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Academic literature on the topic 'Subsonic diffuser'

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Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Subsonic diffuser"

1

Ribi, Beat, and Peter Dalbert. "One-Dimensional Performance Prediction of Subsonic Vaned Diffusers." Journal of Turbomachinery 122, no. 3 (February 1, 1999): 494–504. http://dx.doi.org/10.1115/1.1303816.

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A simple one-dimensional theory to predict the performance of a diffuser using as few empirical factors as possible is presented. The prediction method uses two empirical functions to assess both the pressure recovery and the losses. The functions have been calibrated from experimental data from the company’s standard diffusers. The method is, however, adaptable for any type of subsonic vaned diffusers, provided that the empirical functions can be calibrated from measurements. The pressure rise in the diffuser is calculated from the continuity equation, taking into account the blockage, while the losses are determined by means of displacement and momentum thickness. These values are calculated at design point from an integral boundary layer calculation. To take into account the influence of flow separation at off-design, the calculated displacement and momentum thickness are increased according to empirical functions. When designing a new impeller, the method provides a simple way to evaluate the diffuser, resulting in the best combination in terms of efficiency and range. It further provides a simple means of estimating the change to be expected in a known stage performance characteristic due to a modification of the diffuser geometry.[S0889-504X(00)01703-7]
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Li, Qingkuo, Zhigang Sun, Xingen Lu, Yingjie Zhang, and Ge Han. "Investigation of New Design Principles for the Centrifugal Compressor Vaned Diffusers." International Journal of Aerospace Engineering 2022 (February 25, 2022): 1–16. http://dx.doi.org/10.1155/2022/4480676.

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Diffuser’s aerodynamic performance is crucial for the centrifugal compressors, while at present the universal principles for the optimization design of the vaned diffusers are still not available. In this paper, three vaned diffusers with different inlet Mach numbers were numerically studied in order to explore new design principles for the centrifugal compressor vaned diffusers. It proved that there are practical and effective design principles for the vaned diffuser optimizations, the performance of the vaned diffuser can be improved by carefully control of two aerodynamic parameter distributions: Tangential velocity (Vt) and Meridional velocity (Vm). The vaned diffusers with subsonic, transonic and supersonic inlet conditions were optimized with the new design principles, and the peak efficiencies were increased by 4.23%, 2.15% and 2.59%, respectively. The stage pressure ratios were increased by 3.36%, 1.39% and 6.49%, respectively, and their surge margins were also improved substantially. Finally, since the Vt and Vm could affect each other during the optimization process, an interactive optimization design procedure was also presented in this paper in order to accelerate the optimization process.
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Johnston, J. P. "Review: Diffuser Design and Performance Analysis by a Unified Integral Method." Journal of Fluids Engineering 120, no. 1 (March 1, 1998): 6–18. http://dx.doi.org/10.1115/1.2819663.

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A computational tool, called a Unified Integral Method (UIM) is reviewed. The method is used for preliminary design and performance analysis of simple diffusers with thin inlet boundary layers and subsonic flow in their inviscid core regions. The assumptions needed for application of a UIM are not very restrictive in many practical cases: straight diffusers with thin, turbulent inlet boundary layers and subsonic, irrotational core flows. The method provides designers with useful results including pressure recovery, location of separation and stalled regions, and exit plane profiles which may be used to evaluate total pressure loss and various flow distortion indices. Besides reviewing some basic concepts concerning stall and separation, describing the basis of the method and some details for making the UIM work, actual cases where it was tested versus data are discussed. In addition, UIM results are compared to results obtained by a RANS method run in a well known duct flow solver for a subsonic diffuser where data are also available. In another case, its output and data were compared to results from a CFD code typical of the many design codes in use in industry today. In both cases, the UIM results were as good, or better than those from the higher level methods, and the UIM is much simpler and easier to use as a design tool.
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Zhang, Wei-Li, Doyle D. Knight, and Don Smith. "Automated Design of a Three-Dimensional Subsonic Diffuser." Journal of Propulsion and Power 16, no. 6 (November 2000): 1132–40. http://dx.doi.org/10.2514/2.5688.

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Reichert, B. A., and B. J. Wendt. "Improving curved subsonic diffuser performance with vortex generators." AIAA Journal 34, no. 1 (January 1996): 65–72. http://dx.doi.org/10.2514/3.13022.

