Embodiments of the disclosure relate to performance testing of a gas turbine. In one embodiment, a gas turbine performance testing system can include a server, a transducer system, a signal converter, and an automated gas chromatograph. The transducer system acquires one or more functional parameters of the gas turbine and the signal converter converts the functional parameters acquired by the transducer system to gas turbine operational data. The automated gas chromatograph automatically analyzes a test sample of a natural gas that is used to operate the gas turbine. The gas turbine operational data generated by the signal converter and the analysis information obtained from the test sample are provided to the server for propagating via a communication network, to a client computer where the gas turbine operational data and the analysis information can be used to obtain a gas turbine performance test result.

A modular egress seal assembly includes an annular plate with an axially extending aperture. A base plate is mountable to the annular plate. The base plate includes an aperture extending along the axis when said base plate is mounted to the annular plate thereby forming an axial passageway and a cover plate mountable to said annular plate.

A dynamic characteristic measurement device of the present invention includes magnetic force generators (1a, 1b, 2a, 2b) arranged on the back surface side of impellers (4, 5), the magnetic force generators that oscillate the impellers (4, 5) with magnetic force, an oscillation controller (12) that drives these magnetic force generators, and vibration sensors (13, 14) that detect vibration of a rotation shaft (3). The dynamic characteristic measurement device further includes an arithmetic device (16) that calculates a dynamic characteristic of a rotor (6) by implementing a frequency analysis and a mode analysis based on an oscillation signal from the oscillation controller (12) and a vibration signal from the vibration sensors (13, 14).

A gasket comprising at least one spacer and configured to prevent contact between a mount link of a turbine mount assembly and a turbine frame mount of an aircraft engine, which is a turbine engine in some embodiments, is provided. The at least one spacer includes a pin cutout to receive a turbine frame pawl pin of the engine mount and a pin groove that is expandable so as to enable the turbine frame pawl pin to pass through and into the pin cutout. The gasket may include a grommet for receiving a connecting ring that is coupled to a streamer grommet of a streamer. The streamer may act as an identifier for the gasket.

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.

The invention relates to an instrumented airfoil for mounting in a flow passage through a turbine, compressor, or module of a turbine engine. An instrumentation member is attached to an airfoil and includes information-obtaining means received in a cutout formed in the airfoil and projecting relative to the leading edge or the trailing edge. According to the invention, the instrumentation member also comprises a holder portion that is united with the information-obtaining means and that is attached to the cutout in such a manner that its surface is in alignment respectively with the suction side wall, the pressure side wall, and the leading edge or the trailing edge of the airfoil, the transitions between these respective surfaces not presenting any setbacks.

A dynamic characteristic measurement device of the present invention includes magnetic force generators (1a, 1b, 2a, 2b) that are arranged on the back side of impellers (4, 5), the magnetic force, an oscillation controller (12) that drives these magnetic force generators, and vibration sensors (13, 14) that detect vibration of a rotation shaft (3). The dynamic characteristic measurement device further includes an arithmetic device (16) that calculates a dynamic characteristic of a rotor (6) by implementing a frequency analysis and a mode analysis based on an oscillation signal from the oscillation controller (12) and a vibration signal from the vibration sensors (13, 14).

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 piezo-actuated valve, system, and method of exciting gas turbine turbomachinery are provided. The piezo-actuated valve includes a valve body extending along a first axis between a first and second end, the valve body defining a first opening near the first end, a second opening near the second end, a third opening centrally located on the valve body, and a valve cavity between the first opening and the second opening, a tube connected to the third opening and extending from the valve body along a second axis transverse to the first axis, a shuttle valve assembly slidably disposed within the valve body, wherein the shuttle valve slides between the first end to a first stopper and the second end to a second stopper, a first piezo injector having an injector tip extending through the first opening, and a second piezo injector having an injector tip extending through the second opening.

The invention is a pump testing system that allows users to test centrifugal pumps by the use of an artificially controlled load, measure flow of the pump under controlled operating parameters, and ensure that the pump meets industry standards of operation. The specific embodiment disclosed herein concerns centrifugal pumps used in fire fighting vehicles, but is not limited to such apparatus.