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Relevant bibliographies by topics / Compressors stage

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Academic literature on the topic 'Compressors stage'

Author: Grafiati

Published: 30 May 2022

Last updated: 31 May 2022

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Journal articles on the topic "Compressors stage"

1

Lei, Fan, and Chuhua Zhang. "Preliminary Optimization of Multi-Stage Axial-Flow Industrial Process Compressors Using Aero-Engine Compressor Design Strategy." Applied Sciences 11, no. 19 (October 5, 2021): 9248. http://dx.doi.org/10.3390/app11199248.

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Aero-engine core compressor preliminary design strategy has been successfully applied to the advanced design of gas turbines compressors. However, few researchers have addressed the application of the aero-engine core compressor preliminary design strategy in the preliminary optimal design of industrial process compressors. Here we embedded the aero-engine core compressor preliminary design strategy into a preliminary optimal design method, in which six types of design parameters widely used to define the aero-engine compressor configuration, i.e., aspect ratio, solidity, reaction, rotation speed, outlet axial Mach number, and inlet radius ratio, were used as the design variables. The 4-stage, 5-stage, 6-stage, and 7-stage compressor configuration with the same overall design requirements for a large-scale air separation main compressor were preliminarily optimized by the developed method, in which the 4-stage design has a stage pressure rise level of current aero-engine core compressors, whereas the 7-stage design has that of current industrial process compressors. The optimized compressor configurations were then refined with the throughflow-based detailed design method and finally verified with computational fluid dynamic simulations. It is found that the developed method can optimize design efficiency and accurately predict aerodynamic performance of compressors in a few minutes. Several design guidelines for the advanced industrial process compressors were also identified. This work is of significance in extending aero-engine core compressor design strategy to the design of advanced industrial process compressors.

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2

Li, Ting, Yuchuan Wang, Xiuli Mao, Diyi Chen, Rui Huang, and Quanke Feng. "Development and Experimental Study of the First Stage in a Two-Stage Water-Flooded Single-Screw Compressor Unit for Polyethylene Terephthalate Bottle Blowing System." Energies 13, no. 16 (August 16, 2020): 4232. http://dx.doi.org/10.3390/en13164232.

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The oil-free compressor is a key component in fabricating polyethylene terephthalate (PET) bottles for beverages and water. At present, the main compressor type used for blowing PET bottles is the reciprocating compressor. However, compared to screw compressors, reciprocating compressors have shortcomings of high energy consumption and too many consumable parts. Many manufacturers of PET bottles in Asia are seeking to replace reciprocating compressors with screw compressors, as we know. Screw compressors can be classified as single-screw compressors (SSC) and twin-screw compressors. Since the load in a twin-screw compressor is far larger than that in an SSC, SSCs are more suitable for being developed for high-pressure applications such as PET bottle blowing. This paper presents a performance study on an oil-free single-screw compressor as the first stage of the PET compressor unit. A 5.4 m3·min−1 prototype and its test rig were developed. The thermophysical process of the moist air is theoretically analyzed. The pressure loss on the flow path and the influence of the important parameters are experimentally investigated. It is found that water vapor cannot be separated during the adiabatic compression process. The results also show that the pressure loss from the discharging duct to the check valve accounts for the largest percentage of the total pressure loss. The experimental results further show that the discharge capacity and shaft power increase almost linearly with the motor speed. The efficiency declines with increasing injected water temperature. The discharge capacity and shaft power all increase with the injected water flowrate, and an optimum flowrate is found to ensure a highest isentropic efficiency. With the increase in discharge pressure, the discharge capacity decreases, and the shaft power increases. The isentropic efficiency is found to have its maximum value at a certain discharge pressure.

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Song, T. W., T. S. Kim, J. H. Kim, and S. T. Ro. "Performance prediction of axial flow compressors using stage characteristics and simultaneous calculation of interstage parameters." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 215, no. 1 (February 1, 2001): 89–98. http://dx.doi.org/10.1243/0957650011536598.

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A new method for predicting performance of multistage axial flow compressors is proposed that utilizes stage performance curves. The method differs from the conventional sequential stage-stacking method in that it employs simultaneous calculation of all interstage variables (temperature, pressure and flow velocity). A consistent functional formulation of governing equations enables this simultaneous calculation. The method is found to be effective, i.e. fast and stable, in obtaining solutions for compressor inlet and outlet boundary conditions encountered in gas turbine analyses. Another advantage of the method is that the effect of changing the angles of movable stator vanes on the compressor's operating behaviour can be simulated easily. Accordingly, the proposed method is very suitable for complicated gas turbine system analysis. This paper presents the methodology and performance estimation results for various multistage compressors employing both fixed and variable vane setting angles. The effect of interstage air bleeding on compressor performance is also demonstrated.

