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Academic literature on the topic 'Turbomachinery measurements'

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Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Turbomachinery measurements"

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INOUE, Masahiro, and Masato FURUKAWA. "Measurements of Flow Field in Turbomachinery." Journal of the Society of Mechanical Engineers 89, no. 814 (1986): 1020–26. http://dx.doi.org/10.1299/jsmemag.89.814_1020.

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Choi, Jong-Soo. "Discharge flow measurements of a centrifugal turbomachinery." KSME Journal 8, no. 2 (June 1994): 152–60. http://dx.doi.org/10.1007/bf02953264.

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Camp, T. R., and H. W. Shin. "Turbulence Intensity and Length Scale Measurements in Multistage Compressors." Journal of Turbomachinery 117, no. 1 (January 1, 1995): 38–46. http://dx.doi.org/10.1115/1.2835642.

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This paper describes the measurement and processing of turbulence data from multistage low-speed compressors. Measurements were made at the same relative positions in three four-stage compressors, each having different levels of the design stage loading coefficient. A new method of data processing to calculate turbulence intensities and integral length scales is outlined. Using this method, integral length scales have been measured in turbomachinery flows for the first time. It is shown how the turbulence intensity and integral length scale vary with position in the blade passage, with changing flow coefficient and with the value of the design stage loading coefficient. The results have been used to specify representative inlet conditions for experimental rigs and to improve the application of CFD turbulence models to turbomachinery modeling.
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Kadambi, J. R., R. D. Quinn, and M. L. Adams. "Turbomachinery Blade Vibration and Dynamic Stress Measurements Utilizing Nonintrusive Techniques." Journal of Turbomachinery 111, no. 4 (October 1, 1989): 468–74. http://dx.doi.org/10.1115/1.3262295.

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The vibration of large turbomachinery blading is well known to be one of the most important design factors in modern turbomachinery. Typically, blade vibration is dominated by the unsteady flow phenomena and the interaction effects set up by vibration of blades within a high-velocity compressible fluid medium. This paper addresses the feasibility of developing an in-service noninterference measuring/monitoring system for steam turbine and gas turbine jet engine blade vibrations and stresses. The major purpose of such a measurement system is to provide a technically feasible, cost-effective means to isolate potential turbine and fan blade failures before they occur; thus minimizing costly machinery failure and risk of injury. The techniques that are examined include magnetic, inductive, optical, and laser and acoustic Doppler measurement methods. It appears likely that the most feasible and promising approach would include use of a few properly chosen measurement points on the blading in combination with use of advanced finite-element computational techniques and vibration modal methods. The modal analysis, performed experimentally and/or computationally, is especially useful in converting vibration measurements to the desired dynamic stresses.
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Behr, Thomas, Anestis I. Kalfas, and Reza S. Abhari. "A probabilistic uncertainty evaluation method for turbomachinery probe measurements." E3S Web of Conferences 345 (2022): 02001. http://dx.doi.org/10.1051/e3sconf/202234502001.

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The paper presents a probabilistic uncertainty evaluation method described in the Guide to the Expression of Uncertainty in Measurement (GUM) [1] and its application to the field of Turbomachinery probe measurement techniques. All sources of uncertainties contributing to a measurement result are expressed in terms of probability distributions. Consequently, the overall standard uncertainty of the result can be calculated using the Gaussian error propagation formula. The result of the uncertainty evaluation yields the most probable value of the measurand and describes its distribution in terms of standard or extended uncertainties. A pneumatic five-hole-probe measurement technique has been chosen to show the principle of the probabilistic uncertainty evaluation method. The complete signal chain including the probe calibration, the modeling and the application in the turbine has been included in the analysis. The overall uncertainties of the measured flow angles and flow total and static pressures are presented as a function of the flow Mach number. In addition, the contribution of the individual sources of uncertainty to the overall standard uncertainty is shown. Based on this break down of uncertainties optimization options of the measurement chain are suggested.
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Gossweiler, C. R., P. Kupferschmied, and G. Gyarmathy. "On Fast-Response Probes: Part 1—Technology, Calibration, and Application to Turbomachinery." Journal of Turbomachinery 117, no. 4 (October 1, 1995): 611–17. http://dx.doi.org/10.1115/1.2836579.

