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Artículos de revistas sobre el tema "Inlet distortions"

Autor: Grafiati

Publicado: 7 de diciembre de 2024

Última modificación: 31 de julio de 2025

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1

Ariga, I., S. Masuda, and A. Ookita. "Inducer Stall in a Centrifugal Compressor With Inlet Distortion." Journal of Turbomachinery 109, no. 1 (1987): 27–35. http://dx.doi.org/10.1115/1.3262066.

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The effects of inlet distortion on the inducer stall in a centrifugal compressor are investigated. Cases of both radial and circumferential distortion are investigated. It is shown that the rotating stall onset is amplified by radial distortions, and restrained by circumferential distortions. These results are compared with calculations based on the small disturbance theory. The authors find that the stall onset is governed by the characteristic parameters related to the lower flow rate region for radial distortions, but affected by those of the higher flow rate region for circumferential dist

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2

Lowe, K. Todd. "Laser velocimetry for turbofan inlet distortion applications." Aircraft Engineering and Aerospace Technology 92, no. 1 (2020): 20–26. http://dx.doi.org/10.1108/aeat-11-2018-0285.

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Purpose The purpose of this paper is to assess state-of-the-art techniques for quantifying flow distortion in the inlets of turbofan engines, particularly with respect to the prospects for future flight applications. Design/methodology/approach To adequately characterize the flow fields of complex aircraft inlet distortions, the author has incorporated laser velocimetry techniques, namely, stereoscopic particle image velocimetry (PIV) and Doppler velocimetry based on filtered Rayleigh scattering (FRS), into inlet distortion studies. Findings Overall, the results and experience indicate that th

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3

Pazur, W., and L. Fottner. "The Influence of Inlet Swirl Distortions on the Performance of a Jet Propulsion Two-Stage Axial Compressor." Journal of Turbomachinery 113, no. 2 (1991): 233–40. http://dx.doi.org/10.1115/1.2929091.

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Aeroengine intakes containing S-shaped diffusers produce different types of inlet swirl distortions and essentially a combination of a twin swirl and a bulk swirl. The main object of this investigation was to assess the influence of inlet swirl distortions on the performance of a transonic two-stage axial compressor installed in a turbo jet bypass engine Larzac 04. A typical inlet swirl distortion was simulated by a delta-wing in front of the engine. An experimental method was investigated to measure the performance map of the installed low-pressure compressor for different engine operating li

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4

Fang, Yibo, Dakun Sun, Xu Dong, and Xiaofeng Sun. "Effects of Inlet Swirl Distortion on a Multi-Stage Compressor with Inlet Guide Vanes and Stall Margin Enhancement Method." Aerospace 10, no. 2 (2023): 141. http://dx.doi.org/10.3390/aerospace10020141.

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Inlet swirl distortion is generally considered as a type of velocity distortion, and inlet guide vanes (IGVs) are widely used in the multi-stage compressor of aero-engines to eliminate the tangential velocity of the swirl flow. However, few studies have explored whether there still exists some negative influence of inlet swirl distortion on the compressor, even after the installation of IGVs. Therefore, in this study, the influence of various types of inlet swirl distortions on a multi-stage compressor with the installation of IGVs is investigated. A swirl distortion generator installed in the

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5

Hah, C., D. C. Rabe, T. J. Sullivan, and A. R. Wadia. "Effects of Inlet Distortion on the Flow Field in a Transonic Compressor Rotor." Journal of Turbomachinery 120, no. 2 (1998): 233–46. http://dx.doi.org/10.1115/1.2841398.

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The effects of circumferential distortions in inlet total pressure on the flow field in a low-aspect-ratio, high-speed, high-pressure-ratio, transonic compressor rotor are investigated in this paper. The flow field was studied experimentally and numerically with and without inlet total pressure distortion. Total pressure distortion was created by screens mounted upstream from the rotor inlet. Circumferential distortions of eight periods per revolution were investigated at two different rotor speeds. The unsteady blade surface pressures were measured with miniature pressure transducers mounted

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6

Pečinka, Jiří, Gabriel Thomas Bugajski, Petr Kmoch, and Adolf Jílek. "JET ENGINE INLET DISTORTION SCREEN AND DESCRIPTOR EVALUATION." Acta Polytechnica 57, no. 1 (2017): 22–31. http://dx.doi.org/10.14311/ap.2017.57.0022.