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Hönen, H. "Axial Compressor Stall and Surge Prediction by Measurements." International Journal of Rotating Machinery 5, no. 2 (1999): 77–87. http://dx.doi.org/10.1155/s1023621x9900007x.

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The paper deals with experimental investigations and analyses of unsteady pressure distributions in different axial compressors. Based on measurements in a single stage research compressor the influence of increasing aerodynamic load onto the pressure and velocity fluctuations is demonstrated. Detailed measurements in a 14-stage and a 17-stage gas turbine compressor are reported. For both compressors parameters could be found which are clearly influenced by the aerodynamic load.For the 14-stage compressor the principles for the monitoring of aerodynamic load and stall are reported. Results derived from a monitoring system for multi stage compressors based on these principles are demonstrated. For the 17-stage compressor the data enhancement of the measuring signals is shown. The parameters derived from these results provide a good base for the development of another prediction method for the compressor stability limit. In order design an on-line system the classification of the operating and load conditions is provided by a neural net. The training results of the net show a good agreement with different experiments.

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Kosuri, Lakshmi Thirumala, M. Deepika Krishna, Adilakshmi i. Karapat, B. S. B. Ayyappa Swamy, and Dinesh Nayak S. "A Low Power High Speed Accuracy Controllable Approximate Multiplier Design." International Journal for Research in Applied Science and Engineering Technology 10, no. 4 (April 30, 2022): 1625–30. http://dx.doi.org/10.22214/ijraset.2022.41617.

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Abstract: For energy effective and high performance design, the low power VLSI circuit is used. Multiplier is an essential part of low power VLSI design, since the effectiveness of the digital signal processor depends upon the multiplier. In multiplier circuit, utmost of the power is dissipated across in full adder circuits. Multiplication is one of the important process in microprocessor and there will be a lot of delay because of array multiplier, which can be compressed with the help of the column compressor approach. It uses a selection of half adders, full adders and compressors to sum the partial products in stages until two numbers are left. An 8 * 8 and 16 * 16 bit multiplier design is executed by assigning the adder and compressor. Partial product totality is the speed limiting operation in multiplication due to the propagation detention in adder networks. In order to reduce the propagation detention, compressors are introduced. Compressors calculate the sum and carry at each position concurrently. The attendant carry is added with a advanced significant sum bit in the coming stage. This is continued until the final product is generated. The partial product tree of the multiplier is estimated by the proposed tree compressor ( High Speed Compressor, Dual Stage Compressor, Exact Compressor). Keywords: Partial Products, Half Adder, Full Adder, High Speed Compressor, Dual Stage Compressor, Exact Compressor.

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Qi, Zhaogang, Jun Yang, Jiangping Chen, Haifeng Zhang, and Li Zhang. "Experimental investigation on a two-stage CO2 compressor with high back pressure." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 226, no. 7 (November 10, 2011): 1811–20. http://dx.doi.org/10.1177/0954406211428245.

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In this article, two samples of two-stage rolling piston CO2 compressors with and without intercooler are developed and experimentally studied. These CO2 compressors are high back-pressure compressors, which mean the pressure inside compressor shell is the discharge pressure of the second stage. A test rig was designed to measure the performance and efficiency of this compressor. The test results show that the suction vapor temperature at the second stage inlet pipe has few influences on the performance and efficiency of the first compressor sample with intercooler. The volumetric efficiency linearly decreases with the increase of compression ratio of the suction and discharge pressure, and the volumetric efficiency can maintain in a relative constant range during a wide compression ratio changes in this high back-pressure design. There exists an optimum compression ratio for each suction pressure at the first stage, where the compressor isentropic efficiency is maximum. A generalized volumetric efficiency correlation for two-stage CO2 rolling piston compressor as a function of compression ratio is proposed and it can describe 100% of the test data within ±5.0% with a mean deviation of 1.7%. This would be helpful as a guide for designing such type compressor.

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Hamersztein, A., A. Davidesko, and N. Tzabar. "Numerical optimization of a multistage sorption compressor." Journal of Physics: Conference Series 2116, no. 1 (November 1, 2021): 012113. http://dx.doi.org/10.1088/1742-6596/2116/1/012113.