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A system for fast-response probe measurements in turbomachine flows has been developed and tested. The system has been designed for 40 kHz bandwidth and used with various in-house built probes accommodating up to four piezoresistive pressure transducers. The present generation of probes works accurately up to several bar pressure and 120°C temperature. The probes were found to be quite robust. The use of a miniature pressure transducer placed in the head of a probe showed that a precise packaging technique and a careful compensation of errors can considerably improve the accuracy of the pressure measurement. Methods for aerodynamic probe calibration and off-line data evaluation are briefly presented. These aimed, e.g., in the case of a four-hole probe, at measuring the velocity fluctuations as characterized by yaw, pitch, total pressure, and static pressure and at deriving mean values and spectral or turbulence parameters. Applications of the measuring system to turbomachinery flow in a radial compressor and to a turbulent pipe flow demonstrate the performance of the measuring system.
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Firoozian, R., and R. Stanway. "Modelling and Control of Turbomachinery Vibrations." Journal of Vibration and Acoustics 110, no. 4 (October 1, 1988): 521–27. http://dx.doi.org/10.1115/1.3269560.

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The authors describe an integrated approach to the modelling and active control of lateral vibrations in turbomachinery. Starting with consideration of the control of multiple rotor bending modes, the generation of a state vector from available measurements using an observer is discussed together with the effect on stability of employing a controller of reduced order. The various points are illustrated in an extended case study which also compares the active schemes with one involving a simple passive damper.
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Tisserant, D., and F. A. E. Breugelmans. "Rotor Blade-to-Blade Measurements Using Particle Image Velocimetry." Journal of Turbomachinery 119, no. 2 (April 1, 1997): 176–81. http://dx.doi.org/10.1115/1.2841096.

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The study of turbomachinery flow fields requires detailed experimental data. The rotating parts of turbomachines greatly limit the measurement techniques that can be used. Particle Image Velocimetry (PIV) appears to be a suitable tool to investigate the blade-to-blade flow in a rotor. The facility is a subsonic axial-flow compressor. The experimental apparatus enables the recording of a double-exposed photograph in a circumferential plane located at 85 percent of the blade height. The illumination plane has an axial direction and is provided by a pulsed ruby laser. The tracers used are submicron glycerine oil droplets. Data are processed by Young’s fringes method. Measurements were performed at 3000, 4500, and 6000 rpm with velocities in the range of 30 to 70 m/s. Steady operating conditions are chosen in such a way that the effect of radial velocity on PIV measurements can be neglected. Experimental problems encountered included homogeneous seeding of the flow field and laser light scattering from blade surfaces. The uncertainty affecting the velocity determination corresponds to 2 percent of the measured value. For a given set of operating conditions, 10 PIV pictures are recorded. The periodic flow field is approximated by averaging the experimental data point by point. Upstream and downstream velocity triangles are confirmed by measurements obtained from pressure probes. PIV measurement results were found to be similar to those of a blade-to-blade potential-flow calculation.
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Wadia, A. R., and B. F. Beacher. "Three-Dimensional Relief in Turbomachinery Blading." Journal of Turbomachinery 112, no. 4 (October 1, 1990): 587–96. http://dx.doi.org/10.1115/1.2927697.

