[. The statements, opinions and data contained in the journal, © 1996-2021 MDPI (Basel, Switzerland) unless otherwise stated. Mirzabozorg, A.S.; Bazazzadeh, M.; Hamzezade, M. Numerical study on the effect of single shallow circumferential groove casing treatment on the flow field and the stability of a transonic compressor. NASA-SP-36, Axial Flow Compressors, 2002 (re-release), NTIS. In Proceedings of the 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Sacramento, CA, USA, 9–12 July 2006. Paper no. For the mesh portion over the blade tip, an H-Grid not matching topology was set. Legras, G.; Trebinjac, I.; Gourdain, N.; Ottavy, X.; Castillon, L. A novel approach to evaluate the benefits of casing treatment in axial compressors. Mean-line calculation through a compressor rotor. The aim of this work was to contribute to a better understanding of how circumferential grooves work and to investigate new potentially effective shapes. Paper no. An axial compressor has axial flow, whereby the air or gas passes along the compressor shaft through rows of rotating and stationary blades. Transonic axial compressor rotor, NASA Rotor 37, was used in the present work. NASA Stage 37 and the three-stage NASA 74-A axial compressors were analyzed and the results compared to test data. MAN Diesel & Turbo is the world's leading supplier of industrial axial flow compressors. Wilde, G.L. The evolution of the aerodynamic design of low-speed axial fans during the years. Finally, the performances of the new T-shape grooves are evaluated and compared to the baseline and to the smooth wall cases. The operating range of modern high-bypass turbofan aircraft engines is limited by the axisymmetric breakdown of flow through the compressor known as stall. 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 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. 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. Then, an interface between the two meshes was set in CFX-Pre in order to glue them as a single fluid domain. National Aeronautics and Space Administration. [. In Proceedings of the ASME Turbo Expo 2007, Montreal, QC, Canada, 14–17 May 2007. Haixin, C.; Xudong, H.; Song, F. Cfd investigation on stall mechanisms and casing treatment of a transonic compressor. Received: 5 November 2020 / Revised: 14 December 2020 / Accepted: 23 December 2020 / Published: 4 January 2021, (This article belongs to the Special Issue. All authors have read and agreed to the published version of the manuscript. First, a validation of the computational model was carried out analysing a smooth wall case without grooves. Hager [6] analyzed internal flow of the GE J85-13 multiflow compressor and reported compressor stage temperature and pressure Results presented so far highlight the accuracy and the reliability of the computational model. As the tip leakage vortex interaction with the blade tip clearance flow produces the most critical region of low momentum fluid [, Grooves are circumferentially continuous cavities cut into the endwall above the rotor tip that modify locally the flow field changing and delaying the stall inception process. Van Zante, D.E. Axial Compressor Map Generation Leveraging Autonomous Self-Training AI SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone) SoftInWay, … axial compressor (NASA Rotor 37) under the transonic condition were analyzed numerically by alternatively using the Spalart-Allmaras and the SST -ω turbulence models. 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. It is thought that this particular flow mechanism depends also on the axial position of the groove. Aerodynamic Design of Axial-Flow Compressors. This happens because the reduction of the stall point mass flow rate is not enough to compensate for the decrease of the peak efficiency mass flow rate triggered by the groove. The stall margin definition was used to judge the groove performance, taking into account the peak efficiency mass flow rate reduction. In Proceedings of the ASME Turbo Expo 2008: Power for Land, Sea, and Air, Berlin, Germany, 9–13 June 2008; Paper no. For this reason, it is more suitable for light-weight aerospace applications than the other configurations. [, Muller, M.W. © 2020, National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, National Technical Information Service, distributor]. The obtained results have highlighted the fact that the T4 configuration should be chosen to improve the compressor performances. Cevik, M. Axial Compressor Gas Path Design for Desensitization of Aerodynamic Performance and Stability to Tip Clearance. [, Boretti, A. Rotating stall is the direct cause of blade failures in resonant vibration as well as the indirect cause of mechanical problems due to the frequently associated duality in compressor behavior. A pressure ratio of about 1.8 at an efficiency of about 80 percent has been obtained Weaver, Harold F., Senyitko, Richard G., United States. The test data on these blade profiles is published. by Steven T. Corneliussen. But it is relatively easy to link together several stages and produce a multistage axial compressor. NTRS - NASA Technical Reports Server. Introducing the 2019-2020 NASA Software Catalog. These effects delay stall inception, improving compressor stability. The same discrepancies were registered by Ameri [. On the other hand, near the blade suction surface, the separation was suppressed by a well attached high momentum flow.