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Ibaraki, Seiichi, Tetsuya Matsuo, and Takao Yokoyama. "Investigation of Unsteady Flow Field in a Vaned Diffuser of a Transonic Centrifugal Compressor." Journal of Turbomachinery 129, no. 4 (August 11, 2006): 686–93. http://dx.doi.org/10.1115/1.2720505.

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Transonic centrifugal compressors are used with high-load turbochargers and turboshaft engines. These compressors usually have a vaned diffuser to increase the efficiency and the pressure ratio. To improve the performance of such a centrifugal compressor, it is required to optimize not only the impeller but also the diffuser. However the flow field of the diffuser is quite complex and unsteady because of the impeller located upstream. Although some research on vaned diffusers has been published, the diffuser flow is strongly dependent on the particular impeller exit flow, and some of the flow physics remain to be elucidated. In the research reported here, detailed flow measurements within a vaned diffuser were conducted using a particle image velocimetery (PIV). The vaned diffuser was designed with high subsonic inlet conditions marked by an inlet Mach number of 0.95 for the transonic compressor. As a result, a complex three-dimensional flow with distortion between the shroud and the hub was observed. Also, unsteady flow accompanying the inflow of the impeller wake was confirmed. Steady computational flow analysis was performed and compared with the experimental results.
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Jo, Seonghwi, Sanghyeon Han, Hong Jip Kim, and Kyung Jin Yim. "Numerical Study on the Flow and Heat Transfer Characteristics of a Second Throat Exhaust Diffuser According to Variations in Operating Pressure and Geometric Shape." Energies 14, no. 3 (January 20, 2021): 532. http://dx.doi.org/10.3390/en14030532.

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A numerical study was conducted to investigate the flow and heat transfer characteristics of a supersonic second throat exhaust diffuser for high-altitude simulations. The numerical results were satisfactorily validated by the experimental results. A subscale diffuser using nitrogen was utilized to investigate starting pressure and pressure variation in the diffuser wall. Based on the validated numerical method, the flow and heat transfer characteristics of the diffuser using burnt gas were evaluated by changing operating pressure and geometric shape. During normal diffuser operation without cooling, high-temperature regions of over 3000 K appeared, particularly near the wall and in the diffuser diverging section. After cooling, the flow and pressure distribution characteristics did not differ significantly from those of the adiabatic condition, but the temperature in the subsonic flow section decreased by more than 1000 K. Furthermore, the tendency of the heat flux from the diffuser internal flow to the wall was similar to that of the pressure variations, and it increased with operating pressure. It was confirmed that the heat fluxes of the supersonic and subsonic flows in the diffuser were proportional to the operating pressure to the 0.8 and −1.7 power, respectively. In addition, in the second throat region after separation, the heat flux could be scaled to the Mach number ratio before and after the largest oblique shock wave because the largest shock train affected the heat flux of the diffuser wall.
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Aranake, Aniket, Jin Gyu Lee, Doyle Knight, Russell M. Cummings, John Cox, Micah Paul, and Aaron R. Byerley. "Automated Design Optimization of a Three-Dimensional Subsonic Diffuser." Journal of Propulsion and Power 27, no. 4 (July 2011): 838–46. http://dx.doi.org/10.2514/1.50522.

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Casartelli, E., A. P. Saxer, and G. Gyarmathy. "Numerical Flow Analysis in a Subsonic Vaned Radial Diffuser With Leading Edge Redesign." Journal of Turbomachinery 121, no. 1 (January 1, 1999): 119–26. http://dx.doi.org/10.1115/1.2841219.

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The flow field in a subsonic vaned radial diffuser of a single-stage centrifugal compressor is numerically investigated using a three-dimensional Navier–Stokes solver (TASCflow) and a two-dimensional analysis and inverse-design software package (MISES). The vane geometry is modified in the leading edge area (two-dimensional blade shaping) using MISES, without changing the diffuser throughflow characteristics. An analysis of the two-dimensional and three-dimensional effects of two redesigns on the flow in each of the diffuser subcomponents is performed in terms of static pressure recovery, total pressure loss production, and secondary flow reduction. The computed characteristic lines are compared with measurements, which confirm the improvement obtained by the leading edge redesign in terms of increased pressure rise and operating range.
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YOSHIKAWA, Hisataka, Makoto YAMAMOTO, and Sinji HONAMI. "Numerical Simulation of Subsonic Diffuser for Supersonic Air-Intake(Effects of Blowing on Diffuser Performance)." Transactions of the Japan Society of Mechanical Engineers Series B 65, no. 631 (1999): 876–81. http://dx.doi.org/10.1299/kikaib.65.876.