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The leading edge region of turbomachinery blading in the vicinity of the endwalls is typically characterized by an abrupt increase in the inlet flow angle and a reduction in total pressure associated with endwall boundary layer flow. Conventional two-dimensional cascade analysis of the airfoil sections at the endwalls indicates large leading edge loadings, which are apparently detrimental to the performance. However, experimental data exist that suggest that cascade leading edge loading conditions are not nearly as severe as those indicated by a two-dimensional cascade analysis. This discrepancy between two-dimensional cascade analyses and experimental measurements has generally been attributed to inviscid three-dimensional effects. This article reports on two and three-dimensional calculations of the flow within two axial-flow compressor stators operating near their design points. The computational results of the three-dimensional analysis reveal a significant three-dimensional relief near the casing endwall that is absent in the two-dimensional calculations. The calculated inviscid three-dimensional relief at the endwall is substantiated by airfoil surface static pressure measurements on low-speed research compressor blading designed to model the flow in the high-speed compressor. A strong spanwise flow toward the endwall along the leading edge on the suction surface of the airfoil is responsible for the relief in the leading edge loading at the endwall. This radial migration of flow results in a more uniform spanwise loading compared to that predicted by two-dimensional calculations.
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Kim, Namhyo, and David L. Rhode. "Refined Turbulence Modeling for Swirl Velocity in Turbomachinery Seals." International Journal of Rotating Machinery 9, no. 6 (2003): 451–59. http://dx.doi.org/10.1155/s1023621x03000447.

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A generalized new form of the rotation-sensitive source term coefficient previously proposed by Bardina and colleagues as an extension of the standardk-εturbulence model was developed. The proposal made by Bardina and colleagues focused on rotating flows without significant turbulence generation, and the result was a negative-valued constant coefficient. The new functional form developed here for the coefficient has global as well as local dependence. The new model predictions of laser Doppler anemometry measurements of swirling flows in labyrinth seals were compared with the swirl distribution measurements and with the standardk-εmodel (i.e., no rotation source term) predictions. It was found that for the labyrinth seal cases for which detailed measurements are available, the standardk-εmodel gives unsatisfactory predictions, whereas the new model gives significantly improved predictions.
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Dissertations / Theses on the topic "Turbomachinery measurements"

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Gahagan, Shane G. "Pressure-sensitive paint measurements on a rotor disk surface at high speeds." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1997. http://handle.dtic.mil/100.2/ADA333428.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, June 1997.
Thesis advisor, Raymond P. Shreeve. AD-A333 428. Includes bibliographical references (p. 49-50). Also available online.
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Udrea, Doina Daciana. "High accuracy flow velocity measurements using particle image velocimetry : development and applications." Thesis, University of Warwick, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.300743.

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Mansour, Michel. "A 48kHz bandwidth, 1.8mm diameter entropy probe for aerothermal loss measurements in turbomachinery flows /." Zürich : ETH, 2009. http://e-collection.ethbib.ethz.ch/show?type=diss&nr=18087.

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Flegel, Ashlie Brynn. "Aerodynamic Measurements of a Variable-Speed Power-Turbine Blade Section in a Transonic Turbine Cascade." Cleveland State University / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=csu1387437733.

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Celestina, Richard A. "Development of New Single and High-Density Heat Flux Gauges for Unsteady Heat Transfer Measurements in a Rotating Transonic Turbine." The Ohio State University, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1608551902273547.

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Appukuttan, Ajith. "Probe measurement errors in turbomachinery flows." Thesis, University of Cambridge, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.613303.

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Jaffa, Nicholas Andrew. "Unsteady measurement techniques for turbomachinery flows." Thesis, University of Notre Dame, 2015. http://pqdtopen.proquest.com/#viewpdf?dispub=3732212.

