Interpretation of Adjoint Solutions for Turbomachinery Flows

Marta, André C.; Shankaran, Sriram; Wang, Qiqi; Venugopal, Prem

doi:10.2514/1.j052177

Cited by 15 publications

(11 citation statements)

References 25 publications

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“…In the context of the discrete adjoint, full account of the viscous effects and linearization of the RANS equations coupled with a turbulence model has been attempted by several authors [36,37,38,39,40]. Applications to realistic aerodynamic optimization problems can also be found in [41] for fixed wing aircraft, and in Mani and Mavriplis [42] for rotorcraft.…”

Section: Past Work On Adjoint For Aircraft and Rotorcraft Applicationsmentioning

confidence: 99%

“…It is interesting to quantify the inaccuracies introduced into the gradients by such approximation, as in Dwight and Brezillon [36] and in Lyu et al [37] for the Spalart-Allmaras one-equation turbulence model, and in Marta et al [38] for the k-ω two-equation model. In a discrete adjoint solver, the frozen turbulence can be simulated by simply disabling the differentiated code computing the turbulence model derivatives.…”

Section: Naca0012 Aerofoil In Turbulent Flowmentioning

confidence: 99%

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Fully Implicit Discrete-Adjoint Methods for Rotorcraft Applications

2016

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This paper presents the development of a fully implicit, low-memory, discrete adjoint method by means of automatic source-code differentiation applied to the Helicopter Multi-Block computational fluid dynamics solver. The method is suitable for applications in flight mechanics as well as shape optimization, and is demonstrated in this paper for popular flow cases reported in the literature. In particular, adjoint CFD computations were undertaken for airfoils, wings and rotor blade cases, and the obtained results were found to agree well with published solutions and with finite differences of flow derivatives. The method has been demonstrated for inviscid and viscous cases and results suggest that the current implementation is robust and efficient. The cost of the adjoint computations is relatively low due to the employed source-code differentiation and most of the times it is no more than the cost of a steady-state flow solution.

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Section: Past Work On Adjoint For Aircraft and Rotorcraft Applicationsmentioning

confidence: 99%

Section: Naca0012 Aerofoil In Turbulent Flowmentioning

confidence: 99%

Fully Implicit Discrete-Adjoint Methods for Rotorcraft Applications

2016

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“…The difficulty in developing the adjoint form of the nonreflecting and the mixing plane boundary conditions has hindered its application for turbomachinery flows until recently [11,27,28,32,[43][44][45][46]. Frey et al [11] described a systematic approach to develop a discrete adjoint solver for turbomachinery optimization including the adjoint boundary conditions for the conservative mixing planes.…”

Section: Introductionmentioning

confidence: 99%

“…Frey et al [11] described a systematic approach to develop a discrete adjoint solver for turbomachinery optimization including the adjoint boundary conditions for the conservative mixing planes. Marta et al [32] discussed physical meaning of steady adjoint solutions for turbomachinery. Luo et al [28] presented optimization of the NASA Rotor 67 fan by using a threedimensional viscous adjoint solver and redesigned the blades for three different operating conditions; namely, near peak efficiency, near stall, and near choke.…”

Section: Introductionmentioning

confidence: 99%

A discrete adjoint harmonic balance method for turbomachinery shape optimization

Huang

Ekici

2014

Aerospace Science and Technology

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“…The adjoint method may be categorized into two kinds: the continuous and the discrete adjoint methods. There are various discussions on the differences, advantages, and disadvantages of the two approaches [9][10][11]. We note here only the following.…”

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confidence: 99%

Turbine Blade Row Optimization Through Endwall Contouring by an Adjoint Method

Luo

Liu

McBean

2015

Journal of Propulsion and Power

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This paper presents the application of a viscous continuous adjoint method for the optimization of a low-aspectratio turbine blade row through endwall contouring. A generalized wall-function method is implemented in a Navier-Stokes flow solver with Menter's shear-stress transport k-ω turbulence model to simulate the secondary flow with reduced requirements on grid density. Entropy production through the blade row combined with a flow turning constraint is used as the objective function in the optimization. With the viscous adjoint method, at each design cycle, the complete gradient information needed for optimization can be obtained by solving the flow governing equations and their corresponding adjoint equations only once for each cost function, regardless of the number of design parameters. Flow loss through the blade row is minimized while maintaining the same mass-averaged flow turning at the design condition. The performance of the optimized blade at off-design conditions is also evaluated and compared with that of the original blade.

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Interpretation of Adjoint Solutions for Turbomachinery Flows

Cited by 15 publications

References 25 publications

Fully Implicit Discrete-Adjoint Methods for Rotorcraft Applications

Fully Implicit Discrete-Adjoint Methods for Rotorcraft Applications

A discrete adjoint harmonic balance method for turbomachinery shape optimization

Turbine Blade Row Optimization Through Endwall Contouring by an Adjoint Method

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