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Journal articles on the topic 'COMPRESSOR BLADES DETERIORATION'

Author: Grafiati

Published: 11 September 2023

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1

Gilge, Philipp, Andreas Kellersmann, Jens Friedrichs, and Jörg R. Seume. "Surface roughness of real operationally used compressor blade and blisk." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 14 (2019): 5321–30. http://dx.doi.org/10.1177/0954410019843438.

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Deterioration of axial compressors is in general a major concern in aircraft engine maintenance. Among other effects, roughness in high-pressure compressor reduces the pressure rise and thus efficiency, thereby increasing the specific fuel consumption of an engine. Therefore, it is important to improve the understanding of roughness on compressor blading and their impact on compressor performance. To investigate the surface roughness of rotor blades of a compressors, different stages of an axial high-pressure compressor and a first-stage blisk (BLade–Integrated–dISK) of a regional aircraft eng

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2

Li, Yan-Ling, and Abdulnaser I. Sayma. "Computational fluid dynamics simulations of blade damage effect on the performance of a transonic axial compressor near stall." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 229, no. 12 (2014): 2242–60. http://dx.doi.org/10.1177/0954406214553828.

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Gas turbine axial compressor blades may encounter damage during service for various reasons such as damage by debris from casing or foreign objects impacting the blades, typically near the rotor’s tip. This may lead to deterioration of performance and reduction in the surge margin. The damage breaks the cyclic symmetry of the rotor assembly; thus, computational fluid dynamics simulations have to be performed using full annulus compressor assembly. Moreover, downstream boundary conditions are unknown during rotating stall or surge, and simulations become difficult. This paper presents unsteady

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3

Ghenaiet, A., S. C. Tan, and R. L. Elder. "Prediction of an axial turbomachine performance degradation due to sand ingestion." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 4 (2005): 273–87. http://dx.doi.org/10.1243/095765005x7592.

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Erosion of compressor blades due to operation in particulate environments is a serious problem for the manufacturers and users of industrial and aeronautical gas turbines, because of drastic degradations in performance, mostly through blunting of blade leading edges, reduction of chord and increase of tip clearance and surface roughness. This paper presents a numerical study to assess the effects of erosion by sand ingestion on blade geometry deterioration and the subsequent performance degradation. These computations were carried out for an axial turbomachine in steps; first, calculations of

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4

Ma, Shuai, Jun Hu, Xuegao Wang, and Jiajia Ji. "Effect of Non-Uniformity of Rotor Stagger Angle on the Stability of a Low-Speed Axial Compressor." Energies 15, no. 8 (2022): 2714. http://dx.doi.org/10.3390/en15082714.

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It is well known that variations in stagger angle between rotor blades affect compressor performance. In this paper, the stagger angle of blade No. 8 is increased or decreased by six degrees for non-uniformity, and the influence of rotor non-uniformity caused by the change in only one blade stagger angle on the performance and stability of the compressor is investigated. The experimental results show that whether the local rotor stagger angle increases or decreases, the compressor stability will deteriorate. If the stagger angle of blade No. 8 is reduced by six degrees, the flow coefficient at

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5

Ngoret, Joshua K., and Venkata P. Kommula. "Role of Aluminide coating degradation on Inconel 713 LC used for Compressor Turbines (CT) of Short-haul Aircrafts." MRS Advances 3, no. 38 (2018): 2281–96. http://dx.doi.org/10.1557/adv.2018.207.

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ABSTRACTThis paper investigates the role degradation of protective diffusion aluminide coating on Inconel 713LC used for CT blades of short-haul aircraft fleet played in having the blades prematurely retired from service at 6378 hours, as opposed to their pre-set service time of 10000 hours. The blade samples were subjected to various examinations; X-ray diffraction (XRD), X-ray fluorescence (XRF), scanning electron microscopy (SEM) and energy dispersive spectroscopy (EDS) analyse at the; tips, airfoil, as well as the base, transverse and longitudinal, sectioned and unsectioned. As affirmed by

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6

Rendu, Quentin, and Loic Salles. "Development of a surrogate model for uncertainty quantification of compressor performance due to manufacturing tolerance." Journal of the Global Power and Propulsion Society 7 (August 4, 2023): 257–68. http://dx.doi.org/10.33737/jgpps/168293.

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In gas turbines and jet engines, stagger angle and tip gap variations between adjacent blades lead to the deterioration of performance. To evaluate the effect of manufacturing tolerance on performance, a CFD-based uncertainty quantification analysis is performed in this work. However, evaluating dozens of thousands of rotor assembly through CFD simulations would be computationally prohibitive. A surrogate model is thus developed to predict compressor performance given an ordered set of manufactured blades. The model is used to predict the influence of tip gap and stagger angle variations on ma

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7

Hönen, Herwart, and Matthias Panten. "Recontouring of Jet Engine Compressor Blades by Flow Simulation." International Journal of Rotating Machinery 7, no. 5 (2001): 365–74. http://dx.doi.org/10.1155/s1023621x01000306.