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Abstract Sorption compressors are driven by thermal cycles and have no moving parts, excluding some passive check valves. Such compressors are suitable for powering Joule-Thomson (JT) cryocoolers and can provide reliable and vibration free active cooling system with a potential for high reliability and long operating life. The thermal cycle consists of cooling and heating a sorbent material which is installed in a sorption cell, where the heating is obtained by an inner electric heater and cooling is obtained by the surrounding via the sorption cell envelope. The investigation and optimization of the sorption cells were conducted in previous work, at steady state conditions, by a one-dimensional heat and mass transfer numerical model. The current paper presents a dynamic numerical model of sorption compressors which consist of several sorption cells. The numerical model allows one to three compression stages, with any number of sorption cells at each stage. The model enables the investigation of dimensional parameters and operational parameters, and provides the low and high pressures, pressure fluctuations, and compressor’s efficiency. The current investigation focuses on a three-stage compressor for nitrogen, with low and high pressures of 0.2 and 8 MPa, respectively, and a mass flow rate of about 11 mg/s.

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Dalbert, P., B. Ribi, T. Kmeci, and M. V. Casey. "Radial compressor design for industrial compressors." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 213, no. 1 (January 1, 1999): 71–83. http://dx.doi.org/10.1243/0954406991522194.

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Industrial centrifugal compressors have a very large field of applications in chemical, petrochemical and gas transport applications with an enormous variety of gases, pressure levels and suction volumes. This paper describes the special design features of this type of compressor and sheds light on a method of standardization to overcome the large diversity of machine types. It reviews the aerodynamic and thermodynamic aspects in the design of impellers and diffusers, discusses the importance of the stage matching and illuminates the effect of stage components on stability.

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Giannissis, G. L., A. B. McKenzie, and R. L. Elder. "Experimental Investigation of Rotating Stall in a Mismatched Three-Stage Axial Flow Compressor." Journal of Turbomachinery 111, no. 4 (October 1, 1989): 418–25. http://dx.doi.org/10.1115/1.3262289.

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This paper reports on an examination of rotating stall in a low-speed three-stage axial flow compressor operating with various degrees of stage mismatch. The objective of this study was to simulate the mismatching that occurs in high-speed multistage compressors when operating near surge. The study of the stall zones involved the use of fast response measurement techniques. The study clearly shows how stages can operate in an axisymmetric fashion even when heavily stalled, since rotating stall inception requires the stall of more than one stage. The study also compares conditions required for full-span and part-span stall and suggests that the part-span stall structure is more relevant to high-speed multistage compressors.

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10

Rekstin, A., V. Semenovskiy, K. Soldatova, Y. Galerkin, and K. Sokolov. "The simulation of gas-dynamic characteristics of centrifugal compressors in turbo-expander units." E3S Web of Conferences 124 (2019): 01008. http://dx.doi.org/10.1051/e3sconf/201912401008.

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Prof. Y. Galerkin and his team have developed and completed designs of 19 single-stage centrifugal compressors for turbo-expander packaged units applying Universal Modeling Method for the company “Turbokholod JSC” since 2005. The most powerful compressor is 6500 kW. The highest delivery pressure is 12 MPa. One hundred fifteen turbo-expander packaged units with total capacity 400 000 kW were manufactured, installed and were in operation in December 2018. The gas-dynamic characteristics of compressors comply with technical specification when operated within given range of initial temperatures and initial and final pressures up to 16 combinations for some compressors. The dimensionless characteristics of the compressor stages vary within the range of design parameters: flow rate coefficient 0.0278-0.0697, loading factor 0.43-0.71. The simulation of gas-dynamic characteristics of one of the designed compressors by the newest version of mathematical model is presented as an example, demonstrating the simulation features and effectiveness.

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Dissertations / Theses on the topic "Compressors stage"

1

Baker, Jonathan D. "Analysis of the sensitivity of multi-stage axial compressors to fouling at various stages." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02Sep%5FBaker.pdf.

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2

Gallimore, Simon John. "Spanwise mixing in multi-stage axial compressors." Thesis, University of Cambridge, 1986. https://www.repository.cam.ac.uk/handle/1810/250879.

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3

Barile, Kristina (Kristina Marie). "Impeller loss reduction in multi-stage centrifugal compressors." Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/97364.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 74-75).
Loss generation features for the first stage impeller in a multistage centrifugal compressor are examined using three-dimensional RANS computations. The calculations were carried out for a baseline configuration and for seven other impeller configurations, with the constraints of constant mass flow and constant work per unit mass flow. The computations showed an 8 percent reduction in loss, compared to the baseline, for a configuration that incorporated 60% of the total casing blade angle change in the front 20% chord. Twodimensional interactive boundary layer computations were carried out to demonstrate links between the loss variation and the changes in boundary layer behavior in the front 20% of the blade passage.
by Kristina Barile.
S.M.

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4

DiPietro, Anthony Louis. "Effects of temperature transients on the stall and stall recovery aerodynamics of a multi-stage axial flow compressor." Diss., This resource online, 1997. http://scholar.lib.vt.edu/theses/available/etd-10052007-143638/.

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Bloch, Gregory S. "A wide-range axial-flow compressor stage performance model." Thesis, This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-08182009-040326/.

