Lessons from rotor 37

Denton, J. D.

doi:10.1007/s11630-997-0010-9

Cited by 133 publications

(87 citation statements)

References 5 publications

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“…The configuration and input meshes of Hydra in these experiments model a standard application in CFD, called NASA Rotor37 [17]. It is a transonic axial compressor rotor widely used for validation in CFD.…”

Section: Hydra: Oplus Vs Op2mentioning

confidence: 99%

Acceleration of a Full-Scale Industrial CFD Application with OP2

Reguly

Mudalige

Bertolli

et al. 2016

IEEE Trans. Parallel Distrib. Syst.

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Hydra is a full-scale industrial CFD application used for the design of turbomachinery at Rolls Royce plc. It consists of over 300 parallel loops with a code base exceeding 50K lines and is capable of performing complex simulations over highly detailed unstructured mesh geometries. Unlike simpler structured-mesh applications, which feature high speed-ups when accelerated by modern processor architectures, such as multi-core and many-core processor systems, Hydra presents major challenges in data organization and movement that need to be overcome for continued high performance on emerging platforms. We present research in achieving this goal through the OP2 domain-specific high-level framework. OP2 targets the domain of unstructured mesh problems and follows the design of an active library using source-to-source translation and compilation to generate multiple parallel implementations from a single high-level application source for execution on a range of back-end hardware platforms. We chart the conversion of Hydra from its original hand-tuned production version to one that utilizes OP2, and map out the key difficulties encountered in the process. To our knowledge this research presents the first application of such a high-level framework to a full scale production code. Specifically we show (1) how different parallel implementations can be achieved with an active library framework, even for a highly complicated industrial application such as Hydra, and (2) how different optimizations targeting contrasting parallel architectures can be applied to the whole application, seamlessly, reducing developer effort and increasing code longevity. Performance results demonstrate that not only the same runtime performance as that of the hand-tuned original production code could be achieved, but it can be significantly improved on conventional processor systems. Additionally, we achieve further acceleration by exploiting many-core parallelism, particularly on GPU systems. Our results provide evidence of how high-level frameworks such as OP2 enable portability across a wide range of contrasting platforms and their significant utility in achieving near-optimal performance without the intervention of the application programmer.

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Section: Hydra: Oplus Vs Op2mentioning

confidence: 99%

Acceleration of a Full-Scale Industrial CFD Application with OP2

Reguly

Mudalige

Bertolli

et al. 2016

IEEE Trans. Parallel Distrib. Syst.

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“…The TURBO wake comparison is done for the rotor trailing edge at the 50% stator pitch location. As is characteristic for CFD calculations in general [21,22], TURBO and APNASA show a very deep wake compared to the LDV data. The nature of LDV data acquisition and ensemble averaging could account for most of this difference in wake depth very near the rotor trailing edge.…”

Section: Rotor Lossesmentioning

confidence: 64%

Blade Row Interaction Effects on the Performance of a Moderately Loaded NASA Transonic Compressor Stage

Zante

Chen

2002

Volume 5: Turbo Expo 2002, Parts a and B

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Blade row interaction effects on loss generation in compressors have received increased attention as compressor work-per-stage and blade loading have increased. Two dimensional Laser Doppler Velocimeter measurements of the velocity field in a NASA transonic compressor stage show the magnitude of interactions in the velocity field at the peak efficiency and near stall operating conditions. The experimental data are presented along with an assessment of the velocity field interactions. In the present study the experimental data are used to confirm the fidelity of a three-dimensional, time-accurate, Navier Stokes calculation of the stage using the MSU-TURBO code at the peak efficiency and near stall operating conditions. The simulations are used to quantify the loss generation associated with interaction phenomena. At the design point the stator pressure field has minimal effect of the rotor performance. The rotor wakes do have an impact on loss production in the stator passage at both operating conditions. A method for determining the potential importance of blade row interactions on performance is presented.

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“…1 a) For a fixed passage shock strength, the low post-shock Mach number M re i (observation no.l) could be induced by too thin a post-shock boundary layer on the suction side (Denton, 1996). This is because the subsonic Mach number downstream of the shock is reduced if the flow blockage diminishes.…”

Section: 23mentioning

confidence: 99%

“…The same data were the basis for an extensive CFD code assessment effort sponsored by the ASME International Gas Turbine Institute's Turbomachinery Committee during 1993. Wisler (1993 and Denton (1996) discuss the organization and results of this work. …”

Section: Experimental Programmementioning

confidence: 99%

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North Atlantic Treaty Organization

Mawdsley¹

2007

Encyclopedia of Governance

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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. 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 outside AGARD/RTO. La validation CFD des organes des propulseurs (AGARD AR-355) SyntheseLa recherche de hautes performances des turbomoteurs, motivee, pour les moteurs civils, principalement par la recherche d'economies, et pour les moteurs militaires par F amelioration des performances, les economies et la fiabilite dans des conditions hors tolerances, passe par une connaissance precise de la conception des ecoulements dans le moteur.Aujourd'hui, dans ...

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Lessons from rotor 37

Cited by 133 publications

References 5 publications

Acceleration of a Full-Scale Industrial CFD Application with OP2

Acceleration of a Full-Scale Industrial CFD Application with OP2

Blade Row Interaction Effects on the Performance of a Moderately Loaded NASA Transonic Compressor Stage

North Atlantic Treaty Organization

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