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In modern jet propulsion systems the core engine has an essential influence on the total engine performance. Especially the high pressure compressor plays an important role in this scheme. Substantial factors here are losses due to tip clearance effects and aerodynamic airfoil quality. During flight operation the airfoils are subject to wear and tear on the leading edge. These effects cause a shortening of the chord length and the leading edge profiles become deformed. This results in a deterioration of the engine efficiency performance level and a reduced stall margin.The paper deals with the

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8

Suder, K. L., R. V. Chima, A. J. Strazisar, and W. B. Roberts. "The Effect of Adding Roughness and Thickness to a Transonic Axial Compressor Rotor." Journal of Turbomachinery 117, no. 4 (1995): 491–505. http://dx.doi.org/10.1115/1.2836561.

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The performance deterioration of a high-speed axial compressor rotor due to surface roughness and airfoil thickness variations is reported. A 0.025 mm (0.001 in.) thick rough coating with a surface finish of 2.54–3.18 rms μm (100–125 rms μin.) is applied to the pressure and suction surface of the rotor blades. Coating both surfaces increases the leading edge thickness by 10 percent at the hub and 20 percent at the tip. Application of this coating results in a loss in efficiency of 6 points and a 9 percent reduction in the pressure ratio across the rotor at an operating condition near the desig

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9

Huang, Song, Jinxin Cheng, Chengwu Yang, Chuangxin Zhou, Shengfeng Zhao, and Xingen Lu. "Optimization Design of a 2.5 Stage Highly Loaded Axial Compressor with a Bezier Surface Modeling Method." Applied Sciences 10, no. 11 (2020): 3860. http://dx.doi.org/10.3390/app10113860.

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Due to the complexity of the internal flow field of compressors, the aerodynamic design and optimization of a highly loaded axial compressor with high performance still have three problems, which are rich engineering design experience, high dimensions, and time-consuming calculations. To overcome these three problems, this paper takes an engineering-designed 2.5-stage highly loaded axial flow compressor as an example to introduce the design process and the adopted design philosophies. Then, this paper verifies the numerical method of computational fluid dynamics. A new Bezier surface modeling

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10

Kachan, O., and S. Ulanov. "Features of the process of hot extrusion of blanks of the rotor blades of a GTE compressor." Innovative Materials and Technologies in Metallurgy and Mechanical Engineering, no. 1 (September 14, 2021): 41–46. http://dx.doi.org/10.15588/1607-6885-2021-2-7.

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Purpose. Improving the quality of manufacturing of blanks for compressor rotor blades by hot extrusion. Research methods and equipment. The research was carried out using a crank press with a force of 1000 kN, in split dies in accordance with a serial technological process. The dies were heated up to 150 ... 200 °С, to improve the work when extruding the blanks of the rotor blades made from the titanium alloy ВT8. The thickness of the copper coating was measured with an ИTMП-3 magnetic induction device with an error of ± 2 μm. X-ray spectral microanalysis was performed

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11

Fu, Xi, Chao Ma, Jiewei Lin, and Junhong Zhang. "Numerical Study on Vibration Response and Fatigue Damage of Axial Compressor Blade Considering Aerodynamic Excitation." Metals 11, no. 11 (2021): 1835. http://dx.doi.org/10.3390/met11111835.

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Axial compressor blades with a deformed initial torsion angle caused by aerodynamic excitation resonated at the working speed and changed the rule of fatigue damage accumulation. The fatigue life of a blade has a prediction error, even causing serious flight accidents if the effect of torque causing damage deterioration of the blade fatigue life is neglected. Therefore, in this paper, a uniaxial non-linear fatigue damage model was modified using the equivalent stress with torsional shear stress, and the proposed fatigue model including the torsional moment was used to study the compressor blad

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12

Batcho, P. F., J. C. Moller, C. Padova, and M. G. Dunn. "Interpretation of Gas Turbine Response Due to Dust Ingestion." Journal of Engineering for Gas Turbines and Power 109, no. 3 (1987): 344–52. http://dx.doi.org/10.1115/1.3240046.

