High Resolution RANS Nonlinear Harmonic Study of Stage 67 Tip Injection Physics

Grosvenor, Allan D.; Rixon, Gregory S.; Sailer, Logan M.; Matheson, Michael A.; Gutzwiller, David P.; Demeulenaere, Alain; Gontier, Mathieu; Strazisar, A. J.

doi:10.1115/1.4028550

Cited by 14 publications

(6 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…On a traditional homogenous cluster, this scheme has allowed near-linear scalability with thousands of MPI processes and quick solution time for meshes with billions of points [2,3]. A representative speedup curve is shown in Figure 2.…”

Section: Pre-existing Parallel Modelmentioning

confidence: 99%

Acceleration of the FINE/Turbo CFD solver in a heterogeneous environment with OpenACC directives

Gutzwiller¹,

Srinivasan

Demeulenaere³

2015

Proceedings of the Second Workshop on Accelerator Programming Using Directives

Self Cite

View full text Add to dashboard Cite

Adapting legacy applications for use in a modern heterogeneous environment is a serious challenge for an industrial software vendor (ISV). The adaptation of the NUMECA FINE/Turbo computational fluid dynamics (CFD) solver for accelerated CPU/GPU execution is presented. An incremental instrumentation with OpenACC directives has been used to obtain a global solver acceleration greater than 2X on the OLCF Titan supercomputer. The implementation principals and procedures presented in this paper constitute one successful path towards obtaining meaningful heterogeneous performance with a legacy application. The presented approach minimizes risk and developer-hour cost, making it particularly attractive for ISVs.

show abstract

Section: Pre-existing Parallel Modelmentioning

confidence: 99%

Acceleration of the FINE/Turbo CFD solver in a heterogeneous environment with OpenACC directives

Gutzwiller¹,

Srinivasan

Demeulenaere³

2015

Proceedings of the Second Workshop on Accelerator Programming Using Directives

Self Cite

View full text Add to dashboard Cite

show abstract

“…In the passive flow control methods such as casing treatment (Houghton et al 2012;Sakuma et al 2014;Du et al 2016), blade tip winglet (Han et al 2014(Han et al , 2016 and blade tip modifications (Gourdain et al 2009;Ma et al 2012;Jung et al 2016), the geometrical change always works among the whole operating range and it may lead to a decrease of compressor performance near the design condition. For the active flow control techniques such as plasma actuation (Saddoughi et al 2015;Ashrafi et al 2016), tip injection (Li et al 2015;Grosvenor et al 2015;Khaleghi et al 2016) and casing aspiration (Lee et al 1990;Gmelin et al 2011;Grimshaw et al 2015), however, it can act on the flow fields flexibly either all the time or only when it is needed. As one of the effective active flow control methods, the suction technique attracts the attention from an increasing number of researchers to improve the flow fields in compressors.…”

Section: Introductionmentioning

confidence: 99%

Control of Tip Leakage Flow in Axial Flow Compressor Cascade by Suction on the Blade Tip

Mao

Liu

Tang

2018

JAFM

View full text Add to dashboard Cite

One of the important ways of improving axial compressor performance is to control the tip leakage flow near the endwall region. Numerical computations were conducted to investigate the impact of blade tip suction on the axial compressor cascade performance in current paper. Three suction schemes located on the blade tip with different chordwise coverage were investigated in total. The results show that the cascade overall performance can be effectively enhanced by the proper suction scheme on the blade tip and the best scheme should be arranged at slightly downstream of the onset point of the tip leakage vortex (TLV). The control effectiveness and mechanisms are different for the different suction schemes. For the suction scheme covering the starting point of TLV, the onset point of TLV is shifted downstream, while an additional induced leakage flow near the blade leading edge is generated resulting in the increase of mixing loss. It is more effective when the structure of the main TLV is destroyed and divided into different parts by applying the blade tip suction arranged slightly behind the onset point of TLV. In addition, the blade loading is redistributed near the blade tip after the blade tip suction and the total pressure loss caused by the suction slots should also be considered in the design process.

show abstract

“…Generally, the geometrical modification always works among the whole operating range for passive flow control methods, such as casing treatment, [19][20][21][22][23] blade tip modifications, [24][25][26][27] and blade tip winglet, [28][29][30] which may result in a reduction of performance near design point. While the active flow control can be imposed on the flow fields flexibly either all the time or only when the compressor's operating point moves dangerously close to the stall line, such as plasma actuation, [31][32][33] tip injection, [34][35][36][37][38] and aspiration/suction techniques. [39][40][41][42][43][44] At present, the researches about aspiration mainly focus on the control of the boundary layer separation on blade SS or the 3D separation in the hub corner, [45][46][47][48][49][50] and the results show that the performance of compressor cascade can be improved significantly by applying the suction method.…”

Section: Introductionmentioning

confidence: 99%

Effect of casing aspiration on the tip leakage flow in the axial flow compressor cascade

Mao

Liu

Tang

2017

Proceedings of the Institution of Mechanical Engineers, Part A:

View full text Add to dashboard Cite

Tip leakage flow is usually responsible for the deterioration of compressor performance and stability. The current paper conducts numerical simulations on the impact of casing aspiration on the axial compressor cascade performance. Three aspiration schemes with different chordwise coverage are studied and analyzed. It is found that the cascade performance can be effectively improved by the appropriate casing aspiration, and the optimum aspiration scheme should cover the area including the onset point of tip leakage vortex and its vicinity. The control mechanisms are different for the aspiration schemes located at different blade chord ranges. For the aspiration scheme covering the onset point of tip leakage vortex, the improvement of the cascade performance is mainly due to that the starting point of the tip leakage vortex is shifted downstream. The original tip leakage vortex structure is divided into two parts if the aspiration scheme is located behind the onset point of tip leakage vortex and the final control effect is the combination of the influence from the two different parts of tip leakage vortex. Additionally, the casing aspiration redistributes the blade loading along the chord near blade tip. The results of these investigations may offer guidance for the appropriate design of aspiration scheme in the future updated compressors and the overall total pressure loss coefficient caused by aspiration slot should be considered in the design process.

show abstract

High Resolution RANS Nonlinear Harmonic Study of Stage 67 Tip Injection Physics

Cited by 14 publications

References 9 publications

Acceleration of the FINE/Turbo CFD solver in a heterogeneous environment with OpenACC directives

Acceleration of the FINE/Turbo CFD solver in a heterogeneous environment with OpenACC directives

Control of Tip Leakage Flow in Axial Flow Compressor Cascade by Suction on the Blade Tip

Effect of casing aspiration on the tip leakage flow in the axial flow compressor cascade

Contact Info

Product

Resources

About