Relevant bibliographies by topics / Labyrinth Seals

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  4. Book chapters
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Academic literature on the topic 'Labyrinth Seals'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Labyrinth Seals"

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Zhang, Xiumin, Mingfu Yin, and Huilai Sun. "Establishment and solution of governing equation for plana-grooved liquid seals based on three-control-volume theory." Industrial Lubrication and Tribology 72, no. 3 (November 18, 2019): 257–66. http://dx.doi.org/10.1108/ilt-06-2019-0228.

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Purpose This paper aims to study the dynamic characteristics of the straight-through labyrinth seals, which is applied on an oil sealing belt of hydrostatic support system (HSS) oil pocket, the establishment and solution process of seal governing equation is deduced. Design/methodology/approach The three-control-volume model theory is an efficient approach that is applied well. This paper starts with three relative governing equations for the flow characteristics of straight-through labyrinth seals in the plane direction. Referring to the establishment process of governing equations for circumferentially-grooved liquid seals, the governing equation based on space rectangular coordinate system is established, which are transformed into dimensionless equations through a nondimensionalized process and solved by a perturbation method. It contains a zeroth-order equation, through which a steady fluid distribution is determined, and a first-order equation, through which the seal’s dynamic coefficients can be acquired. Findings The governing equation for plane-grooved straight-through labyrinth seals can be established and solved by the three-control-volume theory. Practical implications This study have important guiding significance for further theoretical research and structural design of the straight-through labyrinth seals on the oil sealing belt of HSS oil pocket. Originality/value In this paper, a straight-through labyrinth seal is installed in an oil sealing belt. The three-control-volume governing equations is established in space rectangular coordinate system, and the shear force of the fluid Y-direction is different from the previous model.
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Lorencin, Ivan, Nikola Anđelić, Vedran Mrzljak, and Zlatan Car. "Exergy analysis of marine steam turbine labyrinth (gland) seals." Pomorstvo 33, no. 1 (June 28, 2019): 76–83. http://dx.doi.org/10.31217/p.33.1.8.

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The paper presents an exergy analysis of marine steam turbine labyrinth (gland) seals - an inevitable component of any marine steam turbine cylinder, in three different operating regimes. Throughout labyrinth seals, steam specific enthalpy can be considered as a constant because the results obtained by this assumption do not deviate significantly from the results of complex numerical models. Changes in labyrinth seals exergy efficiency and specific exergy destruction are reverse proportional. The analyzed labyrinth seals have high exergy efficiencies in each observed operating regime at the ambient temperature of 298 K (above 92%), what indicates seals proper operation. An increase in the ambient temperature resulted with a decrease in labyrinth seals exergy efficiency, but even at the highest observed ambient temperature of 318 K, seals exergy efficiency did not fall below 90.5% in each observed operating regime.
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Soto, E. A., and D. W. Childs. "Experimental Rotordynamic Coefficient Results for (a) a Labyrinth Seal With and Without Shunt Injection and (b) a Honeycomb Seal." Journal of Engineering for Gas Turbines and Power 121, no. 1 (January 1, 1999): 153–59. http://dx.doi.org/10.1115/1.2816303.

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Centrifugal compressors are increasingly required to operate at higher pressures, speeds, and fluid density. In these conditions, compressors are susceptible to rotordynamic instabilities. To remedy this situation, labyrinth seals have sometimes been modified by using shunt injection. In shunt injection, the gas is taken from the diffuser or discharge volute and injected into an upstream chamber of the balance-piston labyrinth seal. The injection direction can be radial or against rotation. This study contains the first measured rotordynamic data for labyrinth seals with shunt injection. A comparison has been made between conventional labyrinth seals, labyrinth seals with shunt injection (radial and against rotation), and a honeycomb seal. Labyrinth seals with injection against rotation are better able to control rotordynamic instabilities than labyrinth seals with radial injection; however, the leakage is slightly higher. The leakage comparison for all seals demonstrates that the honeycomb seal has the best flow control. Test data are presented for a top rotor surface velocity of 110 m/sec, a supply pressure of 13.7 bars, and IPr = 0.95 (injection pressure is 1.05 = 1/0.95 times the seal inlet pressure). For these conditions, and considering effective damping, the labyrinth seal with injection against rotation is better than the honeycomb seal when the pressure ratio across the seal PR < 0.45. On the other hand, the honeycomb seal is better when PR > 0.45. The effectiveness of the shunt-injection against rotation in developing effective damping is reduced with increasing rotor surface velocity.
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Chupp, R. E., and C. A. Dowler. "Performance Characteristics of Brush Seals for Limited-Life Engines." Journal of Engineering for Gas Turbines and Power 115, no. 2 (April 1, 1993): 390–96. http://dx.doi.org/10.1115/1.2906721.

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Brush seals are potential replacements for air-to-air labyrinth seals in gas turbine engines. An investigation has been conducted to determine the performance characteristics of brush seals for application in limited-life gas turbine engines. An elevated temperature, rotating test rig was designed and built to test labyrinth and brush seals in simulated subsonic and supersonic engine conditions. Results from initial tests for subsonic applications demonstrated that brush seals exhibit appreciably lower leakage compared to labyrinth seals, and thus offer significant engine performance improvements. Performance results have been obtained showing the effect of various brush seal parameters, including: initial interference, backplate gap, and multiple brush seals in series.
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Denecke, J., V. Schramm, S. Kim, and S. Wittig. "Influence of Rub-Grooves on Labyrinth Seal Leakage." Journal of Turbomachinery 125, no. 2 (April 1, 2003): 387–93. http://dx.doi.org/10.1115/1.1539516.