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A measurement program currently underway at Arvin/Calspan Advanced Technology Center has been used in the evaluation of observed engine behavior during dust ingestion. The Pratt and Whitney TF33 turbofan and J57 turbojet were used in the investigation. Solid particle ingestion was found to erode the compressor blades and result in substantial performance deterioration. The engines were found to have increased susceptibility to surge at low power settings. The roles that anti-ice and intercompressor bleed airplay in surge avoidance are discussed. A discussion of the fuel controller behavior in

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13

Goeing, Jan, Hendrik Seehausen, Vladislav Pak, Sebastian Lueck, Joerg R. Seume, and Jens Friedrichs. "Influence of combined compressor and turbine deterioration on the overall performance of a jet engine using RANS simulation and Pseudo Bond Graph approach." Journal of the Global Power and Propulsion Society 4 (December 22, 2020): 296–308. http://dx.doi.org/10.33737/jgpps/131109.

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In this study, numerical models are used to analyse the influence of isolated component deterioration as well as the combination of miscellaneous deteriorated components on the transient performance of a high-bypass jet engine. For this purpose, the aerodynamic impact of major degradation effects in a high-pressure compressor (HPC) and turbine (HPT) is modelled and simulated by using 3D CFD (Computational Fluid Dynamics). The impact on overall jet engine performance is then modelled using an 1D Reduced Order Model (ROM). Initially, the HPC performance is investigated with a typical level of ro

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14

Qi, Gong W., and X. Hong Zhang. "Effect of a volute on the unsteady flow in the vane diffuser of a centrifugal compressor." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 230, no. 8 (2016): 773–91. http://dx.doi.org/10.1177/0957650916673935.

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A volute is the only circumferential asymmetric component in a centrifugal compressor, and thus, it should account for the circumferential asymmetry of the flow in a vane diffuser. This study performs a transient numerical analysis to investigate the effect of a volute on the flow in the vane diffuser of a centrifugal compressor under three operating conditions (near-stall, middle, and high mass flow). We compare numerical and experimental performance of the compressor, including polytropic efficiency, total pressure ratio, and unsteady pressure on a diffuser vane. The numerical scheme is prov

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15

Hamed, A., W. Tabakoff, and D. Singh. "Modeling of Compressor Performance Deterioration Due to Erosion." International Journal of Rotating Machinery 4, no. 4 (1998): 243–48. http://dx.doi.org/10.1155/s1023621x98000207.

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This paper presents the results of a simulation of compressor performance deterioration due to blade erosion. The simulation at both design and off-design conditions is based on a mean line row by row model, which incorporates the effects of blade roughness and tip clearance. The results indicate a pronounced effect of blade erosion on the compressor adiabatic efficiency and a lesser effect on the pressure ratio. The loss in performance is mainly caused by the increased blade surface roughness and was highest at 100% speed.

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16

Tabakoff, W. "Compressor Erosion and Performance Deterioration." Journal of Fluids Engineering 109, no. 3 (1987): 297–306. http://dx.doi.org/10.1115/1.3242664.

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Aircraft engines operating in areas where the atmosphere is polluted by small solid particles are typical examples of jet engines operating under hostile atmospheric environment. The particles may be different kinds of sand, volcanic ashes or others. Under these conditions, the gas and particles experience different degrees of turning as they flow through the engine. This is mainly due to the difference in their inertia. This paper presents the results of an investigation of the solid particle dynamics through a helicopter engine with inlet particle separator. The particle trajectories are com

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17

Kellersmann, Andreas, Gerald Reitz, and Jens Friedrichs. "Deterioration effects of coupled blisk blades." Journal of the Global Power and Propulsion Society 2 (October 10, 2018): CKB8N6. http://dx.doi.org/10.22261/jgpps.ckb8n6.

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Performance degradation due to wear of high pressure compressors (HPC) is a major concern in aero-engine operation and maintenance. Among other effects especially erosion of airfoils leads to changed aerodynamic behavior and therefore to deterioration. These affects engine performance parameter like thrust specific fuel consumption (TSFC) and exhaust gas temperature (EGT). Reaching EGT-limit, the engine typically has to be overhauled during a shop visit to restore safety standards and performance. During state of the art shop visits, engines are repaired based on EGT-specifications. To further

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18

Mao, Xiaochen, Bo Liu, and Tianquan Tang. "Effect of casing aspiration on the tip leakage flow in the axial flow compressor cascade." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 3 (2017): 225–39. http://dx.doi.org/10.1177/0957650917724598.

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Tip leakage flow is usually responsible for the deterioration of compressor performance and stability. The current paper conducts numerical simulations on the impact of casing aspiration on the axial compressor cascade performance. Three aspiration schemes with different chordwise coverage are studied and analyzed. It is found that the cascade performance can be effectively improved by the appropriate casing aspiration, and the optimum aspiration scheme should cover the area including the onset point of tip leakage vortex and its vicinity. The control mechanisms are different for the aspiratio

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19

Naeem, M. "Impacts of low-pressure (LP) compressor’s deterioration upon an aero-engine’s high-pressure (HP) turbine blade’s life consumption." Aeronautical Journal 110, no. 1106 (2006): 227–38. http://dx.doi.org/10.1017/s0001924000001202.

