Relevant bibliographies by topics / Compressors – Vibration

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  2. Dissertations / Theses
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Academic literature on the topic 'Compressors – Vibration'

Author: Grafiati
Published: 4 June 2021
Last updated: 9 February 2022

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Journal articles on the topic "Compressors – Vibration"

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Zhang, Li, Shuo Zhang, Yuan Yuan Zhang, and Yan Miao Ma. "A Harmonic Response Analysis of Food Refrigeration Compressor Based on Abaqus." Applied Mechanics and Materials 215-216 (November 2012): 950–54. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.950.

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A harmonic response analysis was conducted on semi-hermetic refrigeration compressor by Abaqus software. The vibration displacement and acceleration response spectrums of the compressor’s key points were obtained. The vibration characteristics of the compressor show that the harmonic response analysis result is consistent with the experimental one. The vibration of the compressor at 50Hz is the most dramatic. The first trough in each direction is found around 70Hz, and after that each direction’s acceleration goes up significantly. At the same time, the conclusion verifies the vibration of compressor’s bottom corners by LMS Test. Lab Signature Testing. The paper provides a scientific reference for the further study on vibration and noise reduction in food refrigeration compressors.
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Widodo, Achmad, Satrio Budi Prasojo, and Ismoyo Haryanto. "THE USE OF TWO-DIMENSIONAL AUTOCORRELATION OF VIBRATION SIGNAL FOR FAULT DETECTION OF RECIPROCATING COMPRESSORS." ROTASI 18, no. 1 (January 1, 2016): 18. http://dx.doi.org/10.14710/rotasi.18.1.18-22.

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Reciprocating compressors are the oldest kind of compressors designed for mass production. These compressors still become- the best choice for several industrial application due to their advantages that give high compression ratio and low mass flow. There are many cases of reciprocating compressors faults, such as fault in valve, wrist-pin, and crankpin bore on connecting rod. In this paper, fault detection of such compressors due to exhaust valve and pin bore faults will be presented based on the vibration signal. At first, time domain and frequency domain will be the basic method for analysis and then it will be completed by spectrogram and two-dimensional autocorrelation. The patterns of vibration signals were analyzed and compared through their vibration signatures. Vibration signatures could give informations related to impending faults in the compressors. Therefore, the fault diagnostics of compressor could be realized
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Motriuk, R. W., and D. P. Harvey. "Centrifugal Compressor Modifications and Their Effect on High-Frequency Pipe Wall Vibration." Journal of Pressure Vessel Technology 120, no. 3 (August 1, 1998): 276–82. http://dx.doi.org/10.1115/1.2842058.

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High-frequency pulsation generated by centrifugal compressors, with pressure wavelengths much smaller than the attached pipe diameter, can cause fatigue failures of the compressor internals, impair compressor performance, and damage the attached compressor piping. There are numerous sources producing pulsation in centrifugal compressors. Some of them are discussed in literature at large (Japikse, 1995; Niese, 1976). NGTL has experienced extreme high-frequency discharge pulsation and pipe wall vibration on many of its radial inlet high-flow centrifugal gas compressor facilities. These pulsations led to several piping attachment failures and compressor internal component failures while the compressor operated within the design envelope. This paper considers severe pulsation conditions at an NGTL compression facility which resulted in unacceptable piping vibration. Significant vibration attenuation was achieved by modifying the compressor (pulsation source) through removal of the diffuser vanes and partial removal of the inlet guide vanes (IGV). Direct comparison of the changes in vibration, pulsation, and performance are made for each of the modifications. The vibration problem, probable causes, options available to address the problem, and the results of implementation are reviewed. The effects of diffuser vane removal on discharge pipe wall vibration as well as changes in compressor performance are described.
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KIM, Minkyu, Byoungha Ahn, and Simwon Chin. "Parameter study of Variation noise in outdoor of air conditioner." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 4 (August 1, 2021): 2822–29. http://dx.doi.org/10.3397/in-2021-2238.

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In the outdoor unit of a room air conditioner, the main factors that made it possible to vary the ability of cooling and heating are the development of BLDC motors, advances in inverter technology, and the development of refrigerant volume control technology. The main reason for this change in cooling and heating capacity is that it is possible to change the RPS of compressors. As the range of the compressor's RPS expands, so does the range of response to load variations. This is mainly based on the capacity of the high-pressure refrigerant produced by the compressor. When the compressor rotates at high speed or low speed, the difference in noise occurs depending on the difference in rotational speed. Of course, fans and motors also contribute to noise fluctuations, but the overall governing factor is the greater contribution of refrigerant from compressors and compressors. The refrigerant flows into the cycle configured in the outdoor unit and varies in speed and flow rate depending on the amount of refrigerant. This results in vibration and noise appearing in the form of radiations, resonances, solid sounds, resonances, and so on. There are several factors that can cause vibration or noise changes depending on the flow velocity and flow rate. In this paper, we selected reactance of compressor motors, mufflers directly connected to compressor discharge ports and accumulator at compressor inlet where fluid vibrations occur the most. First of all, reactance of motor responds quickly to load fluctuations and has a large instantaneous torque to instantaneous load fluctuations. The muffler, which is directly connected to the compressor discharge port, is the first Cavity where high-pressure gas meets, and can evaluate the concentration of kinetic energy that generates noise and improve the collection center to reduce fluctuating noise. The Accumulator is the part with the lowest temperature of refrigerant gas entering the compressor, and the rapid change in the flow path causes the most fluid to generate vibration and radiation of the structure. For this reason, we select three elements first. In this paper, we specifically describe the background of selecting three elements of an air conditioning outdoor unit for the variability of noise over RPS changes. We demonstrate that these factors can review the feasibility of the experiment, explain the results of the analysis, and possibility of reduce the variation noise.
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Peng, Sun, Wang Yanrong, and Zhang Xiaobo. "Effects of Airflow Deflection Angle in Diffuser on Forced Response Caused by Impeller-diffuser Interaction in Centrifugal Compressors." MATEC Web of Conferences 179 (2018): 01009. http://dx.doi.org/10.1051/matecconf/201817901009.