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An experimental investigation on the influence of stator rub-grooves on labyrinth seal leakage is presented in the present paper. In current labyrinth seal designs, abradable lands allow the rotor labyrinth teeth to rub grooves into the stator. These rub-grooves have a large influence on the seal leakage characteristic and impair the overall engine efficiency. To improve the understanding of rub-groove effects, discharge coefficients were determined using a plain nonrotating labyrinth seal model of scale 4:1 considering a wide variation of rub-groove geometries at different seal clearances. Three labyrinth seal types were covered in this investigation that are generally used in gas turbines, namely 1) straight-through labyrinth seals, 2) stepped labyrinth seals with forward facing steps, and 3) stepped labyrinth seals with backward facing steps. To attain a deeper insight into the flow mechanisms, water-channel visualizations were performed. The large data set generated in this study, provides the basis to analyze and quantify the influence of rub-grooves on the seal leakage for the three aforementioned labyrinth seal types. Current results were in agreement with previous studies on worn labyrinth seals for several seal geometries.
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Moore, J. Jeffrey. "Three-Dimensional CFD Rotordynamic Analysis of Gas Labyrinth Seals." Journal of Vibration and Acoustics 125, no. 4 (October 1, 2003): 427–33. http://dx.doi.org/10.1115/1.1615248.

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Labyrinth seals are utilized inside turbomachinery to provide noncontacting control of internal leakage. These seals can also play an important role in determining the rotordynamic stability of the machine. Traditional labyrinth seal models are based on bulk-flow assumptions where the fluid is assumed to behave as a rigid body affected by shear stress at the interfaces. To model the labyrinth seal cavity, a single, driven vortex is assumed and relationships for the shear stress and divergence angle of the through flow jet are developed. These models, while efficient to compute, typically show poor prediction for seals with small clearances, high running speed, and high pressure.* In an effort to improve the prediction of these components, this work utilizes three-dimensional computational fluid dynamics (CFD) to model the labyrinth seal flow path by solving the Reynolds Averaged Navier Stokes equations. Unlike bulk-flow techniques, CFD makes no fundamental assumptions on geometry, shear stress at the walls, as well as internal flow structure. The method allows modeling of any arbitrarily shaped domain including stepped and interlocking labyrinths with straight or angled teeth. When only leakage prediction is required, an axisymmetric model is created. To calculate rotordynamic forces, a full 3D, eccentric model is solved. The results demonstrate improved leakage and rotordynamic prediction over bulk-flow approaches compared to experimental measurements.
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Wang, Zhiguo, Bo Zhang, Yuanxiang Chen, Sheng Yang, Hongmei Liu, and Honghu Ji. "Investigation of Leakage and Heat Transfer Properties of the Labyrinth Seal on Various Rotation Speed and Geometric Parameters." Coatings 12, no. 5 (April 25, 2022): 586. http://dx.doi.org/10.3390/coatings12050586.

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To investigate the influence of the variation of geometric parameters on the leakage and heat transfer characteristics of labyrinth seals at various rotational speeds, the labyrinth seal models with different geometric parameters were numerically simulated based on the control variable methods. Results show the aerodynamic mechanism of leakage characteristics changing with rotational speed, as well as the leakage characteristics of labyrinth seals under the coupling action of geometric parameters and rotating speeds. When the characteristic scale changes along the direction of centrifugal force, the variation trend of labyrinth seal leakage characteristics is consistent at different rotational speeds. However, the leakage characteristics of labyrinth seals show the difference of rotational speed when the feature scale changes along the axis. At the same time, the laws of convective heat transfer on the surface of the rotor and stator are shown by the results of the studies, which provides reference for the thermodynamic analysis of labyrinth seals.
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Wang, Zhiguo, Bo Zhang, Yuanxiang Chen, Sheng Yang, Hongmei Liu, and Honghu Ji. "Investigation of Leakage and Heat Transfer Properties of the Labyrinth Seal on Various Rotation Speed and Geometric Parameters." Coatings 12, no. 5 (April 25, 2022): 586. http://dx.doi.org/10.3390/coatings12050586.

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To investigate the influence of the variation of geometric parameters on the leakage and heat transfer characteristics of labyrinth seals at various rotational speeds, the labyrinth seal models with different geometric parameters were numerically simulated based on the control variable methods. Results show the aerodynamic mechanism of leakage characteristics changing with rotational speed, as well as the leakage characteristics of labyrinth seals under the coupling action of geometric parameters and rotating speeds. When the characteristic scale changes along the direction of centrifugal force, the variation trend of labyrinth seal leakage characteristics is consistent at different rotational speeds. However, the leakage characteristics of labyrinth seals show the difference of rotational speed when the feature scale changes along the axis. At the same time, the laws of convective heat transfer on the surface of the rotor and stator are shown by the results of the studies, which provides reference for the thermodynamic analysis of labyrinth seals.
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Childs, D., D. Elrod, and K. Hale. "Annular Honeycomb Seals: Test Results for Leakage and Rotordynamic Coefficients; Comparisons to Labyrinth and Smooth Configurations." Journal of Tribology 111, no. 2 (April 1, 1989): 293–300. http://dx.doi.org/10.1115/1.3261911.

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Test results are presented for leakage and rotordynamic coefficients for seven honeycomb seals. All seals have the same radius, length, and clearance; however, the cell depths and diameters are varied. Rotordynamic data, which are presented, consist of the direct and cross-coupled stiffness coefficients and the direct damping coefficients. The rotordynamic-coefficient data show a considerable sensitivity to changes in cell dimensions; however, no clear trends are identifiable. Comparisons of test data for the honeycomb seals with labyrinth and smooth annular seals shows the honeycomb seal had the best sealing (minimum leakage) performance, followed in order by the labyrinth and smooth seals. For prerotated fluids entering the seal, in the direction of shaft rotation, the honeycomb seal has the best rotordynamic stability followed in order by the labyrinth and smooth. For no prerotation, or fluid prerotation against shaft rotation, the labyrinth seal has the best rotordynamic stability followed in order by the smooth and honeycomb seals.
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Jiang, Jie, Yi Yong Yang, Yong Jian Li, and Wei Feng Huang. "Influence of Gas Condensability on Labyrinth Seal's Sealability." Applied Mechanics and Materials 575 (June 2014): 355–62. http://dx.doi.org/10.4028/www.scientific.net/amm.575.355.