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AbstractSome in-service deterioration in any mechanical device, such as an aero-engine, is inevitable. As a result of experiencing a deterioration of efficiency and/or mass flow, an aero-engine will automatically adjust to a different set of operating characteristics; thereby frequently resulting in changes of rpm and/or turbine entry temperature in order to provide the same thrust. Rises in the turbine entry-temperatures and the high-pressure turbine’s rotational speed result in greater rates of creep and fatigue damage being incurred by the hot-end components and thereby higher engine’s life

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20

Liang, Dong, Donghai Jin, and Xingmin Gui. "Investigation of Seal Cavity Leakage Flow Effect on Multistage Axial Compressor Aerodynamic Performance with a Circumferentially Averaged Method." Applied Sciences 11, no. 9 (2021): 3937. http://dx.doi.org/10.3390/app11093937.

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The seal cavity leakage flow has a considerable impact on the performance of the aeroengine, especially on the multistage compressor. Thus, a quasi-three-dimensional simulation program named CAM is developed basing on circumferentially averaged throughflow method. The program enables a rapid diagnosis for the performance degradation of multistage compressor caused by labyrinth wear. The coupling flow field between the seal cavity leakage flow and the main flow field at the root of the shrouded stator of a high-loading three-stage compressor with inlet guide vanes (IGV) was simulated by CAM and

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21

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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22

Shi, Yan, Wenguo Xiang, and Shiyi Chen. "Research on Metal Supervision and Inspection Standards for Gas-steam Combined Cycle Units." E3S Web of Conferences 228 (2021): 01011. http://dx.doi.org/10.1051/e3sconf/202122801011.

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Domestic gas-steam combined cycle units start and stop frequently, and the load changes greatly, which accelerate the expansion of defects, such as fatigue, cracks, and organizational deterioration of metal components. In view of the problems caused by the material selection characteristics of gas-steam combined cycle units and the daily shutdown mode, several common typical cases of gas-steam combined cycle units are analyzed, such as compressor blade fatigue fracture, main steam combined valve body fatigue cracks, pipeline and pressure vessel weld fatigue cracks. As well, the gas-steam combi

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Shenouda, Emad F., Ian W. Nelson, and Richard J. Nelson. "Anterior transvertebral transposition of the spinal cord for the relief of paraplegia associated with congenital cervicothoracic kyphoscoliosis." Journal of Neurosurgery: Spine 5, no. 4 (2006): 374–79. http://dx.doi.org/10.3171/spi.2006.5.4.374.

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✓The authors describe a technique for the relief of spinal cord compression associated with congenital kyphoscoliosis. A 13-year-old girl with congenital cervicothoracic kyphoscoliosis had undergone in situ fusion; spastic paraparesis and bladder disturbance developed postoperatively. Spinal cord detethering and posterolateral decompression temporarily arrested the neurological deterioration; however, the patient’s condition then progressed to paraplegia with a partial sensory level at L-1. Imaging demonstrated persisting cord compression at the apex of the kyphotic curve. Transvertebral trans

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MacLeod, J. D., V. Taylor, and J. C. G. Laflamme. "Implanted Component Faults and Their Effects on Gas Turbine Engine Performance." Journal of Engineering for Gas Turbines and Power 114, no. 2 (1992): 174–79. http://dx.doi.org/10.1115/1.2906567.

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Under the sponsorship of the Canadian Department of National Defence, the Engine Laboratory of the National Research Council of Canada (NRCC) has established a program for the evaluation of component deterioration on gas turbine engine performance. The effect is aimed at investigating the effects of typical in-service faults on the performance characteristics of each individual engine component. The objective of the program is the development of a generalized fault library, which will be used with fault identification techniques in the field, to reduce unscheduled maintenance. To evaluate the

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25

Wang, Ming-Yang, Zi-Liang Li, Sheng-Feng Zhao, Yan-Feng Zhang, and Xin-Gen Lu. "Effects of Reynolds number and loading distribution on the aerodynamic performance of a high subsonic compressor airfoil." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 8 (2020): 1069–83. http://dx.doi.org/10.1177/0957650919899541.

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The laminar-turbulent transition process on the compressor blade surface is often induced by the laminar separation flow at low Reynolds number ( Re). In the present study, numerical simulations were conducted to investigate the structure of the laminar separation bubble and its effects on the profile loss of a high subsonic compressor airfoil under different Re conditions, and the mechanism for the performance deterioration of compressor airfoil at low Re was clarified. Besides, the airfoil was redesigned to obtain a series of airfoils with different loading distributions, and the aerodynamic

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Bashir, Khurram, Christopher Y. Cai, Thomas A. Moore, John N. Whitaker, and Mark N. Hadley. "Surgery for Cervical Spinal Cord Compression in Patients with Multiple Sclerosis." Neurosurgery 47, no. 3 (2000): 637–43. http://dx.doi.org/10.1097/00006123-200009000-00022.