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Accurate unsteady measurements are required for studying the flows in high speed turbomachines, which rely on the interaction between rotating and stationary components. Using statistics of phase locked ensembles simplifies the problem, but accurate frequency response in the 10-100 kHz range significantly limits the applicable techniques. This research advances the state of the art for phase resolved measurement techniques using for high speed turbomachinery flows focusing on the following areas: development, validation, and uncertainty quantification. Four methods were developed and implemented: an unsteady total pressure probe, the multiple overheat hot-wire method, the slanted hot-wire method, and the phase peak yaw hot-wire method. These methods allow for the entire phase locked average flow field to be measured (temperature, pressure, and velocity components, swirl angle, etc.). No trusted reference measurement or representative canonical flow exists for comparison of the phase resolved quantities, making validation challenging. Five different validation exercises were performed to increase the confidence and explore the range of applicability. These exercises relied on checking for consistency with expected flow features, comparing independent measurements, and cross validation with CFD. The combined uncertainties for the measurements were quantified using uncertainty estimates from investigations into the elemental error sources. The frequency response uncertainty of constant temperature hot-wire system was investigated using a novel method of illuminating the wire with a laser pulse. The uncertainty analysis provided estimates for the uncertainty in the measurements as well as showing the sensitivity to various sources of error.

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Quinn, Kevin J. "Pressure-sensitive paint measurement technique development for turbomachinery application." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1997. http://handle.dtic.mil/100.2/ADA346041.

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Thesis (Degree of Aeronautical and Astronautical Engineer) Naval Postgraduate School, December 1997.
"December 1997." Thesis advisor(s): Raymond P. Shreeve. Includes bibliographical references (p. 83-84). Also available online.
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Navarra, Kelly R. "Development of the Pressure-Sensitive-Paint Technique for Advanced Turbomachinery Applications." Thesis, Virginia Tech, 1997. http://hdl.handle.net/10919/36840.

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A new pressure-measurement technique which employs the tools of molecular spectroscopy has recently received considerable attention in the fluid mechanics community. Measurements are made via oxygen-sensitive molecules attached to the surface of interest as a coating, or paint. The pressure-sensitive-paint (PSP) technique is now commonly used in stationary wind-tunnel tests; this thesis presents the extension of the technique to advanced turbomachinery applications. New pressure- and temperature-sensitive paints (TSPs) have been developed for application to a state-of-the-art transonic compressor where pressures up to 2 atm and surface temperatures up to 140° C are expected for the first-stage rotor. PSP and TSP data has been acquired from the suction surface of the first-stage rotor of a transonic compressor operating at its peak-efficiency condition. The shock structure is clearly visible in the pressure image, and visual comparison to the corresponding computational fluid dynamics (CFD) prediction shows qualitative agreement to the PSP data.
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Pickering, Todd Michael. "Methods for Validation of a Turbomachinery Rotor Blade Tip Timing System." Thesis, Virginia Tech, 2014. http://hdl.handle.net/10919/47496.

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This research developed two innovative test methods that were used to experimentally evaluate the performance of a novel blade tip timing (BTT) system from Prime Photonics, LC. The research focused on creating known blade tip offsets and tip vibrations so that the results from a BTT system can be validated. The topic of validation is important to the BTT field as the results between many commercial systems still are not consistent. While the system that was tested is still in development and final validation is not complete, the blade tip offset and vibration frequency validation results show that this BTT system will be a valuable addition to turbomachinery research and development programs once completed. For the first test method custom rotors were created with specified blade tip offsets. For the blade tip offset alternate measurement, the rotors were optically scanned and analyzed in CAD software with a tip location uncertainty of 0.1 mm. The BTT system agreed with the scanned results to within 0.13 mm. Tests were also conducted to ensure that the BTT system identified and indexed the blades properly. The second developed test method used an instrumented piezoelectric blade to create known dynamic deflections. The active vibration rotor was able to create measureable deflection over a range of frequencies centered on the first bending mode of the blade. The results for the 110 Hz, 150 Hz, 180 Hz first bending resonance, 200 Hz, and 1036 Hz second bending resonance cases are presented. A strain gage and piezoelectric sensor were attached to the active blade during the dynamic deflection tests to provide an alternate method for determining blade vibration frequency. The BTT system correctly identified the active blade excitation frequencies as well as a 120 Hz frequency from the drive motor. This thesis also explored applying BTT methods and testing to more realistic blade geometry and vibration. Blade vibrations are usually classified by their frequency relative to the rotation speed. Synchronous vibrations are integer multiples of the rotational speed and are often excited by struts or vanes fixed to the engine case. For this reason, special probe placement algorithms were explored that use sine curve fitting to optimize the probe placement. Knowing how the blade will vibrate at operation before testing is critical as well. In preparation for future research, ANSYS Mechanical was used to predict the first three modes of a PT6A-28 first stage rotor blade at 1,966, 5,539, and 7,144 Hz. These frequencies were validated to within 4% using scanning laser vibrometry. The simulation was repeated at speed to produce a Campbell Diagram to highlight synchronous excitation crossings.
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Books on the topic "Turbomachinery measurements"