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Labyrinth seals are widely used in rotating fluid machinery, due to its simplicity, low-cost and reliability. In this paper, the effect of cavities on leakage loss in straight-through labyrinth seals are studied by changing gas condensability. The fluid flow characteristics through straight-through labyrinth seals are obtained by using viscous flow analysis along with a RNG k-ε turbulence model. The numerical calculation and various gas pressure is that leakage of compressible gas is greater than that of incompressible gas. The result is investigated by the heating effect of labyrinth seal and density characteristics of compressible gas.
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Dissertations / Theses on the topic "Labyrinth Seals"

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Khan, Mohammed Ajaz. "Leakage flow in labyrinth seals." Thesis, University of Bradford, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.482781.

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Allcock, D. C. J. "Abradable stator gas turbine labyrinth seals." Thesis, Cranfield University, 1999. http://dspace.lib.cranfield.ac.uk/handle/1826/10702.

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This is a detailed study into the internal aerodynamics of labyrinth seals, with pmic| reference to the effects of abradable honeycomb stators on labyrinth seal leakage.- A extensive experimental programme established tables of friction factor for three different grades of honeycomb used by industry, and examined the effect of both Reynolds number and clearance on these friction factors. The friction factor associated with a aerodynamically smooth surface was also experimentally determined in order to establish the experimental method. The experimental data was used to model the different grades of honeycomb used as stator material in numerical simulations of a number labyrinth seals, and allowed for comparison of the leakage associated with both smooth and abradable stator straight through labyrinth seals. Step-up and step-down seal geometries were also considered, and the effects of pressure ratio, clearance and rotation on labyrinth seal leakage was examined on all modelled seal types. This numerically generated leakage data was comprehensive enough to allow for the creation of a second-generation one-dimensional labyrinth seal leakage predictor tool of the type used by design engineers in network models. This tool accounts for stator material, seal clearance, overall pressure ratio, rotation and seal geometry, and the accuracy associated with this tool allows labyrinth seal leakage to b predicted to within 10%. Functions of discharge coefficient and carry-over factor obtained from the numerical predictions are used by this tool, and as such it is capable of dealing with a large number of different operating conditions for all the seal types modelled.
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Gamal, Eldin Ahmed Mohamed. "Leakage and rotordynamic effects of pocket damper seals and see-through labyrinth seals." Texas A&M University, 2007. http://hdl.handle.net/1969.1/85848.

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This dissertation discusses research on the leakage and rotordynamic characteristics of pocket damper seals (PDS) and see-through labyrinth seals, presents and evaluates models for labyrinth seal and PDS leakage and PDS force coefficients, and compares these seals to other annular gas seals. Low-pressure experimental results are used alongside previously-published high-pressure labyrinth and PDS data to evaluate the models. Effects of major seal design parameters; blade thickness, blade spacing, blade profile, and cavity depth; on seal leakage, as well as the effect of operating a seal in an off-center position, are examined through a series of non-rotating tests. Two reconfigurable seal designs were used, which enabled testing labyrinth seals and PDS with two to six blades. Leakage and pressure measurements were made with air as the working fluid on twenty-two seal configurations. Increasing seal blade thickness reduced leakage by the largest amount. Blade profile results were more equivocal, indicating that both profile and thickness affected leakage, but that the influence of one factor partially negated the influence of the other. Seal leakage increased with increased eccentricity at lower supply pressures, but that this effect was attenuated for higher pressure drops. While cavity depth effects were minor, reducing depths reduced leakage up to a point beyond which leakage increased, indicating that an optimum cavity depth existed. Changing blade spacing produced results almost as significant as those for blade thickness, showing that reducing spacing can detrimentally affect leakage to the point of negating the benefit of inserting additional blades. Tests to determine the effect of PDS partition walls showed that they reduce axial leakage. The pressure drop was found to be highest across the first blade of a seal for low pressure drops, but the pressure drop distribution became parabolic for high pressure drops with the largest drop across the last blade. Thirteen leakage equations made up of a base equations, a flow factor, and a kinetic energy carryover factor were examined. The importance of the carryover coefficient was made evident and a modified carryover coefficient is suggested. Existing fullypartitioned PDS models were expanded to accommodate seals of various geometries.
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Collins, Dermot. "The effects of wear on abradable honeycomb labyrinth seals." Thesis, Cranfield University, 2007. http://hdl.handle.net/1826/1756.

