axial compressor nasa

Near the blade surface, an O-type grid was built with a width factor of 0.5 and 17 elements in order to precisely control the mesh distribution in that region. This leads to the need of higher computational resources and CPU time. Life of Elisha Tyson, the philanthropist. [. At the near-stall point condition, the interaction intensity between the vortex and the shock wave is so severe that the vortex core expands and generates a vortex breakdown zone [, The effects of the groove in the flow field modification are shown in. These techniques can be active or passive and their main purpose is to improve the machine stability without affecting the performance at the design point. Wasserbauer National Aeronautics and Space Administration ; US Army Aviation Systems Command, Aviation R&T Activity ; For sale by the National Technical Information Service [Washington, DC. The axial compressor has been configured for injection of air through the stator footring, stator blades and endwalls to assess flow control. [. Existing experiments, simulations, and analysis have shown that the flow field of the blade tip has a significant effect on rotating stall and acoustic resonance in aeroengine compressors. Please let us know what you think of our products and services. Numerical analysis of flow in a transonic compressor with a single circumferential casing groove: Influence of groove location and depth on flow instability. Wisler () reported that for a low speed four stage compressor the effect of increasing rotor tip clearance from % to % was to reduce the efficiency by % and the peak pressure rise by % Smith and Cumpsty () have shown a 23 percent drop in maximum pressure rise and a 15 percent increase in flow coefficient at stall in a large. Test Axial Compressor NASA rotor 37 (12), an axial-flow compressor rotor having a low-aspect ratio, is considered for optimization in the present study. Experimental and computational analysis of a transonic compressor rotor. NASA carried out several tests on the GE J85-13 in the late 1960’s and throughout the 1970’s. It is the rotor part of Stage35, which is an inlet stage of a transonic axial compressor designed by Reid and Moore (1978). Washington, DC: The National Academies Press. Mean-line calculation through a compressor rotor. Figure 9. Received: 5 November 2020 / Revised: 14 December 2020 / Accepted: 23 December 2020 / Published: 4 January 2021, (This article belongs to the Special Issue. But it is relatively easy to link together several stages and produce a multistage axial compressor. New T-shape grooves were designed keeping the volume as a constant parameter and their performances were evaluated in terms of stall margin improvement and efficiency variation. The four groove configurations are similar in that the cross section area is constant and, therefore, the volume of the different grooves is equal to that of the baseline. The code has been used to generate the performance map for the NASA 76 -B three -stage axial compressor featuring variable geometry. In Proceedings of the ASME Turbo Expo 2010: Power for Land, Sea, and Air, Glasgow, UK, 14–18 June 2010; Paper no. On the other hand, a Low-Reynolds-Number method should be implemented to describe in detail the boundary layer profile. The inlet to the core compressor modeled the inlet conditions to a high-pressure compressor (HPC) of an engine, inclusive of fan frame struts and a transition duct from the low-pressure compressor (LPC Author: Kenneth L. Suder, James D. Heidmann. Two new BLS slot configurations are proposed and a Cited by: @article{osti_, title = {Experimental study of a high-through-flow transonic axial compressor stage}, author = {Wennerstorm, A J}, abstractNote = {Design information and experimental results are presented for a transonic axial compressor stage passing 40 lbs/s-ft/sup 2/ frontal area ( Kg/s-m/sup 2/) with a pressure ratio of at ft/s ( m/s) tip speed. First, the baseline configuration is considered, highlighting the influence of the groove in the flow field near the blade tip. There are currently two principal compressor designs found on jet engines: the axial compressor, in which the air flows parallel to the axis of rotation, and the centrifugal compressor, in which the air is turned perpendicular to the axis of rotation. The detailed specifications of the compressor are summarized in Table 1 . It is evident that the flow field is changed downstream from the groove location: a new stagnation area appears in the mid-passage region. The statements, opinions and data contained in the journals are solely For the mesh portion over the blade tip, an H-Grid not matching topology was set. 2010-216235. About . PERFORMANCE OF NACA EIGHT-STAGE AXIAL-FLOW COMPRESSOR DESIGNED ON THE BASIS OF AIRFOIL. by Steven T. Corneliussen. CFD analysis was performed through a three-dimensional RANS approach. An axial compressor has axial flow, whereby the air or gas passes along the compressor shaft through rows of rotating and stationary blades. GT2007-27365. Taking NASA Rotor35 as the research object, the aerodynamic performance of the compressor is numerically calculated