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Aeroelasticity has always been a significant issue of compressors. Impeller-diffuser interaction (IDI) produces periodic aerodynamic excitation which forces the blades to vibrate in centrifugal compressors, and eventually causes the damage of blades. Therefore, it is of great importance to investigate the IDI in centrifugal compressors and the effects on the vibration of blades. In this paper, it is discussed in detail that the deflection angle of the airflow in diffuser affects the IDI of the centrifugal compressor and the vibration of blades. The results show that if deflection angle is positive, the interaction of the diffuser on impeller and the vibration of main blades are decreased. However, on condition that the deflection angle is excessive, the interaction of the diffuser on the flow field of impeller will be intensified, and the vibration of the main blades will be stronger. Therefore, it is necessary to reasonably control the range of the deflection angle so that centrifugal compressors are able to work in a safer environment.
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Sha, Yun Dong, Feng Tong Zhao, and Jia Han. "Investigation into Noise Frequency Spectrum Characteristics Corresponding to Blade Nonsynchronous Vibration in Multi-Stage Axial Compressor." Advanced Engineering Forum 2-3 (December 2011): 870–75. http://dx.doi.org/10.4028/www.scientific.net/aef.2-3.870.

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Unsteady flow phenomenon occurs in a multi-stage axial compressor. The unsteady flow not only has significant influence on the performance of compressor and the stability of flow, but also can be an excitation source inducing Nonsynchronous vibration (NSV) of rotor blade. NSV is an aeroelastic phenomenon where the rotor blades vibrate at nonintegral multiples of the shaft rotational frequencies in operating regimes where classical flutter is not known to occur. Recently, more and more scholars pay attention to Rotating instabilities (RIs) as one of the unsteady flow phenomenon. RIs have been observed in axial flow fans and centrifugal compressors as well as in low-speed and high-speed axial compressors. They are responsible for the excitation of high amplitude rotor blade vibrations and noise generation. This research aims at revealing the relationships among the unsteady flow behaviors, characteristics of inner sound field and propagation, the vibration of rotor blade in multi-stage axial compressor. The noise in compressor and the vibration of rotor blade have been measured on a high pressure compressor rig testing. The transducer system is connected to the interior casing wall through the acoustic waveguide pipes. The noise is measured by 1/4 inch condenser microphones in different operating of the compressor. The time-domain wave of noise acquired at different work status of the compressor is transformed into frequency spectrum by Fast Fourier Transform (FFT) to investigate characteristics of sound field in multi-stage axial compressor. And the emphasis is focused on the frequency characteristics of the noise corresponding to blade nonsynchronous vibration. It is found that the vibration amplitude of the rotor blade suddenly increases in a pre-arranged structure adjustment and specific rotating speed, and noise signal with special frequency structures appears simultaneously. High amplitude levels of blade vibration have occurred on the first rotor of a multi-stage high pressure compressor. The frequencies are not in resonance with harmonics of the rotor speed. The frequency analysis show that the noise has a special frequency structures with combination of the appeared characteristic frequency and the blade pass frequency of rotor blade (BPF). Because the similarities between the frequency combination and the specific frequency structure of the fluctuating pressure when the rotating instability (RI) appears in the axial compressor have been identified, the acting mechanism of rotating instability may exist in this compressor, i.e. the vibrational excitation to the rotor blade may be aerodynamically caused and associated with a rotating flow instability in the compressor.
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Liu, H. I., X. P. Li, and Y. N. Rui. "Monitor On-Line and Fault Diagnosis to High Speed Centrifugal Hydrogen Compressors Based on the Theories of EMD and Correlation Dimension." Applied Mechanics and Materials 33 (October 2010): 523–27. http://dx.doi.org/10.4028/www.scientific.net/amm.33.523.

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High Speed Centrifugal Hydrogen Compressors are big and critical equipments which are widely used in chemical enterprises. It is very important to monitor their condition on-line and diagnose their failure. Based on the research of EMD (empirical mode decomposition) and correlation dimension and experimental simulation, the vibration signals of a High Speed Centrifugal Hydrogen Compressor’s main spindle are collected when working. Then the signals are decomposed by EMD, their correlation dimensions are calculated and taken as fault feature. Finally, using BP algorithm of a neural network in which there are 3 lays, a satisfied effect of fault diagnosis of a High Speed Centrifugal Hydrogen Compressor has been got. The experiment has confirmed that the method is advanced, reliable and practical. A new method is provided for High Speed Centrifugal Hydrogen Compressors’ fault diagnosis.
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Kluczyk, Marcin. "Vibration Characteristics of Reciprocating Air Compressors Used For Hyperbaric Purposes." Polish Hyperbaric Research 52, no. 3 (September 1, 2015): 17–25. http://dx.doi.org/10.1515/phr-2015-0013.

