Effects of Stator Shroud Injection on the Aerodynamic Performance of a Single-Stage Transonic Axial Compressor

2017 ◽  
Vol 41 (1) ◽  
pp. 9-19
Author(s):  
Cong-Truong Dinh ◽  
Sang-Bum Ma ◽  
Kwang Yong Kim
Keyword(s):  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Single Stage ◽  
Transonic Axial Compressor

Design Optimization of a Single-Stage Transonic Axial Compressor and Test Evaluation of Its Aerodynamic Performance

2012 ◽  
Vol 15 (6) ◽  
pp. 77-84 ◽  
Author(s):  
Tae Choon Park ◽  
Young-Seok Kang ◽  
Oh-Sik Hwang ◽  
Ji-Han Song ◽  
Byeung Jun Lim
Keyword(s):  
Design Optimization ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Single Stage ◽  
Test Evaluation ◽  
Transonic Axial Compressor

Effects of stator splitter blades on aerodynamic performance of a single-stage transonic axial compressor

2020 ◽  
Vol 14 (4) ◽  
pp. 7369-7378
Author(s):  
Ky-Quang Pham ◽  
Xuan-Truong Le ◽  
Cong-Truong Dinh
Keyword(s):  
Stokes Equations ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Aerodynamic Performance ◽  
Numerical Results ◽  
Single Stage ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Operating Stability ◽  
Length Coverage

Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability. Aerodynamic performance of the compressor was evaluated using three-dimensional Reynolds-averaged Navier-Stokes equations using the k-e turbulence model with a scalable wall function. The numerical results for the typical performance parameters without stator splitter blades were validated in comparison with experimental data. The numerical results of a parametric study using four geometric parameters (chord length, coverage angle, height and position) of the stator splitter blades showed that the operational stability of the single-stage axial compressor enhances remarkably using the stator splitter blades. The splitters were effective in suppressing flow separation in the stator domain of the compressor at near-stall condition which affects considerably the aerodynamic performance of the compressor.

Stall Warning Using the Rotor Tip Pressure in a Transonic Axial Compressor With Circumferential Grooves

2018 ◽  
Author(s):  
Byeung Jun Lim ◽  
Tae Choon Park ◽  
Young Seok Kang
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Axial Compressor ◽  
Rotating Stall ◽  
Single Stage ◽  
Stall Inception ◽  
Casing Treatment ◽  
Stall Warning ◽  
Transonic Axial Compressor

In this study, characteristics of stall inception in a single-stage transonic axial compressor with circumferential grooves casing treatment were investigated experimentally. Additionally, the characteristic of increasing irregularity in the pressure inside circumferential grooves as the compressor approaches the stall limit was applied to the stall warning method. Spike-type rotating stall was observed in the single-stage transonic axial compressor with smooth casing. When circumferential grooves were applied, the stall inception was suppressed and the operating point of the compressor moved to lower flow rate than the stall limit. A spike-like disturbance was developed into a rotating stall cell and then the Helmholtz perturbation was overlapped on it at N = 80%. At N = 70 %, the Helmholtz perturbation was observed first and the amplitude of the wave gradually increased as mass flow rate decreased. At N = 60%, spike type stall inceptions were observed intermittently and then developed into continuous rotating stall at lower mass flow rate. Pressure measured at the bottom of circumferential grooves showed that the level of irregularity of pressure increased as flow rate decreased. Based on the characteristic of increasing irregularity of the pressure signals inside the circumferential grooves as stall approaches, an autocorrelation technique was applied to the stall warning. This technique could be used to provide warning against stall and estimate real-time stall margins in compressors with casing treatments.

Numerical Investigation on Internal Flow Field of a Single-Stage Transonic Axial Compressor

2012 ◽  
Vol 15 (6) ◽  
pp. 85-91
Author(s):  
Ji-Han Song ◽  
Oh-Sik Hwang ◽  
Tae Choon Park ◽  
Byung-Jun Lim ◽  
Soo-Seok Yang ◽  
...  
Keyword(s):  
Flow Field ◽  
Numerical Investigation ◽  
Axial Compressor ◽  
Internal Flow ◽  
Single Stage ◽  
Transonic Axial Compressor

Aeromechanic performance of a single-stage transonic axial compressor with recirculation-bleeding channels

2020 ◽  
pp. 1-14
Author(s):  
Cong-Truong Dinh ◽  
Tien-Dung Vuong ◽  
Xuan-Truong Le ◽  
The-Mich Nguyen ◽  
Quang-Hai Nguyen
Keyword(s):  
Axial Compressor ◽  
Single Stage ◽  
Transonic Axial Compressor
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