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Journal ArticleDOI

Computer aided design of radial gas turbines: A method for determining the overall rotor dimensions

01 Dec 1977-Computers & Fluids (Pergamon)-Vol. 5, Iss: 4, pp 219-240
TL;DR: An optimization procedure is used based on one-dimensional analysis of the turbine performance that includes loss predictions due to passage losses, disk friction and clearances.
About: This article is published in Computers & Fluids.The article was published on 1977-12-01. It has received 6 citations till now. The article focuses on the topics: Turbine & Rotor (electric).
Citations
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Journal ArticleDOI
TL;DR: In this paper, heat transfer from a cylinder to a Newtonian fluid in laminar flow is solved using the finite element method for low to intermediate Reynolds numbers, and a new correlation is proposed, based on the calculated results, that covers parameter ranges not included in existing correlations.
Abstract: Heat transfer from a cylinder to a Newtonian fluid in laminar flow is solved using the finite-element method for low to intermediate Reynolds numbers. Calculations are compared with experimental results in the literature for air. Calculations are also done for a broad range of Prandtl numbers, and a new correlation is proposed, based on the calculated results, that covers parameter ranges not included in existing correlations.

27 citations

Journal ArticleDOI
01 Jul 2015
TL;DR: In this paper, a new method of selecting an optimum turbocharger for a specific engine using thermodynamic and turbomachinery analyses is presented in order to select the optimal turbochargers.
Abstract: A new method of selecting an optimum turbocharger for a specific engine using thermodynamic and turbomachinery analyses is presented in this paper. The optimum turbocharger was selected for enhanci...

4 citations

Journal ArticleDOI
TL;DR: In this article, an analytic-numerical solution to the Navier-Stokes equations is developed for the steady laminar flow past a circular cylinder, where series truncation is employed to reduce the governing partial differential equation to a system of ordinary differential equations, which are then numerically integrated.

3 citations

Journal ArticleDOI
TL;DR: In this article, the authors investigate the thermodynamic properties of fluid flow in Trailing Edge (TE) and Leading Edge (LE) leading turbines and show that the pressure, temperature and enthalpy in TE are less than LE and the areas close to the hub have the highest pressure.
Abstract: Centrifugal (radial flow) turbines are widely used in various industries, including power generation industries, so the study on them is of particular importance. The aim of this study was to investigate the thermodynamic properties of fluid flow in Trailing Edge (TE) and (LE) Leading Edge. For this purpose, first, the rotor (impeller) of the radial flow turbine was designed based on some design data such as flow rate, number of blades, rotational speed, diameter and length of the impeller, and then the designed rotor was simulated in 3D. The simulation done in the pressure based method and the turbulence model is SST and the rotational speed was 140,000(RPM). The results showed that the pressure, temperature and enthalpy in TE are less than LE and the areas close to the hub have the highest pressure. Another phenomenon observed is that in the section LE we see the separation of the flow from the blade surface, which then approaches the blade surface again and follows a relatively regular path,so the entropy in TE is greater than LE. At the end, the results of numerical solution were compared with valid data and the error rate and its reasons were discussed.

3 citations

DOI
S. Belbachir1, Abed Elkader Lousdad, Ahmed Allali, Ahmed Alami, Belhadj Boucham 
01 Jan 2020
TL;DR: The main goal of the present investigation is a contribution to the design of the rotor which is among the main turbine elements that require more attention in preliminary conceptual design for safety, reliability and high performance.
Abstract: The main goal of the present investigation is a contribution to the design of the rotor which is among the main turbine elements that require more attention in preliminary conceptual design for safety, reliability and high performance. The modeling and simulation are carried out using a fast tool computational Abaqus software code. It allows a verification of the thermo mechanical characteristics at the different sections of the blades during the design of a centrifugal turbine. It will then be possible to use the design of the blades, and improvement by definition and by changing their shape. The results obtained put into evidence and highlights the effects of the coupling of thermal and mechanical loading conditions which may be considered in rotor design and improving turbine performance.