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Gahagan, Shane G. Pressure-sensitive paint measurements on a rotor disk surface at high speeds. Monterey, Calif: Naval Postgraduate School, 1997.

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United States. National Aeronautics and Space Administration., ed. Data reduction procedures for laser velocimeter measurements in turbomachinery rotors. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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Quinn, Kevin J. Pressure-sensitive paint measurement technique development for turbomachinery application. Monterey, Calif: Naval Postgraduate School, 1997.

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Goldman, Louis J. Three-component laser anemometer measurement systems. Cleveland, Ohio: Lewis Research Center, 1991.

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Barranger, John P. Low-cost FM oscillator for capacitance type of blade tip clearance measurement system. Cleveland, Ohio: Lewis Research Center, 1987.

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Dickinson, Wayne. A benthic chamber with electric stirrer mixing. Woods Hole, Mass: Woods Hole Oceanographic Institution, 1992.

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Elsner, Janusz W. Metrologia turbulencji przepływów. Wrocław: Zakład Narodowy im. Ossolińskich, 1995.

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King, Paul I. Testing, analysis, and code verification of aerodynamics and heat transfer related to turbomachinery: Final report. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1991.

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King, Paul I. Testing, analysis, and code verification of aerodynamics and heat transfer related to turbomachinery: Final report. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1991.

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Kurkov, Anatole P. Measurement of gust response on a turbine cascade. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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Book chapters on the topic "Turbomachinery measurements"

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Merzkirch, Wolfgang, and Kathrin Kalkühler. "Velocity and Turbulence Measurements in the Flow Downstream of Flow Conditioners." In Advances in Fluid Mechanics and Turbomachinery, 125–36. Berlin, Heidelberg: Springer Berlin Heidelberg, 1998. http://dx.doi.org/10.1007/978-3-642-72157-1_11.

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Kassens, I., and M. Rautenberg. "Whirl Distribution Measurements in Front of the Impeller of a Centrifugal Compressor." In Advances in Fluid Mechanics and Turbomachinery, 115–23. Berlin, Heidelberg: Springer Berlin Heidelberg, 1998. http://dx.doi.org/10.1007/978-3-642-72157-1_10.

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Dick, Erik. "Performance Measurement." In Fundamentals of Turbomachines, 175–92. Dordrecht: Springer Netherlands, 2015. http://dx.doi.org/10.1007/978-94-017-9627-9_5.

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Dick, Erik. "Performance Measurement." In Fundamentals of Turbomachines, 183–201. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-93578-8_5.

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Uzol, Oŭuz, and Joseph Katz. "Flow Measurement Techniques in Turbomachinery." In Springer Handbook of Experimental Fluid Mechanics, 919–57. Berlin, Heidelberg: Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-30299-5_14.

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Weyer, H. B. "Fundamentals of Flow Field Measurement Techniques." In Thermodynamics and Fluid Mechanics of Turbomachinery, 467–511. Dordrecht: Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-5153-2_14.

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Abboud, D., M. Elbadaoui, and N. Tableau. "Blade Monitoring in Turbomachines Using Strain Measurements." In Lecture Notes in Mechanical Engineering, 87–96. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-9199-0_9.