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Abstract The article presents problems related to the diagnostics of vibrations in reciprocating compressors driven by motors of less than 100 kW. None of the currently applicable norms concerning the issues of vibration diagnostics broach this subject, and therefore diagnosticians have no reference levels for measured vibration parameters. The present paper focuses on two types of compressors intended for diving purposes and hyperbaric techniques. The paper contains a suggested course of actions at the time of taking measurements. Further suggestions for developing coherent procedures as regards the diagnostics of reciprocating compressors of less than 100 kW have been indicated.
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Wang, Wei Min, and Wei Zheng An. "Investigation on the Subsynchronous Vibration Fault Diagnosis and Control for Centrifugal Compressor." Applied Mechanics and Materials 34-35 (October 2010): 1488–92. http://dx.doi.org/10.4028/www.scientific.net/amm.34-35.1488.

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Centrifugal compressors are widely used to compressor gas in many different processes within the petroleum and chemical industry. Two vibration types of concern in industrial compressors are synchronous and subsynchronous vibration. The latter, more troubling type of vibration, occurs when non-conservative whirling forces(Cross-coupling) act to excite a lateral natural frequency, which lies below the running speed(subsynchronous vibration). In this paper, more attention is paid to impellers from a rotordynamic standpoint and a synthesis gas compress in ammonia plant is analyzed in order to diagnosis the root cause of vibration fault using the best available resources for seals and bearing. Logarithmic decrement predictions for the full rotor model consisting of all the stages and seals are conducted under different bearing structure. On this basis, a resolvent to improve the rotordynamic stability is presented. The field application result indicates that this method is effective.
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Zhou, Ying Ming, Zhi Min Song, Hai Feng Zhao, and Shu Yun Mi. "Vibration Fault Analysis in Screw Compressor and Foundation." Applied Mechanics and Materials 166-169 (May 2012): 1072–75. http://dx.doi.org/10.4028/www.scientific.net/amm.166-169.1072.

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With the characteristics of low noise, low vibration, high reliability and long life, Screw Compressor is the indispensable main equipment which widely used in petrochemical field. The abnormal vibration of Compressor will affect normal operation of the host, lead to damage of some main parts such as Compressor and motor and at the same time it’s an unneglectable hidden trouble for equipment’s safe operation. This article takes the data acquisition of vibration and the analyses of shake for two Ammonia Refrigeration Piston Compressors, and study at the reason about shock then take the effective shockproof treatment plan. All these ensure the stable running of the facility.
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Dissertations / Theses on the topic "Compressors – Vibration"

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Arcot, Ramakant P. "Computer simulation of the Bristol compressor suspension system dynamics." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-09052009-040832/.

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Raubenheimer, Gert. "Vibration excitation of axial compressor rotor blades." Thesis, Stellenbosch : Stellenbosch University, 2011. http://hdl.handle.net/10019.1/17987.

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Thesis (MScEng)--Stellenbosch University, 2011.
ENGLISH ABSTRACT: Turbomachines are exposed to several environmental factors which may cause failure of components. One of these factors, high cycle fatigue, is often caused by blade utter. This thesis forms part of a project of the European Seventh Framework Programme (FP7), called project Future. Project Future is doing theoretical and experimental investigation into the occurrence of utter in turbomachinery. The objective of this thesis was to evaluate the effectiveness of a gas injection system as a means of exciting vibrations on the rst stage rotor blades of a compressor. Unsteady simulations of the excitation velocity perturbations were performed in the Computational Fluid Dynamics (CFD) software, Numeca FINE/Turbo. Experimental testing on the in-house Rofanco compressor test bench, using one prototype of the 15 injector system, provided data that was used to implement boundary conditions and to verify certain aspects of the unsteady simulation results. The simulation results revealed the following: the injector bypass frequency was so dominant that the excitation frequency was hardly detectable in the majority of cases. Furthermore, several secondary frequencies were consistently present. The injector bypass frequency, as well as the secondary frequencies, occurred as a result of the convolution of Fast Fourier Transforms. While the injector bypass frequencies can theoretically be eliminated, it will not be possible to eliminate the secondary frequencies from the blade response. In conclusion, according to the CFD results, it will not be possible to excite a single excitation frequency by making use of a nite number of gas injector vibration exciters.
AFRIKAANSE OPSOMMING: Turbomasjiene word onderwerp aan verskeie omgewingsfaktore wat falings van komponente kan veroorsaak. Een van hierdie faktore, naamlik hoëfrekwensie vermoeidheid, word onder andere veroorsaak deur lem adder. Hierdie tesis is deel van 'n projek in die Sewende Europese Raamwerk Program (European Seventh Framework Programme - FP7), projek Future. Projek Future doen teoretiese en eksperimentele ondersoek na die voorkoms van lemfl adder in turbomasjienerie. Die doelwit van hierdie tesis was om die effektiwiteit van 'n gasinspuiter vibrasie-opwekkingstelsel te evalueer, deur gebruik te maak van onbestendige simulasie in die berekenings vloei-meganika sagtewarepakket, Numeca FINE/Turbo. Eksperimentele toetswerk op die plaaslike Rofanco kompressortoetsbank, met 'n prototipe van die 15 inspuiter stelsel, het inligting verskaf wat gebruik is om die inlaattoestande te spesi seer en simulasieresultate te korreleer. Die simulasieresultate het getoon dat die frekwensie waarteen 'n lem by die inspuiters verbybeweeg, so prominent is, dat dit in die meerderheid van gevalle baie meer prominent is as die opwekkingsfrekwensie. Verder was daar ook deurgaans 'n aantal sekondêre frekwensies teenwoordig. Die teenwoordigheid van die inspuiter verbybeweeg frekwensie en die sekondêre frekwensies is die resultaat van die konvolusie van Vinnige Fourier Transforme. Alhoewel dit in teorie moontlik sal wees om die inspuiter verbybeweeg frekwensie te elimineer, is dit onmoontlik om die sekondêre frekwensies uit die lem vibrasie te elimineer. Ter opsomming, volgens die berekenings vloei-meganika resultate, is dit nie moontlik om met 'n stelsel van 'n eindige aantal inspuiters, 'n enkele vibrasie frekwensie op te wek nie.
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Holzinger, Felix [Verfasser]. "Coupling of tip leakage flow and blade vibration in transonic compressors : Mechanism and countermeasures / Felix Holzinger." Aachen : Shaker, 2018. http://d-nb.info/1159835063/34.