Three-Dimensional Flows in Axial. Charles A. Wasserbauer, Harold F. Weaver, Richard G. Senyitko. Keeping the same groove depth and extending the horizontal arm, a worsening of the stall margin is obtained for the T5 configuration compared to the baseline, while an improvement is recorded for the T6 configuration with respect to T1. The detailed specifications of the compressor are summarized in Table 1 . Mastering Microsoft Internet information server 4. GT ; doi: Axial Compressor Performance Map Prediction Using Artificial Neural Network. Full text of "NASA Technical Reports Server (NTRS) Performance of NACA Eight-stage Axial-flow Compressor Designed on the Basis of Airfoil Theory" See other formats FILE COPY NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS REPORT No. An axial compressor is a gas compressor that can continuously pressurize gases. ; Wood, J.R.; Hathaway, M.D. 2010-216235. Experimental and computational techniques are used to investigate tip clearance flows in a transonic axial compressor rotor at design and part speed conditions. In the multistage compressor, the pressure is multiplied from row to … Numerical studies have been performed under both design and off-design flow conditions to investigate the effects of boundary layer suction (BLS) on corner separation in a highly loaded compressor cascade. Numerical analysis of flow in a transonic compressor with a single circumferential casing groove: Influence of groove location and depth on flow instability. The North American approach to axial compressor design was developed by NASA (then called NACA) through the 's and 50's. Theory of operation. Meherwan P. Boyce, in Gas Turbine Engineering Handbook (Fourth Edition), Axial-Flow Compressors. The first phase of the investigation was the development of efficient supersonic diffusers to decelerate air through the speed of sound. Since it was not possible to create a single structured mesh including both the blade and the groove domains using Turbo-Grid, a separate mesh for the casing treatment was generated using ICEM CFD. At that time, the adiabatic efficiency variation is less than 0.03% per 100 steps. The blade, the hub, and the shroud are considered as no slip smooth adiabatic walls in a rotating (blade and hub) or counter-rotating (shroud) frame type. Journals. However, this benefit is followed by a reduction in the pressure ratio absolute value at the same normalized mass flow rate and a left shift of the choking mass flow rate (20.87 kg/s) for all of the configuration. Active control methods modify the compressor flow using different types of actuators and feedback control systems. National Aeronautics and Space Administration. A low speed, low pressure centrifugal compressor or centrifugal fan, Related Research Articles. This thesis presents a large scale model of axial compressor flows that is detailed enough to describe the modal and spike stall inception processes, and is also amenable to dynamical systems analysis and control design. Steady-state simulations were conducted to investigate the compressor performance. Huang et al. UK Patent 701576-GB, 30 November 1953. The present report is largely a general discussion of some of the essential aerodynamics of single-stage supersonic axial-flow compressors. This historical overview starts from the first fan applications, dating back to the 16th century, and arrives to the modern times of computer-based design techniques, passing through the pioneering times of aerodynamic theories and the times of designing before by: 1. ; data curation, M.P. … Based on the numerical simulation of NASA rotor 37, the steady influence of air injection at blade tip was investigated in this investigation. The results show that surge is initiated by rotating stall, and that the ensuing surge cycle is a sequence of well ordered cause … Corpus ID: 60812016. Written in English. Control of corner separation has attracted much interest due to its improvement of performance and energy utilization in turbomachinery. NASA SP-36 @inproceedings{Johnsen1965AerodynamicDO, title={Aerodynamic Design of Axial-Flow Compressors. This work focuses its attention on possibilities to enhance the stability of an axial compressor using a casing treatment technique. [, Many numerical studies were performed considering the NASA Rotor 37 transonic axial compressor. The paper presents a historical overview of the developments of aerodynamic design methods for low-speed axial-flow fans. The effect of grooves located from 15% to 40% of the chord is The baseline stall margin improvement value is quite low compared to the results obtained by Sakuma et al. [. Choi, K.J. 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