Turbulence characteristics in corner separation in a highly loaded linear compressor cascade

Investigation of Vortical Structures and Turbulence Characteristics in Corner Separation in a Linear Compressor Cascade Using DDES

Analysis of Fan Stage Conceptual Design Attributes for Boundary Layer Ingestion

Flow control mechanisms of a combined approach using blade slot and vortex generator in compressor cascade

An alternative model for evaluating the balance of carrying capacity between functional urban infrastructures

Cantilevered stator hub leakage flow control and loss reduction using non-uniform clearances

Application of Tandem Cascade to Design of Fan Stator with Supersonic Inflow

The multistage axial compressor is one of the critical components of aero-engines and plays a key role in their performance, reliability, and economy. Tip clearance has a significant impact on the performance and stability of multistage axial compressors. Due to blade and disk deformations, tip clearance will vary significantly in different operating conditions. Thus, tip clearance should be accurately estimated when evaluating compressor performance. This paper proposes a new model to predict changes of tip clearance of multistage axial compressors in different operating conditions. A first-principles approach is used to estimate the change of tip clearance caused by thermal and mechanical deformation. The span-wise temperature distribution across each stage of the multistage compressors is considered by the proposed model in this paper. The model was validated by General Electric Company (GE) E3 engine experimental results. Using the model, the performance of an 11-stage axial compressor is simulated. T...

http://journals.sagepub.com/doi/pdf/10.1177/0957650914535389

An 11-stage axial compressor performance simulation considering the change of tip clearance in different operating conditions

The development pattern of the end wall boundary layer (BL) in whole conditions and its effect on the matching of multistage compressor have been studied in detail in this paper. Moreover, one meth...

The effect of end wall boundary layer on matching and corresponding flow control technique for multistage axial compressor

Separation control in compressor cascade is very significant for modern high efficiency compressor. This paper introduces a separation control approach using self-supplied jet in a highly loaded ca...

Li Qiushi

Papers

Cantilevered stator hub leakage flow control and loss reduction using non-uniform clearances

Application of Tandem Cascade to Design of Fan Stator with Supersonic Inflow

An 11-stage axial compressor performance simulation considering the change of tip clearance in different operating conditions

The effect of end wall boundary layer on matching and corresponding flow control technique for multistage axial compressor

Experimental investigation on separation control by slot jet in highly loaded compressor cascade