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Rose, John A. "The experimental characterization of the dynamics of a reciprocating freon compressor system." Thesis, This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-12302008-063244/.

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Arzina, Dina. "Vibration analysis of compressor blade tip-rubbing." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/7109.

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There has been a significant increase in air traffic volume, particularly over the past twenty years. In order to cope with this increase in demand, it has been necessary to increase the efficiency of aircraft engines. Over the years, this has been achieved by reducing the clearance between blade tips and the engine casing. As a consequence of the reduced clearance, tip-rubbing frequently occurs in the engine during operation. The primary aim of this project is to address the vibrations involved in a tip-rubbing phenomenon when a blade of the Intermediate Pressure (IP) compressor in a Trent 900 engine interacts with the casing. Current trends towards blade optimisation tend to make the blade thinner and thus more flexible; therefore, it is very important to be able to successfully predict and prevent nonlinear response of a blade when tip-rubbing occurs. Current literature on the study of nonlinear vibration of a blade in a tip-rub event is limited; this project is understood to be the first to attempt an understanding of the issue. In this thesis, analytical models are presented that predict the nonlinear responses of rotor-stator interactions. These are helpful in understanding nonlinear parameters that can have an effect on the system response. Simulations were started by determining the stresses in the blade due to centrifugal rotation. Resonant frequencies of the blade were determined by modal analysis. Finally, the tip-rubbing event was simulated. The results were used to output frequency response curves which were used to identify if the blades were behaving nonlinearly as a result of tip-rubbing. The primary conclusion from this project is that tip-rubbing can excite nonlinear vibration in the compressor blades. However, the simulation results were affected adversely by hourglassing of the casing segments and should not be considered completely accurate.
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Murphy, William P. "High-speed blade vibration in a transonic compressor." Thesis, Monterey, Calif. : Naval Postgraduate School, 2008. http://handle.dtic.mil/100.2/ADA483477.

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Thesis (M.S. in Engineering Acoustics)--Naval Postgraduate School, June 2008.
Thesis Advisor(s):Hobson, Garth V. ; Baker, Steven. "June 2008." Description based on title screen as viewed on August 26, 2008. Includes bibliographical references (p. 33). Also available in print.
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Stasolla, Vincenzo. "Numerical analysis of aerodynamic damping in a transonic compressor." Thesis, KTH, Skolan för industriell teknik och management (ITM), 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-264359.

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Aeromechanics is one of the main limitations for more efficient, lighter, cheaper and reliable turbomachines, such as steam or gas turbines, as well as compressors and fans. In fact, aircraft engines designed in the last few years feature more slender, thinner and more highly loaded blades, but this trend gives rise to increased sensitivity for vibrations induced by the fluid and result in increasing challenges regarding structural integrity of the engine. Forced vibration as well as flutter failures need to be carefully avoided and an important parameter predicting instabilities in both cases is the aerodynamic damping. The aim of the present project is to numerically investigate aerodynamic damping in the first rotor of a transonic compressor (VINK6). The transonic flow field leads to a bow shock at each blade leading edge, which propagates to the suction side of the adjacent blade. This, along with the fact that the rotating blade row vibrates in different mode shapes and this induces unsteady pressure fluctuations, suggests to evaluate unsteady flow field solutions for different cases. In particular, the work focuses on the unsteady aerodynamic damping prediction for the first six mode shapes. The aerodynamic coupling between the blades of this rotor is estimated by employing a transient blade row model set in blade flutter case. The commercial CFD code used for these investigations is ANSYS CFX. Aerodynamic damping is evaluated on the basis of the Energy Method, which allows to calculate the logarithmic decrement employed as a stability parameter in this study. The least logarithmic decrement values for each mode shape are better investigated by finding the unsteady pressure distribution at different span locations, indication of the generalized force of the blade surface and the local work distribution, useful to get insights into the coupling between displacements and consequent generated unsteady pressure. Two different transient methods (Time Integration and Harmonic Balance) are employed showing the same trend of the quantities under consideration with similar computational effort. The first mode is the only one with a flutter risk, while the higher modes feature higher reduced frequencies, out from the critical range found in literature. Unsteady pressure for all the modes is quite comparable at higher span locations, where the largest displacements are prescribed, while at mid-span less comparable values are found due to different amplitude and direction of the mode shape. SST turbulence model is analyzed, which does not influence in significant manner the predictions in this case, with respect to the k-epsilon model employed for the whole work. Unsteady pressure predictions based on the Fourier transformation are validated with MATLAB codes making use of Fast Fourier Transform in order to ensure the goodness of CFX computations. Convergence level and discrepancy in aerodamping values are stated for each result and this allows to estimate the computational effort for every simulation and the permanent presence of numerical propagation errors.
Aeromekanik är en av huvudbegränsningarna för mer effektiva, lättare, billigare och mer pålitliga turbomaskiner, som ångturbiner, gasturbiner, samt kompressorer och fläktar. I själva verket har flygplansmotorer som designats under de senaste åren har fått tunnare och mer belastade skovlar, men denna trend ger upphov till ökad känslighet för aeromekaniska vibrationer och resulterar i ökande utmaningar när det gäller motorns strukturella integritet. Aerodynamiskt påtvingade vibrationer såväl som fladder måste predikteras noggrant för att kunna undvikas och en viktig parameter som förutsäger instabilitet i båda fallen är den aerodynamiska dämpningen. Syftet med det aktuella projektet är att numeriskt undersöka aerodynamisk dämpning i den första rotorn hos en transonisk kompressor (VINK6). Det transoniska flödesfältet leder till en bågformad stötvåg vid bladets främre kant, som sprider sig till sugsidan på det intilliggande bladet. I och med detta, tillsammans med det faktum att den roterande bladraden vibrerar i olika modformer och detta inducerar instationära tryckfluktuationer, syftar detta arbete på att utvärdera flödesfältslösningar för olika fal. I synnerhet fokuserar arbetet på prediktering av den instationära aerodynamiska dämpningen för de första sex modformen. Den aerodynamiska kopplingen mellan bladen hos denna rotor uppskattas genom att använda en transient bladradmodell uppsatt för fladderberäkningen. Den kommersiella CFD-koden som används för denna utredning är ANSYS CFX. Aerodynamisk dämpning utvärderas med hjälp av energimetoden, som gör det möjligt att beräkna den logaritmiska minskningen som används som en stabilitetsparameter i denna studie. De minsta logaritmiska dekrementvärdena för varje modform undersöks bättre genom att hitta den ostadiga tryckfördelningen på olika spannpositioner, som är en indikering av den lokala arbetsfördelningen, användbar för att få insikt i kopplingen mellan förskjutningar och därmed genererat ostabilt tryck. Två olika transienta metoder används som visar samma trend för de kvantiteter som beaktas med liknande beräkningsinsatser. Den första modformen är den enda med en fladderrisk, medan de högre modformerna har högre reducerade frekvenser, och ligger utanför det kritiska intervallet som finns i litteraturen. Instationärt tryck för alla moder är ganska jämförbart på de högre spannpositioner, där de största förskjutningarna föreskrivs, medan runt midspannet finns mindre jämförbara värden på grund av olika amplitud och riktning för modformen. SSTturbulensmodellen analyseras, som i detta fall inte påverkar predikteringen på ett betydande sätt. Det predikterade instationära trycket baserad på Fourier-transformationen valideras med MATLAB-koder som använder sig av Fast Fourier Transform för att säkerställa noggrannheten hos CFX-beräkningar. Konvergensnivå och skillnader i aerodämpningsvärden anges för varje resultat och detta gör det möjligt att uppskatta beräkningsinsatsen för varje simulering och uppskatta utbredningen av det numeriska felet.
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Rankle, Hugo Elias Camargo. "Acoustic prediction and noise control of a refrigeration compressor." Thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-09052009-040840/.