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Dissertations / Theses on the topic "Subsonic diffuser"

1

Su, Wei-Jen Dimotakis Paul E. Dimotakis Paul E. "Aerodynamic control for a subsonic diffuser /." Diss., Pasadena, Calif. : California Institute of Technology, 2001. http://resolver.caltech.edu/CaltechETD:etd-09042007-145002.

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Boehm, Brian Patrick. "Performance optimization of a subsonic Diffuser-Collector subsystem using interchangeable geometries." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/49589.

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A subsonic wind tunnel facility was designed and built to test and optimize various diffuser-collector box geometries at the one-twelfth scale.  The facility was designed to run continuously at an inlet Mach number of 0.42 and an inlet hydraulic diameter Reynolds number of 340,000. Different combinations of diffusers, hubs, and exhaust collector boxes were designed and evaluated for overall optimum performance. Both 3-hole and 5-hole probes were traversed into the flow to generate multiple diffuser inlet and collector exit performance profile plots. Surface oil flow visualization was performed to gain an understanding of the complex 3D flow structures inside the diffuser-collector subsystem. The cutback radial hardware was found to increase the subsystem pressure recovery by over 10% from baseline resulting in an approximate 1% increase in gas turbine power output.
Master of Science
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McElwain, Brian D. "Unsteady separation point injection for pressure recovery improvement in high subsonic diffusers /." Springfield, Va. : Available from National Technical Information Service, 2002. http://handle.dtic.mil/100.2/ADA405746.

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Thesis (M.S. in Aeronautics and Astronautics and Engineer in Aeronautics and Astronautics)--Massachusetts Institute of Technology, 2002.
Includes bibliographical references (p. 155-156). Also available online.
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McElwain, Brian D. (Brian David) 1978. "Unsteady separation point injection for pressure recovery improvement in high subsonic diffusers." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/10945/11024.

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Serpentine inlet ducts on modem tactical aircraft distort the inlet flow and decrease pressure recovery at the aerodynamic interface plane (AIP). Current inlet designs are more aggressive, increasing distortion and decreasing pressure recovery at the AIP. Often the flow separates from the wall of the diffuser, creating most of the distortion and pressure loss in the inlet. Diffuser separation experiments were conducted at high subsonic cruise conditions in a 2D test section. Periodic injection tangential to the flow at the separation point improved downstream pressure recovery. The injection also increased static pressure measured at the test section walls in the separated region. Flow visualization tests indicated that the separation shrinks as the injection mass flow increases. Pressure recovery also increased as injection mass flow increased. The unsteady component of the injection flow remained constant with injection mass flow, indicating that the steady component of the injection enhanced control of the separation. The preliminary conclusion is that the average velocity of the injection flow should be at least equivalent to the velocity of the core flow to maximize pressure recovery. Experiments were also conducted in a one-sixth scale tactical aircraft diffuser at cruise conditions (3.1 lb/sec, maximum M = 0.65). Periodic injection at the separation point improved the pressure recovery at the AIP. The improvement in pressure recovery at the AIP was limited to the area of pressure loss due to the separation in the diffuser. The diffuser has strong secondary flows that also cause losses at the AIP. These secondary flows prevented the injection from restoring pressure recovery as well as it had in the 2D test section. Higher injection mass flows than in the 2D case were required to achieve the same degree of improvement in pressure recovery at the AIP.
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Kubo, Michal. "Optimalizovaný návrh sacího kanálu turbínového motoru." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2016. http://www.nusl.cz/ntk/nusl-254379.

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This master thesis deals with design of a subsonic intake which is used to supply small jet engine integrate into the fuselage of agile small unmanned aerial vehicle (UAV). Some kinds of these intakes are listed in order to inspire and introduce future designers into this part of jet plane design. This thesis contains a small amount of theory about compressible flow, and necessary knowledge which are important to know before the very first attempt to design an intake. Two models were designed in order to prove that the theory listed in this thesis is useful and can be used as a guide in design process of subsonic intakes. Both designs have the same layout. S-duct design with one intake placed on the belly of fuselage was chosen. After CFD analysis of first model it was found that there are huge area with separated flow and vortex. Separated flow leads to big total pressure loss and pressure distortion. While designing the second model the emphasis was to avoid this vortex and improve flow conditions. This optimization was success and the second design have smaller pressure loss in compare to the first design. The difference is more than 50% at fly speed M=0,8.
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Su, Wei-Jen. "Aerodynamic control for a subsonic diffuser." Thesis, 2001. https://thesis.library.caltech.edu/3326/1/Su_wj_2001.pdf.