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Total pressure distortion is one of the three basic flow distortions (total pressure, total temperature and swirl distortion) that might appear at the inlet of a gas turbine engine (GTE) during operation. Different numerical parameters are used for assessing the total pressure distortion intensity and extent. These summary descriptors are based on the distribution of total pressure in the aerodynamic interface plane. There are two descriptors largely spread around the world, however, three or four others are still in use and can be found in current references. The staff at the University of De

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7

Leinhos, Dirk C., Norbert R. Schmid, and Leonhard Fottner. "The Influence of Transient Inlet Distortions on the Instability Inception of a Low-Pressure Compressor in a Turbofan Engine." Journal of Turbomachinery 123, no. 1 (2000): 1–8. http://dx.doi.org/10.1115/1.1330271.

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While studies on compressor flow instabilities under the presence of inlet distortions have been carried out with steady distortions in the past, the investigation presented here focuses on the influence of transient inlet distortions as generated by variable geometry engine intakes of super- and hypersonic aircraft on the characteristic and the nature of the instability inception of a LPC. The flow patterns (total pressure distortion with a superimposed co- or counterrotating swirl) of the distortions are adopted from a hypersonic concept aircraft. A LARZAC 04 twin-spool turbofan was operated

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8

Ng, Eddie Yin-Kwee, Ningyu Liu, Hong Ngiap Lim, and Daniel Tan. "An Improved Integral Method for Prediction of Distorted Inlet Flow Propagation in Axial Compressor." International Journal of Rotating Machinery 2005, no. 2 (2005): 117–27. http://dx.doi.org/10.1155/ijrm.2005.117.

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An improved integral method is proposed and developed for the quantitative prediction of distorted inlet flow propagation through axial compressor. The novel integral method is formulated using more appropriate and practical airfoil characteristics, with less assumptions needed for derivation. The results indicate that the original integral method (Kim et al., 1996) underestimated the propagation of inlet flow distortion. The effects of inlet flow parameters on the propagation of inlet distortions as well as on the compressor performance and characteristic are simulated and analyzed. From the

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9

Schmid, Norbert R., Dirk C. Leinhos, and Leonhard Fottner. "Steady Performance Measurements of a Turbofan Engine With Inlet Distortions Containing Co- and Counterrotating Swirl From an Intake Diffuser for Hypersonic Flight." Journal of Turbomachinery 123, no. 2 (2000): 379–85. http://dx.doi.org/10.1115/1.1343466.

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The influence of distorted inlet flow on the steady and unsteady performance of a turbofan engine, which is a component of an air-breathing combined propulsion system for a hypersonic transport aircraft, is reported in this paper. The performance and stability of this propulsion system depend on the behavior of the turbofan engine. The complex shape of the intake duct causes inhomogeneous flow at the engine inlet plane, where total pressure and swirl distortions are present. The S-bend intakes are installed axisymmetrically left and right into the hypersonic aircraft, generating axisymmetric m

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10

Engeda, Abraham, Yunbae Kim, Ronald Aungier, and Gregory Direnzi. "The Inlet Flow Structure of a Centrifugal Compressor Stage and Its Influence on the Compressor Performance." Journal of Fluids Engineering 125, no. 5 (2003): 779–85. http://dx.doi.org/10.1115/1.1601255.

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The performance of centrifugal compressors can be seriously degraded by inlet flow distortions that result from an unsatisfactory inlet configuration. In this present work, the flow is numerically simulated and the flow details are analyzed and discussed in order to understand the performance behavior of the compressor exposed to different inlet configurations. In a previous work, complementary to this present work, experimental tests were carried out for the comparison of a centrifugal compressor stage performance with two different inlet configurations: one of which was a straight pipe with

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11

Yang, Bo, and Guoming Zhu. "Impacts of Inlet Circumferential Distortions on the Aerodynamic Performance of a Transonic Axial Compressor." Processes 11, no. 7 (2023): 2175. http://dx.doi.org/10.3390/pr11072175.