1 citations


Cites methods from "Computer aided design of radial gas..."

  • ...Among these works are those of Benson (1977) [11] describing a method for determining the overall dimensions of a rotor of a radial turbine under operating conditions....

    [...]

References
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Journal ArticleDOI
TL;DR: In this paper, a number of methods for representing the losses in radial gas turbines for predicting the off-design performance are reviewed, and it is shown that reasonable predictions of the turbine performance may be made using one-dimensional theories if the nozzle gas exit angle is based on the cos−1(o/s) rule with some deviations due to rotor speed.

58 citations

Journal ArticleDOI
TL;DR: In this paper, the authors present the results of a number of investigations concerned with the boundary-layer characteristics of turbomachine blade rows and their relation to the over-all blade loss.
Abstract: This paper presents the results of a number of investigations concerned with the boundary-layer characteristics of turbomachine blade rows and their relation to the over-all blade loss. It is demonstrated how the over-all blade loss can be obtained from the momentum boundary-layer thickness. The momentum boundary-layer thickness is in turn shown to be correlated by flow Reynolds number and total blade surface diffusion. By assuming Zweifel’s form of blade-loading diagram the total blade surface diffusion parameter can be determined as a function of blade solidity and reaction across the blade row. Thus, this type of loss analysis enables an approximate predetermination of the over-all blade row loss as derived from fundamental boundary-layer concepts. In addition, it shows the effect on over-all blade loss of varying such design features as solidity and reaction.

26 citations

01 Aug 1949
TL;DR: In this paper, the authors presented numerical examples for steady, two-dimensional, compressible, nonviscous flow in centrifugal compressors with thin straight blades, the center lines of which generate the surface of a right circular cone when rotated about the axis of the compressor.
Abstract: Six numerical examples are presented for steady, two-dimensional, compressible, nonviscous flow in centrifugal compressors with thin straight blades, the center lines of which generate the surface of a right circular cone when rotated about the axis of the compressor. A seventh example is presented for incompressible flow. The solutions were obtained in a region of the compressors, including the impeller tip, that was considered to be unaffected by the diffuser vanes or by the impeller-inlet configuration. Each solution applies to radial and mixed flow compressors with various cone angles but with the same angle between blades on the conic flow surface. The solution also apply to radial and mixed flow turbines with the rotation and the flow direction reversed. The effects of variations in the following parameters were investigated: (1) flow rate, (2) impeller-tip speed, (3) variation of passage height with radius, and (4) angle between blades on conic flow surface. The numerical results are presented in plots of the streamlines and constant Mach number lines. Correlation equations are developed whereby the flow conditions in any impeller with straight blades can be determined (in the region investigated by this analysis) for all operating conditions.

18 citations

Journal ArticleDOI
01 Jun 1965
TL;DR: In this paper, a discussion of the flow pattern in the rotor passages of a radial gas turbine showed that loss data for predicting turbine performance could only be adequately obtained from rotating cascades or turbine tests.
Abstract: A discussion of the flow pattern in the rotor passages of a radial gas turbine showed that loss data for predicting turbine performance could only be adequately obtained from rotating cascades or turbine tests. The details are given of an analysis of the radial gas turbine tests described by Hiett and Johnston. The analysis showed that the deviation in the nozzle gas leaving angle was dependent not only on the nozzle geometry and gas leaving angle but also on the rotor speed and geometry. Two rotor loss coefficients were obtained, one, ζRA, was similar in form to the conventional axial turbine type loss coefficient, the other, ζRB, could be used with Wallace's theory for predicting the off-design characteristics of the turbine. The two loss coefficients are shown to be related. The results showed that ζRB could be expressed as a function of the gas incident angle and the relative velocity at the rotor tip for each turbine. The conventional loss coefficient ζRA had a minimum value at negative incidence to ...

11 citations