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This thesis reports on work undertaken to understand the effects, due to wear, on the performance of abradable honeycomb labyrinth seals. The phenomena studied are aerodynamic in nature and include compressible flow, turbulent flow, recirculation and separation at a range of pressure ratios from 1.20 up to 3.50. Four primary methods of investigation were used: experimental, numerical using CFD, numerical using theoretical derivations and numerical using established labyrinth seal specific computer codes. Effects of seal clearance, pressure ratio and tooth to groove location have been investigated with overall performance and inter-seal pressure distribution recorded experimentally and numerically for comparison. Worn experimental results, when compared to their unworn equivalent, recorded large increases in mass flow of up to 50% when the labyrinth teeth are located centrally in the groove. Significant performance enhancements were achieved through offsetting the teeth with respect to the groove, particularly in an upstream sense. There was a marked deterioration with the labyrinth teeth located at the groove exit. Inter-seal pressure distributions showed that the first and final teeth did most of the work achieving significantly larger pressure drops which goes against current seal understanding of increasing pressure drop through the seal. Numerical work was undertaken to further investigate these effects. However, due to the complex 3-D geometry of an abradable honeycomb labyrinth seal a 2-D simplification technique was developed to speed up the investigative process. Using this technique CFD was found capable of replicating the experimental data regarding overall seal performance and inter-seal pressure distributions. The pressure on the final tooth proved to be the hardest experimental data to recreate using CFD, particularly at high pressure ratios when shocks are likely to form. Further numerical work was undertaken using computer codes and theoretical derivations. This work proved that the understanding of the seal loss coefficients used by both methods was not adequate for the current study with the experimental data recreated least successfully. Suggestions are given for enhancement of seal design, including axial location and seal computational routines, which will limit the impact of a 1.5% increase in operational cost that is likely to accrue from seal deterioration.
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Joubert, Stephanus Lourens. "Mathematical modeling of leakage flow through labyrinth seals / Lourens Joubert." Thesis, North-West University, 2003. http://hdl.handle.net/10394/389.

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Optimization of gas turbine systems has identified the need for simplified mathematical models to calculate the losses experienced within turbo machines. One such loss is that of the flow through labyrinth seals. As part of a larger study, this study concentrates on the development of such loss models to aid in the performance prediction of turbo machines. The aim of this study was therefore firstly to understand the nature of labyrinth leakage flows and secondly to investigate mathematical models to calculate or predict such leakages through most common geometries. Finally the ability of these models was evaluated by implementing the models into an "engineering tool" in Engineering Equation Solver (EES). From a detailed literature survey, a few models for calculating and describing labyrinth seal leakages were identified. An "engineering tool" was subsequently developed by combining these models and the governing coefficients in the EES software. Although experimental validation would have been the optimum, a lack of such facilities together with a limited budget required alternative methods to be investigated. It was therefore decided to use Computational Fluid Dynamics (CFD) software such as Star-CD and Fluent. These software packages are accepted by the industry as a design standard and visualizing tool for validation. The results obtained compared favourably with that of the "engineering tool". It therefore proved that the suggested models offer good potential to be used for performance prediction of labyrinth seals.
Thesis (M.Ing. (Mechanical Engineering))--North-West University, Potchefstroom Campus, 2004.
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Xi, Jinxiang. "Seal inlet disturbance boundary conditions for rotordynamic models and influence of some off-design conditions on labyrinth rotordynamic instability." Texas A&M University, 2005. http://hdl.handle.net/1969.1/4971.

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Systematic parametric studies were performed to better understand seal-inlet rotordynamics. A CFD-perturbation model was employed to compute the seal-inlet flow disturbance quantities. Seal inlet disturbance boundary condition correlations were proposed from the computed seal-inlet quantities using the important parameters. It was found that the cosine component of the seal-inlet swirl velocity disturbance W1C has a substantial impact on the cross-coupled stiffness, and that the correlations for W1C and W1S should be used to replace the historical guess that seal inlet W1C = 0 and W1S = 0. Also, an extremely precise relationship was found between the swirl disturbance W1C and the seal-inlet swirl velocity (ωRsh − ¯W0). Thus, the number of experiments or computer runs needed to determine the effect of spin speed, shaft radius and/or inlet swirl velocity on the cross-coupled stiffness is greatly reduced by plotting the simplified relationship of the cross-coupled stiffness against the swirl slip velocity. The benefits of using the new seal-inlet boundary condition correlations were assessed by implementing them into a CFD-perturbation model. Consistently improved agreement with measurements was obtained for both liquid annular seals and gas labyrinth seals. Further, the well-established CFD-perturbation model with new boundary condition correlations was employed to investigate the rotordynamics of two off-design situations. The first case considered the influence of labyrinth seal teeth damage on the performance and the rotordynamic characteristics of impeller eye seals in centrifugal compressors. The second case considered the influence of rotor-axial-shifting on rotordynamic forces for high-low labyrinth seals in steam turbines during the start-up and shut-down process. The results should provide useful information for labyrinth seal design and fault diagnosis of stability problems in turbines and compressors.
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Zhuang, Qingyuan. "Parametric Study on the Aeroelastic Stability of Rotor Seals." Thesis, KTH, Kraft- och värmeteknologi, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-116689.

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Labyrinth seals are widely used in rotating machinery and have been shown to experience aeroelastic instabilities. The rapid development of computational fluid dynamics now provides a high fidelity approach for predicting the aeroelastic behavior of labyrinth seals in three dimension and exhibits great potential within industrial application, especially during the detailed design stages. In the current publication a time-marching unsteady Reynolds- averaged Navier-Stokes solver was employed to study the various historically identified parameters that have essential influence on the stability of labyrinth seals. Advances in understanding of the related aeroelastic (flutter) phenomenon were achieved based on extensive yet economical numerical analysis of a simplified seal model. Further, application of the same methodology to several realistic gas turbine labyrinth seal designs confirmed the perceived knowledge and received agreements from experimental indications. Abbott’s criteria in describing the labyrinth seal aeroelastic behaviors were reaffirmed and further developed.
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Dai, Yushuang. "Large eddy simulation of labyrinth seals and rib shapes for internal cooling passges." Thesis, University of Cambridge, 2018. https://www.repository.cam.ac.uk/handle/1810/271753.