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NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. Experiments have been conducted in the GALCIT Supersonic Shear Layer Facility to investigate some aspects of mass injection in subsonic diffusers. The goal of the experiment is to study aerodynamic control in subsonic diffusers by investigating downstream velocity profiles. These experiments were designed to address several key issues like effects due to velocity change (for one-stream and two-stream flows), and effects due to density variation. The effect of the separation bubble (stall flow) on the performance of the diffuser has also been investigated. One-stream experiments were performed with non-reacting (cold) runs using [...] in the high-speed section at different velocities and zero velocity at the low-speed section. Detailed analysis of data obtained shows a slight dependency of the reattachment point of the separation bubble on Reynolds number. As the flow rate in the high-speed section increases, the reattachment point of the separation bubble shifted slightly downstream. Two-stream flow (low- and high-speed sections) experiments were performed using [...] in the high-speed section and a density-matched mixture of Argon/Helium in the low-speed section. As the mass injection is increased in the low-speed section, the reattachment point of the separation bubble moved further downstream. While keeping the same velocity ratio (low- and high-speed sections), as the overall flow velocity increases, the reattachment point moved further downstream. Also, experiments with a higher density ratio using Argon in the low-speed section and [...] in the high-speed section were performed. As the density of the low-speed section increases, the reattachment point of the separation bubble moved upstream due to shear-layer entrainment effect. Finally, as the reattachment point of the separation bubble shifted further downstream, the diffuser pressure coefficient decreases, therefore, the performance of the diffuser is degraded. Schlieren flow visualization and pressure probes were used in the experiments.
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(6636125), Udit Vyas. "Aerodynamic Optimization of Compact Engine Intakes for High Subsonic Speed Turbofans." Thesis, 2019.

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Within the gas turbine industry, turbofan engines are widely implemented to enhance engine efficiency, specific thrust, and specific fuel consumption. However, these turbofans have yet to be widely implemented into microgas turbine engines. As turbofans become implemented into smaller engines, the need to design engine intakes for high-speed mission becomes more vital. In this work, a design procedure for compact, highly diffusive engine intakes for high subsonic speed applications is set about. The aerodynamic tradeoffs between cruise and takeoff flights are discussed and methods to enhance takeoff performance without negatively impacting high-speed cruise performance is discussed. Intake performance is integrated into overall engine analysis to help guide future mission analyses. Finally, an experimental model for engine intakes is developed for application to linear wind tunnels; allowing future designers to effectively validate numerical results.

A multi-objective optimization routine is performed for compact engine intakes at a Mach number of 0.9. This optimization routine yielded a family of related curves that maximize intake diffusive capability and minimize intake pressure losses. Design recommendations to create such optimal intakes are discussed in this work so that future designers do not need to perform an optimization. Due to high diffusion rate of the intake, the intake performance at takeoff suffers greatly (as measured by massflow ingestion). Methods to enhance takeoff performance, from designing a variable geometry intake, to creating slots, to sliding intake components are evaluated and ranked for future designers to get an order of magnitude understanding of the types of massflow enhancements possible. Then, off-design performance of the intake is considered: with different Mach number flights, non-axial flow conditions, various altitudes, and unsteady engine operation considered. These off-design effects are evaluated to generate an intake map across a wide engine operational envelope. This map is then inputted into an engine model to generate a performance map of an engine; which allows for mission planning analysis. Finally, various methods to replicate intake flow physics in a linear wind tunnel are considered. It is shown that replicating diffuser curvature in a linear wind tunnel allows for best replication of flow physics. Additionally, a method to non-dimesnsionalize intake performance for application to a wind tunnel is developed.

This work can be utilized by future engine intake designers in a variety of ways. The results shown here can help guide future designers create highly compact diffuser technology, capable of operating across a wide breadth of conditions. Methods to assess intake performance effects on overall engine performance are demonstrated; and an experimental approach to intake analysis is developed.

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Books on the topic "Subsonic diffuser"

1

National Aeronautics and Space Administration (NASA) Staff. Computational Study of Separating Flow in a Planar Subsonic Diffuser. Independently Published, 2018.

