Effect of Wet Steam on Aerodynamic Performance of Low-Pressure Exhaust
                        Passage with Last Stage Blade

Lin, Aqiang; Chang, Xinye; Cao, Lihua; Zhang, H.; Sun, Liping

doi:10.29252/jafm.12.06.29757

Cited by 7 publications

(3 citation statements)

References 23 publications

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“…Then, the static pressure recovery and total pressure loss coefficients are used to characterize the performance of exhaust passage [13,14]. Lin et al [15] numerically investigated the three-dimensional flow field of exhaust hood with consideration of various inflow conditions of inlet angle, swirl strength and wetness. They found that the performance is a strong function of inflow conditions.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Analysis of Aerodynamic Characteristics of Exhaust Passage with Consideration of Wet Steam Effect in a Supercritical Steam Turbine

Lin

Cai

et al. 2020

Energies

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To investigate the aerodynamic performance of exhaust passage under multi-phase flow, an actual case is conducted in the low-pressure double exhaust passages of 600 MW steam turbine. Then, the flow field is compared and analyzed with and without the built-in extraction pipelines based on the Eulerian–Eulerian homogenous medium multiphase method. Results show that the upstream swirling flow and downstream mixed swirling flow are the main causes to induce the entropy-increase in the exhaust passage. Moreover, the flow loss and static-pressure recovery ability in the exhaust hood are greater than those in the condenser neck. Compared with the flow field without the steam extraction pipelines, the entropy-increase increases, the static pressure recovery coefficient decreases, and the spontaneous condensation rates of wet steam decrease in the downstream area of the pipelines. With the increase of steam turbine loads, an increment in entropy-increase in the exhaust passage is 0.98 J/(kg·K) lower than that without steam extraction pipelines. Moreover, the incrementing range of uniformity coefficient is increased from 14.5% to 40.9% at the condenser neck outlet. It can be concluded that the built-in exhaustion pipeline can improve the aerodynamic performance of exhaust passage and better reflect the real state of the flow field. These research results can serve as a reference for turbine passage design.

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Section: Introductionmentioning

confidence: 99%

“…A full-scale low-pressure (LP) cylinder of a supercritical large power steam turbine[15].98 Calculational domain of a LP exhaust passage with the addition of LSBs and extraction 100 pipelines [15]. 1.…”

mentioning

confidence: 99%

Numerical Analysis of Aerodynamic Characteristics of Exhaust Passage with Consideration of Wet Steam Effect in a Supercritical Steam Turbine

Lin

Cai

et al. 2020

Energies

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“…It compresses the incoming air through high-speed rotating blades and then enhances air pressure [1]. However, the flow loss inside the compressor is critical to the performance of aero engines under high reverse pressure gradients, especially for tip leakage flow and secondary flow [1][2][3]. Currently, the commercial codes of computational fluid dynamics are usually conducted for numerical analysis, due to the improvement of computational accuracy in the field of turbomachinery [4], flow loss [5], heat transfer [6,7], etc.…”

Section: Introductionmentioning

confidence: 99%

Numerical Analysis of High-Altitude Inlet Air on Boundary Layer Flow Loss in an Aero-Engine Compressor

Gao

Yang

et al. 2020

Energies

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A numerical analysis is performed to explore the high altitude and high Mach flight on the effect of wall boundary layer loss in the compressor. The accuracy for solution results by the application of the similarity criterion and parameter definition of the air inlet is compared with the existing experimental test result. The results indicate that the radial adverse pressure gradient in the rotor domain gradually increases along the span direction and decreases as flight Mach number increases; meanwhile, the circumferential adverse pressure gradient on the pressure side of the rotor blade is correspondingly larger and less than that on the suction side. In particular, the entropy increase along the streamwise shows a decreasing trend and an increasing trend inside the hub and shroud wall boundary layers, respectively. At 2.1 Ma, the entropy increase in the rotor domains enhances by 24.36–27.80% inside the shroud boundary layer, relative to the hub boundary layer; however, it decreases by 0.97–8.54% in the stator domain. With the increase in flight Mach number from 2.1 to 3.4, the average entropy increase reductions in the rotor domain decrease by 18.99–24.97% within the hub boundary layer and 5.71–8.1% within the shroud boundary layer. In the stator domain, it drops by 18.45–9.03% inside the hub boundary layer and 6.88–8.67% inside the shroud boundary layer. It was therefore found that, as Mach number increases from 2.1 to 3.4, the entropy increase reduction is larger inside the hub boundary layer than inside the shroud boundary layer.

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Optimum Blade Geometry C-9015A to Reduce Blade Erosion

Masood,

Zabelin,

Fokin

et al. 2024

Lecture Notes in Networks and Systems

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Effect of Wet Steam on Aerodynamic Performance of Low-Pressure Exhaust Passage with Last Stage Blade

Cited by 7 publications

References 23 publications

Numerical Analysis of Aerodynamic Characteristics of Exhaust Passage with Consideration of Wet Steam Effect in a Supercritical Steam Turbine

Numerical Analysis of Aerodynamic Characteristics of Exhaust Passage with Consideration of Wet Steam Effect in a Supercritical Steam Turbine

Numerical Analysis of High-Altitude Inlet Air on Boundary Layer Flow Loss in an Aero-Engine Compressor

Optimum Blade Geometry C-9015A to Reduce Blade Erosion

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