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ABSTRACT OBJECTIVE The goal of this study was to investigate the clinical and paraclinical features, treatment, and outcomes of patients with multiple sclerosis (MS) and coexisting spinal cord compression secondary to either cervical spondylosis or cervical disc disease. Patients with MS commonly experience neurological disabilities that present as myelopathy associated with bladder dysfunction. For some patients with MS, however, this neurological deterioration may result from coexisting spinal cord compression attributable to either spondylosis or a herniated disc. Overlapping symptoms of th

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Kleopa, Kleopas A., Leslie N. Sutton, Joseph Ong, Gihan Tennekoon, and Albert E. Telfeian. "Conus medulla—cauda compression from nerve root hypertrophy in a child with Dejerine—Sottas syndrome: improvement with laminectomy and duraplasty." Journal of Neurosurgery: Spine 97, no. 2 (2002): 244–47. http://dx.doi.org/10.3171/spi.2002.97.2.0244.

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✓ This 7-year-old boy with Dejerine—Sottas syndrome caused by a mutation in the myelin protein zero gene began to suffer rapid deterioration with increasing leg weakness, loss of the ability to ambulate, and bowel and bladder incontinence. Magnetic resonance imaging of the spine revealed nerve root hypertrophy resulting in compression of the conus medullaris and cauda equina. Decompressive surgery was successful in reversing some of his deficits.

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Kurz, R., and K. Brun. "Degradation in Gas Turbine Systems." Journal of Engineering for Gas Turbines and Power 123, no. 1 (2000): 70–77. http://dx.doi.org/10.1115/1.1340629.

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Any prime mover exhibits the effects of wear and tear over time. The problem of predicting the effects of wear and tear on the performance of any engine is still a matter of discussion. Because the function of a gas turbine is the result of the fine-tuned cooperation of many different components, the emphasis of this paper is on the gas turbine and its driven equipment (compressor or pump) as a system, rather than on isolated components. We will discuss the effect of degradation on the package as part of a complex system (e.g., a pipeline, a reinjection station, etc.). Treating the gas turbine

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Datsenko, Vadym, and Ludmila Boyko. "Determining the influence of compressor flow path abrasive wear on the gas turbine engine characteristics." Eastern-European Journal of Enterprise Technologies 2, no. 1 (122) (2023): 12–24. http://dx.doi.org/10.15587/1729-4061.2023.275546.

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The operation of a gas turbine engine (GTE) in a dusty atmosphere leads to wear of the elements of the flowing part and, as a result, to a deterioration in its parameters and characteristics. Helicopter and tank gas turbine engines operating in a dusty atmosphere, as well as gas turbine units of compressor stations operated in areas with high dust concentrations, are subjected to the greatest wear. When operating GTE under such conditions, the compressor is subjected to stronger wear. In this regard, the task addressed in this paper is determining the effect of abrasive wear of the compressor

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Jhaveri, Subir N., Shivam K. Kiri, and Sharan S. Jhaveri. "Anterior Placement of Cemented Fenestrated Screws in Conjunction with Anterior Reconstruction in Elderly Patients with Severe Vertebral Collapse and Paraparesis." Back Bone Journal 3, no. 1 (2022): 20–23. http://dx.doi.org/10.13107/bbj.2022.v03i01.035.

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Background: Elderly patients with severe osteoporosis are prone to sustain osteoporotic vertebral compression fractures (OVCF’s). Sometimes, they undergo significant vertebral collapse and kyphosis, leading to significant canal compromise and neurological deterioration. Case Description: We present a case series of three patients, of which two had OVCF’s of L1 and L3, respectively, while one patient had Koch’s spine D12 and L1. All three cases had severe vertebral collapse leading to kyphosis, severe pain, and canal compromise, neurological deterioration with paraparesis, and bowel bladder inv

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Kokieva, Galia, Martha Ivanova, and Varvara Trofimova. "The study of reducing soil mechanical deformation in tilling." E3S Web of Conferences 273 (2021): 05006. http://dx.doi.org/10.1051/e3sconf/202127305006.

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Due to the use of heavy machines, mechanical deformation with the inevitable deterioration in its physico-biological properties is undergoing in agriculture of heavy machines and subfall layers of the soil. The density of the arable and subframe horizons increases, decreases, due to the moisture in the soil. The productivity of cultural plants is influenced by effective fertility not only arable layer, but also subfectant, so it is necessary to take into account the effects on them of agricultural machinery and tractors. At the first stage, the soil particles in close proximity to the paw are

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Goeing, Jan, Hendrik Seehausen, Lennart Stania, et al. "Virtual process for evaluating the influence of real combined module variations on the overall performance of an aircraft engine." Journal of the Global Power and Propulsion Society 7 (March 13, 2023): 95–112. http://dx.doi.org/10.33737/jgpps/160055.