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6

Davis, William L. "Stall analysis in a transonic compressor stage and rotor." Thesis, Monterey, Calif. : Naval Postgraduate School, 2009. http://handle.dtic.mil/100.2/ADA501343.

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Thesis (M.S. in Mechanical Engineering)--Naval Postgraduate School, June 2009.
Thesis Advisor(s): Gannon, Anthony J. "June 2009." Description based on title screen as viewed on July 13, 2009. DTIC Identifiers: TCR (Transonic Compressor Rig). Author(s) subject terms: Compressor, Transonic, Stall, Surge. Includes bibliographical references (p. 73-74). Also available in print.

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Aubry, Anne-Raphaëlle. "Return channel loss reduction in multi-stage centrifugal compressors." Thesis, Massachusetts Institute of Technology, 2012. http://hdl.handle.net/1721.1/76091.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2012.
Cataloged from PDF version of thesis.
Includes bibliographical references (p. 61-63).
This thesis presents concepts for improving the performance of return channels in multi-stage centrifugal compressors. Geometries have been developed to reduce both separation and viscous losses. A number of different features with potential to reduce separation have also been investigated. The final proposed geometry uses a vaneless diffuser which narrows on the shroud side at the beginning of the 180' bend, an axially extended 1800 bend with increasing radius of curvature, and return channel vane leading edge radial position at an increased radius compared to the baseline. Three-dimensional calculations showed a 9% loss reduction compared to previous work [1], with a cumulative loss reduction of 19% compared to a baseline geometry. The geometry developed was based on specified inlet conditions. To examine the potential for increased performance if this constraint was removed, a return channel geometry was also defined that incorporated the same features but allowed modified inlet conditions, specifically radial inlet flow. The design of the impeller required for this new inlet flow was not considered. An overall loss reduction of 23% compared to baseline was found from the calculations. Modification of the impeller geometry is thus proposed as future work.
by Anne-Raphaëlle Aubry.
S.M.

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8

Davis, Milton W. "A stage-by-stage post-stall compression system modeling technique: methodology, validation, and application." Diss., Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/50002.

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A one-dimensional, stage-by-stage axial compression system mathematical model has been constructed which can describe system behavior during post-stall events such as surge and rotating stall. The model uses a numerical technique to solve the nonlinear conservation equations of mass, momentum, and energy. Inputs for blade forces and shaft work are provided by a set of quasi-steady stage characteristics modified by a first order lagging equation to simulate dynamic stage characteristics. The model was validated with experimental results for a three-stage, low-speed compressor and a nine-stage, high-pressure compressor. Using these models, a parametric study was conducted to determine the effect of inlet resistance, combustor performance, heat transfer, and stage characteristic changes due to hardware modification on post—stall system behavior.
Ph. D.
incomplete_metadata

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9

Davis, Milton W. Jr. "A stage-by-stage post-stall compression system modeling technique: methodology, validation, and application." Diss., Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/50002.

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A one-dimensional, stage-by-stage axial compression system mathematical model has been constructed which can describe system behavior during post-stall events such as surge and rotating stall. The model uses a numerical technique to solve the nonlinear conservation equations of mass, momentum, and energy. Inputs for blade forces and shaft work are provided by a set of quasi-steady stage characteristics modified by a first order lagging equation to simulate dynamic stage characteristics. The model was validated with experimental results for a three-stage, low-speed compressor and a nine-stage, high-pressure compressor. Using these models, a parametric study was conducted to determine the effect of inlet resistance, combustor performance, heat transfer, and stage characteristic changes due to hardware modification on post—stall system behavior.
Ph. D.
incomplete_metadata

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10

Russler, Patrick M. "An investigation of the surge behavior of a high-speed ten-stage axial flow compressor." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-09192009-040554/.

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Books on the topic "Compressors stage"

1

Steinke, Ronald J. Design of 9.271-pressure-ratio five-stage core compressor and overall performance for first three stages. Cleveland, Ohio: Lewis Research Center, 1986.

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2

Hill, Philip G. An educational introduction to transonic compressor stage design principles. Warrendale, Pa: Society of Automotive Engineers, 1993.

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3

Haynes, Joel M. Active control of rotating stall in a three-stage axial compressor. Cambridge, Mass: Gas Turbine Laboratory, Massachusetts Institute of Technology, 1993.

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4

Wilde, Geoffrey. Flow matching of the stages of axial compressors. Derby: Rolls-Royce Heritage Trust, 1999.

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5

O'Brien, Joseph Morton. Transonic Compressor Test Rig rebuild and initial results with the Sanger stage. Monterey, Calif: Naval Postgraduate School, 2000.

