Abstract: Provided is a cooler and an engine testing apparatus having the same. The cooler includes a guide unit configured to make a gas flow, a liquid supply unit arranged in the guide unit to supply a liquid into the guide unit, a liquid column guide unit connected to the guide unit and having a column of the liquid, and a liquid storage unit connected to the liquid column guide unit and storing the liquid.

Abstract: Provided are a normal fault simulation experiment device with an adjustable angle and an adjustable fracture initiation position and a method of using the same, which relate to the technical field of normal fault simulation experiments. The device includes a base, a column, a baffle plate, a hydraulic lifting apparatus, a lower angle adjusting apparatus, a push rod apparatus, an upper loading apparatus, an upper angle adjusting apparatus, a front baffle plate and a transparent side plate. The hydraulic lifting apparatus and the lower angle adjusting apparatus are disposed below an experimental body, the upper loading apparatus and the upper angle adjusting apparatus are disposed above the experimental body, the transparent side plate is disposed on a rear side surface of the experimental body, and a plurality of strip-shaped front baffle plates are disposed on a front side surface of the experimental body.

Abstract: A system and method of non-intrusive thrust measurement of a gas turbine engine. The system comprises a transmitter disposed at a boundary of fluid flow and at least one receiver adapted to receive transmissions from the transmitter. A processor is coupled to the receivers to determine a parameter from a characteristic of the transmission at the receiver suite and adapted to determine a thrust parameter from the parameter. A method for non-intrusively measuring engine thrust includes transmitting a wave across the exhaust plume, receiving the transmitted wave and determining a measurement parameter of the exhaust plume based on a characteristic of the received wave, and comparing the measurement parameter to a reference parameter and determining the thrust based on the comparison.

Abstract: Systems and methods for controlling a fluid based system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states, the dynamic states input to an open loop model based on the model operating mode, wherein the open loop model generates current state derivatives, solver state errors, synthesized parameters as a function of the dynamic states and a model input vector. A constraint on the state derivatives and solver state errors is based on a series, of utilities that are based on mathematical abstractions of physical laws that govern behavior of the component. The model processor may include an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters.

Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring an actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Abstract: Commanding GTs to base load level based upon measured ambient condition for each GT; commanding each GT to adjust a power output to match scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and an emissions scale factor, wherein the nominal emissions value at the ambient condition and the emissions scale factor are stored in a pre-existing emissions model for the GT.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: modelling each GT in the set of GTs at a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring an actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and a nominal emissions value at the ambient condition.

Abstract: Systems, methods and apparatus for monitoring rub detection in a machine are provided. An electrical signal may be provided for transmission to and into a component of the machine. A capacitance associated with the electrical signal in the component may be monitored. Based at least in part upon a determined change in the monitored capacitance, a potential rub condition for the component of the machine.

Abstract: A method for monitoring the health of a compressor of a gas turbine is disclosed. The method includes receiving a plurality of turbine data points, wherein the plurality of turbine data points may include one or more operating parameters, at least one of a computer discharge temperature (CTD), and one or more performance parameters. The plurality of turbine data points may be categorized based on the one or more operating parameters. A statistical variability measure of at least one of the CTD and the one or more performance parameters may be computed for each of the plurality of bands. An alarm indicator may be computed based on the at least one statistical variability measure. The method may also include combining two or more of the operating parameters, the CTD and the performance parameters using sensor fusion techniques. The alarm indicator may be computed based on the combined parameters.

Abstract: A test bench for a reaction engine including a nozzle having a divergent. The bench includes a mechanism for holding the divergent in position, capable of holding the divergent so that its axis is vertical, and capable of interacting with a downstream portion of the divergent located in the downstream half thereof to limit distortion and/or displacement of this downstream portion. The test bench enables the divergent to remain undamaged even if lateral forces are applied to it during testing.

Abstract: An apparatus and method for inducing waves within a container arranged to permit a through-flow of fluid flowing generally from an inlet of the container to an exit of the container, wherein the container has wave inducing means located at the exit of the container, the wave inducing means being operable to vary the area of the exit thereby inducing waves within the container. The apparatus may form part of a combustor test rig.

Abstract: A turbopump for a rocket engine includes a rotor shaft with a turbine connected to drive the rotor and a centrifugal impeller connected to be driven by the rotor. An electromagnetic powered motor is formed as part of the turbopump and is powered to drive the rotor at a low speed in order to test for an amount of torque required to drive the rotor at the low speed. A load cell is connected to the motor that rotates the rotor shaft. From the use of a load cell the amount of torque required to rotate the rotor can be determined and compared to a known value in order to determine if the turbopump is damaged and requires repairs.

Abstract: The fundamental idea of the invention consists of the construction of the test device from a stationary inner basic structure (1, 7 to 11) that juts out from the wall of the test bench and houses the drive shaft (13) for the fan to be tested, from mobile, interchangeable external housing modules (18 to 24) which can be aligned in relation to one another by means of connected optical elements (32, 33), from interchangeable fittings (41 to 44, 48) for conducting air and noise reduction, in addition to interchangeable measuring devices (38 to 40) that are connected to a modular telemetry unit for determining performance data and aerodynamic and acoustic conditions required by the fan and the fittings.