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The effects of real combined variances in components and modules of aero engines, due to production tolerances or deterioration, on the performance of an aircraft engine are analysed in a knowledge-based process. For this purpose, an aero-thermodynamic virtual evaluation process that combines physical and probabilistic models to determine the sensitivities in the local module aerodynamics and the global overall performance is developed. Therefore, an automatic process that digitises, parameterises, reconstructs and analyses the geometry automatically using the example of a real turbofan high-p

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33

Kim, Beom Su, So Young Lee, Jun Hwan Choi, Mina Seok, Su yeon Ko, and Hyun Jung Lee. "Rapidly Progressing Dysphagia After Thoracic Spinal Cord Injury in a Patient With Ankylosing Spondylitis: A Case Report." Geriatric Orthopaedic Surgery & Rehabilitation 14 (March 2, 2023): 215145932311593. http://dx.doi.org/10.1177/21514593231159353.

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Introduction Ankylosing spondylitis (AS) is a chronic systemic inflammatory disease affecting the axial skeleton, including the sacroiliac joint, which causes vertebral fusion in the advanced stage. However, reports of anterior cervical osteophytes compressing the esophagus and causing dysphagia in patients with AS are rare. Here, we present the case of a patient with AS and anterior cervical osteophytes who exhibited rapidly progressing dysphagia after thoracic spinal cord injury (SCI). Case Presentation The patient, a 79-year-old man, was previously diagnosed with AS and had syndesmophytes a

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Siegal, Tzony, and Tali Siegal. "Surgical Decompression of Anterior and Posterior Malignant Epidural Tumors Compressing the Spinal Cord: A Prospective Study." Neurosurgery 17, no. 3 (1985): 424–32. http://dx.doi.org/10.1227/00006123-198509000-00005.

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Abstract Of 167 episodes of spinal epidural neoplastic compression, 86 were treated by operation. The surgical approach was prospectively selected according to the location of the tumor in the spinal canal. Decompression was achieved by 61 vertebral body resections (VBRs) and by 25 laminectomies. The indications for operation were: (a) neurological relapse after previous radiotherapy, (b) the need to make a tissue diagnosis, (c) a radioresistant tumor, and (d) neurological deterioration during radiotherapy. Before VBR, 28% (17 of 61) were still able to walk, 51% (31 of 61) were pareparetic, an

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Cearns, Michael D., Samantha Hettige, Paolo De Coppi, and Dominic N. P. Thompson. "Currarino syndrome: repair of the dysraphic anomalies and resection of the presacral mass in a combined neurosurgical and general surgical approach." Journal of Neurosurgery: Pediatrics 22, no. 5 (2018): 584–90. http://dx.doi.org/10.3171/2018.5.peds17582.

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OBJECTIVEIt is well established that Currarino syndrome (CS) may be associated with spinal dysraphism. Here, the authors report on 10 CS patients with dysraphic anomalies who had undergone a combined neurosurgical and general surgical approach to repair the dysraphic anomalies and resect the presacral mass in a single operation. They discuss the spectrum of spinal dysraphism that may coexist in CS in the context of its developmental etiology.METHODSChildren with a confirmed CS diagnosis who had undergone the combined operative approach were identified from a departmental database. Presenting f

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Morini, Mirko, Michele Pinelli, Pier Ruggero Spina, and Mauro Venturini. "Numerical Analysis of the Effects of Nonuniform Surface Roughness on Compressor Stage Performance." Journal of Engineering for Gas Turbines and Power 133, no. 7 (2011). http://dx.doi.org/10.1115/1.4002350.

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Gas turbine performance degradation over time is mainly due to the deterioration of compressor and turbine blades, which, in turn, causes a modification of the compressor and turbine performance maps. Since the detailed information about the actual modification of the compressor and turbine performance maps is usually unavailable, the component performance can be modeled and investigated by the following: scaling the overall performance map, using stage-by-stage models of the compressor and turbine, and scaling each single stage performance map to account for each stage deterioration, or perfo

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Goodhand, Martin N., Robert J. Miller, and Hang W. Lung. "The Impact of Geometric Variation on Compressor Two-Dimensional Incidence Range." Journal of Turbomachinery 137, no. 2 (2014). http://dx.doi.org/10.1115/1.4028355.

