Topic
Diffuser (thermodynamics)
About: Diffuser (thermodynamics) is a research topic. Over the lifetime, 6731 publications have been published within this topic receiving 54738 citations.
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Patent•
02 Dec 1976TL;DR: In this paper, airflow exiting a centrifugal compressor is diffused in multiple shaped passages tangential to the compressor impeller to reduce its Mach number and then directed through deswirl vanes to the entrance of a combustor.
Abstract: Airflow exiting a centrifugal compressor is diffused in multiple shaped passages tangential to the compressor impeller dumped into a plenum to reduce its Mach number and then directed through deswirl vanes to the entrance of a combustor. Deswirl at reduced Mach number significantly reduces pressure losses resulting in reduced complexity and manufacturing cost for the diffuser deswirl system.
23 citations
Patent•
08 Aug 2006
TL;DR: In this paper, a low solidity vaned airfoil diffuser for a centrifugal compressor was proposed, where each blade has a lean angle (85) greater than zero and wherein the hub stagger angle (70) may be the same as or may be different from the shroud stagger angle for each blade.
Abstract: A low solidity vaned airfoil diffuser (2) for a centrifugal compressor wherein each blade has a lean angle (85) greater than zero and wherein the hub stagger angle (70) may be the same as or may be different from the shroud stagger angle (80) for each blade. Preferably the lean angle (85) is in a range from 5-60 degrees, and the hub stagger angle (70) and the shroud stagger angle (80) is from 13 to 30 degrees. The diffuser can be employed in a centrifugal compressor used in an air separation plant.
23 citations
TL;DR: In this paper, the effect of pulsating flow on the flow distribution within automotive exhaust catalysts was examined and it was shown that the flow uniformity at 16 Hz was similar to the steady equivalent whereas improved uniformity was seen at higher frequencies resulting in a reduced pressure drop.
Abstract: Conversion efficiency, durability and pressure drop of automotive exhaust catalysts are dependent on the flow distribution within the substrate. This study examines the effect of pulsating flow on the flow distribution within these systems. The flow distribution was measured for a range of flow rates at pulsation frequencies of 16, 32, 64 and 100 Hz. It was shown that the flow uniformity at 16 Hz was similar to the steady equivalent whereas improved uniformity was seen at the higher frequencies resulting in a reduced pressure drop. It was further found that flow maldistribution under pulsating conditions was less sensitive to increases in flow rate compared to steady-state flow. Downstream of the monolith strong pulses were observed although the pulse shapes changed across the substrate diameter. Flow maldistribution correlated well with a non-dimensional parameter derived from the inlet flow velocity, pulsation frequency and diffuser length.
23 citations
24 May 1993
TL;DR: In this paper, the authors compared the aerodynamic performance of single stage centrifugal compressors with thin flat plate, low solidity vaned diffusers to conventional thin vaned Diffusers, and found that the low-solidity vane inlet incidence angle is an important design parameter that influences both compressor operating range and efficiency.
Abstract: Test results are presented comparing the aerodynamic performance of single stage centrifugal compressors with thin flat plate, low solidity vaned diffusers to conventional thin vaned diffusers. The test data were acquired from a low Mach number process gas compressor and a high Mach number industrial air compressor. The data are all normalized relative to baseline vaneless diffuser results. Performance parameters of stability, head rise to surge, overload flow margin, and stage efficiency are compared. The low solidity vane inlet incidence angle is shown to be an important design parameter that influences both compressor operating range and efficiency.Copyright © 1993 by ASME
23 citations
01 Dec 2001
TL;DR: In this paper, a variable geometry axisymmetric inlet has been developed at ISAS since 1993, and a control test of an inlet is conducted at ONERA S3MA supersonic wind tunnel to accomplish an automatic operation of the inlet.
Abstract: A development study of variable geometry axisymmetric inlet has been done at IS AS since 1993. Total pressure recovery and mass capture ratio of the inlets are obtained by the wind tunnel tests at ISAS supersonic wind tunnel and NASA GRC 1-by 1-foot supersonic wind tunnel. In Feb 2000, a control test of an inlet is conducted at ONERA S3MA supersonic wind tunnel to accomplish an automatic operation of the inlet. As a result, we succeeded in controlling the inlet automatically and about 90% of the maximum inlet performances are achieved without manual operation. The configuration of the supersonic and subsonic diffuser is modified to increase the mass capture in the subsonic flight without the increase of the total pressure loss in the supersonic flight, and new type of inlet configuration is designed (Type-M). Although, type-M inlet can make 75% of total pressure recovery at Mach 3.5, it is necessary to improve the bleed system of the spike surface. A flyable inlet model whose cowl diameter is 740mm is now on the drawing board.
23 citations