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Addabbo, Tommaso, Elia Landi, Riccardo Moretti, Marco Mugnaini, Lorenzo Parri, and Marco Tani. "A Distributed Condition Monitoring System for the Non-invasive Temperature Measurement of Heat Fluids Circulating in Turbomachinery Pipes Based on Self-Powered Sensing Nodes." In Lecture Notes in Electrical Engineering, 343–48. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-11973-7_40.

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Adachi, Tsutomu. "Flow Measurements in the Moving Blade Passage of a Single-Stage Axial-Flow Fan." In Turbomachinery Fluid Dynamics and Heat Transfer, 349–65. Routledge, 2017. http://dx.doi.org/10.1201/9780203734919-17.

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Hobson, Garth V., Andrew J. H. Williams, and Humberto J. Ganaim Rickel. "Unsteady Laser-Doppler-Velocimetry Measurements in a Cascade of Controlled-Diffusion Compressor Blades at Stall." In Turbomachinery Fluid Dynamics and Heat Transfer, 327–47. Routledge, 2017. http://dx.doi.org/10.1201/9780203734919-16.

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Conference papers on the topic "Turbomachinery measurements"

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Doukelis, A., and K. Mathioudakis. "Turbomachinery Flow Measurements Using Long-Nose Probes." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38488.

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The present work provides a detailed account of a pneumatic measuring technique appropriate for flow field measurements in turbomachinery configurations, making use of long-nose 5-hole probes. The way of obtaining flow quantities in a frame of reference on the sensing head of the probe is first addressed. Transformation of velocity co-ordinates from the probe frame to a stationary frame, customary for turbomachinery flows, is then discussed. Sources of error are also discussed, with particular attention on those that can be introduced by the nose geometry and the co-ordinate transformations. The potential of the measuring technique is demonstrated by presenting the application of the technique for measurements in an annular cascade facility. The results are compared to results obtained by a 3-D Laser-Doppler Anemometer.
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Lombard, J. P., E. Seinturier, and J. L. Raynaud. "Modal Characterization of Turbomachinery Bladed Disks by Optical Measurements." In ASME 2003 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/detc2003/vib-48622.

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The dynamic design of bladed disks consists in making sure that structural modes are not excited by the harmonics caused by engine speed (coincidences predicted after a Campbell diagram analysis). In practice, it is impossible to avoid every single coincidence over the whole operating range. An engine test is carried out at the end of the design cycle, in order to determine vibration levels. By means of this test and the validated FE model, the designer verifies frequency margins, and from this, is able to determine whether or not the bladed disk is likely to be at risk from vibration fatigue, otherwise known as High Cycle Fatigue (HCF). This analysis needs several FE calculations whose models have been updated in relation to component tests to measure stress distribution (use of strain gauges). One of the drawbacks of this type of measurement lies in the intrusive character of instrumentation used, which upsets the dynamic behavior of the blades in particular for high level modes. This document puts forward the application of non-intrusive, optical measurements, and highlights the accuracy that can be obtained by measuring mode shapes. Furthermore, this paper highlights the importance of defining levels of accuracy for measurements obtained, for example, in characterizing frequency scatterings for each blade individually, scatterings which are translated by an amplification of the structure aeroelastic response.
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Hösgen, Christian, Stephan Behre, Herwart Hönen, and Peter Jeschke. "Analytical Uncertainty Analysis for Hot-Wire Measurements." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56623.