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An important question for a designer is how, in the design process, to deal with the small geometric variations which result from either the manufacture process or in-service deterioration. For some blade designs geometric variations will have little or no effect on the performance of a row of blades, while in others their effects can be significant. This paper shows that blade designs which are most sensitive are those which are susceptible to a distinct switch in the fluid mechanisms responsible for limiting blade performance. To demonstrate this principle, the sensitivity of compressor 2D i

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Abdelwahid, Mohammed Balla, Eimad Eldin Elhadi Musa, Hazim Mohammed Taha, Sohaib Osman Hamed, and Esra Abdulrahman Mohamed Alhassan. "Performance Analysis of Eroded Compressor Stage." Journal of Karary University for Engineering and Science, December 21, 2021. http://dx.doi.org/10.54388/jkues.v1i2.94.

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Erosion of compressor blades due to operation in dusty environments is a serious problem for the manufacturers and users of gas turbine engines, because of significant degradations in performance. This study has been devoted to estimating the change of performance parameters of an axial compressor stage due to erosive deterioration. The influence of erosion considered as consequences of a reduction of rotor blade airfoils, and an increase of tip clearance. The results of this study obtained using the CFD code “NUMECA Fine/Turbo”. This CFD code is a steady, quasi-three-dimensional Reynolds Aver

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Lorenz, Max, Markus Klein, Jan Hartmann, Christian Koch, and Stephan Staudacher. "Prediction of Compressor Blade Erosion Experiments in a Cascade Based on Flat Plate Specimen." Frontiers in Mechanical Engineering 8 (July 25, 2022). http://dx.doi.org/10.3389/fmech.2022.925395.

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Erosion is an essential deterioration mechanism in compressors of jet engines. Erosion damage predictions require the determination of erosion rates through flat plate experiments. The applicability of the erosion rates is limited to conditions that are comparable to the prevailing boundary conditions of the flat plate experiment. A performed dimensional analysis enables the correct transfer of the flat plate erosion rates to the presented physical calculation model through limits in spatial and time resolution. This efficient approach avoids computationally intensive single-impact computation

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Ishaque, Ghulam, Qun Zheng, Naseem Ahmad, Mingcong Luo, and Sanaullah Khushak. "Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor." International Journal of Turbo & Jet-Engines, March 10, 2022. http://dx.doi.org/10.1515/tjj-2021-0080.

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Abstract Two-phase flow CFD simulations are conducted to investigate the performance characteristics of an axial flow compressor operating under an excessive amount of water intrusion exposed to a rainy atmosphere. In order to obtain a certain compressor behavior under the water film irregularities, the blade surfaces are divided into a small number of regions depending on the film thickness. In addition, to examine the droplets interaction with rotating blades and splashing process, a self-compiled FORTRAN code has been used. The results showed that uneven roughening of blade surfaces is the

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Kurz, Rainer, Grant Musgrove, and Klaus Brun. "Experimental Evaluation of Compressor Blade Fouling." Journal of Engineering for Gas Turbines and Power 139, no. 3 (2016). http://dx.doi.org/10.1115/1.4034501.

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Fouling of compressor blades is an important mechanism leading to performance deterioration in gas turbines over time. Experimental and simulation data are available for the impact of specified amounts of fouling on the performance as well as the amount of foulants entering the engine for defined air filtration systems and ambient conditions. This study provides experimental data on the amount of foulants in the air that actually stick to a blade surface for different conditions. Quantitative results both indicate the amount of dust as well as the distribution of dust on the airfoil, for a dry

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Tabakoff, Widen, and Robert Mason. "Dust-Induced Deterioration of Compressor First Stage Blades in Supersonic Cascade Erosion Wind Tunnel." International Journal of Turbo and Jet Engines 24, no. 2 (2007). http://dx.doi.org/10.1515/tjj.2007.24.2.85.

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Kurz, Rainer, and Klaus Brun. "Fouling Mechanisms in Axial Compressors." Journal of Engineering for Gas Turbines and Power 134, no. 3 (2012). http://dx.doi.org/10.1115/1.4004403.

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Fouling of compressor blades is an important mechanism leading to performance deterioration in gas turbines over time. Fouling is caused by the adherence of particles to airfoils and annulus surfaces. Particles that cause fouling are typically smaller than 2 to 10 microns. Smoke, oil mists, carbon, and sea salts are common examples. Fouling can be controlled by appropriate air filtration systems, and can often be reversed to some degree by detergent washing of components. The adherence of particles is impacted by oil or water mists. The result is a build up of material that causes increased su

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Богоявленский, А., and A. Bogoyavlenskiy. "Metrological aspects of pre-flight anti-icing procedures for civil aircraft." World of measurement, September 25, 2019, 22–26. http://dx.doi.org/10.35400/1813-8667-2019-3-22-26.