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The turbine is one of the key components in gas turbine engines. To prevent the turbine blades from being badly damaged by their harsh working environment, it is necessary to keep them cool. This can be achieved by enhancement of the heat transfer performance through internal cooling passages. However, the large quantity of flow within this internal cycle inevitably results in mass flow loss, which is a major source of loss in turbomachinery. Therefore labyrinth seals are also investigated in this study, attempting to reduce the flow leakage and further increase the turbine efficiency. Large Eddy Simulation ( LES ) is used for its capability to capture the complex unsteady flow features in this study. Different rib shapes in a fully developed ribbed channel are investigated, aiming to improve the heat transfer performance. An immersed boundary method ( IBM ) is used with LES to generate complex geometries. With the use of IBM , the range of geometries can be represented on a background Cartesian grid. To obtain the best sealing performance, an investigation is undertaken into the possibility of optimising labyrinth seal planforms using a genetic algorithm ( GA ). By making use of the large number of populations, a much faster calculation can be achieved toward the objective function. Three hundred LES calculations are carried out, and an optimised design is generated that maximises the sealing effectiveness. The optimised design shows a leakage reduction of about 27.6% compared to the baseline geometry. The optimisation process employing a GA will be continued. It is expected that automated optimisation as presented will become increasingly important in the design process of future turbomachines, particularly for flows with strong parameter interactions, with an aim to further improve the overall efficiency of gas turbines.
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Choi, Dong Chun. "A novel isolation curtain to reduce turbine ingress heating and an advanced model for honeycomb labyrinth seals." Texas A&M University, 2005. http://hdl.handle.net/1969.1/3799.

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A combination of 3-D and 2-D computational fluid dynamics (CFD) modeling as well as experimental testing of the labyrinth seal with hexagonal honeycomb cells on the stator wall was performed. For the 3-D and 2-D CFD models, the hexagonal honeycomb structure was modeled using the concept of the baffle (zero-thickness wall) and the simplified 2-D fin, respectively. The 3-D model showed that even a small axial change of the tooth (or honeycomb wall) location, or a small circumferential change of the honeycomb wall location significantly affected the flow patterns and leakage characteristics especially for small tooth tip clearance. Also, the local details of the flow field were investigated. The seven basic procedural steps to develop a 2-D axisymmetric honeycomb labyrinth seal leakage model were shown. Clearly demonstrated for varying test conditions was the 2-D model capability to predict the 3-D honeycomb labyrinth flow that had been measured at different operating conditions from that used in developing the 2-D model. Specifically, the 2-D model showed very close agreement with measurements. In addition, the 2-D model greatly reduced the computer resource requirement needed to obtain a solution of the 3-D honeycomb labyrinth seal leakage. The novel and advanced strategy to reduce the turbine ingress heating, and thus the coolant requirement, by injecting a “coolant isolation curtain” was developed numerically using a 3-D CFD model. The coolant isolation curtain was applied under the nozzle guide vane platform for the forward cavity of a turbine stage. Specifically, the isolation curtain serves to isolate the hot mainstream gas from the turbine outer region. The effect of the geometry change, the outer cavity axial gap clearance, the circumferential location of the injection curtain slot and the injection fluid angle on the ingress heating was investigated. Adding the chamfer to the baseline design gave a similar or higher maximum temperature T* max than did the baseline design without chamfer, but implementation of the injection curtain slot reduced substantially T* max of the outer region. In addition, a more desirable uniform adiabatic wall temperature distribution along the outer rotor and stator surfaces was observed due to the presence of the isolation curtain.
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Jin, Hanxiang. "Surface Patterning and Rotordynamic Response of Annular Pressure Seals Used in Turbomachinery." Diss., Virginia Tech, 2020. http://hdl.handle.net/10919/96731.

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Rotordynamic instability problems in turbomachinery have become more important in recent years due to rotordynamic components with higher speeds and higher power densities. These features typically lead to increased instability risk in rotor dynamic components as fluids-structure interactions take place. In addition, critical damage of rotordynamic components can result from high level vibrations of supporting bearing system, where the reduced rotor speed can lead to system operating near the rotor critical speed. Therefore, increased accuracy in modeling of rotordynamic components is required to predict the potential instability issues in high performance rotordynamic design. The instability issue may potentially be eliminated in design stage by varying the characteristics of the unstable components. One such turbomachinery component is the annular pressure seal. The annular pressure seals are specifically designed to prevent the fluid leakage from high pressure stage to low pressure stage in turbomachinery. Typical annular pressure seals have two different flow regions, an annular jet-flow region between the rotor and stator, and cylindrical or circumferential indentions on the stator/rotor surface that serve as cavities where flow recirculation occurs. As the working fluid enters the cavities and recirculates, the kinetic energy is reduced, resulting in a reduction of leakage flow. The current challenge is to model with higher precision the interaction between the rotordynamic components and the working fluid. In this dissertation, this challenge was overcome by developing a hybrid Bulk Flow/CFD method to compute rotordynamic responses for the annular pressure seals. In addition, design of experiments studies were performed to relate the surface patterning with the resulting rotordynamic response for the annular pressure seals, in which several different geometry specifications were investigated. This study on annular pressure seal design generated regression models for rotordynamic coefficients that can be used as optimization guidelines. Research topics related to the annular pressure seals were presented in this dissertation as well. The reduced order model of both hole-pattern seals and labyrinth seals were investigated. The results showed that the flow field representing the flow dynamics in annular pressure seals can be expressed as a combination of first three proper orthogonal decomposition modes. In addition, supercritical state of carbon dioxide (sCO2) process fluid was examined as the working fluid in a preliminary study to better understand the effects on annular pressure seals. The results showed that the performance and stability in the annular pressure seals using sCO2 as process fluid can both be improved.
Doctor of Philosophy
This dissertation focused on understanding the correlations between surface patterning and rotordynamic responses in the annular pressure seals. The annular pressure seals are a specific type of rotordynamic component that was designed to prevent the fluid leakage from high pressure stage to low pressure stage in turbomachinery. As the working fluid enters the cavities and recirculates, the kinetic energy is reduced, resulting in a reduction of leakage flow through the annular pressure seals. Rotordynamic instability becomes an issue that may be related to the annular pressure seals in some cases. In recent years, rotordynamic components with higher rotor speeds and higher power densities are commonly used in industrial applications. These features could lead to increased instability risk in rotor-bearing systems as fluids-structure interactions take place. Therefore, high precision modeling of the rotodynamic components is required to predict the instability issues in high performance rotordynamic design. The instability issue may potentially be eliminated in design stage by varying the characteristics of the potentially unstable components. In this study, the surface patterning and rotordynamic responses were investigated for several different annular pressure seal models with a hybrid Bulk Flow/Computational Fluid Dynamics method. This dissertation provides for the first time regression models for rotordynamic coefficients that can be used as optimization guidelines. Research topics related to the annular pressure seals were presented in this dissertation as well. The reduced order model of both hole-pattern seals and labyrinth seals were investigated. The results showed that the flow field representing the flow dynamics in annular pressure seals can be expressed as a combination of first three proper orthogonal decomposition modes. In addition, supercritical state of carbon dioxide (sCO2) process fluid was examined to better understand the effects of working fluid on annular pressure seals. The results showed that the performance and stability in the annular pressure seals using sCO2 as process fluid can both be improved.
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Books on the topic "Labyrinth Seals"