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Distortion, such as total pressure distortion, is a common phenomenon at the inlet of an axial compressor. Nonuniform inflow can greatly affect the aerodynamic performance and the stability of the compressor. In this paper, a sinusoidal distortion model is used at the inlet. Then, a series of unsteady computational fluid dynamics (CFD) simulations with a full-annulus model is conducted. Three kinds of the total pressure distortions, such as circumferentially covering 60, 120, and 180-degs sectors above 70% span of the blade at the inlet section, are adopted. Based on the results, how the rotat

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12

Baretter, Alberto, Benjamin Godard, Pierric Joseph, et al. "Experimental and Numerical Analysis of a Compressor Stage under Flow Distortion." International Journal of Turbomachinery, Propulsion and Power 6, no. 4 (2021): 43. http://dx.doi.org/10.3390/ijtpp6040043.

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On many occasions, fan or compressor stages have to face azimuthal flow distortion at inlet, which affects their performance and stability. These flow distortions can be caused by external events or by some particular geometrical features. The aim of this work is to propose a joined numerical and experimental analysis of the flow behavior in a single axial compressor stage under flow distortion. The distortions are generated by different grids that are placed upstream to the rotor. Experimentally, the flow analysis is based on the measurements obtained by a series of unsteady pressure sensors

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13

Li, H. D., and L. He. "Single-Passage Analysis of Unsteady Flows Around Vibrating Blades of a Transonic Fan Under Inlet Distortion." Journal of Turbomachinery 124, no. 2 (2002): 285–92. http://dx.doi.org/10.1115/1.1450567.

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Computations of unsteady flows due to inlet distortion driven blade vibrations, characterized by long circumferential wavelengths, typically need to be carried out in multi-passage/whole-annulus domains. In the present work, a single-passage three-dimensional unsteady Navier-Stokes approach has been developed and applied to unsteady flows around vibrating blades of a transonic fan rotor (NASA Rotor-67) with inlet distortions. The phase-shifted periodic condition is applied using a Fourier series based method, “shape-correction,” which enables a single-passage solution to unsteady flows under i

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14

Longley, J. P., H. W. Shin, R. E. Plumley, et al. "Effects of Rotating Inlet Distortion on Multistage Compressor Stability." Journal of Turbomachinery 118, no. 2 (1996): 181–88. http://dx.doi.org/10.1115/1.2836624.

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In multispool engines, rotating stall in an upstream compressor will impose a rotating distortion on the downstream compressor, thereby affecting its stability margin. In this paper experiments are described in which this effect was simulated by a rotating screen upstream of several multistage low-speed compressors. The measurements are complemented by, and compared with, a theoretical model of multistage compressor response to speed and direction of rotation of an inlet distortion. For corotating distortions (i.e., distortions rotating in the same direction as rotor rotation), experiments sho

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15

Guo, Jin, and Jun Hu. "Development of body force model for steady inlet distortions in high-speed multistage compressor." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 9 (2016): 1650–59. http://dx.doi.org/10.1177/0954410016656880.

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This study aims at establishing a three-dimensional numerical model, compressor aerodynamic performance analysis model, to simulate the impact of complicated distorted flow on multistage axial flow compressor based on the body force model. The model solves the compressible three-dimensional Euler equations, which are modified to include source terms representing the effect of the blade rows. In this study, the association between blade source terms and entry Mach number together with attack angle could be established with the deviation angle model and loss model. In this paper, compressor aero

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16

Zhang, Mingming, and Anping Hou. "Investigation on stall inception of axial compressor under inlet rotating distortion." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 231, no. 10 (2015): 1859–70. http://dx.doi.org/10.1177/0954406215623978.

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This paper applies a numerical approach to improve the understanding of reaction to various inflow conditions for the compressor system and the mechanism of stall inception under rotating inflow distortions. Full annulus, unsteady, three-dimensional computational fluid dynamics has been used to simulate an axial low-speed compressor operating under rotating distorted inflow conditions. The development of the flow through the rotor is then explained in terms of the redistribution of the flow field and the process of stall inception. The results suggest that the increased flow incidence close to

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17

Sanchez Villacreses, Santiago, Jun Yao, Yufeng Yao, and Budi Chandra. "Investigation of Microjet Engine Inlet Pressure Distortions at Angled Inflow Velocity Conditions." Fluids 10, no. 2 (2025): 49. https://doi.org/10.3390/fluids10020049.