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L, Burley Richard, Johns Albert L, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Analytical and experimental studies of a short compact subsonic diffuser for a two-dimensional supersonic inlet. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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National Aeronautics and Space Administration (NASA) Staff. Analytical and Experimental Studies of a Short Compact Subsonic Diffuser for a Two-Dimensional Supersonic Inlet. Independently Published, 2018.

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A full Navier-Stokes analysis of subsonic diffuser of a a bifurcated 70/30 supersonic inlet for high speed civil transport application. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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A full Navier-Stokes analysis of subsonic diffuser of a a bifurcated 70/30 supersonic inlet for high speed civil transport application. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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H, Anderson Bernhard, Shaw Robert J. 1946-, and United States. National Aeronautics and Space Administration., eds. A full Navier-Stokes analysis of subsonic diffuser of a a bifurcated 70/30 supersonic inlet for high speed civil transport application. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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H, Anderson Bernhard, Shaw Robert J. 1946-, and United States. National Aeronautics and Space Administration., eds. A full Navier-Stokes analysis of subsonic diffuser of a a bifurcated 70/30 supersonic inlet for high speed civil transport application. [Washington, DC]: National Aeronautics and Space Administration, 1994.

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Conference papers on the topic "Subsonic diffuser"

1

Ribi, Beat, and Peter Dalbert. "One-Dimensional Performance Prediction of Subsonic Vaned Diffusers." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-433.

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A simple 1-d-theory to predict the performance of a diffuser using as few empirical factors as possible is presented. The prediction method uses two empirical functions to assess both the pressure recovery and the losses. The functions have been calibrated from experimental data from the company’s standard diffusers. The method is, however, adaptable for any type of subsonic vaned diffusers provided that the empirical functions can be calibrated from measurements. The pressure rise in the diffuser is calculated from the continuity equation taking into account the blockage, while the losses are determined by means of displacement and momentum thickness. These values are calculated at design point from an integral boundary layer calculation. To take into account the influence of flow separation at off-design the calculated displacement and momentum thickness are increased according to empirical functions. When designing a new impeller the method provides a simple way to evaluate the diffuser resulting in the best combination in terms of efficiency and range. It further provides a simple means of estimating the change to be expected in a known stage performance characteristic due to a modification of the diffuser geometry.
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2

Mayer, David, Bernhard Anderson, and Timothy Johnson. "3D subsonic diffuser design and analysis." In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-3418.

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Casartelli, E., A. P. Saxer, and G. Gyarmathy. "Performance Analysis in a Subsonic Radial Diffuser." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-153.

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Steady-state numerical investigations in a subsonic vaned radial diffuser are presented. The 3D flow field has been computed with a commercial Navier-Stokes code (TASCflow), using two different types of axially variable but circumferentially uniform inlet flow conditions, one based on realistic (measured) time-averaged impeller outflow, the other on an idealized distribution. Two different vane leading-edge shapes were investigated. The leading edge redesign is based on the 2D analysis and inverse-design software package MISES. For a complete operating speed line a detailed analysis of the flow structure and loss distribution within the diffuser is presented and the results obtained for the different inlet flow conditions and geometries are critically compared. The performance of the diffuser and its subcomponents is evaluated in terms of dimensionless quantities such as blockage, total-pressure-loss and pressure-recovery coefficients. Based on the comparisons and the cross performance analysis of the various effects due to leading edge redesign and different inlet velocity profiles, several design guidelines are postulated.
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Zhang, Weili, Doyle Knight, and Don Smith. "Automated design of a three dimensional subsonic diffuser." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-665.

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LEE, C., and C. BOEDICKER. "Subsonic diffuser design and performance for advanced fighter aircraft." In Aircraft Design Systems and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-3073.

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MAYER, DAVID, and W. KNEELING. "Evaluation of two flow analyses for subsonic diffuser design." In 30th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-273.

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Kanazaki, Masahiro. "Multi-Objective Design Optimization System for a Subsonic Diffuser." In AIAA 1st Intelligent Systems Technical Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-6513.

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Asghar, Asad, Robert A. Stowe, William D. E. Allan, and Derrick Alexander. "Entrance Aspect Ratio Effect on S-Duct Inlet Performance at High-Subsonic Flow." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57875.