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Snow-ice deposits formed on the outer surfaces of aircrafts on the ground during parking can have a negative impact during take-off due to the deterioration of aerodynamic and flight performance, a significant and even critical decrease in lift, increased drag, blocking controls, difficulty or blocking of landing gear retraction, damage to the blades of inlet guide vanes and/or the blades of an engine compressor. To exclude the influence of snow and ice deposits, anti-icing treatment is performed, including their removal and/or protection from subsequent formation. For

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Богоявленский, А., and A. Bogoyavlenskiy. "Metrological aspects of pre-flight anti-icing procedures for civil aircraft." World of measurement, November 21, 2019, 26–31. http://dx.doi.org/10.35400/1813-8667-2019-4-26-31.

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Snow-ice deposits formed on the outer surfaces of aircrafts on the ground during parking can have a negative impact during take-off due to the deterioration of aerodynamic and flight performance, a significant and even critical decrease in lift, increased drag, blocking controls, difficulty or blocking of landing gear retraction, damage to the blades of inlet guide vanes and/or the blades of an engine compressor. To exclude the influence of snow and ice deposits, anti-icing treatment is performed, including their removal and/or protection from subsequent formation. For this purpose, special an

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Morini, M., M. Pinelli, P. R. Spina, and M. Venturini. "Influence of Blade Deterioration on Compressor and Turbine Performance." Journal of Engineering for Gas Turbines and Power 132, no. 3 (2009). http://dx.doi.org/10.1115/1.4000248.

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Gas turbine operating state determination consists of the assessment of the modification due to deterioration and fault of performance and geometric data characterizing machine components. One of the main effects of deterioration and fault is the modification of compressor and turbine performance maps. Since detailed information about actual modification of component maps is usually unavailable, many authors simulate the effects of deterioration and fault by a simple scaling of the map itself. In this paper, stage-by-stage models of the compressor and the turbine are used in order to assess th

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Rao, P. Naga Srinivasa, and V. N. Achutha Naikan. "An Optimal Maintenance Policy for Compressor of a Gas Turbine Power Plant." Journal of Engineering for Gas Turbines and Power 130, no. 2 (2008). http://dx.doi.org/10.1115/1.2795762.

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This paper proposes a condition based maintenance policy for compressors of industrial gas turbine. Compressor blade fouling contributes a major performance loss in the operation of gas turbine. Water washing is usually done for recovery of the blade fouling problem. There exist two different washing methods, namely, online and offline washings. Many researchers suggested that performing a combined program of regular online washing plus periodic offline washing would give fruitful results with respect to economy. However, such studies are of empirical nature or have considered only determinist

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Döring, Felix, Stephan Staudacher, Christian Koch, and Matthias Weißschuh. "Modeling Particle Deposition Effects in Aircraft Engine Compressors." Journal of Turbomachinery 139, no. 5 (2017). http://dx.doi.org/10.1115/1.4035072.

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Airborne particles ingested in aircraft engines deposit on compressor blading and end walls. Aerodynamic surfaces degrade on a microscopic and macroscopic scale. Blade row, compressor, and engine performance deteriorate. Optimization of maintenance scheduling to mitigate these effects requires modeling of the deterioration process. This work provides a deterioration model on blade row level and the experimental validation of this model in a newly designed deposition test rig. When reviewing previously published work, a clear focus on deposition effects in industrial gas turbines becomes eviden

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Ghenaiet, Adel. "Study of Sand Particle Trajectories and Erosion Into the First Compression Stage of a Turbofan." Journal of Turbomachinery 134, no. 5 (2012). http://dx.doi.org/10.1115/1.4004750.

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Aero-engines operating in dusty environments are subject to ingestion of erodent particles leading to erosion damage of blades and a permanent drop in performance. This work concerns the study of particle dynamics and erosion of the front compression stage of a commercial turbofan. Particle trajectories simulations used a stochastic Lagrangian tracking code that solves the equations of motion separately from the airflow in a stepwise manner, while the tracking of particles in different cells is based on the finite element method. As the locations of impacts and rates of erosion were predicted,

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Malhotra, Ashima, Shraman Goswami, and Pradeep Amboor Madathil. "Performance deterioration of axial compressor rotor due to uniform and non-uniform surface roughness." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, March 14, 2022, 095441002110689. http://dx.doi.org/10.1177/09544100211068912.

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Surface roughness is a significant source of performance loss in gas turbine engines. The fan and compressor, being the initial components of the gas turbine engine, are more prone to surface roughness effects due to the ingestion of debris at low atmospheric conditions. This paper attempts to numerically study the impact of uniform and non-uniform surface roughness on axial compressor rotor performance. NASA rotor 37 is used as the validation test case for the numerical methodology, and the results show a good match between the experimental and computational fluid dynamics data. Detailed flow

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