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The Armfield CM14 microjet axial flow turbine engine has been tested in open space at ambient conditions with engine inlet pressure at the aerodynamic interface plane (AIP) measured by a built-in pressure sensor for validating computational fluid dynamics (CFD) studies. A three-dimensional computational domain of the test engine intake duct configuration is defined, followed by mesh convergence studies. The latter results in a fine mesh of 5.7 million cells on which CFD-predicted engine inlet pressures are in good agreement with the experimental measurements at the AIP face for 20–100% throttl

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18

Verma, Vishwas, Gursharanjit Singh, and AM Pradeep. "The effect of inlet distortion on low bypass ratio turbofan engines." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 8 (2020): 1395–413. http://dx.doi.org/10.1177/0954410020909190.

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Inlet flow non-uniformity, commonly known as inflow distortion, has been a long-standing problem in the history of gas turbine engines. Distortion can be present in the form of total pressure, total temperature or inflow incidence or any combinations of these. The search for better and robust performance requires engines that can sustain a large amount of inlet distortion without considerable loss in the thrust. In the present paper, the effect of total pressure distortion on a single-stage compressor and low bypass ratio fans are studied. Distortion near hub and tip in the form of step radial

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19

Li, Yue Feng, Qing Zhen Yang, and Xue Jiao Deng. "Aerodynamic Design Investigation on Inlet-Exhaust System Using Super-Ellipse Method." Applied Mechanics and Materials 246-247 (December 2012): 446–50. http://dx.doi.org/10.4028/www.scientific.net/amm.246-247.446.

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Generally, the shape index n is selected in a form when design the inlet-exhaust system using traditional super-ellipse method. Unfortunately, this selection process is time-consuming and not precise enough, so the cross-section designed by super-ellipse method may get distortions easily, which influences the inner flow and the total pressure of the inlet-exhaust system greatly. Associating the shape index n with the variation pattern of the inlet-exhaust cross-section, an improved super-ellipse method is developed to design the inlet-exhaust system. This method ensures the precision and uniqu

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20

Cousins, W. T., K. K. Dalton, T. T. Andersen, and G. A. Bobula. "Pressure and Temperature Distortion Testing of a Two-Stage Centrifugal Compressor." Journal of Engineering for Gas Turbines and Power 116, no. 3 (1994): 567–73. http://dx.doi.org/10.1115/1.2906857.

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Altitude pressure and temperature inlet distortion testing of the two-stage centrifugal compressor in the T800-LHT-800 engine is described. The test setup and the testing techniques are reviewed and the results of the test are presented. The generation of classical 180 deg patterns of both pressure and temperature distortion is discussed. Temperature distortion was created using a hydrogen burner system while pressure distortion was created in the classical manner, using screens. Results of both individual and combined temperature and pressure distortions in both opposed and concurrent pattern

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21

Taghavi Zenouz, Reza, Mehran Eshaghi Sir, and Mohammad Hosein Ababaf Behbahani. "Performance of a Low Speed Axial Compressor Rotor Blade Row under Different Inlet Distortions." Mechanical Sciences 8, no. 1 (2017): 127–36. http://dx.doi.org/10.5194/ms-8-127-2017.

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Abstract. Responses of an axial compressor isolated rotor blade row to various inlet distortions have been investigated utilizing computational fluid dynamic technique. Distortions have been imposed by five screens of different geometries, but with the same blockage ratio. These screens were embedded upstream of the rotor blade row. Flow fields are simulated in detail for compressor design point and near stall conditions. Performance curves for distorted cases are extracted and compared to the undisturbed case. Flow simulations and consequent performance characteristics show that the worst cas

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22

Manwaring, S. R., and S. Fleeter. "Forcing Function Effects on Rotor Periodic Aerodynamic Response." Journal of Turbomachinery 113, no. 2 (1991): 312–19. http://dx.doi.org/10.1115/1.2929109.

