Inverse Design and Active Control Concepts in Strong Unsteady Heat Conduction

1988 ◽  
Vol 41 (6) ◽  
pp. 270-277 ◽  
Author(s):  
George S. Dulikravich
Keyword(s):  
Thermal Conditions ◽  
Coolant Flow ◽  
Geometric Constraints ◽  
Inverse Design ◽  
Optimal Time ◽  
Design And Optimization ◽  
Design Engineers ◽  
Thermal Boundary Conditions ◽  
Internally Cooled ◽  
Unsteady Heat Conduction

A summary of recent research in the field of inverse design and optimization of coolant flow passages in the internally cooled configurations is presented. The methodology allows design engineers to prescribe desired surface temperature and heat flux distributions and to fix portions of the multiply connected realistically shaped configurations. The shapes of the resulting coolant flow passages can be arbitrarily or circularly shaped with a capability to maintain certain manufacturing geometric constraints. Unsteady cooling of organs and tissues in bioengineering is demonstrated by determining optimal time variation of thermal boundary conditions on the walls of the cooling container while maintaining the geometry and size of the configuration. Another concept suggests that components subjected to strong unsteady cooling or heating can be optimized for the desired time dependent overspecified surface thermal conditions by determining the corresponding instantaneous temperatures of the coolant flow passages. This effect can be achieved by applying optimal control of distributed coolant flow rates in each flow passage.

The Inverse Design of Internally Cooled Turbine Blades

1985 ◽  
Vol 107 (1) ◽  
pp. 123-126 ◽  
Author(s):  
S. R. Kennon ◽  
G. S. Dulikravich
Keyword(s):  
Heat Flux ◽  
Cross Section ◽  
Turbine Blades ◽  
Design Procedure ◽  
Coolant Flow ◽  
Surface Shape ◽  
Inverse Design ◽  
Flow Passage ◽  
Hollow Blade ◽  
Internally Cooled

A methodology is developed for the inverse design and/or analysis of interior coolant flow passage shapes in internally cooled configurations with particular applications to turbine cascade blade design. The user of this technique may specify the temperature (or heat flux) distribution along the blade outer fixed surface shape and the unknown interior coolant/blade interface. The numerical solution of the outer gas flow field determines the remaining unspecified blade outer surface quantity—surface heat flux if temperature was originally specified or vice versa. Along the unknown coolant flow passage shape the designer has the freedom to specify the desired temperature distribution. The hollow blade wall thickness distribution is then found from the solution of Laplace’s equation governing the temperature field within the solid portion of the hollow blade, while satisfying both boundary conditions of temperature and heat flux at the fixed outer blade surface, and the specified temperature boundary condition on the evolving inner surface. A first order panel method, coupled with Newton’s N-dimensional interation scheme, is used for the iterative solution of the unknown coolant/blade interface shape. Results are shown for a simple eccentrical bore pipe cross section and a realistic turbine blade cross section. The inverse design procedure is shown to be efficient and stable for all configurations that have been tested.

Inverse Design and Optimization of a Return Channel for a Multistage Centrifugal Compressor

2004 ◽  
Vol 126 (5) ◽  
pp. 799-806 ◽  
Author(s):  
A´rpa´d Veress ◽  
Rene´ Van den Braembussche
Keyword(s):  
Design Method ◽  
Design Procedure ◽  
Leading Edge ◽  
Secondary Flows ◽  
Inverse Design ◽  
Navier Stokes ◽  
Design And Optimization ◽  
The Cross ◽  
Return Channel ◽  
The Impact

The design and optimization of a multistage radial compressor vaneless diffuser, cross-over and return channel is presented. An analytical design procedure for 3D blades with prescribed load distribution is first described and illustrated by the design of a 3D return channel vane with leading edge upstream of the cross-over. The analysis by means of a 3D Navier–Stokes solver shows a substantial improvement of the return channel performance in comparison with a classical 2D channel. Most of the flow separation inside and downstream of the cross-over could be avoided in this new design. The geometry is further improved by means of a 3D inverse design method to smooth the Mach number distribution along the vanes at hub and shroud. The Navier–Stokes analysis shows a rather modest impact on performance but the calculated velocity distribution indicates a more uniform flow and hence a larger operating range can be expected. The impact of vane lean on secondary flows is investigated and further performance improvements have been obtained with negative lean.