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Brandsen, Jacobus Daniel. "Prediction of axial compressor blade vibration by modelling fluid-structure interaction." Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/85616.

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Thesis (MScEng)-- Stellenbosch University, 2013.
ENGLISH ABSTRACT: The Council for Scientific and Industrial Research has developed a vibration excitation system. The system is designed to excite the rotor blades of an axial compressor in the specified vibration mode and at the specified frequency. The vibration excitation system was tested on Stellenbosch University’s Rofanco compressor test bench. A two-way staggered fluid-structure interaction (FSI) model was created that was capable of simulating the vibration of the rotor blades excited by the system. The results of the FSI model were verified using available experimental data. It was concluded that the FSI model is able to recreate the vibration excited by the system to within the desired level of accuracy. In addition, the results of the FSI model showed that the vibration excitation system should be able to excite the blades in the selected vibration mode and at the selected frequency provided that the excitation frequency is close the natural frequency of the first bending mode. The results also suggested that a transient computational fluid dynamics model should be sufficient for the prediction of the aerodynamic forces acting on the rotor blades. Furthermore, a one-way staggered FSI model should be adequate for calculating the motions of the blades.
AFRIKAANSE OPSOMMING: Die Wetenskaplike en Nywerheidnavorsingsraad het ’n vibrasie-opwekkingstelsel ontwerp om die rotorlemme van ’n aksiaalvloei kompressor in die gespesifiseerde vibrasiemodus en teen die gespesifiseerde frekwensie op te wek. Die vibrasieopwekkingstelsel is met behulp van die Universiteit Stellenbosch se Rofanco kompressortoetsbank getoets. Daarna is ’n tweerigting vloeistof-struktuur-interaksie model geskep om die vibrasie van die rotorlemme, wat deur die stelsel opgewek is, te simuleer. Beskikbare eksperimentele data is gebruik om die resultate van die vloeistof-struktuur-interaksie model te bevestig. Die gevolgtrekking is gemaak dat die model wél die vibrasie van die lemme met die nodige akkuraatheid kan simuleer. Die resultate van die vloeistof-struktuur-interaksie model toon ook dat die stelsel die lemme in die gekose vibrasiemodus en teen die gekose frekwensie behoort te kan opwek, solank die opwekkingsfrekwensie na aan die natuurlike frekwensie van die eerste buigmodus is. Voorts dui die resultate daarop dat ’n berekeningsvloeimeganika model die aërodinamiese laste van die lemme sal kan voorspel. ’n Eenrigting vloeistof-struktuur-interaksie model behoort voldoende te wees om die beweging van die rotorlemme te bereken.
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Muhammad, Moosa. "Numerical investigation of self-excited vibrations of a compressor cascade /." Stockholm, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-507.

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Books on the topic "Compressors – Vibration"

1

Sound and vibrations of positive displacement compressors. Boca Raton, Fla: CRC Press, 2007.