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A series of experiments are performed in an extensively instrumented axial flow research compressor to investigate the effects of different low reduced frequency aerodynamic forcing functions and steady loading level on the gust-generated unsteady aerodynamics of a first-stage rotor blade row. Two different two-per-rev forcing functions are considered: (1) the velocity deficit from two 90 deg circumferential inlet flow distortions, and (2) the wakes from two upstream obstructions, which are characteristic of airfoil or probe excitations. The data show that the wake-generated rotor row first ha

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23

Giuliani, James E., and Jen-Ping Chen. "Fan Response to Boundary-Layer Ingesting Inlet Distortions." AIAA Journal 54, no. 10 (2016): 3232–43. http://dx.doi.org/10.2514/1.j054762.

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24

Levy, Y., and J. Pismenny. "Nonlinear Oscillations in Compressor under Rotating Inlet Distortions." International Journal of Turbo and Jet Engines 23, no. 3 (2006): 165–72. http://dx.doi.org/10.1515/tjj.2006.23.3.165.

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25

Sohail, Muhammad Umer, Hossein Raza Hamdani, Asad Islam, et al. "Prediction of Non-Uniform Distorted Flows, Effects on Transonic Compressor Using CFD, Regression Analysis and Artificial Neural Networks." Applied Sciences 11, no. 8 (2021): 3706. http://dx.doi.org/10.3390/app11083706.

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Non-uniform inlet flows frequently occur in aircrafts and result in chronological distortions of total temperature and total pressure at the engine inlet. Distorted inlet flow operation of the axial compressor deteriorates aerodynamic performance, which reduces the stall margin and increases blade stress levels, which in turn causes compressor failure. Deep learning is an efficient approach to predict catastrophic compressor failure, and its stability for better performance at minimum computational cost and time. The current research focuses on the development of a transonic compressor instabi

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26

Han, Fenghui, Zhe Wang, Yijun Mao, Jiajian Tan, and Wenhua Li. "Flow Control of Radial Inlet Chamber and Downstream Effects on a Centrifugal Compressor Stage." Applied Sciences 11, no. 5 (2021): 2168. http://dx.doi.org/10.3390/app11052168.

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Radial inlet chambers are widely used in various multistage centrifugal compressors, although they induce extra flow loss and inlet distortions. In this paper, the detailed flow characteristics inside the radial inlet chamber of an industrial centrifugal compressor have been numerically investigated for flow control and performance improvement. First, the numerical results are validated against the experimental data, and flow conditions inside the inlet chambers with different structures are compared. They indicate that, in the non-guide vane scheme, sudden expansions, tangential flows and flo

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27

Arshad, Ali, Qiushi Li, Simin Li, and Tianyu Pan. "Effects of inlet radial distortion on the type of stall precursor in low-speed axial compressor." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 1 (2016): 55–67. http://dx.doi.org/10.1177/0954410016670679.

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Experimental investigations of the effect of inlet blade loading on the rotating stall inception process are carried out on a single-stage low-speed axial compressor. Temporal pressure signals from the six high response pressure transducers are used for the analysis. Pressure variations at the hub are especially recorded during the stall inception process. Inlet blade loading is altered by installing metallic meshed distortion screens at the rotor upstream. Three sets of experiments are performed for the comparison of results, i.e. uniform inlet flow, tip, and hub distortions, respectively. Re

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28

Tan, J., X. Wang, D. Qi, and R. Wang. "The effects of radial inlet with splitters on the performance of variable inlet guide vanes in a centrifugal compressor stage." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 225, no. 9 (2011): 2089–105. http://dx.doi.org/10.1177/0954406211407799.

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Variable inlet guide vanes (VIGVs) can regulate pressure ratio and mass flow at constant rotational speed in centrifugal compressors as a result of inducing a controlled prewhirl in front of impellers. Radial inlets and VIGVs are typical upstream components in front of the first-stage impellers in many industrial centrifugal compressors. However, previous investigations on VIGVs in centrifugal compressors were mostly conducted under the condition of axial inlets, and this study aims to focus on the effects of radial inlet on the VIGVs performance of a centrifugal compressor stage. The axial in

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29

Liu, ZX, HZ Diao, XC Zhu, and ZH Du. "Numerical investigation of the axial compressor performance with inlet distortions." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 8 (2017): 1434–41. http://dx.doi.org/10.1177/0954410017699853.

