Three-Dimensional Navier-Stokes Computation of Turbomachinery Flows Using an Explicit Numerical Procedure and a Coupled k-ε Turbulence Model

Kunz, Robert F.; Lakshminarayana, B.

doi:10.1115/91-gt-146

Cited by 10 publications

(9 citation statements)

References 19 publications

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“…This Runge-Kutta time integration was first used for the solution of Euler equations by Jameson et al (1981), associated with a space centred discretisation, but it is also used with upwind space discretisation. All these schemes were initially developed in an explicit approach, and for turbomachinery simulations some examples of 2D or 3D calculations have been presented by Engel (1994), Couaillier (1991), Denton (1982), and Kunz (1992).…”

Section: Time Discretisationmentioning

confidence: 99%

The North Atlantic Treaty Organization

Prescott¹

2013

An Institutional Approach to the Responsibility to Protect

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la Validation CFD des organes des propulseurs) edited by J. Dunham Approved for public r»leraö; Dia«ibi.;{ioT' üJV.1'; riled dn Report of the Propulsion and Energetics Panel Working Group 26.According to its Charter, the mission of AGARD is to bring together the leading personalities of the NATO nations in the fields of science and technology relating to aerospace for the following purposes:-Recommending effective ways for the member nations to use their research and development capabilities for the common benefit of the NATO community;•-Providing scientific and technical advice and assistance to the Military Committee in the field of aerospace research and development (with particular regard to its military application);-Continuously stimulating advances in the aerospace sciences relevant to strengthening the common defence posture;-Improving the co-operation among member nations in aerospace research and development;-Exchange of scientific and technical information;-Providing assistance to member nations for the purpose of increasing their scientific and technical potential;-Rendering scientific and technical assistance, as requested, to other NATO bodies and to member nations in connection with research and development problems in the aerospace field.The highest authority within AGARD is the National Delegates Board consisting of officially appointed senior representatives from each member nation. The mission of AGARD is carried out through the Panels which are composed of experts appointed by the National Delegates, the Consultant and Exchange Programme and the Aerospace Applications Studies Programme. The results of AGARD work are reported to the member nations and the NATO Authorities through the AGARD series of publications of which this is one.Participation in AGARD activities is by invitation only and is normally limited to citizens of the NATO nations.* AGARD merged with the Defence Research Group of NATO (DRG) on 1 January 1998 to form the Research and Technology Organization (RTO) of NATO. However, both AGARD and DRG will continue to issue publications under their own names in respect of work performed in 1997. Executive SummaryThe high performance of aircraft turbine engines -mainly oriented towards economy in civil engines and towards performance, economy and off-design reliability in military applications -depends on the correct design of gas flows in the engine. Today, this is mainly done by numerical computer simulation instead of the much more costly experimentation with hardware. The working group undertook to analyse the quality of computer codes in use and to show ways for improvement. Many discrepancies between codes were detected and it was recognized that even the researchers actively working in this field were unaware of the full scale of this phenomenon. The military will gain from the newly designed engines as well as from possible improvement in upgrades. It should be noted that this kind of down-toearth analysis, despite its merits, has not been undertaken on an international basis ou...

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Section: Time Discretisationmentioning

confidence: 99%

The North Atlantic Treaty Organization

Prescott¹

2013

An Institutional Approach to the Responsibility to Protect

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“…The dominant physical phenomena in tipclearance flows, including blade unloading and leakage jet roll-up, are determined essentially by an inviscid mechanism. For this reason, several useful tip-clearance models have been developed based on primarily inviscid considerations, such as Rains (1954), Horlock (1967), Lakshminarayana (1970), Moore and Tilton (1988) and Chen et al (1991). The semitheoretical tip-clearance model developed by Laksluninarayana (1970) using lifting-line theory has been used widely in the gas turbine industry.…”

Section: Nomenclaturementioning

confidence: 99%

Three-Dimensional Navier-Stokes Analysis of Turbine Rotor and Tip-Leakage Flowfield

Luo¹,

Lakshminarayana

1997

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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The 3-D viscous flowfield in the rotor passage of a single-stage turbine, including the tip-leakage flow, is computed using a Navier-Stokes procedure. A grid-generation code has been developed to obtain embedded H grids inside the rotor tip gap. The blade tip geometry is accurately modeled without any “pinching”. Chien’s low-Reynolds-number k-ε model is employed for turbulence closure. Both the mean-flow and turbulence transport equations are integrated in time using a four-stage Runge-Kutta scheme. The computational results for the entire turbine rotor flow, particularly the tip-leakage flow and the secondary flows, are interpreted and compared with available data. The predictions for major features of the flowfield are found to be in good agreement with the data. Complicated interactions between the tip-clearance flows and the secondary flows are examined in detail. The effects of endwall rotation on the development and interaction of secondary and tip-leakage vortices are also analyzed.

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“…This treatment, which was common for both the leading and the trailing edges, has the disadvantage of requiring grid lines that are very close to the flow direction near the leading and the trailing edges. This problem is related to the ambiguity of calculating metrics locally; Kunz and Lakshminarayana (1991) have already presented a way of circumventing the problem.…”

Section: The Particular Treatment At the Leading And Trailing Edgesmentioning

confidence: 99%

Modeling of Tip Clearance Flows Through an Improved 3-D Pressure Correction Navier-Stokes Solver

et al. 1993

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Mechanical constraints dictate the existence of tip clearances in rotating cascades, resulting to a flow leakage through this clearance which considerably influences the efficiency and range of operation of the machine. Three-dimensional Navier-Stokes solvers are often used for the numerical study of compressor and turbine stages with tip-clearance. The quality of numerical predictions depends strongly on how accurately the blade tip region is modelled; in this respect the accurate modelling of tip region was one of the main goals of this work. In the present paper, a 3-D Navier-Stokes solver is suitably adapted so that the flat tip surface of a blade and its sharp edges could be accurately modelled, in order to improve the precision of the calculation in the tip region. The adapted code solves the fully elliptic, steady, Navier-Stokes equations through a space-marching algorithm and a pressure correction technique; the H-type topology is retained, even in cases with thick leading edges where a special treatment is introduced herein. The analysis is applied to two different cases, a linear cascade and a compressor rotor, and comparisons with experimental data are provided.

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Three-Dimensional Navier-Stokes Computation of Turbomachinery Flows Using an Explicit Numerical Procedure and a Coupled k-ε Turbulence Model

Cited by 10 publications

References 19 publications

The North Atlantic Treaty Organization

The North Atlantic Treaty Organization

Three-Dimensional Navier-Stokes Analysis of Turbine Rotor and Tip-Leakage Flowfield

Modeling of Tip Clearance Flows Through an Improved 3-D Pressure Correction Navier-Stokes Solver

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