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Swansson, N. S. Investigation of blade vibration T55-L-11C compressor stages 1 and 2. Melbourne, Victoria: Aeronautical Research Laboratories, 1985.

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Pisarevskiĭ, V. M. Gasiteli kolebaniĭ gaza. Moskva: "Nedra", 1986.

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Gross, Neil Lionel. Investigation of noise and vibration within an oil flooded sliding vane rotary air compressor. Birmingham: Aston University. Department of Mechanical and Production Engineering, 1990.

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Osburn, Nicholas Glen. Implementation of a two probe tip-timing technique to determine compressor blade vibrations. Monterey, Calif: Naval Postgraduate School, 2000.

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Newman, Frederick A. Experimental vibration damping characteristics of the third-stage rotor of a three-stage transonic axial-flow compressor. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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Czechowski, Edward S. Critical factors in the application of a diesel engine drive on a centrifugal gas compressor: A Master's project in Industrial Technology. 1996.

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Soedel, Werner. Sound and Vibrations of Positive Displacement Compressors. CRC, 2006.

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Book chapters on the topic "Compressors – Vibration"

1

Dadd, M. W., P. B. Bailey, G. Davey, T. Davis, and B. J. Thomlinson. "Vibration Reduction in Balanced Linear Compressors." In Cryocoolers 11, 175–82. Boston, MA: Springer US, 2002. http://dx.doi.org/10.1007/0-306-47112-4_23.

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Enghardt, Lars, Armin Faßbender, and Jakob Hurst. "Sound Sources of Radial Compressors—A Numerical Study on the Outlet Side." In Flinovia—Flow Induced Noise and Vibration Issues and Aspects-II, 71–84. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-76780-2_5.

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Nagy, Ramona, Remus Stefan Maruta, and Karoly Menyhardt. "Vibration Analysis of High-Pressure Pneumatic Compressor." In Springer Proceedings in Physics, 403–11. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-54136-1_41.

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Buchwald, Patrick, Christian U. Waldherr, Jochen Schell, Heinrich Steger, and Damian M. Vogt. "Experimental and Numerical Modal Analysis of an Axial Compressor Blisk." In Vibration Engineering for a Sustainable Future, 379–87. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-48153-7_48.

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Li, Yuan, Yang Lin, Ling Fan, Yu Zhang, and Yunfeng Chang. "Study on Vibration Tracing and Vibration Reduction Technology of Reciprocating Compressor Pipeline." In Lecture Notes in Mechanical Engineering, 629–38. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-8331-1_47.

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Bruins, P. C., A. de Koning, and T. Hofman. "Low Vibration 80 K Pulse Tube Cooler with Flexure Bearing Compressor." In Cryocoolers 12, 109–14. Boston, MA: Springer US, 2002. http://dx.doi.org/10.1007/0-306-47919-2_16.

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Grellmann, W., R. Steiner, I. Kotter, M. Neitzel, M. Maier, and K. von Diest. "Mechanical Vibration Behaviour of a Compressor Blade Made from a High-Performance Composite." In Deformation and Fracture Behaviour of Polymers, 429–38. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-662-04556-5_29.

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Brandão, André, Joilson Rangel, and Rodolfo Melo. "Root Cause Investigation of High Frequency Structural Vibration on a High Pressure Hydrogen Compressor." In Mechanisms and Machine Science, 366–79. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-99268-6_26.

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Pichler, Kurt. "Early Fault Detection in Reciprocating Compressor Valves by Means of Vibration and pV Diagram Analysis." In Predictive Maintenance in Dynamic Systems, 167–205. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-05645-2_6.

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Yamaguchi, N., T. Sato, S. Umemura, and T. Ohwaki. "A Non-synchronous Vibration of Moving Blades Coupled with the Bleed Chamber Resonance in an Axial Compressor." In Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers, 829–42. New York, NY: Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4613-9341-2_42.

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Conference papers on the topic "Compressors – Vibration"

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Upreti, K. C., and Dwaipayan Banerjee. "Preventing Small Bore Piping/Tubing Failures in Reciprocating Compressors." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94535.

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API-618 Standard requires pulsation and vibration analysis of reciprocating compressors systems to prevent the system from damages. This analysis is carried out on major piping but often small bore connections are missed out in analysis and mistakes in site fabrication add up to this problem. These small bore connections on reciprocating compressor causes serious problems due to vibrations around reciprocating compressor. This paper describes the issues of small-bore connection on Refinery CCR Platformer Net Gas Compressors where series of failures observed on small bore connection and associated tubing. Vibration/pulsation was the major contributing factor to various failures. Contributory Reasons for failure were analysed and reasons was found due to inadequate design of piping & tubing supports, Transmittal of vibration to platforms. It was found that small bore connections for PT, volume bottle drains, TI/TW were vibrating with high vibration velocity and amplitude. Max Vibration readings were found 705 micron. The dominant peak of vibration frequency is located at 15/17 X RPM. All vibrations were low frequency vibrations (< 300 Hz). The problem was overcome by reducing SBC length and provision of better supports, reduced span for tube and pipe supports, replacement of tubes with higher schedule carbon steel pipes, shifting of instruments to less vibration areas such as basement of compressor house etc. Various modifications explained for reduction of vibration levels. Study compares condition prior to modification and new modification proposals. Modification improved vibration levels and no further failure reported. Study indicates that more attention is warranted for small-bore attachments both in design stage and during operation. It is recommended to remove SBCs wherever possible, redesigning them so they are less susceptible to vibrations and relocating them to areas of less base motion.
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Lerche, Andrew H., J. Jeffrey Moore, and Timothy C. Allison. "Experimental Study of Blade Vibration in Centrifugal Compressors." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45928.

