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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.


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Patent
Yoichi Yoshinaga1, Hiromi Kobayashi1, Shinjiro Ueda1, Yoshihiro Takada1, Hideo Nishida1 
06 Feb 1981
TL;DR: A vaneless diffuser disposed on the outer periphery of an impeller of a centrifugal compressor and including a pair of opposed diffuser plates of a disk shape defining therebetween a fluid channel is formed with a plurality of guide vanes extending from the inlet of the diffuser to its outlet.
Abstract: A vaneless diffuser disposed on the outer periphery of an impeller of a centrifugal compressor and including a pair of opposed diffuser plates of a disk shape defining therebetween a fluid channel is formed with a plurality of guide vanes extending from the inlet of the diffuser to its outlet. The guide vanes which are disposed on at least one of the pair of diffuser plates and extend immediately from the outlet of the impeller in the direction of flow of a fluid through the fluid channel has a height smaller than one-half the width of the fluid channel and gradually decreasing in going from the inlet of the diffuser toward its outlet.

39 citations

F. K. Moore1
01 Jun 1988
TL;DR: In this paper, a theory is presented to predict the occurrence of weak rotating waves in a centrifugal compression system with a vaneless diffuser, and conditions for a neutral rotating disturbance are found.
Abstract: A theory is presented to predict the occurrence of weak rotating waves in a centrifugal compression system with a vaneless diffuser. As in a previous study of axial systems, an undisturbed performance characteristic is assumed known. Following an inviscid analysis of the diffuser flow, conditions for a neutral rotating disturbance are found. The solution is shown to have two branches; one with fast rotation, the other with very slow rotation. The slow branch includes a dense set of resonant solutions. The resonance is a feature of the diffuser flow, and therefore such disturbances must be expected at the various resonant flow coefficients regardless of the compressor characteristic. Slow solutions seem limited to flow coefficients less than about 0.3, where third and fourth harmonics appear. Fast waves seem limited to a first harmonic. These fast and slow waves are described, and effects of diffuser-wall convergence, backward blade angles, and partial recovery of exit velocity head are assessed.

39 citations

Patent
Davis D Y1
29 Dec 1971
TL;DR: In this paper, the discharge shutter valve is used to close one or more diffuser passages while leaving the remaining passages completely open, thereby providing a pump with high head rise over the complete operating range of the pump.
Abstract: A centrifugal pump is supplied with a discharge shutter valve which provides a variable diffuser for the pump. The shutter valve includes a hollow, slotted cylinder positioned for movement into a variety of operative positions between the impeller and the diffuser vane passages. Each operative position completely closes one or more of the diffuser passages while leaving the remaining passages completely open, thereby providing a pump with high head rise over the complete operating range of the pump.

39 citations

Patent
30 Dec 1985
TL;DR: In this paper, a gas compressor is used in a jet engine for propulsion of a flight vehicle at velocities ranging from static to very high Mach numbers, where the mixture of the compressed air flow from the diffuser and the fuel is ignited to produce thrust.
Abstract: A gas compressor is provided which can be utilized in a jet engine for propulsion of a flight vehicle at velocities ranging from static to very high Mach numbers. The jet engine includes a housing with an inlet, a mixing chamber in fluid communication with the inlet, a diffuser section in fluid communication with the mixing chamber, a combustion chamber in fluid communication with the diffuser section and an outlet in communication with the combustion chamber. Auxiliary gas injection nozzles located downstream of the mixing chamber direct a high velocity gas stream toward the outlet to induce a region of sufficiently low pressure within the mixing chamber to cause a supersonic flow of gas from the inlet section through the mixing chamber. Cryogenic fuel is injected into the mixing chamber to modify the stagnation enthalpy, pressure and temperature of the supersonic flow therethrough. Fuel is injected into the combustion chamber where the mixture of the compressed air flow from the diffuser and the fuel is ignited to produce thrust. The outlet is adjustable to provide the amount of back pressure required in the combustion chamber for stable operation.

39 citations


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