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6

Newman, Frederick A. Experimental vibration damping characteristics of the third-stage rotor of a three-stage transonic axial-flow compressor. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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7

Chmielniak, Tadeusz. SYMKOM'99: International conference compressor & turbine stage flow path theory, experiment & user verification. Łódź: Politechnika Łʹodzka, Instytut Maszn Przeoływowych, 1999.

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8

Swansson, N. S. Investigation of blade vibration T55-L-11C compressor stages 1 and 2. Melbourne, Victoria: Aeronautical Research Laboratories, 1985.

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9

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. Design of 9.271-pressure-ratio five-stage core compressor and overall performance for first three stages. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Design of 9.271-pressure-ratio five-stage core compressor and overall performance for first three stages. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Book chapters on the topic "Compressors stage"

1

Du, W. H., H. Wu, and L. Zhang. "Off-design Performance Analysis of Multi-Stage Transonic Axial Compressors." In New Trends in Fluid Mechanics Research, 504. Berlin, Heidelberg: Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-75995-9_167.

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2

Wilson, K. B., and D. R. Gedeon. "Development of Single and Two-Stage Pulse Tube Cryocoolers with Commercial Linear Compressors." In Cryocoolers 12, 139–47. Boston, MA: Springer US, 2003. http://dx.doi.org/10.1007/0-306-47919-2_20.

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Boiarski, M. J., V. M. Brodianski, and R. C. Longsworth. "Retrospective of Mixed-Refrigerant Technology and Modern Status of Cryocoolers Based on One-Stage, Oil-Lubricated Compressors." In Advances in Cryogenic Engineering, 1701–8. Boston, MA: Springer US, 1998. http://dx.doi.org/10.1007/978-1-4757-9047-4_214.

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Alfsen, Erik M., and Frederic W. Shultz. "General Compressions." In Geometry of State Spaces of Operator Algebras, 211–49. Boston, MA: Birkhäuser Boston, 2003. http://dx.doi.org/10.1007/978-1-4612-0019-2_7.

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Alfsen, Erik M., and Frederic W. Shultz. "Ideals, Faces and Compressions." In State Spaces of Operator Algebras, 130–75. Boston, MA: Birkhäuser Boston, 2001. http://dx.doi.org/10.1007/978-1-4612-0147-2_3.

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Ferrone, Alex. "Theatrical Compressions of Time and Space." In Stage Business and the Neoliberal Theatre of London, 89–141. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-63598-5_3.

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Wartzek, Fabian, Felix Holzinger, Christoph Brandstetter, and Heinz-Peter Schiffer. "Realistic Inlet Distortion Patterns Interacting with a Transonic Compressor Stage." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 285–302. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-21127-5_17.

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Bonhoff, K., and H. Barthels. "Operating Experiences of a Two-Stage Metal Hydride Hydrogen Compressor." In Hydrogen Power: Theoretical and Engineering Solutions, 383–88. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-015-9054-9_51.

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Groza, Doru, Ioan Călin Roșca, and Gheorghe Alexandru Radu. "Balancing of a Single Stage Reciprocating Compressor with Elastic Elements." In CONAT 2016 International Congress of Automotive and Transport Engineering, 305–10. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-45447-4_34.

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Pfotenhauer, J. M., and J. H. Baik. "Compressor-Specific Design of a Single Stage Pulse Tube Refrigerator." In Cryocoolers 11, 249–57. Boston, MA: Springer US, 2002. http://dx.doi.org/10.1007/0-306-47112-4_33.

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Conference papers on the topic "Compressors stage"

1

Kerrebrock, J. L., D. P. Reijnen, W. S. Ziminsky, and L. M. Smilg. "Aspirated Compressors." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-525.

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The performance of compressors can be improved in two ways by judicious removal from the flow path of the viscous flow in the boundary layers. First, removal of the boundary layer fluid just prior to or in a region of rapid pressure rise, either at shock incidence or more generally at the point of rapid pressure rise on the suction surface of the airfoil, can enable significant increases in the diffusion, hence in the work done by a stage for any given blade speed. Second, removal of the high entropy fluid in the boundary layer minimizes the required compression work in subsequent stages of compression, thereby raising the compression efficiency. Analysis has shown that the latter effect can result in approximately one half point increase in efficiency for each percent of (high entropy) fluid removal. Design studies have been carried out for two different stages to assess the increase in pressure ratio that may be achieved. One stage that has been designed would produce a pressure ratio of 2 at a tip speed of 1000 ft/sec, and may be very attractive for the fan stage of high-bypass turbofan engines. The other stage would produce a pressure ratio of 3 at a tip speed of 1500 ft/sec, and should be attractive as the first stage of a core compressor or the fan stage of a low-bypass ratio engine. An experiment has been completed, to examine the effect of boundary layer removal just prior to shock impingement on the suction surface of blades in a transonic rotor. The suction was implemented on 5 of the 23 blades of the rotor, providing a direct comparison of the flow behavior with and without suction. Analysis of the data has shown that the blades with suction have increased mass flow and that the flow more closely followed the suction surface near the trailing edge. The differences between aspirated and normal blades were most pronounced when the rotor was very close to stall. The third and fourth of the blades in the group with suction appear to be representative of the behavior to be expected of a rotor with suction on all blades. They exhibited improved efficiency and increased mass flow. The rotor as a whole with suction showed different stall behavior than its counterpart without boundary layer control. Future plans include the fabrication and experimental evaluation in the MIT Blowdown Compressor, of one of the two stages discussed above. In this experiment suction will be applied to all the blades in both rotor and stator, so that the increased work enabled by suction can be realized. This research was supported by AFOSR, Dr. James McMichael, and by AlliedSignal Aircraft Engines, Dr. Arun Sehra.