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This paper presents an analytical approach to quantify the uncertainty of velocity-, angle- and turbulence intensity measurements obtained by hot-wire anemometry. Based on the given results of the model, the paper points out the most critical parameters influencing the quality of the flow measurement. The proposed approach is divided into three subsections, each accounting for the uncertainties due to the measurement equipment, probe calibration and measurements in the test-rig respectively. For every subsection the propagation of uncertainties is stated in the form of analytical formulas starting with the measurands, e.g. voltage, pressure, temperature, and ending with velocity, angle and turbulence intensity. The approach is applied to data, obtained by a triple hot-wire probe, on two-dimensional traverses in a 1.5-stage cold air turbine. The calibration process and, in particular, the temperature and pressure deviation between calibration and measurement are identified as having a major impact on the measurement uncertainty. With respect to the Aachen test-rig the uncertainty in velocity measurements is lower than 3.5%. The investigation of the turbulence intensity uncertainty yields an increase in uncertainty with increasing turbulence intensity but an insensitivity towards pitch- and yaw-angle uncertainty.
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CATTAFESTA, L., and A. EPSTEIN. "Gas temperature measurements in short duration turbomachinery test facilities." In 24th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3039.

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Fagan, John R., and Sanford Fleeter. "Laser two-focus velocimetry (L2F) for turbomachinery flow measurements." In ICALEO® ‘88: Proceedings of the Optical Methods in Flow & Particle Diagnostics Conference. Laser Institute of America, 1988. http://dx.doi.org/10.2351/1.5057973.

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Sever, I. A., A. B. Stanbridge, and D. J. Ewins. "Turbomachinery blade vibration measurements with tracking LDV under rotation." In Seventh International Conference on Vibration Measurements by Laser Techniques: Advances and Applications. SPIE, 2006. http://dx.doi.org/10.1117/12.693172.

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Egbert, Scott C., Darrel Zeltner, Mohsen Rezasoltani, and Dale R. Tree. "High Pressure Optical Measurements of Temperature at Turbine Rotor Inlet Conditions." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14154.

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Abstract The measurement of combustion product gas temperature is valuable for the development and control of many combustion systems. In gas turbine engines, measurement of the rotor inlet temperature remains particularly challenging because of harsh operating conditions and limited access. The Integrated Spectral Band Ratio (ISBR) method is a non-intrusive optical emission gas temperature measurement technique suitable for this application. Optical fibers made of sapphire were used to transmit the radiative signal from the post combustion zone to a Fourier Transform Infrared (FTIR) spectrometer without the need for probe cooling. The ratio of spectral bands of H2O, nominally 100 cm−1 wide between 4600 and 6200 cm−1 were used to infer temperature. ISBR and thermocouple measurements were obtained during two temperature sweeps; one at high load and one at low load (pressures of 1.2 and 0.7MPa, respectively). The average of three thermocouples 76 mm downstream of the ISBR measurements were consistently on the order of 200 K lower, consistent with a radiative correction and the heat loss between the two measurements. The change in ISBR temperature (95 K) during the sweep was similar to the change in average thermocouple temperature (89 K). Repeatability of the optical measurement at a given operating condition was on the order of ± 15 K and the absolute uncertainty of a single ISBR temperature measurement was estimated to be ± 61 K. A linear correlation with an R-squared value of 0.97 was also found between raw optical signal and thermocouple measurements suggesting that once a calibrated measurement is obtained, changes in gas temperature can be determined using a correlation of the raw signal to produce the temperature.
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Gregory, J., H. Sakaue, and J. Sullivan. "Unsteady pressure measurements in turbomachinery using porous pressure sensitive paint." In 40th AIAA Aerospace Sciences Meeting & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-84.

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Arnold, Frank, Ulf Tapken, Roland Bauers, and Jörgen Zillmann. "Turbomachinery Exhaust Noise Radiation Experiments - Part 1: Polar Directivity Measurements." In 14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2857.

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Fernelius, Mark, and Steven E. Gorrell. "Thermocouple Recovery Factor for Temperature Measurements in Turbomachinery Test Facilities." In 52nd Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-0791.

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Reports on the topic "Turbomachinery measurements"

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Katz, Joseph, and Charles Meneveau. Instrumentation to Support PIV and HPIV Measurements in an Axial Turbomachine Flow Visualization Facility. Fort Belvoir, VA: Defense Technical Information Center, June 2001. http://dx.doi.org/10.21236/ada388848.

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