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In this paper, a three-dimensional body force model for predicting compressor performance and stability is implemented in the Ansys CFX. The influence of the blade rows on the flow field is represented by the source terms of CFX-solver equation. At first, a high-speed and high-pressure-ratio transonic compressor with the clean inlet is investigated. The overall performance and the flow fields are in agreement well with those of the experimental date, so the model is reliable and correct. Then, the effects of the circumferential distortions in the inlet total pressure and the total temperature

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30

Xu, Dengke, Chen He, Dakun Sun, and Xiaofeng Sun. "Stall inception prediction of axial compressors with radial inlet distortions." Aerospace Science and Technology 109 (February 2021): 106433. http://dx.doi.org/10.1016/j.ast.2020.106433.

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31

Klein, A. "The relation between losses and entry-flow conditions in short dump diffusers for combustors." Aeronautical Journal 92, no. 920 (1988): 390–96. http://dx.doi.org/10.1017/s0001924000016523.

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SummaryAn experimental correlation is presented between the losses and the inlet flow conditions in short dump diffusers for turbojet combustors. Cascades of compressor blades upstream of the diffuser were used to make the flow field at inlet similar to that in a real jet engine. The flow field was altered in two ways — by varying the distance between the cascades and the diffuser inlet plane and by changing the blade aspect ratio. The measurements show clearly that distortions in the radial direction affect the losses to a much larger extent than non-uniformities in the circumferential direct

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32

Han, Fenghui, Yijun Mao, and Jiajian Tan. "Influences of flow loss and inlet distortions from radial inlets on the performances of centrifugal compressor stages." Journal of Mechanical Science and Technology 30, no. 10 (2016): 4591–99. http://dx.doi.org/10.1007/s12206-016-0930-y.

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33

Hynes, T. P., and E. M. Greitzer. "A Method for Assessing Effects of Circumferential Flow Distortion on Compressor Stability." Journal of Turbomachinery 109, no. 3 (1987): 371–79. http://dx.doi.org/10.1115/1.3262116.

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This paper describes the development of a new analysis to predict the onset of flow instability for an axial compressor operating in a circumferentially distorted inlet flow. A relatively simple model is used to examine the influence of various distortions in setting this instability point. It is found that the model reproduces known experimental trends for the loss of stability margin with increasing distortion amplitude and with changes in reduced frequency. In particular, there is a recognizable “critical sector angle” which characterizes loss of stability margin. To the authors’ knowledge,

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34

Voigt, Jonas, and Jens Friedrichs. "Development of a Multi-Segment Parallel Compressor Model for a Boundary Layer Ingesting Fuselage Fan Stage." Energies 14, no. 18 (2021): 5746. http://dx.doi.org/10.3390/en14185746.

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The present methodological study aims to assess boundary layer ingestion (BLI) as a promising method to improve propulsion efficiency. BLI utilizes the low momentum inflow of the wing or fuselage boundary layer for thrust generation in order to minimize the required propulsive power for a given amount of thrust for wing or fuselage-embedded engines. A multi-segment parallel compressor model (PCM) is developed to calculate the power saving from full annular BLI as occurring at a fuselage tail center-mounted aircraft engine, employing radially subdivided fan characteristics. Applying this method

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35

Bre´ard, C., M. Vahdati, A. I. Sayma, and M. Imregun. "An Integrated Time-Domain Aeroelasticity Model for the Prediction of Fan Forced Response due to Inlet Distortion." Journal of Engineering for Gas Turbines and Power 124, no. 1 (2000): 196–208. http://dx.doi.org/10.1115/1.1416151.

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The forced response of a low aspect-ratio transonic fan due to different inlet distortions was predicted using an integrated time-domain aeroelasticity model. A time-accurate, nonlinear viscous, unsteady flow representation was coupled to a linear modal model obtained from a standard finite element formulation. The predictions were checked against the results obtained from a previous experimental program known as “Augmented Damping of Low-aspect-ratio Fans” (ADLARF). Unsteady blade surface pressures, due to inlet distortions created by screens mounted in the intake inlet duct, were measured al

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36

Zhang, Meijie, and Xinqian Zheng. "Criteria for the matching of inlet and outlet distortions in centrifugal compressors." Applied Thermal Engineering 131 (February 2018): 933–46. http://dx.doi.org/10.1016/j.applthermaleng.2017.11.140.