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Kang, Young Seok, Tae Choon Park, Byeung Jun Lim, and Hyung Soo Lim. "Comparison of Stall Characteristics of Multi-Stage and Single-Stage Transonic Axial Compressors." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64115.

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This study experimentally investigated compressor instability characteristics of two transonic axial compressors. From the stall precursors when their operating points are approaching the stall line, stall initiation and its development and its transition to compressor surge were measured with high frequency pressure transducers, step by step. First part of this paper describes three-stage transonic axial compressor instability characteristics. The compressor has been designed to have positive incidence angle in order from third stage to first stage as compressor outlet throttle valve closes at the design speed. Then periodic modal signal appeared from the third stage before it spread toward the first stage as a precursor of the compressor stall. However, the actual compressor stall took place from the first stage and developed toward the third stage. Interestingly, the stall cell spread toward downstream by spiral direction, which means stall cell moves with axial and circumferential velocity components. When the stall cell reached the collector through the third stage, sudden strong one-dimensional fluctuation, system surge, appeared. Then operating point revolved along the hysteresis loop on the compressor map repeatedly before anti-surge valve opened. Second part of this paper describes a single stage transonic compressor instability characteristics. Different from the three-stage compressor, spike type stall precursor was detected just ahead of rotating stall cell appearance. Before spike initiation there was no warning signal of compressor stall. When the spike was fully developed to the rotating stall, the operating points deviated from the operating line and settled at deteriorated operating points until the anti-surge valve opened. Also a weak compressor system Helmholtz frequency was detected regardless of the rotating speed. To identify the overall compressor instability behavior and difference between two axial compressors, Greizter’s B parameter was found to be very useful. B parameter of the three stage compressor was about 0.83, it means classic surge could occur at the final stage of instability. On the other hand, B parameter of the single stage compressor was 0.62. According to this B parameter, the single stage compressor stall would no longer develop to compressor surge and it well agrees with experimental results.

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Lawlor, Shawn P., John B. Hinkey, Steven G. Mackin, Scott Henderson, Jonathan Bucher, Paul M. Brown, and Ram Pudupatty. "Supersonic Compression Stage Design and Test Results." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-59914.

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Ramgen Power Systems, Inc. (RPS) is developing a family of high performance supersonic compressors that combine many of the aspects of shock compression systems commonly used in supersonic flight inlet design with turbo-machinery design practices employed in conventional axial and centrifugal compressor design. The result is a high efficiency compressor that is capable of single stage pressure ratios in excess of those available in existing axial or centrifugal compressors. A variety of design configurations for land-based compressors utilizing this system have been explored. A proof-of-concept system has been designed to demonstrate the basic operational characteristics of this family of compressors when operating on air. The test unit was designed to process ~1.43 kg/s and produce a pressure ratio across the supersonic rotor of 2.25:1. The theory of operation of this system will be reviewed along with selected results from initial performance tests.

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4

Hale, Alan, Jacqueline Chalk, Jason Klepper, and Karl Kneile. "Turbine Engine Analysis Compressor Code - TEACC. II - Multi-stage compressors and inlet distortion." In 17th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-3214.

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5

Rodgers, C. "The Efficiencies of Single-Stage Centrifugal Compressors for Aircraft Applications." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-077.

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The thrust of most recent advances in single– and two–stage centrifugal compressor technology by the aerospace community has been motivated by interest in increasing airbreathing propulsion system power density, and improving specific fuel consumption with higher stage pressure ratios. Advances in the last decade have made it appropriate to review the major design parameters influencing the efficiency levels of single–stage centrifugal compressors for aircraft applications. A simple efficiency correlation was derived for advanced single–stage centrifugal compressors. It was based upon four critical parameters: • Inlet Specific Speed • Impeller Tip Diameter • Inducer Tip Relative Mach Number • Exit Discharge Mach Number The correlation was shown to predict attainable state–of–the–art efficiencies within a band width of ± 2 % points. This was considered acceptable for preliminary compressor and engine design work.