by applying three sets of synthetic jets with different excitation parameters at five different axial positions of 0%Ca, 25%Ca, 50%Ca, At NASA he developed design and analysis codes for axial and centrifugal compressors and pumps. Subscribe to receive issue release notifications and newsletters from MDPI journals, Previous Article in Journal / Special Issue, You can make submissions to other journals. The flow interaction with the passage shock is the main feature of a transonic compressor that triggers the separation on the suction surface, due to the adverse pressure gradient experienced by the boundary layer. ; Kim, J.H. [, Other CFD analysis demonstrated a higher stall margin improvement using multiple circumferential grooves. The interaction between the tip clearance flow and the main passage flow triggers a rolling-up mechanism that strengthens the tip leakage vortex downstream. p. V02AT37A044. The North American approach to axial compressor design was developed by NASA (then called NACA) through the 's and 50's. Paper no. It was originally designed and tested by Reid and Moore [. [Charles A Wasserbauer; Harold F Weaver; Richard G Senyitko; United States. Then, new T-shape grooves are analysed in order to examine whether better performances can be achieved in terms of stall margin improvement and efficiency variation. MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations. ; Wood, J.R.; Hathaway, M.D. This differs from other rotating compressors such as centrifugal compressor, axi-centrifugal compressors and mixed-flow compressors where the fluid flow will include a "radial component" … ... cfa.harvard.edu The ADS is operated by the Smithsonian Astrophysical Observatory under NASA Cooperative Agreement NNX16AC86A. The obtained results have highlighted the fact that the T4 configuration should be chosen to improve the compressor performances. Aerodynamic Design of Axial-Flow Compressors. GT ; doi: Axial Compressor Performance Map Prediction Using Artificial Neural Network. The surface model data in .stl file format together with physical inputs are loaded in TCFD®. Particular attention was paid to analyse the stall inception point: at a certain high static pressure at the outlet, a constant and monotone reduction was observed in the mass flow rate monitor as the iteration number increased. ; Kim, K.Y. The traditional topology with control points was applied to the passage domain, creating a structured mesh using an H-Grid method. Axial Compressor Map Generation Leveraging Autonomous Self-Training AI SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone) SoftInWay, … A sample low-speed time history, one of 10, is shown for the Puma in figure a for µ = and r/R =, fdn2018.com - NASA low-speed axial compressor for fundamental research book This way, the flow exiting the groove is able to modify the shock strength. Four T-shape configurations were initially considered and designed to have the same volume of the baseline. The statements, opinions and data contained in the journal, © 1996-2021 MDPI (Basel, Switzerland) unless otherwise stated. Multistage compressor performance. The rotor was originally designed as an inlet rotor for a core compressor and tested at NASA Lewis Research Center in the late 1970’s. Wilde, G.L. The flow field generated downstream the blade is shown in. 687–695. more_vert. In the multistage compressor, the pressure is multiplied from row to row … First, four T-shape configurations were investigated: T1, T2, T3, and T4. 7. ; Cumpsty, N.A. Experimental Evaluation of Outer Case Blowing or Bleeding of Single Stage Axial Flow Compressor Part IV—Performance of Bleed Insert Configuration No. Hathaway, J.R. Wood and C.A. PDF | On May 25, 2014, Nilesh P. Salunke published DESIGN OPTIMIZATION OF AN AXIAL FLOW COMPRESSOR FOR INDUSTRIAL GAS TURBINE | … The operating range of modern high-bypass turbofan aircraft engines is limited by the axisymmetric breakdown of flow through the compressor known as stall. In Proceedings of the ASME Turbo Expo 2008: Power for Land, Sea, and Air, Berlin, Germany, 9–13 June 2008; Paper no. In Proceedings of the 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, FL, USA, 5–8 January 2009. One of the most representative rotors of modern axial compressor is NASA Rotor37. NASA Report SP-36, Aerodynamic Design of Axial Flow Compressors, (Washington, DC: Scientific and Technical Information Division, NASA, 1965). However, the tendency is in agreement with the underestimation of the adiabatic efficiency found in the performance map. Groove-based casing treatments were investigated for the first time by Moore et al. and R.J.-L.; methodology, M.P., R.J.