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Blade vibration in turbomachinery is a common problem that can lead to blade failure by high cycle fatigue. Although much research has been performed on axial flow turbomachinery, little has been published for radial flow machines such as centrifugal compressors and radial inflow turbines. This work develops a test rig that measures the resonant vibration of centrifugal compressor blades. The blade vibrations are caused by the wakes coming from the inlet guide vanes. These vibrations are measured using blade mounted strain gauges during a rotating test. The total damping of the blade response from the rotating test is compared to the damping from the modal testing performed on the impeller. The mode shapes of the response and possible effects of mistuning are also discussed. The results show that mistuning can affect the phase cancellation which one would expect to see on a system with perfect cyclic symmetry.
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Wachter, J. "Analysis of Impeller Vibration in Radial Compressors." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-219.

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The prediction of the dynamic behaviour of the impellers is of considerable importance in the design of turbomachines. The excitation possibilities of the radial impellers by the forces or imposed displacements are various and an appreciation of the life of radial impellers is strongly bounded to an accurate dynamic analysis. Therefore, it is necessary to analyze them in order to improve the geometry or modify the design. In order to better understand and explain the dynamic behaviour of impellers, a series of impeller models with various numbers of blades of radial or tangential extention have been examined. Because of complexity of analytical analysis shown in earlier works, the eigenfrequencies and modes of the impellers were evaluated using a Finite Element program. Interferometric holography served as a means to visualize the dynamic behaviour of the impellers. An experimental modal analysis was used to identify the modal parameters. A detailed application of these methods to an actual centrifugal impeller was also reported along with theoretical and experimental investigations on the impeller models.
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Rämmal, Hans, and Mats Abom. "Experimental Determination of Sound Transmission in Turbo-Compressors." In SAE 2009 Noise and Vibration Conference and Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2009. http://dx.doi.org/10.4271/2009-01-2045.

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Srinivasan, Anand. "Differentiating Benign and Unstable Vibrations in Integral Geared Centrifugal Compressors." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-69071.

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Industrial turbomachinery pose several rotordynamic challenges with the ever expanding envelope of design parameters. Monitoring and understanding vibration signatures of rotating equipment remains to be more of an art, despite the availability of state-of-the-art design and diagnostic techniques. Vibration characteristics of any machine can broadly be classified as synchronous or non-synchronous spectra. While synchronous vibrations can be fairly easily mitigated by balancing, non-synchronous vibrations typically necessitate a more involved treatment and analysis based on the nature of the problem. A rotor-bearing system is said to be unstable if the amplitude of vibration increases with time in an outward spiraling orbit, until the rotor contacts the stator. In the rotordynamics literature, a sub-synchronous vibration is typically associated with rotor-bearing instability. However, although it seems counter intuitive, not all non-synchronous vibrations are necessarily unstable (i.e., of the self-excited type). This paper focuses on classifying and differentiating benign sub-synchronous vibrations from potentially unstable ones, based on vibration data collected on integral geared centrifugal compressors. Guidelines have been suggested to appropriately correlate sub-synchronous vibrations with the health of a turbomachine. Both design techniques and measured vibration spectra have been presented to augment the discussions.
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D’Elia, Gianluca, and Giorgio Dalpiaz. "Incoming Stall Identification in Axial Compressors by Vibration Analysis." In ASME 2013 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/detc2013-12810.

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This work addresses on a complete vibro-acoustic characterization of an axial compressor with the aim to foresee the rotor instability. The tests were performed on a turboshaft Allison 250-C18. The compressor is composed of six axial stages and one centrifugal stage. Four vibration signals were simultaneously measured by means of accelerometers, while the acoustic signals were measured by means of two microphones. Two different kinds of tests have been carried out on the compressor that operates at constant speed: in the course of the first test the six signals were acquired at different positions of the throttle opening, whereas during the second test, the signals were acquired while the throttle was gradually opened. The test results show a sensitive increase of the sub-synchronous activity in the accelerometers spectrum map, moreover, closing the throttle, the amplitude of the spectrum components increases. These phenomena can be related to the rotating stall behavior.
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Meyer, Michael, and Cassandra Gentry-Grace. "Vibration Characteristics of Segmented Stator Assemblies in Axial Compressors." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26047.

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A common component in axial compressors used in turbo machinery applications is the segmented stator assembly with fixed airfoils attached to inner and outer bands forming a partial ring. Understanding the potential for vibratory responses of these components during engine operation is vital to avoid harmful vibrations. However, an accurate prediction of segmented stator assembly vibratory characteristics is difficult due to the partial nature of their cyclic symmetry and high part to part manufacturing variation. Numerous analyses related to laboratory tests, engine tests and theoretical studies have been performed to advance the understanding and better quantify the segmented stator assembly dynamic behavior. A summary of the component dynamic behavior is provided through a series of lessons learned from the various analyses completed. The segmented stator assemblies can be thought of as cyclically symmetric parts with properties of extreme mistuning. These properties are realized when one attempts to evaluate the components using experimental and theoretical approaches traditionally reserved for cyclically symmetric components. Specifically, harmonic indices are often employed to identify modes of interest in a cyclically symmetric system with reference to known engine order excitations. However, with segmented stator assemblies, there is a high density of modal frequency distribution across the engine operating range and mode shapes can suffer from significant contamination of the diametral patterns. These observations complicate linking specific modes to known engine order excitations. This study implements traditional FEA approaches and reduced order models in an attempt to predict the key vibratory modes of concern and to show which component features most significantly affect the vibratory characteristics of segmented stator assemblies. Observations made during bench tests are compared to theoretical analyses and confirm the challenges of assessing the dynamic properties of segmented stator assemblies. This work supports emerging segmented stator design evaluation techniques, an area that is critical to successful integration of these components into turbo machinery applications.
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Holzinger, F., F. Wartzek, M. Jüngst, H. P. Schiffer, and S. Leichtfuß. "Self-Excited Blade Vibration Experimentally Investigated in Transonic Compressors: Rotating Instabilities and Flutter." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43628.