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6

Methel, Jeanne, William J. Gooding, John C. Fabian, Nicole L. Key, and Mark Whitlock. "The Development of a Low Specific Speed Centrifugal Compressor Research Facility." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56683.

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To achieve aggressive specific fuel consumption goals, aircraft engines are tending toward higher overall pressure ratios and higher bypass ratios for turbofans. As sizes decrease to meet these requirements, centrifugal compressors become a viable option as the last stage of the high pressure compressor. The last stages of an axial compressor in a small core engine face reduced efficiency due to the relatively large tip clearances with respect to blade height, and therefore, it may be more appropriate to finish the final compression stage with a low specific speed centrifugal compressor. A new facility, the Centrifugal STage for Aerodynamics Research (CSTAR) Facility, has been developed at Purdue University in cooperation with Rolls-Royce to gain further understanding of the complex aerodynamics found in such centrifugal compressors. The experimental data acquired in this facility will be utilized to develop and validate design tools for centrifugal compressors used in axial-centrifugal high-pressure compressors. The facility models the last (centrifugal) stage of an axial-centrifugal compressor and operates at engine-representative Mach numbers. In this paper, the facility is described in detail, and the baseline steady-state performance of the compressor is presented.

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7

Fulton, John W. "Rotor Stability Criteria for Multi-Stage Centrifugal Compressors." In ASME 2003 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/detc2003/vib-48459.

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The American Petroleum Standard 617, 7th edition [1], screens new designs of centrifugal compressors using its Figure 1.2-5, which plots mean gas density versus rotor flexibility ratio. The purpose is to avoid rotor instability from causing unacceptable vibrations, typically whirling of the first-forward bending mode. The API figure is based on a plot by Fulton [2,3] of the same variables showing a number of compressors tested near the threshold of instability, thus forming an empirical basis for a Stability Map. This paper develops a method to derive a threshold line, using a set of typical industrial rotors varying in flexibility and running on tilt pad bearings. Instability requires a tangential force (normal to the bending displacement) to act on the rotor in the direction of whirl. The source of this force is taken to be the (tooth type) labyrinth seals inside the compressor. This tangential force is represented as linear function of whirl/spin scaled by gas density. This function is applied to the set of rotors to produce a threshold line. The derivation thus forms a basis for understanding the Stability Map.

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8

Wang, Ting, and Jobaidur R. Khan. "Overspray and Interstage Fog Cooling in Compressor Using Stage-Stacking Scheme: Part 1—Development of Theory and Algorithm." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50322.

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Compressor intercooling has traditionally been employed to reduce compressor work and augment gas turbine output power. Conventional intercooling schemes are usually applied through non-mixed heat exchangers between two compressor stages or by cooling the outside of the compressor casing. Any cooling schemes that may affect the flow field inside the compressors have not been favorably considered due to concerns of any disturbance that might adversely affect the compressor’s performance stability. As the inlet fog cooling scheme has become popular as an economic and effective means to augment gas turbine output power on hot or dry days, consideration has been given to applying fog cooling inside the compressors by injecting fine water droplets between stages (i.e. interstage fogging). This paper focuses on developing a stage-by-stage wet-compression theory for overspray and interstage fogging that includes the analysis and effect of pre-heating and pre-cooling at each small stage of the overall compressor performance. An algorithm has been developed to calculate the local velocity diagram and allow a stage-by-stage analysis of the fogging effect on airfoil aerodynamics and loading with known 2-D meanline rotor and stator geometries. Thermal equilibrium model for water droplet evaporation is adopted. The developed theory and algorithm are integrated into the system-wise FogGT program to calculate the overall gas turbine system performance.

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Ashrafi, Farzad, Mathias Michaud, and Huu Duc Vo. "Delay of Rotating Stall in Compressors Using Plasma Actuators." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42559.

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Rotating stall is a well-known aerodynamic instability in compressors that limits the operating envelope of aircraft gas turbine engines. An innovative method for delaying the most common form of rotating stall inception using an annular DBD (Dielectric Barrier Discharge) plasma actuator had been proposed. A DBD plasma actuator is a simple solid-state device that converts electricity directly into flow acceleration through partial air ionization. However, the proposed concept had only been preliminarily evaluated with numerical simulations on an isolated axial rotor using a relatively basic CFD code. This paper provides both an experimental and a numerical assessment of this concept for an axial compressor stage as well as a centrifugal compressor stage, with both stages being part of a low-speed two-stage axial-centrifugal compressor test rig. The two configurations studied are the two-stage configuration with a 100 mN/m annular casing plasma actuator placed just upstream of the axial rotor leading edge, and the single-stage centrifugal compressor with the same actuator placed upstream of the impeller leading edge. The tested configurations were simulated with a commercial RANS CFD code (ANSYS CFX) in which was implemented the latest engineering DBD plasma model and dynamic throttle boundary condition, using single-passage multiple blade row computational domains. The CFD simulations indicate that in both types of compressors the actuator delays the stall inception by pushing the incoming/tip clearance flow interface downstream into the blade passage. In each case, the predicted reduction in stalling mass flow matches the experimental value reasonably well.

