Abstract: An aircraft includes a gas turbine engine and an optically-based measurement system. The gas turbine engine is configured to ingest a first mass flow and to exhaust a second mass flow. The optically-based measurement system is configured to determine the first and second mass flows in response to performing an imaging process on the gas turbine engine.

Abstract: A method of determining flow speed in a low pressure environment. The method includes obtaining bi-directional acoustic data from a plurality of transducer pairs as a fluid moves relative to the plurality of transducer pairs. The method further includes measuring phase lags corresponding to the bi-directional acoustic data, and determining bi-directional flight times using the phase lags. Additionally, the method includes calculating a flow speed of the fluid corresponding to each transducer pair from the bi-directional flight times. The method includes correcting for at least one of temperature effects, pressure effects, and wake effects, using a system model. The method further includes generating a report including the flow speed of the fluid.

Abstract: A hook anchor for anchoring a fixation rod to a bone is disclosed. The hook anchor includes a hook body shaped in a curve of diminishing radius and a locking mechanism. The locking mechanism is to securely fix the hook anchor to the fixation rod. The curve of diminishing radius may be the shape of at least a portion of a Fibonacci curve. The bone can include at least one of a rib, a pelvis, and a vertebra. The hook body can be configured to engage with at least one of a spinous process a transverse process, and a pedicle of the vertebra.

Abstract: The invention relates to a method for estimating a dead zone at closing of a flap (P1) of a discharge valve (VBV1) of a turbomachine, in which the actual position of the actuator (V1) is measured for a setpoint closing signal of the flap (P1), a static angle is determined from the actual position, a closing dead zone is determined, corresponding to the fact that the joint (J1) is compressed so as to not let the primary flow pass through the orifice (O1) in the secondary flow, by the fact that the dead zone is equal to a reference dead zone, which has been predetermined on a reference turbomachine operating on the ground, to which the measured static angle has been added and from which a reference static angle, which has been predetermined on the reference turbomachine operating in flight, has been subtracted.

Abstract: An apparatus measuring thrust of an aircraft gas turbine engine includes a core shaft connecting a turbine and compressor, a fan and gearbox with a sun gear driven by the core shaft, a plurality of planet gears, an annulus gear mounted in a static structure, and a planet carrier driven by the fan via fan shaft. The apparatus includes a sensor to measure force applied by the annulus gear on the static structure and first and second sensors to measure rotational speed of the core and fan shafts. A processor determines restoring torque on the annulus gear from measurement of force applied by the gear on the static structure, torque applied to the fan by the planet carrier using rotational speeds of core and fan shafts and restoring torque on the annulus gear, and thrust of the fan from torque applied to the fan and the fan's rotational speed.

Abstract: A method of calibrating an engine core of a gas turbine engine, wherein the engine core includes a turbine, combustion equipment, a compressor, and a core shaft connecting the turbine to the compressor, the core shaft arranged to drive a propulsive fan of the gas turbine engine, the method including: providing a resistance load on the core shaft, the resistance load arranged to replicate the load of a propulsive fan; driving the engine core; measuring a performance parameter or the engine core; measuring a thrust generated by the engine core; and determining power rating data of the engine core, providing a correlation between the performance parameter and the thrust.

Abstract: An example test fixture includes a lower frame having a first rocker rail and a second rocker rail coupled to the first rocker rail, wherein each of the first rocker rail and the second rocker rail has a respective curved surface that allows the lower frame to tilt about a first axis; a rotatable base coupled to the lower frame; an upper frame having a mounting system configured to couple a transmission of an aircraft to the upper frame; a support frame that couples the upper frame to the rotatable base; and a rotary actuator configured to rotate the rotatable base, the support frame, and the upper frame about a second axis perpendicular to the first axis.

Abstract: A system for total pressure measurement of a propulsive stream through a turbine engine, the system incorporates a track circumferentially mounted on a fan exhaust nozzle proximate a trailing edge. A carriage is mounted in the track and adapted for translation through a range of azimuthal angles relative to an engine centerline. A pressure measurement rake extends from the carriage and has a probe mount protruding radially inward into a fan flow duct with a plurality of pressure probes mounted to a leading edge of the probe mount.

