Development of an Automated Preliminary Combustion Chamber Design Tool

Pegemanyfar, Nima; Pfitzner, Michael; Eggels, Ruud; Bank, Ralf von der; Zedda, Marco

doi:10.1115/gt2006-90430

Cited by 8 publications

(11 citation statements)

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“…In order to account for emission changes, a parametric description of the combustor air distribution is required. The driving parameters for air distribution and thus emission performance are local air-fuel-ratios at injector afr 1 and primary zone exit afr 2 ,   (8) where ̇1 is the mass flow at the injector, ̇2 is the mass flow at the primary zone exit and ̇f uel is the fixed fuel mass flow. The parameter γ 1 defines the position of the primary mixing ports and thus the primary zone length l 1 =(γ 1 /γ cc )l cc whereas γ 2 defines the secondary mixing ports position and thus the secondary zone length l 2 =(γ 2 /γ cc )l cc , respectively, where l cc is the combustor length, see Eqs.…”

Section: B Air Distribution Parameterizationmentioning

confidence: 99%

Optimization of Air Distribution in a Preliminary Design Stage of an Aero-Engine Combustor

Angersbach

Bestle

2014

14th AIAA Aviation Technology, Integration, and Operations Conference

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The design of a modern aero-engine combustor is strongly driven by severe emission regulations. The paper describes an automated preliminary aero-thermal design process for a rich-burn combustor by combining different low fidelity analysis tools in order to speed up the preliminary design loop and provide improved combustor designs. Design evaluation is performed by a knowledge-based preliminary design tool coupled with a network solver. The preliminary design tool provides a 2D geometry model and cooling layout based on industrial in-house design rules. The 1D network solver then calculates the air distribution inside the combustor for two state-of-the-art combustor cooling schemes, i.e., single skin cooling and double skin tiled cooling. The computed air distribution is subsequently used to predict emissions which are minimized by using a genetic multi-objective optimization algorithm. As a result, better designs are obtained with the prescribed approach compared to a human reference design. Nomenclature, c i,j = flow/geometry specific constants λ = node mass source afr 1 = air-fuel-ratio of injector ρ = fluid density afr 2 = air-fuel-ratio at primary zone exit Indices c = port style • cc = combustor chamber cb = circumferential blockage factor • i,o = inner/inlet, outer/outlet f r = radial factor • m = middle d = diameter • p = port h, h = height, constraint vector • pp,sp = primary/secondary ports l = length • pz,sz = primary/secondary zones = mass flow • 3 = compressor exit n = number • 4 = turbine entry p = pressure • TO = take-off conditions p = parameter vector Abbreviations r = radius CFD = computationalsfluid dynamics s i,j = flow direction at node i,j NO x = nitrogen oxides v = velocity NSGA-II = non-dominated sorting V = volume genetic algorithm-II α = combustor cant angle SN = smoke number

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Section: B Air Distribution Parameterizationmentioning

confidence: 99%

Optimization of Air Distribution in a Preliminary Design Stage of an Aero-Engine Combustor

Angersbach

Bestle

2014

14th AIAA Aviation Technology, Integration, and Operations Conference

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“…The film cooling effectiveness as well as the heat transfer coefficient is calculated from different correlations depending on the cooling concept [6,24,25]. In the case of effusion or impingement-effusion cooling a superposition of the film cooling effectiveness of each cooling jet must be regarded due to the film overlaying [12].…”

Section: Heat Transfermentioning

confidence: 99%

“…A more detailed design process for conventional combustors is presented in [12,13]. A combustor design derived from spreadsheets and correlations is taken and linked with an automated tool chain consisting of CAD file and CFD mesh generation and CFD analysis.…”