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Gwehenberger, Tobias, Martin Thiele, Martin Seiler, and Douglas Robinson. "Single-Stage High-Pressure Turbocharging." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59322.

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To meet the ever-increasing demands that will be made on engines, and especially on planned new engine generations, in the future, the power density of their turbochargers will have to be significantly increased. Raising the brake mean effective pressure, introducing Miller timing and providing support for exhaust-gas treatment all presuppose an increase in the turbo’s compressor pressure ratio while keeping the turbo unit as compact as possible. To fulfill all of these conditions with single-stage turbocharging, a new approach to future turbocharger design is needed, especially when additional expensive materials, such as titanium, are not to be used. On the compressor side, when using proven aluminum compressors, this requires additional cooling of the compressor wheels. But other turbocharger components too, such as the turbine, bearings, shaft seals and also the casings and their connections, are exposed to higher thermal and mechanical stresses as a result of the pressure ratios being far higher than those of turbochargers currently on the market. The challenge, which could also be called a balancing act, in dimensioning new turbochargers for single-stage high-pressure turbocharging with aluminum compressors is to design the components with the help of the available tools such that sufficient safety and component lifetime are achieved while performance and component efficiency are optimized. By using the available calculation tools, such as FEM or for the fluid dynamics CFD, it is now possible to achieve compressor pressure ratios of up to 5.8 in continuous operation with single-stage turbocharging while ensuring a compact turbocharger design and aluminum compressors. The paper describes how ABB Turbo Systems Ltd has successfully developed and qualified a new single-stage high-pressure turbocharger generation with radial turbine which allows compressor pressure ratios of up to 5.8 in continuous operation at 100% engine load. First successful engine tests with the new A100 radial turbocharger generation have been carried out both on medium- and on high-speed engines. The first frame sizes of the new A100 high-pressure turbocharger series have been released for market introduction, setting a significant new benchmark for turbocharging advanced diesel and gas engines.

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Reports on the topic "Compressors stage"

1

Boyer, Keith. Characterization of Stall Inception in High-Speed Single-Stage Compressors. Fort Belvoir, VA: Defense Technical Information Center, December 1994. http://dx.doi.org/10.21236/ada291275.

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Tan, Choon S. Developing a Research Roadmap on Performance Limiting Flow Processes in High-Stage Loading Compressors. Fort Belvoir, VA: Defense Technical Information Center, March 2005. http://dx.doi.org/10.21236/ada432196.

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Skone, Timothy J. Compressor, Single-Stage Centrifugal, Operation. Office of Scientific and Technical Information (OSTI), September 2012. http://dx.doi.org/10.2172/1509358.

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Mitchell, Matthew P. Two Stage Sibling Cycle Compressor/Expander. Fort Belvoir, VA: Defense Technical Information Center, February 1994. http://dx.doi.org/10.21236/adb204760.

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5

Cornacchia, M., P. Craievich, S. Di Mitri, G. Penco, M. Venturini, and A. Zholents. Running fermi with one-stage compressor: advantages, layout,performance. Office of Scientific and Technical Information (OSTI), May 2007. http://dx.doi.org/10.2172/929314.

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6

Raubenheimer, T. A Two-Stage Bunch Compressor Option for the US Cold LC. Office of Scientific and Technical Information (OSTI), July 2004. http://dx.doi.org/10.2172/827343.

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Tan, Choon S. Performance Limiting Flow Processes in High-State Loading High-Mach Number Compressors. Fort Belvoir, VA: Defense Technical Information Center, March 2008. http://dx.doi.org/10.21236/ada481548.

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8

Chen, Jen-Ping, Michael D. Hathaway, and Gregory P. Herrick. Prestall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation. Fort Belvoir, VA: Defense Technical Information Center, October 2008. http://dx.doi.org/10.21236/ada500494.

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Vega, L. A. Accelerated life test of the USDOE OC-OTEC experimental system refurbished with magnetic bearings for the 3rd stage vacuum compressor. Final report. Office of Scientific and Technical Information (OSTI), April 1997. http://dx.doi.org/10.2172/663602.

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