Approach to High-Performance Transonic Compressor Design

Oana, Mineyasu; Kawamoto, Osamu; Ohtani, Hideo; Yamamoto, Y.

doi:10.2514/1.9243

Cited by 7 publications

(2 citation statements)

References 7 publications

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“…Ibaraki [9,10] found that the interaction of shock wave and tip leakage flow enhanced the blockage of the blade channel and caused flow loss in a transonic centrifugal compressor. Owing to the complex flow behavior mentioned above, the efficiency [11] and Stable Flow Range (SFR) [12,13] declined sharply with increasing pressure ratio in a centrifugal compressor. Therefore, the low efficiency and narrow SFR severely restrict the development and application of high-pressure-ratio centrifugal compressors, and this situation could become more severe with the design pressure ratio increased to an ultra-high level (higher than 10.0).…”

Section: Introductionmentioning

confidence: 99%

Effect of Self-Recirculating Casing Treatment on the Aerodynamic Performance of Ultra-High-Pressure-Ratio Centrifugal Compressors

et al. 2023

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The motivation to design a more efficient and compact aircraft engine leads to a continuous increase in overall pressure ratio and decrease in the stage number in compressors. Compared to the traditional multi-stage compressor, a single-stage ultra-high-pressure-ratio centrifugal compressor with a pressure ratio higher than 10.0 can significantly improve the engine’s power-to-weight ratio and fuel economy with a reduced structure complexity. Thus, it has great potential to be adopted in the compression system of advanced aero engines, such as turboshaft engines, in the future. However, the highly narrow Stable Flow Range (SFR) of ultra-high-pressure-ratio centrifugal compressors is a severe restriction for engineering applications. This research focuses on the aerodynamic performance of a ultra-high-pressure-ratio centrifugal compressor, and three-dimensional simulation is employed to investigate the effect of Self-Recirculating Casing Treatment (SRCT) on the performance and stability of the centrifugal compressor. Firstly, the parametric model of SRCT is established to investigate the effect of geometry parameters (rear slot distance and rear slot width) on the aerodynamic performance of the centrifugal compressor. It is concluded that SRCT improves the compressor’s SFR but deteriorates its efficiency. Also, a non-linear and non-monotone relationship exists between the SFR and rear slot distance or width. Then, the flow mechanism behind the effect of SRCT is explored in detail. By introducing the SRCT, an additional flow path is provided across the blade along the circumferential direction, and the behavior of the shock wave and tip leakage flow is significantly changed, resulting in the obviously different loading distribution along the streamwise direction. As a result, the mixing and flow separation loss are enhanced in the impeller flow passage to deteriorate the efficiency. On the other hand, the blockage effect caused by the mixing of slot recirculation and mainstream flow near the impeller inlet increases the axial velocity and reduces the incidence angle below the 90% spanwise section, which is considered to effectively stabilize the impeller flow field and enhance the stability.

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Section: Introductionmentioning

confidence: 99%

Effect of Self-Recirculating Casing Treatment on the Aerodynamic Performance of Ultra-High-Pressure-Ratio Centrifugal Compressors

et al. 2023

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“…Even small value of efficiency improvement means a lot, especially for big power plants or engines running for long duration. Experimental work needed for developing compressors is very expensive, see [1]. The high cost of the experimental work needed for such improvements, is pushing the research towards implementing software codes for optimization besides the experimental work, to shorten the required experimental work as possible.…”

Section: Introductionmentioning

confidence: 99%

Three Dimensional Multi-Objective Design Optimization of Centrifugal Compressor Impeller

Elnashar

Wahba

Abdelrahman

2007

International Conference on Aerospace Sciences and Aviation Tec

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A method for centrifugal compressor impeller's multi-objective design optimization was developed. The method was applied to a tested twelve radial bladed centrifugal compressor impeller, available in the open literature, as a test case characterized by three-dimensional viscous turbulent flow structure. The optimization target was to maximize the total-to-total adiabatic efficiency, and pressure ratio of the impeller at the design point, considering constant mass flow rate, rotational speed, and nearly constant torque. The aerodynamic analysis was performed using (CFX BladeGen) commercial software. This software solves the three-dimensional turbulent Navier-Stokes flow equations, with zero-equation turbulence model using finite volume method. The capabilities of the software were first validated by comparing the computed results with, an experimental data made by Mizuki [10, 11]. In this experimental work, yaw probes distributed along the impeller channel, were used to determine total and static pressures for hub and shroud. GAlib software was used to apply Genetic algorithm for handling of the optimization problem. The optimal impeller configuration, which corresponds to maximum efficiency, and maximum pressure ratio, keeping the same mass flow rate and rpm, was obtained with only 0.7% violation of the original torque value. A comparison between original and optimized impellers was made, which revealed the causes for efficiency and pressure ratio improvements.

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Scale-Adaptive Simulation of the Unsteady Turbulent Flow in a High-Speed Centrifugal Compressor with a Wedge-Type Vaned Diffuser

Zamiri

Choi

Chung

2019

Flow Turbulence Combust

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Approach to High-Performance Transonic Compressor Design

Cited by 7 publications

References 7 publications

Effect of Self-Recirculating Casing Treatment on the Aerodynamic Performance of Ultra-High-Pressure-Ratio Centrifugal Compressors

Effect of Self-Recirculating Casing Treatment on the Aerodynamic Performance of Ultra-High-Pressure-Ratio Centrifugal Compressors

Three Dimensional Multi-Objective Design Optimization of Centrifugal Compressor Impeller

Scale-Adaptive Simulation of the Unsteady Turbulent Flow in a High-Speed Centrifugal Compressor with a Wedge-Type Vaned Diffuser

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