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This paper investigates the vibrations that occurred on the blisk rotor of a 1.5-stage transonic research compressor designed for aerodynamic performance validation and tested in various configurations at Technische Universität Darmstadt. During the experimental test campaign self-excited blade vibrations were found near the aerodynamic stability limit of the compressor. The vibration was identified as flutter of the first torsion mode and occurred at design speed as well as in the part-speed region. Numerical investigations of the flutter event at design speed confirmed negative aerodynamic damping for the first torsion mode, but showed a strong dependency of aerodynamic damping on blade tip clearance. In order to experimentally validate the relation between blade tip clearance and aerodynamic damping, the compressor tests were repeated with enlarged blade tip clearance for which stability of the torsion mode was predicted. During this second experimental campaign, strong vibrations of a different mode limited compressor operation. An investigation of this second type of vibration found rotating instabilities to be the source of the vibration. The rotating instabilities first occur as an aerodynamic phenomenon and then develop into self-excited vibration of critical amplitude. In a third experimental campaign, the same compressor was tested with reference blade tip clearance and a non-axisymmetric casing treatment. Performance evaluation of this configuration repeatedly showed a significant gain in operating range and pressure ratio. The gain in operating range means that the casing treatment successfully suppresses the previously encountered flutter onset. The aeroelastic potential of the non-axisymmetric casing treatment is validated by means of the unsteady compressor data. By giving a description of all of above configurations and the corresponding vibratory behavior, this paper contains a comprehensive summary of the different types of blade vibration encountered with a single transonic compressor rotor. By investigating the mechanisms behind the vibrations, this paper contributes to the understanding of flow induced blade vibration. It also gives evidence to the dominant role of the tip clearance vortex in the fluid-structure-interaction of tip critical transonic compressors. The aeroelastic evaluation of the non-axisymmetric casing treatment is beneficial for the design of next generation casing treatments for vibration control.
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Holzinger, F., F. Wartzek, M. Nestle, H. P. Schiffer, and S. Leichtfuß. "Self-Excited Blade Vibration Experimentally Investigated in Transonic Compressors: Acoustic Resonance." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43618.

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This paper investigates the acoustically induced rotor blade vibration that occurred in a state-of-the-art 1.5-stage transonic research compressor. The compressor was designed with the unconventional goal to encounter self-excited blade vibration within its regular operating domain. Despite the design target to have the rotor blades reach negative aerodamping in the near stall region for high speeds and open inlet guide vane, no vibration occurred in that area prior to the onset of rotating stall. Self-excited vibrations were finally initiated when the compressor was operated at part speed with fully open inlet guide vane along nominal and low operating line. The mechanism of the fluid-structure-interaction behind the self-excited vibration is identified by means of unsteady compressor instrumentation data. Experimental findings point towards an acoustic resonance originating from separated flow in the variable inlet guide vanes. A detailed investigation based on highly resolved wall pressure data confirms this conclusion. The paper documents the spread in aerodynamic damping calculated by various partners with their respective aeroelastic tools for a single geometry and speed line. This significant spread proves the need for calibration of aeroelastic tools to reliably predict blade vibration. The paper contains a concise categorization of flow induced blade vibration and defines criteria to quickly distinguish the different types of blade vibration. It further gives a detailed description of a novel test compressor and thoroughly investigates the encountered rotor blade vibration.
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Haupt, U., A. N. Abdelhamid, N. Kaemmer, and M. Rautenberg. "Excitation of Blade Vibration by Flow Instability in Centrifugal Compressors." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-283.

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Experiments were conducted to investigate the interactions between blade vibrations and self-excited flow oscillations in a high performance centrifugal compressor system. Unsteady pressure fluctuations and dynamic stress levels were measured during compressor operation near choke, in self-excited oscillating flow conditions and near surge for four different speed lines. The unsteady pressure field for every operating condition was determined from the simultaneous recording of the output of twelve dynamic pressure transducers which were successively positioned in two peripheral and one meridional planes. Corresponding blade vibration data were collected using an eight channel telemetry system transmitting the outputs of semi-conductor strain gages located on different blades. Analysis of the measurements showed that the unsteady pressure field due to self-excited flow oscillations can be characterized by multiples of rotating and non-rotating pressure patterns at different frequencies. The blade vibration signals clearly demonstrated the excitation of the blade by each of the different unsteady pressure patterns and the frequencies of the unsteady flow field demonstrates the complexity of this flow phenomena and the need to understand the mechanism of its occurrence in order to avoid blade resonance excitation and failure during compressor operation.
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Reports on the topic "Compressors – Vibration"

1

Davey, Gordon. Vibration Reduction in Balanced Linear Compressors. Fort Belvoir, VA: Defense Technical Information Center, April 2001. http://dx.doi.org/10.21236/ada387915.

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Yashar, David A., and W. Vance Payne. Vibration signatures for three positive displacement compressors. Gaithersburg, MD: National Institute of Standards and Technology, 2004. http://dx.doi.org/10.6028/nist.ir.7183.

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Roman, Kenneth M. The Use MEMS to Detect Vibrations Associated With Abnormal Scroll Compressor Operation. Fort Belvoir, VA: Defense Technical Information Center, May 2000. http://dx.doi.org/10.21236/ada389659.

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