Abstract: Apparatus and methods for testing a turbomachine, with the apparatus including a loading device housing, a disk, and a non-contacting seal. The loading device housing has an inner surface and a fluid inlet configured to receive a pressurized gas. The disk is located outside of a turbomachine housing in which the turbomachine is disposed and is coupled to a shaft of the turbomachine, proximal an axial end of the shaft. The disk is received in the loading device housing and is axially moveable in the loading device housing while the shaft is rotating. The non-contacting seal is disposed between the inner surface and the disk.

Abstract: Systems, methods and apparatus for monitoring rub detection in a machine are provided. An alternating current voltage signal may be transmitted or communicated to at least one component of the machine. The transmitted signal may be monitored in the at least one component and at least one characteristic associated with the monitored signal may be compared to an expected value for the at least one characteristic. Based at least in part on the comparison, a rub condition or potential rub condition may be identified between the at least one component and another component of the machine.

Abstract: The present invention relates to a turbofan propulsion simulator means, in particular for a turbofan of an aircraft or spacecraft, wherein the turbofan propulsion simulator means comprises a modular configuration, wherein the turbofan propulsion simulator means comprises a module, wherein the module is a turbine means to drive the turbofan of the turbofan propulsion simulator means, wherein the turbine means can be coupled with at least two fan means, characterized in that, the at least two fan means to be connected with the turbofan propulsion simulator means comprises almost or essentially the same mass and/or almost or essentially the same barycentre.

Abstract: The fundamental idea of the invention consists of the construction of the test device from a stationary inner basic structure (1, 7 to 11) that juts out from the wall of the test bench and houses the drive shaft (13) for the fan to be tested, from mobile, interchangeable external housing modules (18 to 24) which can be aligned in relation to one another by means of connected optical elements (32, 33), from interchangeable fittings (41 to 44, 48) for conducting air and noise reduction, in addition to interchangeable measuring devices (38 to 40) that are connected to a modular telemetry unit for determining performance data and aerodynamic and acoustic conditions required by the fan and the fittings.

Abstract: A turbofan test cell pre-dressing unit that enables the installation of the engine in a test cell in minimal time is provided.

Abstract: A method for determining the radial deformation of a blade in a turbine that includes: 1) taking an initial measurement of the blade with one or more proximity sensors disposed around the circumference of a stage of blades; 2) after the initial measurement, taking a second measurement of the blade with the one or more proximity sensors; 3) making a determination of the radial deformation of the blade by comparing the initial measurement to the second measurement. The initial measurement and the second measurement may be taken while the turbine is operating.

Abstract: A turbofan text cell pre-dressing unit that enables the installation of the engine in a text cell in minimal time is provided.

Abstract: An exhaust system for a combustion source is disclosed. The exhaust system may have a passageway connected to receive an exhaust flow from the combustion source, and a sensor disposed within the passageway. The sensor may generate a signal indicative of the concentration of a constituent in the exhaust flow. The exhaust system may also have a controller in communication with the sensor to receive the signal. The controller may be configured to selectively communicate a flow of calibration gas with the sensor during operation of the combustion source, and compare the signal received during the selective communication with a reference value. The controller may be further configured to adjust the sensor output in response to the comparison.

Abstract: A test apparatus can include a jet engine and a first frame configured to support the jet engine. In one example, the test apparatus can include means for flexibly coupling the jet engine to the first frame to allow movement between the jet engine and the first frame during a test procedure. In another example, a test apparatus is provided that is configured to support a jet engine. The test apparatus can include a frame, a flex member, a first attachment element and a second attachment element. In yet another example, a test apparatus can be provided with a frame, a flex member and a limiting element.

Abstract: A method of inspecting an internal feature of a gas turbine component includes removing a portion of the turbine component to expose the internal feature, treating the surfaces of the internal feature to provide the surfaces with a substantially uniform coloration, generating an electronic model of the internal feature, analyzing the electronic model generated with reference to a nominal electronic model, and providing an output based on the analysis of the electronic model generated.

Abstract: A degradation monitoring system including: a machine; a sensor affixed to the machine, the sensors measuring a operational parameters of the machine; a set of filters receptive of information about the machine from the sensors and the filters responsively generate status signals; and comparators for comparing the status signals to stored signals, wherein the comparators indicate at least one of a presence of degradation of the machine, or a cause of degradation of the machine.

Abstract: The invention relates to a test bench for testing wind turbine equipment. The test bench comprises one or more load applying means directly or indirectly applying load to the equipment during said test and wherein the test bench comprises angle adjustment means for adjusting a test angle (A) of the equipment in relation to a horizontal plane. The invention further relates to methods for testing wind turbine equipment.

Abstract: Systems and methods for testing gas turbine engines are provided. In this regard, a representative system for testing a gas turbine engine having an inlet includes an inflatable seal having an interior chamber operative to receive pressurized gas such that the seal inflates to engage circumferentially about the exterior of an inlet of a gas turbine engine.

Abstract: A turbofan text cell pre-dressing unit that enables the installation of the engine in a text cell in minimal time is provided.