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Hendricks, Robert C. Three-step labyrinth seal for high-performance turbomachines. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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Hendricks, Robert C. Three-step labyrinth seal for high-performance turbomachines. Cleveland, Ohio: Lewis Research Center, 1987.

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Hendricks, Robert C. Three-step labyrinth seal for high-performance turbomachines. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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W, Pugh D., and United States. National Aeronautics and Space Administration., eds. Development of gas-to-gas lift pad dynamic seals: Final report. [Washington, D.C.]: National Aeronautics and Space Administration, 1987.

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W, Pugh D., and United States. National Aeronautics and Space Administration., eds. Development of gas-to-gas lift pad dynamic seals: Final report. [Washington, D.C.]: National Aeronautics and Space Administration, 1987.

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United States. National Aeronautics and Space Administration., ed. A comparison of experimental and theoretical results for labyrinth gas seals with honeycomb stators. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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C, Hendricks Robert, United States. National Aeronautics and Space Administration., and U.S. Army Research Laboratory., eds. Relative performance comparison between baseline labyrinth and dual-brush compressor discharge seals in a T-700 engine test. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

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J, Hall E., Delaney R. A, and United States. National Aeronautics and Space Administration., eds. Aeropropulsion technology (APT): Task 23--stator seal cavity flow investigation. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

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L, Rhode D., and United States. National Aeronautics and Space Administration., eds. Design of a pump wear ring labyrinth seal: Final report. College Station, Tex: Turbomachinery Laboratories, Texas A&M University, Mechanical Engineering Dept., 1987.

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Williston, William C. Rotordynamic effects driven by fluid forces from a geometrically imperfect labyrinth seal. Monterey, Calif: Naval Postgraduate School, 1993.

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Book chapters on the topic "Labyrinth Seals"

1

Sanjay kumar, S. M., and C. Suresh. "Vibrational Study of Labyrinth Seals for Turbomachines." In Lecture Notes on Multidisciplinary Industrial Engineering, 133–45. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-8468-4_12.

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Kim, Tong Seop, Yungmo Kang, and Hee Koo Moon. "Aerodynamic Performance of Double-Sided Labyrinth Seals." In Fluid Machinery and Fluid Mechanics, 377–82. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-89749-1_60.

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Fritz, Erhard, Werner Haas, and Heinz K. Müller. "Liquid-collecting labyrinth seals for machine tool spindles." In Fluid Sealing, 703–10. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2412-6_43.

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Cangioli, Filippo, Giuseppe Vannini, Paolo Pennacchi, Lorenzo Ciuchicchi, Leonardo Nettis, Steven Chatterton, and Andrea Vania. "Development and Validation of a Bulk-Flow Model for Staggered Labyrinth Seals." In Mechanisms and Machine Science, 471–90. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-99262-4_34.

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Thieleke, G., and H. Stetter. "Identification of Friction Factors for Modelling the Exciting Forces caused by Flow in Labyrinth Seals." In Rotordynamics ’92, 140–49. London: Springer London, 1992. http://dx.doi.org/10.1007/978-1-4471-1979-1_18.

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Song, Chenxing, Yu Fan, Mingchun Deng, Ziyue Liu, and Yi Shen. "Research on the Method to Formulate the Allowable Standard for Aero-Engine Labyrinth Seals Clearances." In Lecture Notes in Electrical Engineering, 711–18. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-7423-5_69.

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Kirk, R. Gordon. "Labyrinth Seal." In Encyclopedia of Tribology, 1903–7. Boston, MA: Springer US, 2013. http://dx.doi.org/10.1007/978-0-387-92897-5_130.

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Ha, Yunseok, Yeongdo Lee, Byul An, and Yongbok Lee. "Experiment and CFD Analysis of Plain Seal, Labyrinth Seal and Floating Ring Seal on Leakage Performance." In Proceedings of the 11th IFToMM International Conference on Rotordynamics, 391–405. Cham: Springer International Publishing, 2023. http://dx.doi.org/10.1007/978-3-031-40455-9_32.

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Wei, Yuan, Zhaobo Chen, Yinghou Jiao, Xin Du, and Zhouqiang Zhang. "Effects of Clearance on Leakage Flow Characteristics of Labyrinth Brush Seal." In Proceedings of the 9th IFToMM International Conference on Rotor Dynamics, 2019–29. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-06590-8_167.

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Zhang, Xiang, Renwei Che, Yinghou Jiao, and Huzhi Du. "Simulation Study for Hole Diaphragm Labyrinth Seal at Synchronous Whirl Frequency." In Proceedings of the 11th IFToMM International Conference on Rotordynamics, 71–77. Cham: Springer International Publishing, 2023. http://dx.doi.org/10.1007/978-3-031-40455-9_7.