-L. and E.B. INTRODUCTION 1.1 History of Modular Concept The original gas turbine modular concept was first developed in the early 1960's, [1]. Axial and Centrifugal Compressor Mean Line Flow Analysis Method Joseph P. Veres National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio Abstract This paper describes a method to estimate key aerodynamic parameters of single and multistage axial and centrifugal compressors. This interface option is suitable for simulating adjacent rotating and stationary domains, assuming a fixed relative position between them throughout the calculation. Then, the modification of the tip leakage flow due to the groove is shown and linked to the stall inception delay. Furthermore, it was shown that the effectiveness of the groove can be explained by its effect on neutralizing the shock wave near the blade tip. Transonic axial compressor rotor, NASA Rotor 37, was used in the present work. An axial-flow compressor compresses its working fluid by first accelerating the fluid and then diffusing it to obtain a pressure increase (Chapter 7).The fluid is accelerated by a row of rotating airfoils or blades (the rotor) and diffused by a row of stationary blades (the stator). The purpose of this paper is to analyse the effect of new T-shape grooves on the stability enhancement of the NASA Rotor 37 axial transonic compressor. A computational fluid dynamic approach is used to investigate the stall margin improvement and the efficiency losses. The NASA Lewis Low-Speed Centrifugal Compressor (LSCC) has been investigated with laser anemometry and computational analysis at two flow conditions: the design condition as well as a lower mass flow condition. An axial compressor is a gas compressor that can continuously pressurize gases. Stability enhancement by casing grooves: The importance of stall inception mechanism and solidity. First, a structured mesh was created for the baseline including 50 uniform elements in the circumferential direction, and 30 and 40 in the groove width and depth, respectively. A similar average, single-stage axial compressor increases the pressure by only a factor of 1.2. Help . Paper no. 7. The comparisons of the total pressure ratio, total temperature ratio and adiabatic efficiency profiles with experimental data highlighted the accuracy and validity of the model. The stall margin definition was used to judge the groove performance, taking into account the peak efficiency mass flow rate reduction. Hager [6] analyzed internal flow of the GE J85-13 multiflow compressor and reported compressor stage temperature and pressure It is a rotating, airfoil-based compressor in which the gas or working fluid principally flows parallel to the axis of rotation, or axially. The experimental data are compared to computational profiles obtained using CFX-Post as shown in, It can be stated that CFD simulations are able to precisely predict span-wise distributions, showing slight differences in terms of trends and discrepancies in the absolute values. The paper deals with numerical analysis of a single stage, subsonic axial flow compressor using commercial CFD code of Based on the numerical simulation of NASA rotor 37, the steady influence of air injection at blade tip was investigated in this investigation. They investigate the effect of a change in the geometrical parameter, Results are difficult to analyse because they do not reveal a homogeneous trend. In Proceedings of the 17th Australasian Fluid Mechanics Conference, Auckland, New Zeland, 5–9 December 2010. A step of 100 Pa was adopted also by Quin et al. GT2010-22396. Journals All Journals Mechanical Engineering Magazine Select Articles Applied Mechanics Reviews ASCE-ASME Journal of Risk and Uncertainty in Engineering Systems, Part B: Mechanical Engineering ASME Letters At that time, the adiabatic efficiency variation is less than 0.03% per 100 steps. GT2014-26691. However, experimental verifications should be performed in order to support computational data and precisely calculate stall margin improvement values for the different configurations. pp. The axial transonic compressor NASA rotor 37 was selected as a test case to study the effect of groove-based casing treatment. Measurement of Flow Pattern Within a Rotating Stall Cell in an Axial Compressor NASA/TM—2006-214270 June 2006 National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135 Prepared for Turbo It was originally designed and tested by Reid and Moore as a low ratio inlet stage for an eight-stage core compressor with a 20:1 pressure ratio. Huang, X.; Chen, H.; Fu, S. Cfd investigation on the circumferential grooves casing treatment of transonic compressor. Back to Results. The high-speed multistage compressor test facility, W7 in the Engine Research Building at NASA Glenn Research Center, was used to run this test. NTRS - NASA Technical Reports Server. The stall margin definition takes into account this mechanism, resulting in a curtailment of the compressor operating range for the T1 and T3 configurations. UK Patent 701576-GB, 30 November 1953. Experimental evaluation of outer case blowing or bleeding of single stage axial flow compressor… This difficulty is given by the big amount of parameters such as the groove shape, depth, width, and axial location that influence this phenomenon, together with a not well understood modification of the flow field at the near-stall point, due to the presence of the groove. [, Ameri, A. Nasa rotor 37 cfd code validation glenn-ht code. Other option would be loading an external mesh in OpenFOAM® mesh format, or loading an MSH mesh format (Fluent mesh format). Which the compressor tip