Session: 34-03 Endwall, Seal & Leakage Flows

Paper Number: 81904

81904 - The Influence of Shrouded Stator Cavity Boundary Conditions on Performance of a 1.5-Stage Low-Speed Research Compressor 

The cavity leakage flow has a significant influence on the aerodynamic performance of shrouded stators in axial compressor due to the mixing interaction between the leakage flow and mainstream. A number of numerical researches have been carried out to predict and understand the cavity leakage flow. However, details about boundary conditions of the labyrinth seal cavity in numerical simulation are scarce in opening literature. Therefore, a four-stage low-speed research compressor (LSRC) with shrouded stators in Shanghai Jiao Tong University was investigated numerically in this paper, aiming at studying the influence of different cavity boundary conditions. A numerical research on the front 1.5-stage (IGV-rotor-stator) of LSRC was performed using NUMECA on different interface boundary conditions between the cavity and mainstream. The rotating speeds of the cavity domain was also considered in the simulation. The investigation indicates different boundary conditions make great impact on the aerodynamic performance of the compressor. Validated by the experimental data, when using the full non-matching connections between cavity and mainstream while cavity domain rotating, the steady three-dimensional RANS simulation of the 1.5-stage compressor can well predict the distributions of total pressure loss and the outlet flow angle near the hub. As the rotating speed of cavity domain increasing, the flow separation inside the stator passage becomes more intense.

Key words: axial compressor, LSRC, shrouded stator, cavity leakage flow, boundary condition

Presenting Author: Runzhu Shao School of aeronautics and astronautics,Shanghai Jiao Tong University

Presenting Author Biography: The author is a postgraduate sutdent in School of aeronautics and astronautics, Shanghai Jiao Tong University,mainly does research on cavity leakage flow of axial compressor.

Authors:

Runzhu Shao Shanghai Jiao Tong University
Mingmin Zhu Shanghai Jiao Tong University
Jinfang Teng Shanghai Jiao Tong University
Xiaoqing Qiang Shanghai Jiao Tong University