On the Coupling of Inverse Design and Optimization Techniques for Turbomachinery Blade Design

2006 ◽  
Author(s):  
Duccio Bonaiuti ◽  
Mehrdad Zangeneh
Keyword(s):  
Mechanical Design ◽  
Design Method ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Optimization Techniques ◽  
Operating Conditions ◽  
Inverse Design ◽  
Design Parameters ◽  
Optimization Strategy ◽  
Design And Optimization

Optimization strategies have been used in recent years for the aerodynamic and mechanical design of turbomachine components. One crucial aspect in the use of such methodologies is the choice of the geometrical parameterization, which determines the complexity of the objective function to be optimized. In the present paper, an optimization strategy for the aerodynamic design of turbomachines is presented, where the blade parameterization is based on the use of a three-dimensional inverse design method. The blade geometry is described by means of aerodynamic parameters, like the blade loading, which are closely related to the aerodynamic performance to be optimized, thus leading to a simple shape of the optimization function. On the basis of this consideration, it is possible to use simple approximation functions for describing the correlations between the input design parameters and the performance ones. The Response Surface Methodology coupled with the Design of Experiments (DOE) technique was used for this purpose. CFD analyses were run to evaluate the configurations required by the DOE to generate the database. Optimization algorithms were then applied to the approximated functions in order to determine the optimal configuration or the set of optimal ones (Pareto front). The method was applied for the aerodynamic redesign of two different turbomachine components: a centrifugal compressor stage and a single-stage axial compressor. In both cases, both design and off-design operating conditions were analyzed and optimized.

scholarly journals Optimization of Clearance Volume for Performance Improvement of Reciprocating Compressor

2019 ◽  
Vol 8 (10) ◽  
pp. 1688-1694
Keyword(s):  
Performance Improvement ◽  
Working Condition ◽  
Optimal Time ◽  
Reciprocating Compressor ◽  
Stroke Length ◽  
Design And Optimization ◽  
Multi Stage ◽  
Compressor Performance ◽  
Effective Part ◽  
Piston Stroke

The paper addresses to engineers who do design and optimization work in the field of reciprocating compressors. In this paper theoretical and exact contemplations are given which permit to foresee the valve misfortunes. Suction valve misfortunes are additionally bring about a decrease of limit. The most effective part in the development of a reciprocating compressor depends strongly on improvement of its performance. For this purpose, a performance characteristic evaluation of a two stroke reciprocating air compressor is carried out in this paper. By and large stream misfortunes of compressor valves are affected by the valve geometry as well as are intensified by valve pocket misfortunes. The aims were to improve compressor performance by illustrating the effects of various parameters such as clearance between head and piston, stroke length, friction losses, compressor running time, background working condition and air leakage. The effect of each parameter was compared with given performance condition and after it was demonstrated the most important parameter on the performance. The parameter was measured using three techniques. The experiment addressed some factors that led to the inefficient performance of the reciprocating compressor air system and cause energy losses. The results advocate the optimal time for starting time of starting each stage of the two–stage reciprocating compressor. The work in addition may give a insight for the development of the design of multi-stage compression and presents some key design parameter.

Inverse Design of Coolant Flow Passage Shapes With Partially Fixed Internal Geometries

1985 ◽  
Author(s):  
Stephen R. Kennon ◽  
George S. Dulikravich
Keyword(s):  
Heat Flux ◽  
Surface Temperature ◽  
Turbine Blade ◽  
Outer Boundary ◽  
Turbine Blades ◽  
Design Procedure ◽  
Coolant Flow ◽  
Inverse Design ◽  
Original Design ◽  
Flow Passage

A method is described for the inverse design of complex coolant flow passage shapes in internally cooled turbine blades. This method is a refinement and extension of a method developed by the authors for designing a single coolant hole in turbine blades. The new method allows the turbine designer to specify the number of holes the turbine blade is to have. In addition, the turbine designer may specify that certain portions of the interior coolant flow passage geometry are to remain fixed (eg. struts, surface coolant ejection channels, etc.). Like the original design method, the designer must specify the outer blade surface temperature and heat flux distribution and the desired interior coolant flow passage surface temperature distributions. This solution procedure involves satisfying the dual Dirichlet and Neumann specified boundary conditions of temperature and heat flux on the outer boundary of the airfoil while iteratively modifying the shapes of the coolant flow passages using a least squares optimization procedure that minimizes the error in satisfying the specified Dirichlet temperature boundary condition on the surface of each of the evolving interior holes. Portions of the inner geometry that are specified to be fixed are not modified. A first order panel method is used to solve Laplace’s equation for the steady heat conduction within the solid portions of the hollow blade, making the inverse design procedure very efficient and applicable to realistic geometries. Results are presented for a realistic turbine blade design problem.

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