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Diffuser (thermodynamics)

About: Diffuser (thermodynamics) is a research topic. Over the lifetime, 6731 publications have been published within this topic receiving 54738 citations.


Papers
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Journal ArticleDOI
TL;DR: In this article, the authors used computational fluid dynamics to search for the links between the observed pattern of attack seen in a bauxite refinery's heat exchanger headers and the hydrodynamics inside the header.

20 citations

Patent
09 Jun 2009
TL;DR: In this article, a nacelle for a turbofan gas turbine engine is described, where an inner wall of the nacels defines an air intake which directs air into the fan section of the engine.
Abstract: A nacelle for a turbofan gas turbine engine is provided. An inner wall of the nacelle defines an air intake which directs air into the fan section of the engine. The intake has, in flow series, an intake lip, a throat and a diffuser. The diffuser has, in flow series, first and second flow conditioning sections over both of which the flow cross-sectional area of the diffuser increases with increasing downstream distance from the throat. In addition, over the second section the nacelle inner wall lies substantially on a surface of an oblique circular cone having an apex which is offset from the centreline of the engine.

19 citations

Patent
14 Jan 1981
TL;DR: An improved pulverized fuel burning method and apparatus having means for decreasing the pressure drop through the burner nozzle and decreasing the formation of nitric oxides, including a splash plate to breakup a natural forming fuel-rope, a deflector to deflect the fuel rope, and a diffuser to disperse the pulverised fuel into a more desirable fuel burning distribution pattern.
Abstract: An improved pulverized fuel burning method and apparatus having means for decreasing the pressure drop through the burner nozzle and decreasing the formation of nitric oxides, including a splash plate to breakup a natural forming fuel-rope, a deflector to deflect the fuel-rope, and a diffuser to disperse the pulverized fuel into a more desirable fuel burning distribution pattern.

19 citations

Patent
Pierre G. Schwaar1
04 Aug 1969
TL;DR: In this article, the axial-flow section discharges air at subsonic absolute velocity, whereafter the air is radially accelerated and diffused in the outlet portion of the mixed flow section.
Abstract: 1280113 Centrifugal and axial-flow compressors; gas turbine engines AVCO CORP 30 June 1970 [4 Aug 1969] 31621/70 Headings F1C and F1G A compressor in or for a gas turbine engine comprises an axial-flow section 32, 46, Fig. 1, and a downstream, contra-rotating mixed-flow section 62. The axial-flow section discharges air at subsonic absolute velocity. The mixed-flow section has an inlet portion which is of substantially constant flow area and receives the air at supersonic relative velocity to thereby produce shock waves and reduce supersonic flow to subsonic, whereafter the air is radially accelerated and diffused in the outlet portion of the mixed-flow section. The impeller blades of the latter may be divided into an inlet row and and outlet row separated by a row of stator blades, Fig. 3 (not shown). Stator vanes (150), Fig. 8 (not shown), may be located immediately upstream of the mixed-flow section to equalize the relative velocity of the entering air over the radial extent of the annular flow duct. In the gas turbine engine shown, the compressed air is discharged through a diffuser 84 into combustion apparatus 18 comprising an annular series of cylindrical combustion units 90 which deliver hot gases into a duct 92. The latter discharges the gases through a full-admission inlet nozzle to drive turbine wheels 98, 114, which drive the respective compressor sections, and to either drive a further turbine wheel having an output shaft 30 or exhaust through a nozzle to produce propulsive thrust. Alternatively, the two compressor sections may be driven by a single turbine wheel via gearing. Sump housings 54, 72, 120 for the shaft bearings are each sealed at both ends by friction or labyrinth seal assemblies 60, 74, 106, 122.

19 citations

Journal ArticleDOI
TL;DR: It is suggested that a STED can be started with a normal shock forming ahead of the second-throat contraction because the high speed flow in the region close to the wall of the diffuser serves to release the mass blocked by the normal shock, leading to a decrease in chamber pressure as well as the start of the system.
Abstract: The start condition of a second-throat ejector-diffuser (STED) system has been studied by solving the axisymmetric Navier-Stokes equations with a high order conservative supra-characteristics method (CSCM). According to the conventional concept, when a STED is started, the flow passing through the second-throat contraction should be supersonic so that the normal shock swallowing condition applying for a supersonic windtunnel holds. The present numerical results, however, suggest that a STED can be started with a normal shock forming ahead of the second-throat contraction because the high speed flow in the region close to the wall of the diffuser serves to release the mass blocked by the normal shock, leading to a decrease in chamber pressure as well as the start of the system. This not only contradicts the conventional concept of the start of a STED, but also provides an explanation for the experimental discrepancy between the start conditions of a STED and a supersonic windtunnel.

19 citations


Performance
Metrics
No. of papers in the topic in previous years
YearPapers
20224
2021156
2020186
2019216
2018236
2017263