A fast multiobjective optimization approach to S-duct scoop inlets design with both inflow and outflow

Zeng, Lifang; Pan, Dingyi; Ye, Shangjun; Shao, Xueming

doi:10.1177/0954410018795806

Cited by 5 publications

(3 citation statements)

References 18 publications

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“…Furthermore, according to previous studies, Rodriguez 17 used k-ω SST turbulence model to predict distortion of L-inlet duct for the design of Siemens gas turbine, which was proven by engineering application. Fiola 25 and Zeng 7 found that k-ω SST turbulence model can predict the separation flow well with the experimental data. Compared to the k-ε RNG model, the k-ω SST model is known for its improved numerical stability nearby the wall.…”

Section: Methodsmentioning

confidence: 73%

“…The Sshaped bend design which has been investigated a lot is the typical prototype of aero-engine inlet. [4][5][6][7] On the other hand, the L-shaped bend design is widely used in ground gas turbine inlet and marine gas turbine inlet due to the constraint of space layout that minimum space and avoidance of inhaling ground particles are required. The L-inlet duct would not only increase the pressure drop, but also aggravate the flow distortion, which may reduce the efficiency and cause surge in some severe conditions.…”

Section: Introductionmentioning

confidence: 99%

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Fast multi-objective optimization design of gas turbine L-inlet duct

Xin,

Min,

Pan

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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With ever-increasing demand for high efficiency and high stability gas turbine under the goal of carbon neutrality, the design of L-inlet duct has set stricter demands for low pressure loss and low flow distortion. No general optimization guidelines on both pressure loss and distortion for L-inlet duct were found in open literature. Four geometry parameters including inlet width, inlet length, contraction geometry angle and truncated cone geometry angle are explored for their effects on the trends of pressure loss and flow distortion. Optimization geometry parameters of the L-inlet duct are analysed, and the flow characteristics are thoroughly examined. The flow field characteristic of ΔPt, DC60, SC60 from surrogate model are validated by CFD, the relative errors are 0.37%, −3.92% and 1.75%, respectively. At the design point EF = 35 comparing with original scheme of the L-inlet duct, ΔPt decreases 21.14%, DC60 decreases 45.37%, and SC60 decreases 38.7%. For all off design conditions, the optimization results are better than original scheme. It is estimated that gas turbines can achieve a 0.144% reduction in power loss and a 0.333% improvement in surge margin.

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Section: Methodsmentioning

confidence: 73%

Section: Introductionmentioning

confidence: 99%

Fast multi-objective optimization design of gas turbine L-inlet duct

Xin,

Min,

Pan

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

Self Cite

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“…Baals et al [70] and Nichols et al [71] provided a detailed study of the effect of inlet lip geometry on aerodynamic performance. They reported that the NACA 1-series airfoils provide good performance by delaying sonic and separated flow for a large span of duct-to-flight-velocity ratios and Ma numbers [70][71][72][73]. Furthermore, Re [74] studied the aerodynamic performance of various NACA 1-series inlets and concluded that the inlet critical Ma number depends on the lip shape [74,75].…”

Section: X-45 X-47bmentioning

confidence: 99%

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

Aleisa¹,

Kontis²,

Pirlepeli³

et al. 2023

Journal of Aircraft

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The design of unmanned combat aerial vehicles (UCAVs) is primarily governed by the low-observability requirement for military applications rather than aerodynamic performance. The conceptual design and optimization of UCAV models via size and shape variables for different missions in different flow regimes form a research area for military vehicle design. Flying wing UCAVs experience flow separation during takeoff and landing, and furthermore exhibit stability issues. The aerodynamic performance of these UCAVs can be significantly improved by redesigning their leading-edge sweep angle and wing planform. In the present work, the initial weight determination, aerodynamic sizing, and planform with and without inlet lip integration, and the conceptual design of a nonconstant leading-edge flying wing UCAV configuration are performed. Next, the obtained conceptual design is downscaled 1:20 to be used as a wind-tunnel model and optimized for low-speed conditions using a kriging-based surrogate model with a vortex-lattice method to maximize the lift-to-drag ratio. Later, the optimized design is validated using an open-source computational fluid dynamics code, OpenFOAM 8.0, to verify the accuracy of the surrogate model and to investigate the aerodynamic characteristics. The optimized UCAV design exhibited improved aerodynamic characteristics in terms of the lift-to-drag ratio. Furthermore, the aerodynamic performance and flowfield of the optimized UCAV model with and without inlet lip integration have been evaluated at low and high speeds.

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