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37

Manwaring, S. R., D. C. Rabe, C. B. Lorence, and A. R. Wadia. "Structures and Dynamics Committee Best Paper of 1996 Award: Inlet Distortion Generated Forced Response of a Low-Aspect-Ratio Transonic Fan." Journal of Turbomachinery 119, no. 4 (1997): 665–76. http://dx.doi.org/10.1115/1.2841176.

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This paper describes a portion of an experimental and computational program (ADLARF), which incorporates, for the first time, measurements of all aspects of the forced response of an airfoil row, i.e., the flow defect, the unsteady pressure loadings, and the vibratory response. The purpose of this portion was to extend the knowledge of the unsteady aerodynamics associated with a low-aspect-ratio transonic fan where the flow defects were generated by inlet distortions. Measurements of screen distortion patterns were obtained with total pressure rakes and casing static pressures. The unsteady pr

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38

Giel, P. W., J. R. Sirbaugh, I. Lopez, and G. J. Van Fossen. "Three-Dimensional Navier–Stokes Analysis and Redesign of an Imbedded Bellmouth Nozzle in a Turbine Cascade Inlet Section." Journal of Turbomachinery 118, no. 3 (1996): 529–35. http://dx.doi.org/10.1115/1.2836699.

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Experimental measurements in the inlet of a transonic turbine blade cascade showed unacceptable pitchwise flow nonuniformity. A three-dimensional, Navier–Stokes computational fluid dynamics (CFD) analysis of the imbedded bellmouth inlet in the facility was performed to identify and eliminate the source of the flow nonuniformity. The blockage and acceleration effects of the blades were accounted for by specifying a periodic static pressure exit condition interpolated from a separate three-dimensional Navier–Stokes CFD solution of flow around a single blade in an infinite cascade. Calculations o

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39

Mirzaev, Z. N., M. S. Guseynov, and T. G. Aigumov. "MATHEMATICAL MIXER MODEL WITH FORMATION OF HETERODYNE ANTIPHASE SIGNAL." Herald of Dagestan State Technical University. Technical Sciences 46, no. 3 (2019): 97–107. http://dx.doi.org/10.21822/2073-6185-2019-46-3-97-107.

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Objectives To carry out calculations involved in the design of a microwave mixer with a diplexer with the formation of the antiphase heterodyne signal using a slot resonator.Method In order to calculate and optimise the characteristics, design and topological parameters of microwave mixers, the results of the design bandpass filter PF and low-pass filter (LPF) mixers of through-feed type were used. The characteristics of mixers and their structural elements were calculated using the Serenade software package intended for the automated calculation of microwave devices. A distinct feature of des

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40

Rai, Man Mohan, and Robert P. Dring. "Navier-Stokes analyses of the redistribution of inlet temperature distortions in a turbine." Journal of Propulsion and Power 6, no. 3 (1990): 276–82. http://dx.doi.org/10.2514/3.25431.

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41

Mao, Yinbo, and Thong Q. Dang. "A three-dimensional body-force model for nacelle-fan systems under inlet distortions." Aerospace Science and Technology 106 (November 2020): 106085. http://dx.doi.org/10.1016/j.ast.2020.106085.

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42

Duvenhage, K., J. A. Vermeulen, C. J. Meyer, and D. G. Kröger. "Flow distortions at the fan inlet of forced-draught air-cooled heat exchangers." Applied Thermal Engineering 16, no. 8-9 (1996): 741–52. http://dx.doi.org/10.1016/1359-4311(95)00063-1.

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43

MAAMMEUR, Moustafa, Abdallah BENAROUS, Ahmed BETTAHAR, and Abdelkarim LIAZID. "Passive Flow Control for Centrifugal Compressors with Bents Intake Manifold." Mechanics 29, no. 5 (2023): 369–76. http://dx.doi.org/10.5755/j02.mech.30987.