Abstract: An object of the present invention is to provide a thrust testing device for a linear actuator, which can test thrust more accurately and greatly reduce the working intensity of test operators.

Abstract: A system and method are provided for detecting an impending stall or surge in a radial compressor. The system and method may include a plurality of detection devices configured to detect a transition of a low momentum zone of a gas flow through the diffuser from a first position adjacent a shroud wall of the diffuser to a second position adjacent a hub wall of the diffuser. The system and method may also include a control system electrically coupled to the plurality of detection devices and configured to receive a plurality of information signals. Each information signal may be transmitted by a respective one of the plurality of detection devices and may correlate to a location of the low momentum zone. The control system may be configured to process the plurality of information signals and detect the impending stall or surge based on the location of the low momentum zone.

Abstract: A compliant mounting adapter for mounting an engine to a test stand includes: a body having: a first mounting interface configured for being coupled to the test stand; a second mounting interface configured for being coupled to the engine, the second mounting interface spaced-away from the first mounting interface; and a spanning element interconnecting the first and second mounting interfaces. The body is sufficiently flexible so as to permit movement relative movement of the two mounting interfaces, in response to forces generated by engine operation, in at least two degrees of freedom, and has a predetermined stiffness in each of the at least two degrees of freedom, with the predetermined stiffness of each degree of freedom being substantially independent from the stiffness of the other degrees of freedom.

Abstract: In some aspects, techniques and systems for modeling fluid flow are described. Pressure gradient values for respective nodes of a one-dimensional flow model are computed. The nodes represent locations of fluid flow along a flow path, and the pressure gradient values are computed based on an approximation of the flow velocity at a point on the flow path. A pressure drop between two opposite ends of the flow path is calculated based on the pressure gradient values. An improved approximation of the flow velocity for the point on the flow path is calculated based on a difference between the calculated pressure drop and a pressure drop boundary condition.

Abstract: An improved system, apparatus and method for estimating thrust from an engine, and more specifically, a system for estimating thrust from strain gauge and accelerometer measurements. At least one strain gauge is mounted on an engine mount to measure strain to estimate a constant velocity or steady-state portion of thrust. At least one accelerometer is mounted on the vehicle to measure acceleration to estimate a transient portion of thrust. Steady-state thrust estimation and transient thrust estimation are combined to estimate thrust from the engine. An algorithm provides steps for estimating thrust from strain gauge and accelerometer measurements.

Abstract: The invention relates to an apparatus comprising: a measuring head (10) having a slot (18) for receiving a measurement cell (26) and means (28) for emitting electromagnetic radiation, and means (32, 36) for detecting radiation from said emission means (28) after it has passed through the measurement cell (26); means (16) for translatably driving and means (12, 14) for translatably guiding, allowing the substantially vertical longitudinal movement of the measurement head (10); at least two recesses (44) each intended for receiving a measurement cell (26) and arranged one above the other in a longitudinal direction, the recesses (44) as well as the driving means (16) and the guiding means (12, 14) being configured such that during the translational movement of the measurement head (10) along the nominal travel thereof each recess is placed inside the slot (18) of the measurement head (10).

Abstract: A system and method of monitoring oil consumption in a gas turbine engine system are provided. When the gas turbine engine is not running the reservoir oil level, reservoir oil temperature, and reservoir attitude are sensed. The current gas turbine engine system oil quantity is determined based on at least the sensed reservoir oil level, the sensed reservoir oil temperature, and the sensed reservoir attitude. When a predetermined event has occurred, an average gas turbine engine system oil quantity is automatically calculated. The gas turbine engine system oil consumption rate is determined from a plurality of the average oil quantities.

Abstract: A method for providing an indication of thrust available from a gas turbine engine, the method comprises measuring fan aerodynamic speed to produce an actual fan aerodynamic speed measurement, determining a difference between the actual fan aerodynamic speed measurement and an expected fan aerodynamic speed measurement, and if the difference is less than a predetermined threshold value, indicating that sufficient thrust is available.