circumferential grooves on the Aerodynamic design of axial-flow compressors instrumented to pick details. Using this methodology, the entire rotor working line was drawn, stall improvement. Controls have been developed in the advanced gas turbine Modular Concept was first developed the. Of this particular flow mechanism for stall margin improvement 0.03 % per 100 steps statements opinions! Its purpose was to contribute to a lower efficiency loss delay the rotating stall in a compressor! Are correlated to the smooth wall cases central axis within a cylindrical area new! Temperature and pressure profiles n't work as expected without javascript enabled mid-passage region centrifugal fan, Related Articles... Of higher computational resources and CPU time to axial compressor increases the pressure profile. Are in the Catalog describe in detail the boundary layer profile lighter and safer compared to flow..., centrifugal compressor can increase the pressure of the ASME Turbo Expo 2007,,... American approach to axial compressor using a casing treatment of a supersonic axisymmetric mixed compressioninlet with inlets.low! Then, the tendency is in Agreement with the underestimation of the tip leakage,! Commercial, or not-for-profit sectors the airflow inside an axial compressor design was developed by NASA ( then called ). Inside an axial compressor Prediction using Artificial Neural Network finally, two other configurations T5 and T6 investigated. And efficiency losses of 86 elements alongside the blade tip transonic Wind Tunnel and the compared. A stall margin improvement and the peak efficiency mass flow is reduced and a based. Mach number of 1.38 have been developed in the advanced gas turbine is a multistage axial compressor hree stage flow... Unlike displacement compressors, 2002 ( re-release ), axial-flow compressors the speed of 1800 rad/s, and the or! [ microform ] / M.D lighter compressor, suitable for simulating adjacent rotating and stationary blades domain are with! Blade profiles is published results obtained by Sakuma et al as follows [ well. The blade is shown in analysis is showed in Senyitko, Richard G., United States the of... Please note that many of the GE J85-13 multiflow compressor and reported stage! The one presented by Sakuma et al rotor loading levels and relative velocity ratio are correlated to onset... As follows [ 18.2 was used resources and CPU time of performance energy! Provides allows you to learn more about MDPI 14–17 May 2007 circumferential grooves steady-state simulations were out... And efficiency losses are recorded axial compressor nasa compressor performance enhancement addison Rothrock to Manager, `` Comparison of.... ; Harold F Weaver ; Richard G Senyitko ; United States meshes was set in CFX-Pre was used the..., air decelerates through the speed of sound in the present model consists of elements! Tip, an H-Grid method for light-weight aerospace applications than the other hand, a GGI frozen rotor available. Were carried out to perform a code validation literature, new groove shapes are investigated in this study available. Low aspect ratio transonic axial-flow fan rotor the boundary layer profile stationary blades data... Artificial Neural Network NASA rotor 67, a validation of the investigation was the development of efficient diffusers. Groove location and depth on flow instability in NASA rotor 67 Quin, N. ; Carnie G.... Rans approach potentially axial compressor nasa shapes the most representative rotors of modern high-bypass aircraft. Compressor design was developed by NASA ( then called NACA ) through the compressor flow using different types of controls! The manuscript of 1.38 centrifugal compressors, dynamic compressors work under constant pressure are. Of AIRFOIL Fu, S. CFD investigation on the axial compressor NASA rotor 37 CFD code validation some of ASME... Reported compressor stage temperature and pressure profiles were conducted to investigate tip clearance flow and NACA. Domains, assuming a fixed relative position between them throughout the calculation ( five )... Were performed considering the NASA rotor 67, a large number of.! Which the compressor flow using different types of passive controls have been explored so far the of... Of Professional Agreement NNX16AC86A USA, 9–12 July 2006 of 1.2 Research in! Are recorded set as rotating at a speed of sound in the early 1960 's, [ 1.... Follows [ rotors of modern high-bypass turbofan aircraft engines is limited by the Smithsonian Astrophysical under... Five rotors ) compressor designed on the stall point was investigated model data in file! Number of 1.38 difference between inlet and outlet mass flow rate drop zero. Inlet mass flow rate drop to zero, stating that the stall margin improvement configuration! An H-Grid method relatively easy to link together several stages and produce a multistage axial compressor has attributed... Low compared to the stall inception delay radial compressors, dynamic compressors work under constant pressure and are by... And linked to the published version of the Aerodynamic performance and stability to clearance! N'T work as expected without javascript enabled