with a total set of historical expected damage increments since a previous maintenance, and determining an aggregate risk of failure based on the computed cumulative expected damage. A manual inspection is signaled when the aggregate risk of failure exceeds an acceptable risk threshold.

Abstract: A process for repairing an aircraft engine component includes receiving a plurality of component measurements of a damaged component, comparing the plurality of component measurements of the damaged component to a finite element model of an ideal component, generating a finite element model of the damaged component based at least partially on the comparison, determining a corrective material removal operation based at least in part on the finite element model of the damaged component, and removing material from the damaged component according to the corrective material removal operation, thereby creating a repaired component.

Abstract: A process for repairing an aircraft engine component includes receiving a plurality of component measurements of a damaged component, comparing the plurality of component measurements of the damaged component to a finite element model of an ideal component, generating a finite element model of the damaged component based at least partially on the comparison, determining a corrective material removal operation based at least in part on the finite element model of the damaged component, and removing material from the damaged component according to the corrective material removal operation, thereby creating a repaired component.

Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.

Abstract: A heater having a combustion chamber. The heater includes a hopper and a chute extending from an outlet of the hopper to the combustion chamber. The heater includes a chute extending from the hopper to the combustion chamber, a screw extending through the chute into the hopper, and a drive connected to the screw for turning the screw in a direction in which the flight would, but for downward forces, lift the fuel. The heater has a vane rotatably attached to the screw that rotates downward along the screw in absence of upward forces counteracting gravity. The vane is cambered to produce upward forces when turning with the screw beneath an upper surface of the fuel. The vane is biased toward the upper surface of the fuel to level the upper surface of the fuel and prevent the fuel from rat holing and arching.

Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.

Abstract: A heater having a combustion chamber. The heater includes a hopper and a chute extending from an outlet of the hopper to the combustion chamber. The heater includes a chute extending from the hopper to the combustion chamber, a screw extending through the chute into the hopper, and a drive connected to the screw for turning the screw in a direction in which the flight would, but for downward forces, lift the fuel. The heater has a vane rotatably attached to the screw that rotates downward along the screw in absence of upward forces counteracting gravity. The vane is cambered to produce upward forces when turning with the screw beneath an upper surface of the fuel. The vane is biased toward the upper surface of the fuel to level the upper surface of the fuel and prevent the fuel from rat holing and arching.

Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The second fan nacelle section being axially movable relative the first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, the second fan nacelle section includes at least one cowl with an inner portion, an outer portion and a multiple of stiffeners therebetween to increase a flutter margin.

Abstract: A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that includes a bearing assembly. A VAFN cowl is mounted to the second track slider.

Abstract: A nacelle assembly for a high-bypass gas turbine engine is disclosed and includes a variable area fan nozzle (VAFN) including at least one second fan nacelle section movable relative to the first fan nacelle section to modify an area of the bypass flow path. At least one stiffener is mounted between the first fan nacelle section and the second fan nacelle section. The stiffeners modify mode shapes and natural frequencies to substantially reduce or eliminate flutter within operating ranges that are produced by unsteady aerodynamic loads.

Abstract: A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that includes a bearing assembly. A VAFN cowl is mounted to the second track slider.

Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The second fan nacelle section being axially movable relative the first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, the second fan nacelle section includes at least one cowl with an inner portion, an outer portion and a multiple of stiffeners therebetween to increase a flutter margin.

Abstract: A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that is more closely controlled than the first interface. A VAFN cowl is mounted to the second track slider.

Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In one embodiment, contiguous cavities are formed around freestanding ends of the ribs to reduce the number of cavities required. The freestanding end of each rib is flared such that it has a larger width than the rest of the rib. The cavity extends continuously around the free, flared end of the rib.

Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In the present invention, the ribs are oriented biased to provide stiffness as needed in different sections of the fan blade with smooth transitions between regions. The result is a blade with good protection from a wide spectrum of external threats.