Numerical Analysis and Validation of the Rotor Blade Vibration Response Induced by High Pressure Compressor Deep Surge

Giersch, Thomas; Figaschewsky, Felix; Hönisch, Peter; Kühhorn, Arnold; Schrape, Sven

doi:10.1115/gt2014-26295

Cited by 11 publications

(10 citation statements)

References 12 publications

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“…of surge highlighted. Three-dimensional URANS simulations of post-stall transients require very large computational power and most models found in recent publications have attempted to reduce the size of the domain, for example by modelling a single passage (Giersch et al, 2014), part of the annulus (Crevel et al, 2014), or using a hybrid backward difference formula/harmonic balance method (Sun et al, 2019). Full-annulus URANS simulations have been carried out by (Zhao et al, 2018) using the code AU3D, which successfully modelled a deep surge event and full-span rotating stall of a modern, high-speed, multi-stage, core compressor.…”

Section: Figure 1 -Example Of Rotating Stall and Deep Surge Trajectormentioning

confidence: 99%

Three-dimensional low-order surge model for high-speed axial compressors

Righi¹,

Pachidis²,

Könözsy³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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Surge in modern aero-engines can lead to violent disruption of the flow, damage to the blade structures and eventually engine shutdown. Knowledge of unsteady performance and loading during surge is crucial for compressor design, however, the understanding and prediction capability for this phenomenon is still very limited. While useful for the investigation of specific cases, costly experimental tests and high-fidelity CFD simulations cannot be used routinely in the design process of compressor systems. There is therefore an interest in developing a low-order model which can predict compressor performance during surge with sufficient accuracy at significantly reduced computational cost. This paper describes the validation of an unsteady 3D through-flow code developed at Cranfield University for the low-order modelling of surge in axial compressors. The geometry investigated is an 8-stage rig representative of a modern aero-engine IP compressor. Two deep surge events are modelled at part speed and full speed respectively. The results are compared against high-fidelity, full annulus, URANS simulations conducted at Imperial College. Comparison of massflow, pressure and temperature time histories shows a close match between the low-order and the higher-fidelity methods. The low-order model is shown capable of predicting many transient flow features which were observed in the high-fidelity simulations, while reducing the computational cost by up to two orders of magnitude.

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Section: Figure 1 -Example Of Rotating Stall and Deep Surge Trajectormentioning

confidence: 99%

Three-dimensional low-order surge model for high-speed axial compressors

Righi¹,

Pachidis²,

Könözsy³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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show abstract

“…Another publication [17] continued this development and demonstrated good agreement between the properties of optically recorded blades and experimental vibration measurements. Some research studies have also appeared in the field of aircraft and automotive turbochargers [18,19], but their results are not very applicable, particularly with regard to the point of identification of the mistuning and the cause of the mistuning of marine engine turbocharger bladed discs.…”

Section: Introductionmentioning

confidence: 99%

Effective Mistuning Identification Method of Integrated Bladed Discs of Marine Engine Turbochargers

Píštěk

Kučera

Fomin

et al. 2020

JMSE

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Radial turbine and compressor wheels form essential cornerstones of modern internal combustion engines in terms of economy, efficiency and, in particular, environmental compatibility. As a result of the introduction of exhaust gas turbochargers in the extremely important global market for diesel engines, higher engine efficiencies are possible, which in turn reduce fuel consumption. The associated reduced exhaust emissions can answer questions that results from environmentally relevant aspects of the engine development. In shipping, the international Maritime Organisation (IMO) prescribes the step-by-step reduction of nitrogen oxide and other types of emissions. To reduce these emissions, various systems are being developed, in which turbochargers are an important part. The requirements for the reliability and service life of turbochargers are constantly increasing. Turbocharger blade vibration is one of the most important problems to be solved when designing the rotors. In the case of real rotors, so-called mistuning arises, which is a slight deviation of the properties of the individual blades from the design parameters. The article deals with an effective method of mistuning identification for cases of integrated bladed discs of marine engine turbochargers. Unlike approaches that use costly scanning laser Doppler vibrometers, this method is based on using only a simple laser vibrometer in combination with a computational model of the integrated bladed disc. The added value of this method is, in particular, a significant reduction in the cost of laboratory equipment and a reduction in the time required to obtain the results.

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“…In this study part-span rotating stall was observed across a range or rotational speeds and VSV settings. Another experimental activity was performed at DLR (the German Aerospace Center), where performance and mechanical loads during surge were measured on a high-speed IPC [7,8].…”

Section: Introductionmentioning

confidence: 99%

“…This approach, although it offers the best accuracy and fidelity, is still too computational expensive to be used for multiple simulations or the creation of rotating stall characteristics. An attempt was also made to create a complete compressor map using AU3D [7]. However, to reduce computational cost, only a single passage was modelled; the rotating stall characteristic was then only approximated, as rotating stall could not be actually modelled.…”

Section: Introductionmentioning

confidence: 99%

On the prediction of the reverse flow and rotating stall characteristics of high-speed axial compressors using a three-dimensional through-flow code

Righi

Pachidis

Könözsy

2020

Aerospace Science and Technology

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This paper presents the development of a low-order three-dimensional through-flow code created at Cranfield University in the UK, named ACROSS (Axial Compressor Rotating Stall and Surge simulator), and its application to create the reverse flow and rotating stall characteristics of a modern high-speed compressor. The compressor modelled is a six-stage axial-flow machine, representative of a modern aero-engine highpressure compressor. The tool has been previously validated using experimental data from two low-speed compressor rigs. This article describes how the tool's robustness and computational speed have been improved by introducing higher-order schemes to model the circumferential fluxes and the rigid movement of the flow in the rotating blade rows. Further improvements include variable axial discretization, an algorithm to introduce random flow perturbations in the flow field and an improved plenum model. The compressor is first modelled in reverse flow conditions to create its reverse-flow characteristics and these are then compared against results from high-fidelity 3D CFD simulations. Results obtained suggest that despite the presence of three-dimensional flow features, 2D axi-symmetric simulations are adequate to generate the full range of reverse flow characteristics of the compressor. The rotating stall characteristics at 77% and 100% corrected rotational speed are created by modelling several steady rotating stall cases in 3D. Using the code ACROSS, the complete map of the compressor modelled, comprising of forward flow, reverse flow and rotating stall characteristics, was created in only 5 days using 3 desktop workstations. For comparison, state-of-the-art high-fidelity 3D CFD requires several days to simulate a single rotating stall case on a high performance computing facility.

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Numerical Analysis and Validation of the Rotor Blade Vibration Response Induced by High Pressure Compressor Deep Surge

Cited by 11 publications

References 12 publications

Three-dimensional low-order surge model for high-speed axial compressors

Three-dimensional low-order surge model for high-speed axial compressors

Effective Mistuning Identification Method of Integrated Bladed Discs of Marine Engine Turbochargers

On the prediction of the reverse flow and rotating stall characteristics of high-speed axial compressors using a three-dimensional through-flow code

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