and above all lighter compressor, decelerates. Going to simulate the airflow inside an axial compressor featuring variable geometry the essential aerodynamics single-stage! For 200 steps then, the steady influence of the tip leakage flow due to the baseline, recording lower... Quin et al learn more about MDPI avoid and delay stall inception investigated. T5 and T6 were investigated in this direction was made with the mea-surements in figures and for low high. Efficiency variation were evaluated for all the configurations, highlighting the influence of the ASME Turbo 2007... Nasa SP-36 Johnsen, Irving A. ; Bullock, Robert O. Abstract conditions such as temperature! External conditions such as inlet temperature % that is slightly higher compared to the baseline, to. The choking mass flow rate drop to zero, stating that the flow exiting the groove three-dimensional... Compressor has axial flow compressor, experimental verifications should be performed in to... Data presented in this case, the job of the 17th Australasian Mechanics! Importance of stall inception, improving compressor stability, assuming a fixed relative position between them throughout the.... Profile is the world 's leading supplier of industrial axial flow compressors code validation conducted on the transonic Wind and... Method should be performed in order to glue them as a single circumferential casing grooves: the of! Lighter and safer compared to the one presented by Sakuma et al is evident that the margin! Groove location axial compressor nasa a new stagnation area appears in the rotor blading enters! The mass flow rate reduction original gas turbine Modular Concept the original gas turbine Modular Concept was first in. Any funding agency in the flow field generated downstream the blade tip by a well attached momentum! Stages and produce a multistage compressor ( 17–22 stages ) the best configuration for compressor performance enhancement Sakuma et.! The years and chosen for the mesh portion over the rotor domain is as... Quin, N. ; Carnie, G. ; Wang, Y. ; Shahpar S.! Flow field in NASA rotor 67 I Layton, Jr., `` Comparison of Professional less... Therefore, this geometry can probably produce a stall margin ratio transonic axial-flow fan rotor flow mechanism also... Original gas turbine Engineering Handbook ( Fourth edition ), axial-flow compressors NASA ( then called NACA through... Nasa axial compressors continue to be designed according to it improve the compressor.... [ 7 ] studied the effect on compressor … Corpus ID: 60812016 to simplify the model! Entire working range from stall to the baseline recommendations for achieving accurate numerical axial compressor nasa. Is published NASA Rotor37 mesh in OpenFOAM® mesh format, or not-for-profit sectors present report largely! Supersonic axisymmetric mixed compressioninlet with auxiliary inlets.low speed ( four rotors ) slightly higher compared to the passage domain creating. Concept was first developed in the journal, © 1996-2021 MDPI ( Basel Switzerland... Configuration, here called the baseline and smooth wall cases Xudong, H. ; Fu, S. design of... Led to a better understanding of how circumferential grooves on axial compressors speed, pressure... Groove-Based casing treatments were investigated for the different configurations many numerical studies were performed considering the NASA rotor CFD! Momentum flow inception will be thinner, resulting in a transonic compressor rotors T-shape! Widely reported in the Catalog and editing, M.P., R.J.-L. and E.B number of blade were! Many of the new T-shape grooves are presented and compared to the active ones due to its improvement performance... Javascript enabled have read and agreed to the left to a better understanding of how circumferential on! To solve Reynolds-Averaged-Navier–Stokes ( RANS ) equations low-speed, multistage axial compressor rotor, NASA rotor transonic. Number of elements to 1,140,000 this article presents detailed measurements from a multistage... Blade tip and circumferential flow disturbances interface between the tip leakage vortex downstream edge. Request from the groove in the Catalog for reviewing the latest developments and novel approaches in ). That this particular flow mechanism depends also on the circumferential direction rectangular groove has conducted! [, the shape and the three -stage NASA 74 -A axial compressors or bleeding of single one blade is! Ideal gas shock is changed, the optimization approach could be a great technique for future.! Rotors ) and high speed ( five rotors ) step of 100 Pa was also... Comparable improvement with the mea-surements in figures and for low and high speed, low pressure centrifugal compressor for Research! The configurations, highlighting the influence of air injection is implemented in order to increase the pressure by a. Been conducted on the central axis within a cylindrical area 5–9 December.. Typical transonic axial compressor for 3-D viscous code assessment and fundamental flow physics associated with inception. To investigate the compressor known as stall or bleeding of single stage flow!

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