PADRAM: Parametric Design and Rapid Meshing System for Turbomachinery Optimisation

Shahpar, Shahrokh; Lapworth, Leigh

doi:10.1115/gt2003-38698

Cited by 112 publications

(69 citation statements)

References 14 publications

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“…Simulations were performed using the Rolls-Royce plc. PADRAM-HYDRA system Lapworth 2003, Lapworth andShahpar 2004) that includes the parameterization of the blade shape, meshing, CFD analysis, postprocessing, and objective/constraints evaluation. The parameterization approach adopted in this system is very flexible but can result in a large scale optimization problem.…”

mentioning

confidence: 99%

Large Scale Optimization of Transonic Axial Compressor Rotor Blades

Shahpar¹,

Polynkin²,

Toropov³

2008

49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference &Amp;lt;br> 16th AIAA/ASME/AHS Ada

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I.Problem Formulation n the present work the Multipoint Approximation Method (MAM) by Toropov et al. (1993) has been applied to the shape optimization of an existing transonic compressor rotor (NASA rotor 37) as a benchmark case. Simulations were performed using the Rolls-Royce plc. PADRAM-HYDRA system Lapworth 2003, Lapworth andShahpar 2004) that includes the parameterization of the blade shape, meshing, CFD analysis, postprocessing, and objective/constraints evaluation. The parameterization approach adopted in this system is very flexible but can result in a large scale optimization problem.For this pilot study, a relatively coarse mesh has been used including around 470,000 nodes. The parameterization was done using 5 engineering blade parameters like axial movement of sections along the engine axis in mm (XCEN), circumferential movements of sections in degrees (DELT), solid body rotation of sections in degrees (SKEW), and leading/trailing edge recambering (LEM0/TEMO) in degrees. The design variables were specified using 6 control points at 0 % (hub), 20%, 40%, 60%, 80%, and 100% (tip) along the span. Thus the total number of independent design variables N was 30. B-spline interpolation was used through the control points to generate smooth design perturbations in the radial direction.The objective function is the adiabatic efficiency that has to be maximized where P and T are total mass averaged pressure and temperature, respectively. The constraints are the pressure ratio and mass flow rate that have to be within 1% of the same characteristic for the datum blade, i.e. 2.15 ± 1.0% for pressure ratio and 20.1 kg/s ± 0.5% for mass flow rate. II. Software ToolsIn this work the Rolls-Royce SOFT-PADRAM-HYDRA design system (SOPHY) is used. SOPHY (Shahpar 2004) is a fully integrated flexible aerodynamic design optimization system. The main elements of the SOPHY system are as follows:SOFT provides four state-of-the-art optimization libraries namely, local and global optimization algorithms, Design of Experiment (DoE), Statistical Variational Analysis (ANOVA) and Response Surface Methodology (RSM). SOFT also provides an integrating platform to define the automation strategy, see Figure 1.PADRAM is a multi-passage, multi-stage parametric geometry modeller and rapid meshing system. The PADRAM design space for the blades consists of global parameters such as stagger angle, camber angles at leading and trailing edges, lean and sweep at different spanwise locations and pitch (rotor and stator). The PADRAM design space has recently been extended to include an endwall profiling and fillet design capability. PADRAM uses an automatic multiblock mesh generator to create the grid consisting of O-H-C topology. The mesh generation is very fast and does not require user interaction during the optimization. The parametric design system has been extended to non-blading applications, for example nacelle design and exhaust design systems (Lapworth and Shahpar 2004

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confidence: 99%

Large Scale Optimization of Transonic Axial Compressor Rotor Blades

Shahpar¹,

Polynkin²,

Toropov³

2008

49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference &Amp;lt;br> 16th AIAA/ASME/AHS Ada

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“…These are part of the Rolls-Royce in-house HYDRA suite of codes, which have been extensively validated and applied to various industrial cases (see for example [18,19]). More details regarding the underlying theory and implemented algorithm can be found in [3,20,21].…”

Section: Mathematical Backgroundmentioning

confidence: 99%

Linking Parametric Cad With Adjoint Surface Sensitivities

Vasilopoulos

Agarwal²,

Meyer

et al. 2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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Abstract. The goal of this work is to present an efficient CAD-based adjoint process chain for calculating parametric sensitivities (derivatives of the objective function with respect to the CAD parameters) in timescales acceptable for industrial design processes. The idea is based on linking parametric design velocities (geometric sensitivities computed from the CAD model) with adjoint surface sensitivities. A CAD-based design velocity computation method has been implemented based on distances between discrete representations of perturbed geometries. This approach differs from other methods due to the fact that it works with existing commercial CAD packages (unlike most analytical approaches) and it can cope with the changes in CAD model topology and face labeling. Use of the proposed method allows computation of parametric sensitivities using adjoint data at a computational cost which scales with the number of objective functions being considered, while it is essentially independent of the number of design variables. The gradient computation is demonstrated on test cases for a Nozzle Guide Vane (NGV) model and a Turbine Rotor Blade model. The results are validated against finite difference values and good agreement is shown. This gradient information can be passed to an optimization algorithm, which will use it to update the CAD model parameters.

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“…A structured multi-block grid topology is automatically generated using Rolls-Royce's code, PADRAM (Shahpar & Lapworth 2003). A front view of the 25/Un/Un/Un% tip grid and a meridional view of the 25% tip is presented in Figure 4a) and b) respectively.…”

Section: Computational Setupmentioning

confidence: 99%

Rotational Speed of a Damaged Fan Operating at Windmill

Mohankumar

Wilson

2017

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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Following an engine shut-down event due to the loss of a fan blade, the fan rotates in an unbalanced windmill condition leading to undesirable structural excitation. The flow through a fan stage containing idealised damaged rotors is investigated numerically at the windmill condition. Specifically, predictions of rotational speed and flow are presented, which agree with undamaged engine scale test data, and the governing rotor flow features are understood. Results of an undamaged rotor show the tip and hub sections operate as a turbine and compressor respectively, with small flow deviation from the geometric exit angle. Introducing axisymmetric tip damage acts to remove blade sections that induce high positive whirl thereby reducing turbine work extraction, and in turn rotational speed. Non-axisymmetric tip damage is then considered to understand the impact of rotor-to-rotor flow interaction, between blades of different damage levels, upon the rotational speed. In all instances the non-axisymmetric rotational speed is higher than the average of the component axisymmetric speeds.

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PADRAM: Parametric Design and Rapid Meshing System for Turbomachinery Optimisation

Cited by 112 publications

References 14 publications

Large Scale Optimization of Transonic Axial Compressor Rotor Blades

Large Scale Optimization of Transonic Axial Compressor Rotor Blades

Linking Parametric Cad With Adjoint Surface Sensitivities

Rotational Speed of a Damaged Fan Operating at Windmill

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