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Centrifugal compressors installations often require bents conduits at the intake due to space constraints. The intake bent manifold creates flow distortion affecting unfavorably the global performance of the compressor. The degradation caused by the inadequate inlet conditions due to turbulence and inlet flow disturbance, which negatively affects the flowing fluid through the curved intake manifold. Hence, significant distortions, within presence of single or twin core vortices whirling off center of the impeller intake alter flow incidence angle and consequently the impeller circumferential e

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44

Yamamoto, K., and W. F. Ng. "THE DEVELOPMENT OF FLOW DISTORTIONS AT THE FAN FACE FOR AN AXISYMMETRIC SUPERSONIC INLET." Journal of Sound and Vibration 203, no. 1 (1997): 75–85. http://dx.doi.org/10.1006/jsvi.1996.0763.

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45

Sayma, A. I., M. Vahdati, and M. Imregun. "Multi-bladerow fan forced response predictions using an integrated three-dimensional time-domain aeroelasticity model." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 214, no. 12 (2000): 1467–83. http://dx.doi.org/10.1243/0954406001523425.

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A non-linear integrated aeroelasticity system to predict the forced vibration response of aero-engine fans is presented in this paper. The computational fluid dynamics (CFD) solver, which uses Favre-averaged Navier-Stokes equations on unstructured grids of mixed elements, is coupled to a modal model of the structure so that the effects of blade flexibility can be accommodated. The structural motion due to unsteady fluid forces is computed at every time step and the flow mesh is moved to follow the structure so that the resulting flow unsteadiness is determined in a time-accurate fashion. Two f

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46

Pinelli, L., G. Giannini, M. Marconcini, R. Pacciani, A. Notaristefano, and P. Gaetani. "The Effect of Entropy Waves Features on the Indirect Noise Generation within an Aeronautical High-Pressure Turbine stage." Journal of Physics: Conference Series 2893, no. 1 (2024): 012128. https://doi.org/10.1088/1742-6596/2893/1/012128.

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Abstract First stages of aeronautical high-pressure turbine are subjected to inlet distortions generated by the combustor systems. Such disturbances, characterized by velocity and temperature fluctuations, are referred to as vorticity and entropy waves and they are convected downstream by the main flow. Such disturbances interact with the turbine stages affecting the stage efficiency, heat exchange and generating noise emissions. This work summarizes a comprehensive numerical campaign on the effect of different Entropy Waves features (i.e. radial position, clocking and swirl direction) on the

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47

Salta, C. A., and D. G. Kröger. "Effect of inlet flow distortions on fan performance in forced draught air-cooled heat exchangers." Heat Recovery Systems and CHP 15, no. 6 (1995): 555–61. http://dx.doi.org/10.1016/0890-4332(95)90065-9.

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48

Han, Fenghui, Zhe Wang, Yijun Mao, Jiajian Tan, and Wenhua Li. "Experimental and numerical studies on the influence of inlet guide vanes of centrifugal compressor on the flow field characteristics of inlet chamber." Advances in Mechanical Engineering 12, no. 11 (2020): 168781402097490. http://dx.doi.org/10.1177/1687814020974909.

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Inlet chambers (IC) are the typical upstream component of centrifugal compressors, and inlet guide vanes in the IC have a great impact on its internal flow and aerodynamic loss, which will significantly influence the performance of the downstream compressor stages. In this paper, an experimental study was carried out on the flow characteristics inside a radial IC of an industrial centrifugal compressor, including five testing sections and 968 measuring points for two schemes with and without guide vanes. Detailed distributions of flow parameters on each section were obtained as well as the ove

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49

OOKITA, Akihiro, Shigeki MASUDA, and Ichiro ARIGA. "Effects of inlet distortions on performance characteristics of a centrifugal compressor. Investigations concerning the unstable phenomenon." Transactions of the Japan Society of Mechanical Engineers Series B 51, no. 472 (1985): 3970–79. http://dx.doi.org/10.1299/kikaib.51.3970.

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Mahalakshmi, N. V., G. Krithiga, S. Sandhya, J. Vikraman, and V. Ganesan. "Experimental investigations of flow through conical diffusers with and without wake type velocity distortions at inlet." Experimental Thermal and Fluid Science 32, no. 1 (2007): 133–57. http://dx.doi.org/10.1016/j.expthermflusci.2007.02.008.

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