Pressure Recovery Performance of Straight-Channel, Single-Plane Divergence Diffusers at High Mach Numbers

Runstadler, P. W.

doi:10.21236/ad0865300

Cited by 6 publications

(5 citation statements)

References 5 publications

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“…For high supersonic flows, some other formulation would have to be used. (6) The boundary layer velocity profile in the streamline direction may be described by the power-law equation…”

Section: Two-dimensional Boundary Layer Methodsmentioning

confidence: 99%

“…Results using this method have been compared with experimental data for rectangular diffusers (6). A comparison of calculated and experimental pressure coefficients for several arbitrary cases of inlet Mach number, blockage, and divergence angle, e, is shown in Fig.…”

Section: Rectangular Diffusermentioning

confidence: 99%

“…(1)(2)(3)(4)). For diffusers (conical, rectangular) this is done by empirically relating the diffuser pressure recovery coefficient to the diffuser geometry and inlet flow conditions (5,6). A more rigorous way of estimating these losses would be to calculate the surface boundary layers and from these obtain a massaveraged estimate of channel losses.…”

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confidence: 99%

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A Method for Calculating Turbulent Boundary Layers and Losses in the Flow Channels of Turbomachines

Schumann

1987

Volume 1: Turbomachinery

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An i n t e r a c t i v e i n v i s c i d c o r e flow-boundary l a y e r method i s p r e s e n t e d f o r t h e c a l c u l a t i o n o f turhomachine channel f l o w s . F o r t h i s method, a one-dimensional i n v i s c i d c o r e f l o w i s assumed.The end-wall and b l a d e s u r f a c e boundary l a y e r s a r e c a l c u l a t e d u s i n q an i n t e -2 g r a l e n t r a i n m e n t method. The boundary l a y e r s are % assumed t o b e c o l l a t e r a l and t h u s a r e two-dimensional.& The boundary l a y e r e q u a t i o n s a r e w r i t t e n i n a streaml i n e c o o r d i n a t e system. The streamwise v e l o c i t y prof i l e s a r e approximated b y power law p r o f i l e s . C o m p r e s s i b i l i t y i s accounted f o r i n t h e streamvise d i r e c t i o n h u t n o t i n t h e normal d i r e c t i o n . E q u a t i o n s a r e d e r i v e d f o r t h e s p e c i a l cases of c o n i c a l and two-dimensional r e c t a n g u l a r d i f f u s e r s . F o r t h e s e cases, t h e assumptions o f a one-dimensional c o r e f l o w and c o l 1 a t e r a l boundary l a y e r s a r e Val i d . R e s u l t s u s i n g t h e method a r e compared w i t h experiment and good q u a n t i t a t i v e agreement i s o b t a i n e d . i f f u s e r t h r o a t d i amet e r terms i n v e l o c i t y g r a d i e n t e q u a t i o n e n t r a i n m e n t f u n c t i o n

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“…For high supersonic flows, some other formulation would have to be used. (6) The boundary layer velocity profile in the streamline direction may be described by the power-law equation…”

Section: Two-dimensional Boundary Layer Methodsmentioning

confidence: 99%

Section: Rectangular Diffusermentioning

confidence: 99%

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A Method for Calculating Turbulent Boundary Layers and Losses in the Flow Channels of Turbomachines

Schumann

1987

Volume 1: Turbomachinery

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“…The overall design parameters, such as area ratio, length-width ratio and equivalent included angle, empirically derived relationships together with 1D flow assumptions [14]. The relationship between specific will be chosen using traditional diffuser data [21]. However, increasing use is being made of 3D compu-speed and impeller efficiency is widely used to optimize the design [15].…”

Section: Fig 2 Small Automotive Turbochargermentioning

confidence: 99%

Turbocharger aerodynamic design

Flaxington

Swain

1999

Proceedings of the Institution of Mechanical Engineers, Part C:

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The aerodynamic design of turbochargers is described, covering radial compressors and turbines and also axial turbines. The paper concentrates upon those aspects that are peculiar to turbocharger design, including the approach adopted, and highlights the importance of companyspecific empirical data. Turbochargers have to be physically adaptable to suit many different sizes of engine, with a great variety of operating duties. The need for turbochargers to achieve the highest obtainable performance at the lowest cost while maintaining durability levels comparable with the engine contributes to the design challenges that are discussed.

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“…Due to the higher diffusion in the inlet region (C pi ), the blockage in front of the throat increases. Rundstadler( 4 ) shows this factor has a detrimental effect on C pCH , so that CpCH decreases.…”

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confidence: 99%

Vaned Diffuser Inlet Flow Conditions for a High Pressure Ratio Centrifugal Compressor

Verdonk

1978

Volume 1A: General

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This paper contains a theoretical and experimental investigation of the flow in the vaneless and semi-vaneless space of a transonic radial compressor diffuser, especially for working points corresponding to the mass flow below choking values, in the efficient operating regimes. A type-dependent finite difference calculation has been developed for the inviscid flow. This method has been combined with a shock-boundary layer-interaction theory, which allows a more realistic calculation of the velocity distribution, taking into account the boundary layer variation along the sidewalls. In parallel with this analytical study, several diffuser geometries were also performance tested. A special data-reduction program allowed calculation of the throat blockage and the velocity distribution throughout the diffuser based on static and total pressure measurements. Schlieren pictures were also taken in order to have a better insight in the real flow phenomena at the diffuser entrance. From this experimental data, a detailed comparison with the analytical study was made. This combined theoretical and experimental study made it possible to show the influence of the geometrical parameters of the vaneless and semi-vaneless space on the velocity distribution, and on the throat blockage. Together with the data available in literature for channel diffusers, it allows a better prediction of the overall performances of diffuser systems.

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Pressure Recovery Performance of Straight-Channel, Single-Plane Divergence Diffusers at High Mach Numbers

Cited by 6 publications

References 5 publications

A Method for Calculating Turbulent Boundary Layers and Losses in the Flow Channels of Turbomachines

A Method for Calculating Turbulent Boundary Layers and Losses in the Flow Channels of Turbomachines

Turbocharger aerodynamic design

Vaned Diffuser Inlet Flow Conditions for a High Pressure Ratio Centrifugal Compressor

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