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This paper reports the internal performance evaluation of S-duct diffusers with different entrance aspect ratios as part of an ongoing parametric investigation of a generic S-duct inlet. The generic S-duct diffusers were a rectangular-entrance (aspect ratio 1.5 and 2.0) transitioning S-duct diffuser in high subsonic (Mach number > 0.8) flow. The test section was manufactured using rapid prototyping for facilitating the parametric investigation of the geometry. Streamwise static pressure and exit-plane total pressure were measured in a test-rig using surface pressure taps and a 5-probe rotating rake, respectively and the baseline and a variant was simulated through computational fluid dynamics. The investigation indicated the presence of streamwise and circumferential pressure gradients leading to a three dimensional flow in the S-duct diffuser and distortion at the exit plane. The static pressure recovery increased for the diffuser with higher aspect ratio. Total pressure losses and circumferential and radial distortions at the exit plane were higher than that of the podded nacelle type of inlet. The increase in the total pressure recovery was observed for the increase in the aspect ratio for the baseline area ratio (1.57) S-ducts, but without a clear trend for the other area ratio (1.8) ducts. The work represents the beginning of the development of a database for the performance of a particular type of generic inlet. This database will be useful for predicting the performance of aero-engines and air vehicles in high subsonic flight.
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Kmecl, Tomaz, and Peter Dalbert. "Optimization of a Vaned Diffuser Geometry for Radial Compressors: Part I — Investigation of the Influence of Geometry Parameters on Performance of a Diffuser." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-437.

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In the present investigation the influence of different diffuser geometry parameters on the stage efficiency and operating range of radial compressor stages has been studied. In addition to a parallel-walled vaneless diffuser, 20 vaned diffusers were experimentally tested with three different impellers having the same meridional contour. All diffusers were designed for industrial compressor stages with subsonic diffuser flow and had parallel sidewalls, diffuser vanes with simple circular are profiles of constant thickness and rounded leading edges. In the first part of this investigation the length of the vaneless space, the number of diffuser vanes, the vane length, the inlet vane angle of a diffuser, and the solidity have been altered systematically. The results show that the throat area of a diffuser, and consequently the number of diffuser vanes, are the most important parameters affecting the operating range of a diffuser. The vaneless space extent and the diffuser vane inlet angle have a significant effect on diffuser efficiency, while their effect on operating range is much smaller. Changing these two parameters induces primarily a shift of diffuser characteristics. The diffuser vane length is a very important parameter at overload, where high losses in a diffuser channel occur when using a long diffuser vane.
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Sinha, Prasanta K., Biswajit Haldar, Amar N. Mullick, and Bireswar Majumdar. "Flow Investigation Through a 30° Turn Diffusing Duct in Subsonic Flow Regime." In ASME 2009 International Mechanical Engineering Congress and Exposition. ASMEDC, 2009. http://dx.doi.org/10.1115/imece2009-12456.

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Curved diffusers are an integral component of the gas turbine engines of high-speed aircraft. These facilitate effective operation of the combustor by reducing the total pressure loss. The performance characteristics of these diffusers depend on their geometry and the inlet conditions. In the present investigation the distribution of axial velocity, transverse velocity, mean velocity, static and total pressures are experimentally studied on a curved diffuser of 30° angle of turn with an area ratio of 1.27. The centreline length was chosen as three times of inlet diameter. The experimental results then were numerically validated with the help of Fluent, the commercial CFD software. The measurements of axial velocity, transverse velocity, mean velocity, static pressure and total pressure distribution were taken at Reynolds number 1.9 × 105 based on inlet diameter and mass average inlet velocity. The mean velocity and all the three components of mean velocity were measured with the help of a pre-calibrated five-hole pressure probe. The velocity distribution shows that the flow is symmetrical and uniform at the inlet and exit sections and high velocity cores are accumulated at the top concave surface due to the combined effect of velocity diffusion and centrifugal action. It also indicates the possible development of secondary motions between the concave and convex walls of the test diffuser. The mass average static pressure recovery and total pressure loss within the curved diffuser increases continuously from inlet to exit and they attained maximum values of 35% and 14% respectively. A comparison between the experimental and predicated results shows a good qualitative agreement between the two. Standard k-ε model in Fluent solver was chosen for validation. It has been observed that coefficient of pressure recovery Cpr for the computational investigation was obtained as 38% compared to the experimental investigation which was 35% and the coefficient of pressure loss is obtained as 13% in computation investigation compared to the 14% in experimental study, which indicates a very good qualitative matching.
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