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Conference papers on the topic "Labyrinth Seals"

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Vakili, Ahmad D., Abraham J. Meganathan, Sricharan Ayyalasomayajula, Stephen Hesler, and Lewis Shuster. "Advanced Labyrinth Seals for Steam Turbine Generators." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-91263.

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A new class of knives (C-Shaped) for reduced labyrinth seal discharge has been designed and assessed through two dimensional numerical modeling of the seal’s internal flow passages. Modeling procedures used for the analysis have been previously validated by comparison with static labyrinth seal experiments. The objectives of the new seal are to: 1) reduce flow leakage through the seal and 2) introduce structural flexibility in the knives so that design clearances could be maintained even after rub events during startup. The baseline chosen for comparative evaluation is an N2 packing used in GE steam turbines. The new seals have compliant C-shaped knives instead of the straight knives, found in an N2 packing. The best performing configuration has one tall ‘C’ shaped long knife and three ‘C’ shaped short knives in each stage. It was found that the best configuration at clearances similar to the baseline seal reduces flow leakage by 42%. Two dimensional numerical structural analyses showed that the new seal knife is more flexible than a straight knife. This is also intuitive by virtue of its geometric profile. A non-dimensional geometric parameter correlates with the degree of flexibility in the knife. These results indicate a potential for design of labyrinth seals that maintain lower design clearances throughout their life time by carefully selecting the knives’ geometric parameters and incorporating high performance composite materials. Then, the new design would result in significantly lower steam leakage.
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Chougule, Hasham H., Douglas Ramerth, Dhinagaran Ramchandran, and Ramnath Kandala. "Numerical Investigation of Worn Labyrinth Seals." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90690.

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The objective of this study was to develop a Computational Fluid Dynamics (CFD) based methodology to obtain the flow characteristics of worn and unworn labyrinth seals which will be applicable over a wide range of seal geometries. In this paper, we present a process to analyze worn and unworn seals with honeycomb lands using the CFX suite of software. Honeycomb structure poses an additional challenge due to disparate length scales. This was addressed by using separate meshes for the honeycomb and the seal tooth and by connecting them with a generalized grid interface in CFX. The challenges involved in modeling worn seals and an approach for quality meshing of the same was discussed. Comparisons were made with the test data from seals with unworn honeycomb lands. The leakages for the worn seals were also analyzed.
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Corral, Roque, Almudena Vega, and Michele Greco. "Conceptual Flutter Analysis of Stepped Labyrinth Seals." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91621.

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Abstract A simple non-dimensional model to describe the flutter onset of two-fin straight labyrinth seals [1] is extended to stepped seals. The effect of the axial displacement of the seal is analyzed first in isolation. It is shown that this fundamental mode is always stable. In a second step, the combination of axial and torsion displacements is used to determine the damping of modes with arbitrary torsion centers. It is concluded that the classical Abbot’s criterion stating that seals supported in the low-pressure side of the seal are stable provided that natural frequency of the mode is greater than the acoustic frequency breaks down under certain conditions. An analytical expression for the non-dimensional work-per-cycle is derived and new non-dimensional parameters controlling the seal stability identified. It is finally concluded the stability of stepped seals can be assimilated to that of a straight through seal if the appropriate distance of the torsion center to the seal is chosen.
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Ferguson, J. G. "Brushes as High Performance Gas Turbine Seals." In ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1988. http://dx.doi.org/10.1115/88-gt-182.

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Brush seals are the first simple and practical alternative, to the finned labyrinth, for gas turbine air system seals. Their use has been made possible by a combination of innovative design features, combined with advanced materials and manufacturing techniques. Due to the very high rubbing speeds and temperatures, existing in gas turbine air system seal positions, finned labyrinths have been used almost exclusively since the invention of the gas turbine. Development over the years has reduced their leakage flow to the ultimate, but leakage is very much dependent on clearance. A brush seal, replacing the best possible finned labyrinth seal, needing a clearance of 0.7mm, can reduce the flow to approximately 10% of that of the finned seal. The main advantages of brush seals, therefore, are their dramatic improvement in sealing performance. This is combined, however, with their ability to maintain this performance even during and after transient differential movements. These advantages have been developed and demonstrated after many hours rig and engine running. Back to back engine tests, with brush seals, replacing finned labyrinths in key air system seals, have demonstrated a significant improvement in thrust for a given stator outlet temperature (SOT). Flight trials are in progress, on an engine fitted with brush seals, as a further step to their in service use.
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Zimmerman, H., A. Kammerer, and K. H. Wolff. "Performance of Worn Labyrinth Seals." In ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-131.

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The major sealing device between rotating and static aeroengine parts is still of labyrinth type. Nowadays the fins and the stator may be coated and the running conditions very often cause heavy rubs which leads to severe surface imperfections. This paper investigates the influence of rounded fins and worn coatings on the discharge coefficients of straight through labyrinth seals. The relevant effects of Reynolds number are investigated. Some measured fin and coating surfaces from engine parts are presented. Experimental and numerical results show a strong effect of wear on labyrinth seal performance.
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Pena de Souza Barros, Glycon, Carlos Barreira Martinez, Edna Maria de Faria Viana, Hélio Augusto Goulart Diniz, and Willian Moreira Duarte. "LABYRINTH SEALS - A LITERATURE REVIEW." In Brazilian Congress of Thermal Sciences and Engineering. ABCM, 2018. http://dx.doi.org/10.26678/abcm.encit2018.cit18-0775.

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Roche, Brian P. "Alternatives in Gearbox Seals for Main Drive Gearboxes." In SNAME 11th Propeller and Shafting Symposium. SNAME, 2006. http://dx.doi.org/10.5957/pss-2006-15.

