Blade Geometry Optimization for Axial Flow Compressor

Zheng, Rongye; Xiang, Jianhua; Sun, Jinju

doi:10.1115/gt2010-22229

Cited by 6 publications

(5 citation statements)

References 12 publications

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“…Besides this, some complex flow phenomena such as the shockwave/boundary-layer interaction and the tip clearance flow in the transonic flow would adversely affect the accuracy of the numerical simulation. A similar underestimation of the aerodynamic performance of Rotor 67 using fine/turbo was also reported in the work of Zheng et al [22]. Figure 7 plots the contour of the relative Mach number under near peak efficiency conditions at the section of 30%, 70%, and 90% spans from the hub.…”

Section: Numerical Methods and Validationsupporting

confidence: 80%

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

et al. 2020

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The implementation of a three-dimensional viscous inverse design used for an axial compressor is introduced in this paper. The derivation process of the inverse design algorithm is also described in detail. Moreover, an improved blade update method and a modified relaxation factor are included to enhance the inverse design algorithm. The inverse design is built on an in-house inverse design module coupled with commercial Computational Fluid Dynamic (CFD) software NUMECATM. In contrast to analysis design, the pressure loading and the normal thickness distribution along the blade surfaces are prescribed during the process of inverse design. The numerical methods used to solve the flow field are verified using the experimental data of the transonic fan rotor NASA Rotor 67. A recovery test for the Rotor 67 is carried out to validate the developed three-dimensional inverse design tool. To explore the potential application of the inverse design system, it is then used to improve the aerodynamic performance of a transonic fan Rotor 67 and a multi-row compressor Stage 35 at a near peak efficiency point by reorganizing the pressure loading distribution on the blade surfaces.

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Section: Numerical Methods and Validationsupporting

confidence: 80%

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

et al. 2020

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“…13 It can be seen that the variation trend of numerical result is consistent with the experimental data, which shows the reliability and credibility of the numerical calculation method. After the fan blade static aeroelastic deflection, the overall aerodynamic characteristic 14 Sadeghi and Liu, 15 and Castaneda et al 16 whose results underestimate about 1.2%, 0.75%, and 1.15%, respectively. Fan blade static aeroelastic deflection enhances its capability of channel flow.…”

Section: Resultsmentioning

confidence: 96%

Investigations on static aeroelastic problems of transonic fans based on fluid–structure interaction method

Wang

Song

2016

Proceedings of the Institution of Mechanical Engineers, Part A:

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Fan blades of high bypass ratio gas turbine engines are subject to substantial aerodynamic and centrifugal loads, producing the well-known phenomenon of blade untwist. Accurate fan blade shape prediction is very crucial for high-performance aero-engine. In order to investigate the effects of static aeroelastic deflections on aerodynamic performances, a time domain two-way fluid-structure interaction method was applied to simulate the deflection of NASA Rotor 67 fan blades under different operating conditions. This paper pays attention to the deviation of fan profile and aerodynamic performance due to the varying aerodynamic loads, especially for off-design conditions. The results show that the static aeroelastic deflection has a 1.8% impact on the total pressure ratio under near stall condition, and a 1.7% impact on the choke mass flow rate, relative to the cold configuration. Thus, the blade design in industrial practice should adopt a two-way fluid-structure interaction method to consider the influence of static aeroelastic problems on aerodynamic performance.

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“…The results showed that the Spalart-Allmaras model (SA) and the Shear Stress Transport model (SST) could converge to near stall point and provide the reasonable results. According to the available research works (Zheng et al, 2010;Zhou et al, 2017) based on NASA Rotor 67's simulation by NUMECA/EURANUS. The Spalart-Allmaras was used most as a turbulence model.…”

Section: Methodsmentioning

confidence: 99%

Numerical Investigation on the Performance of Transonic Axial Compressor with Naturally Aspirated Slots on Blade

Aksorn-In¹,

Chen²,

Zhao³

et al. 2019

Proceedings of Global Power &Amp; Propulsion Society

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The stable operating range is one of the key performance parameters on safety for general compressors. In order to improve the stable range, the flow control technique by slotted rotor was computationally studied and investigated based on the case of well-known transonic axial compressor (NASA Rotor 67). The principle of slotted blade is that the rotor blade is manufactured with the aim to have a slot (connecting between pressure side and suction side) at designed location. Then, the fluid is able to flow from pressure side to suction side by the pressure differences. This effect could literally energize the mainstream flow including the retarded flow caused by the aerodynamic losses. As a result, the operating range of compressor would be improved. Throughout this work, the action mechanism of the slot and the impact on compressor performance were analyzed by the prominent commercial software, NUMECA/EURANUS. The slot was located at three significant areas (e.g., leading edge, midchord, and trailing edge). Moreover, it was also located relative to the axial tip chord of the rotor blade. The stability improvement and the modified performance of the investigated compressor (e.g., pressure ratio and efficiency) were evaluated and compared with those of original blade. The location of slot giving the best improvement was finally identified. Afterwards, the optimum location would be selected for the further investigation by orienting the slot to be inclined configuration. In addition, the geometry of slot would be changed to nozzle as well for high velocity flow at the exit in order to gain more energization (more improvement).

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Blade Geometry Optimization for Axial Flow Compressor

Cited by 6 publications

References 12 publications

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

Investigations on static aeroelastic problems of transonic fans based on fluid–structure interaction method

Numerical Investigation on the Performance of Transonic Axial Compressor with Naturally Aspirated Slots on Blade

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