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.

This fin tip position measurement method comprises: a jig installation step for installing a jig having a flat measurement surface expanded in a circumferential direction and an axial direction to a tip of at least one among a plurality of seal fins that protrude in a radial direction with respect to an axial line, extend in the circumferential direction, and are arranged in a direction in which the axial line extends; a first measurement step for measuring a distance from the axial line to the measurement surface by scanning the measurement surface with a laser beam; and a first calculation step for calculating a distance from the axial line to the tip of the seal fin by adding a radial dimension of the jig to the distance to the measurement surface.

An aero damping measurement system is provided. The system includes a shroud defining a tunnel, a hub disposed within the tunnel, and a plurality of blades coupled to the hub. The blades may rotate about the hub. A gas pressure probe may have a tip extending to the tunnel to deliver a pressurized burst into the tunnel. An aeromechanical identification system may include a pressurized gas source, a valve in fluid communication with the pressurized gas source, and the gas pressure probe may be in fluid communication with the valve. The valve may control a flow of a pressurized gas from the pressurized gas source into the gas pressure probe. A pressure sensor may be coupled to the gas pressure probe and configured to measure a pressure within the gas pressure probe.

A test cell for an aircraft turbojet, wherein the test cell comprises a U-shaped configuration, with a passageway in the form of an elongated corridor, an inlet chimney, and an outlet chimney. The corridor includes a securing area with a securing arm for holding the turbojet during its test. The passageway furthermore reveals an upstream shutter and a downstream shutter, the two shutters including one pivoting flap or a series of pivoting flaps. In the event of a fire, the shutters close due to autonomous return means. Gravity allows the flap(s) to come down to the closed position and to confine the turbojet in order to rapidly stifle the fire.

An apparatus and a process for experimentally determining a heat transfer coefficient of a surface which includes a duct having an outer passage for water flow and an inner passage for air flow, the two passages separated by a thin wall membrane such that the water flow establishes a datum temperature on the thin wall membrane, and where air flowing through the second passage and over the thin wall membrane surface which can include heat transfer enhancements features will be heated by the features, and where the heat transfer coefficient can be determined from the surface temperature of the thin wall membrane and the change in temperature of the air flow. The duct with the thin wall membrane and heat transfer enhancement features is produced using a plastic or metallic additive manufacture process for low cost and quit turnaround time.

A test bench for turbomachine comprising: an installation zone for turbomachine; an active system for attenuating the noise emissions produced by the turbomachine. The active system includes an attenuation zone with emitters such as loudspeakers; a first microphone placed downstream of the turbomachine; and a second microphone placed downstream of the attenuation zone. The system reduces the turbomachine waves on the basis of the measurements from the first microphone and from the second microphone. The invention also proposes a method for attenuating the noise emissions from the turbomachine tested in the test bench.

A transportable gas turbine module including a baseplate supporting at least a gas turbine and a load drivingly connected to the gas turbine. The module further comprises a structure surrounding the gas turbine and the load and connected to the baseplate. The baseplate is designed such that it can support a heavy duty as turbine having a rated power of not less than 80 MW.

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.

A sensor system includes a sensor and a mast on which the sensor is mounted. The mast includes a core body and a shroud, wherein the shroud is provided about the core body, and the shroud is independently rotatable with respect to the core body under the influence, in use, of a fluid flow flowing past the shroud. The shroud is shaped so that, from at least one fluid flow direction, the shroud presents a different flow resistance in dependence upon the rotational orientation of the shroud. The rotational orientation of the shroud adjusts to reduce the flow resistance produced by the shroud to the fluid flow in response to the commencement of, or a change in the fluid flow direction to, one of the at least one fluid flow direction.

According to one aspect, a system for testing an engine includes a dynamometer coupled to the engine. The dynamometer is responsive to a control signal. The system further includes a controller that derives the control signal from an engine operation parameter.