Calculation of multistage turbomachinery using steady characteristic boundary conditions

Chima, Rodrick V.

doi:10.2514/6.1998-968

Cited by 34 publications

(22 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The shear stress limiter has been shown to improve results for shock separated flows 14 . For multistage turbomachinery SWIFT uses a mixing plane approach with steady characteristic boundary conditions written in terms of perturbations about the mean flow from the neighboring blade row 13 . This allows close spacing between the blade rows without forcing the flow to be axisymmetric.…”

Section: Swift Codementioning

confidence: 99%

“…SWIFT is a multiblock Navier-Stokes analysis code for turbomachinery developed by Chima [9][10][11][12][13] . For the original ASME and AGARD rotor 37 test case [6][7] SWIFT used a central-difference scheme and an algebraic turbulence model.…”

Section: Introductionmentioning

confidence: 99%

“…A mixing plane model 13 was used to analyze stage 35. Details of the experimental data and SWIFT code are described briefly.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

SWIFT Code Assessment for Two Similar Transonic Compressors

Chima

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

Self Cite

View full text Add to dashboard Cite

Section: Swift Codementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

SWIFT Code Assessment for Two Similar Transonic Compressors

Chima

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

Self Cite

View full text Add to dashboard Cite

“…This subsection discusses the development of the exact adjoint boundary condition for Chima's steady averaging-plane approach [53] Thus,…”

Section: Rotor-stator Interfacementioning

confidence: 99%

Adjoint-Based Constrained Aerodynamic Shape Optimization for Multistage Turbomachines

Walther

Nadarajah

2015

Journal of Propulsion and Power

View full text Add to dashboard Cite

This work proposes a framework for fully-automatic gradient-based constrained aerodynamic shape optimization in a multistage turbomachinery environment. A turbomachinery solver which solves the Reynolds-averaged Navier-Stokes (RANS) equations to a steady-state in both rotating and stationary domains is developed. Characteristic-based inlet and outlet boundary conditions are imposed, while adjacent rotor and stator rows are coupled by mixing-plane interfaces. To allow for an efficient but accurate gradient calculation, the turbomachinery RANS solver is adjointed at a discrete level. The systematic approach for the development of the discrete adjoint solver is discussed. Special emphasis is put on the development of the turbomachinery specific features of the adjoint solver, i.e. on the derivation of flow-consistent adjoint inlet and outlet boundary conditions and, to allow for a concurrent rotor-stator optimization and stage coupling, on the development of an exact adjoint counterpart to the non-reflective, conservative mixing-plane formulation used in the flow solver.The adjoint solver is validated by comparing its sensitivities with finite-difference gradients obtained from the flow solver. A parallelized, automatic grid perturbation scheme utilizing radial basis functions, which is accurate and robust as well as able to handle complex multi-block grid configurations, is employed to calculate the gradient

show abstract

“…[17][18][19] Three turbomachinery blades were analyzed and the results were compared to experimental data. In each case the upwind schemes gave significant improvements over the C-D scheme.…”

Section: Introductionmentioning

confidence: 99%