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A variety of sealing devices have been used to seal Marine Main Reduction Gears. One means of sealing Main Reduction Gears today is the labyrinth seal. While the labyrinth seal has been successfully employed in some applications, it has performed unsatisfactorily in others. This paper discusses mechanical seals as alternatives to labyrinth seals for use in Marine Main Reduction Gears. Along with a discussion a/Labyrinth Seals, various types of mechanical seals are considered, along with their respective advantages and disadvantages. Split Circumferential Seals are described in particular. Seal design features, as well as test results, are presented.
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Moore, J. Jeffrey. "Three-Dimensional CFD Rotordynamic Analysis of Gas Labyrinth Seals." In ASME 2001 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/detc2001/vib-21394.

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Abstract Labyrinth seals are utilized inside turbomachinery to provide non-contacting control of internal leakage. These seals can also play an important role in determining the rotordynamic stability of the machine. Traditional labyrinth seal models are based on bulk-flow assumptions where the fluid is assumed to behave as a rigid body affected by shear stress at the interfaces. To model the labyrinth seal cavity, a single, driven vortex is assumed and relationships for the shear stress and divergence angle of the through flow jet are developed. These models, while efficient to compute, typically show poor prediction for seals with small clearances, high running speed, and high pressure (Childs, 1993). In an effort to improve the prediction of these components, this work utilizes three-dimensional computational fluid dynamics (CFD) to model the labyrinth seal flow path by solving the Reynolds Averaged Navier Stokes equations. Unlike bulk-flow techniques, CFD makes no fundamental assumptions on geometry, shear stress at the walls, as well as internal flow structure. The method allows modeling of any arbitrarily shaped domain including stepped and interlocking labyrinths with straight or angled teeth. When only leakage prediction is required, an axisymmetric model is created. To calculate rotordynamic forces, a full 3D, eccentric model is solved. The results demonstrate improved leakage and rotordynamic prediction over bulk-flow approaches compared to experimental measurements.
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Denecke, J., V. Schramm, S. Kim, and S. Wittig. "Influence of Rub-Grooves on Labyrinth Seal Leakage." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30244.

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An experimental investigation on the influence of stator rub-grooves on labyrinth seal leakage is presented in the present paper. In current labyrinth seal designs, abradable lands allow the rotor labyrinth teeth to rub grooves into the stator. These rub-grooves have a large influence on the seal leakage characteristic and impair the overall engine efficiency. To improve the understanding of rub-groove effects, discharge coefficients were determined using a plain non-rotating labyrinth seal model of scale 4:1 considering a wide variation of rub-groove geometries at different seal clearances. Three labyrinth seal types were covered in this investigation that are generally used in gas turbines, namely (1) straight-through labyrinth seals, (2) stepped labyrinth seals with forward facing steps and (3) stepped labyrinth seals with backward facing steps. To attain a deeper insight into the flow mechanisms, water-channel visualizations were performed. The large data set generated in this study, provides the basis to analyze and quantify the influence of rub-grooves on the seal leakage for the three labyrinth seal types listed above. Current results were in agreement with previous studies on worn labyrinth seals for several seal geometries.
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Corral, Roque, Michele Greco, and Luis Matabuena. "Non-Linear Flutter Analysis of Labyrinth Seals." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82142.

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Abstract A simple nonlinear model to describe labyrinth seal flutter has been developed to assess the aeromechanic stability of straight-through labyrinth seals subjected to large gap variations. The model solves the one-dimensional integral mass, momentum, and energy equations of the seal for a prescribed motion numerically until a periodic state is reached. The model accounts for the effect, previously neglected, of high clearance variations on the stability. The results show that when the vibration amplitudes are small, the work-per-cycle coincides with the prediction of the Corral and Vega model (2018, “Conceptual Flutter Analysis of Labyrinth Seals Using Analytical Models. Part I: Theoretical Background”, ASME J. Turbomach.140(10), pp. 121006) and Corral et al. (2021, “Higher-Order Conceptual Model for Seal Flutter”, ASME J. Turbomach. 143(7), pp.071006), but for large vibration amplitudes nonlinearities alter the stability limit. In realistic cases, when the discharge time of the seal is much longer than the vibration period, the nonlinear effects are significant and tend to increase the unstable range of operating conditions. Furthermore, seals supported either on the high-pressure or low-pressure sides, stable for small vibration amplitudes, can destabilise when the vibration amplitude increases. The linear stability, though close in many situations to the nonlinear threshold, is not conservative, and attention must be paid to nonlinear effects.
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Reports on the topic "Labyrinth Seals"

1

Lee. L51588 Improved Internal Seals for Pipeline Centrifugal Compressors. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), May 1988. http://dx.doi.org/10.55274/r0010524.

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Reviews current technology of internal labyrinth seals and concludes that internal leakage can reduce compressor efficiencies as much as 3 to 6 percent. Discusses limitations on abradable seals with tighter clearances and the effect of compressor surge on both types of seals. Proposes resiliently mounted seals as subject for future investigation to accommodate rotor movement without excessive seal wear.
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2

Martinez-Sanchez, Manuel, and John Dugundji. Fluid Dynamic - Structural Interactions of Labyrinth Seals. Fort Belvoir, VA: Defense Technical Information Center, June 1986. http://dx.doi.org/10.21236/ada174461.

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3

Childs, D. W., and D. L. Rhode. The Measurement and Prediction of Rotordynamic Forces for Labyrinth Seals. Fort Belvoir, VA: Defense Technical Information Center, March 1988. http://dx.doi.org/10.21236/ada197185.

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4

Chan, Y. T., R. C. Buggeln, and H. McDonald. Three-Dimensional Dynamic Labyrinth Seal Analysis. Fort Belvoir, VA: Defense Technical Information Center, January 1987. http://dx.doi.org/10.21236/ada185353.

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