Section: Introductionmentioning

confidence: 99%

Development and application of a pre-design tool for aero-engine combustors

Tietz

Behrendt

2011

CEAS Aeronaut J

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A software tool was developed to design aeroengine combustors on a preliminary level. Only a small set of input parameters is required to design conventional as well as lean combustors. During the design calculation the combustor contour, the geometry of the desired cooling concept and the air flow distribution within the combustor are optimized. Optimization targets are to minimize the cooling air consumption with respect to the material temperature limits and to reach homogeneous material temperatures as well as a stable combustion. In the case of a staged burner the burner air and fuel fractions are optimized regarding minimal NO x production (qualitative) for the design condition. Off-design calculations on the basis of designed combustors can be executed for engine conditions other than take-off to calculate the altered conditions within the combustor. This paper shows the design and off-design process of the combustor tool in detail. In a second part application examples are given. The presented results show the capabilities of the tool for the pre-design of lean combustors with respect to the trade-off between the reduction of NO x emissions and the reduction of the fuel consumption as well as the capabilities for identifying potential cooling issues.

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“…Meanwhile, the UG system provides powerful secondary tools of UG/OPEN API, Menu Script and UIStyler development to customize user interface and application programs as needed. Pegemanyfar [2] presented a design tool, which was for the combustion chamber preliminary design, driven by the EXCEL database and generated by the UG software. LIU et al [3] developed an automated…”

Section: Introductionmentioning

confidence: 99%

A General Integrated Method for Design Analysis and Optimization of Missile Structure

Wang

Yang²,

Guo

et al. 2019

Algorithms

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In the demonstration phase of a missile scheme, to obtain the optimum proposal, designers need to modify the parameters of the overall structure frequently and significantly, and perform the structural analysis repeatedly. In order to reduce the manual workload and improve the efficiency of research and development, a general integrated method of missile structure modeling, analysis and optimization was proposed. First, CST (Class and Shape transformation functions) parametric method was used to describe the general structure of the missile. The corresponding software geometric modeling and FEM (Finite Element Method) analyzing of the missile were developed in C/C++ language on the basis of the CST parametric method and UG (Unigraphics) secondary development technology. Subsequently, a novel surrogate model-based optimation strategy was proposed to obtain a relatively light mass missile structure under existing shape size. Eventually, different missile models were used to verify the validity of the method. After executing the structure modeling, analysis and optimization modules, satisfactory results can be obtained that demonstrated the stability and adaptability of the proposed method. The method presented saves plenty of time comparing to the traditional manual modeling and analysis method, which provides a valuable technique to improve the efficiency of research and development.3D modeling program based on the UG secondary development technology, which has improved the modeling efficiency. Wang et al. [4] used the technology of UG/KF secondary development for the automatic modeling of the wind turbine blades, and the aerodynamic characteristics of the impeller were analyzed by the Fluent software. Moreover, He et al. [5] implemented the parametric modeling of the blended-wing-body underwater glider structure by using UG secondary development technology and studied its structural performance with ANSYS. Therefore, UG is considered as an excellent tool that can realize the integration of modeling and simulation.Meanwhile, airfoils have been parameterized in a wide variety of ways. Among them, CST is considered to be a more effective method, which can represent the different types of geometries in a generic way with fewer parameters. Kulfan and Bussoletti [6] proposed a parameterization method that based on class and shape transformation functions, which has the advantages of high precision and fewer variables. The CST method is a powerful and versatile means to describe complex aeronautical shapes ranging from 2D airfoils to 3D geometries of aircraft using analytical functions. Since it has been introduced, this parameterization method has been the subject of several studies [7]. Marco Ceze of the University of Michigan studied the characteristics of CST parameterization and found that the ill-conditioning of parameterization when fitting airfoil with high-order Bernstein polynomials [8]. Straathof et al. proposed a parameterization method that used a combination of Bernstein polynomials and B-splines to allow...

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Development of an Automated Preliminary Combustion Chamber Design Tool

Cited by 8 publications

References 0 publications

Optimization of Air Distribution in a Preliminary Design Stage of an Aero-Engine Combustor

Optimization of Air Distribution in a Preliminary Design Stage of an Aero-Engine Combustor

Development and application of a pre-design tool for aero-engine combustors

A General Integrated Method for Design Analysis and Optimization of Missile Structure

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