A method for testing platforms (e.g., live, virtual, and/or constructive platforms associated with autonomous aircraft systems and their component subsystems) in a live/virtual/constructive (LVC) environment. In embodiments, the method includes determining, via a testbed engine, the development state of a platform component under test. The method includes retrieving a test to be executed, the test including test conditions to be applied to the component. The method includes determining whether the component is enabled to respond to the test conditions. The method includes, if the component is enabled to respond to the test conditions, executing the test while monitoring the component to detect a first output response and a second output response. The method includes identifying, via the testbed engine, at least one change in the development state of the component by comparing the first and second output responses.

The gas turbine engine can have a first and second rotary components structurally joined to one another via a connector, a first spigot fit between the connector and the first rotary component, the first spigot fit forming an interference fit at a first operating condition and forming a gap at a second operating condition, a second spigot fit between the connector and the first rotary component, the second spigot fit forming an interference fit at the second operating condition and forming a gap at the first operating condition, the gas turbine engine being further configured to form a radial interference fit between the connector and the second rotary component in both the first and second operating conditions.

A gas turbine engine includes an engine casing and a combustor liner enclosed within the engine casing. The engine includes a flow path for cooling the combustor liner with an air stream and located in between the engine casing and the combustor liner. The engine includes an inspection port penetrating the engine casing, the flow path, and the combustor liner and wherein the inspection port is positioned to allow an operator to view sacrificed zones of a sacrificial support structure.

The invention relates to a method for producing an ice projectile. The method comprises the steps of: —providing a quantity of water; providing a quantity of alcohol corresponding to at least 5 wt.-% of the quantity of water; mixing the quantity of water with the quantity of alcohol; transferring the mixture to means for cooling and solidifying the mixture to form a piece of ice; cooling the mixture in the cooling and solidifying means to a mixture-solidification temperature in order to produce at least one piece of ice; and launching the or each piece of ice at a target using launching means.

A scanning fixture for use in moving a tool across a surface of an object is arranged to be attached to the object and comprises: a carriage arranged to have the tool connected thereto; and a frame arranged to be mounted on the object and to have the carriage mounted thereon. The frame comprises: a first mount arranged to be mounted on the object; a second mount arranged to be mounted on the object; a carriage support arranged to extend between the first and second mounts, across a surface of the object, and to have the carriage moveably connected thereto. The carriage support is a modular carriage support, comprising a plurality of modules rotatably mounted on an elongate member. The plurality of modules together form a path along which the carriage can move. The tool may be a probe for use in inspecting the object. The fixture may comprise one or more encoders arranged to generate position data for the carriage.

A device for measuring the characteristics of an air flow in an annular passage of a turbo-machine. The device includes a rod which extends along a first axis and carries means for measuring air flow characteristics. The rod also sealingly engages and slides in a first tubular part extended by a second tubular part. The second tubular part sealingly passes along the first axis through a slider mounted in a slide for sliding along a second axis perpendicular to the first axis. The rod engages the second tubular part with an annular clearance.

In a method for determining an equivalent modal unbalance for the first bending characteristic form of a shaft-elastic rotor, which unbalance is to be compensated for, a rotor model is created describing the geometric shape and material properties of the shaft-elastic rotor. The magnitude of compliance of the rotor model is calculated at a measurement point and at the center of gravity of the rotor at an assumed speed. The shaft-elastic rotor is received in a rotatable bearing and accelerated to the assumed speed which is below its first critical speed. Subsequently, the magnitude of outward deflection at the measurement point of the shaft-elastic rotor rotating at the assumed speed can be measured. The equivalent modal unbalance for the first bending characteristic form of the shaft-elastic rotor, which unbalance is to be compensated for, can be calculated from the magnitudes of the calculated compliance and the measured outward deflection.

A system for calibrating the trip speed of a mechanical overspeed sensing device by manipulating the compression of a spring of the overspeed sensing device. The system may include a rotatable annular mount, on which the mechanical overspeed sensing device is mounted and a trip sensor. The system may drive a rotational movement of the annular mount with a varying speed over time during a test run. The system may designate a rotational speed of the annular device at which the trip sensor is struck by the mechanical overspeed sensing device as a measure trip speed. The measured trip speeds may be determined for various compressions of the spring of an exemplary mechanical overspeed sensing device and based on a desired tripping speed received from a user, a compression value of the spring may be selected for which the closest measured tripping speed to the desired tripping speed is obtained.

A forced air convection apparatus and method for cooling turbomachines is provided. The forced air convection apparatus for cooling a turbomachine, the apparatus comprising: a duct assembly having one or more outlets which are removably joinable to one or more corresponding air intakes of the turbomachine, and further having one or more inlets which are removably joinable to one or more corresponding exhausts of the turbomachine to enable closed loop recirculatory airflow through the turbomachine and the duct assembly and back to the turbomachine; and an air handling system having a blower arranged to blow air from the one or more inlets of the duct assembly to the one or more outlets of the duct assembly, and further having a heat exchanger configured to cool the air flowing through the duct assembly.

An airfoil assembly for a turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, the airfoil extending axially between a leading edge and a trailing edge to define a chord-wise direction and also extending radially between a root and a tip to define a span-wise direction. An aperture and at least one slot can define at least a portion of a release plane extending through the outer wall.