Computer Program for Aerodynamic and Blading Design of Multistage Axial-Flow Compressors.

Crouse, J. E.; Gorrell, W. T.

doi:10.21236/ada109888

Cited by 19 publications

(11 citation statements)

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“…This program has been extracted from the NASA Design p rogran: which is a streamline curvature design procedure (8). Blade section nomenclature is presented in Fig.…”

Section: Analysis Methodsmentioning

confidence: 99%

The Use of Optimization Techniques to Design-Controlled Diffusion Compressor Blading

Sanger

1983

Journal of Engineering for Power

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A method is presented for automating compressor blade design using numerical optimization and is applied to the design of a controlled diffusion stator blade row. A general purpose optimization procedure is employed, which is based on conjugate directions for locally unconstrained problems and on feasible directions for locally constrained problems. Coupled to the optimizer is an analysis package consisting of three analysis programs which calculate blade geometry, inviscid flow, and blade surface boundary layers. The optimization concepts are briefly discussed. Selection of design of a two-dimensional blade section is discussed, and design results are presented.

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“…This program has been extracted from the NASA Design p rogran: which is a streamline curvature design procedure (8). Blade section nomenclature is presented in Fig.…”

Section: Analysis Methodsmentioning

confidence: 99%

The Use of Optimization Techniques to Design-Controlled Diffusion Compressor Blading

Sanger

1983

Journal of Engineering for Power

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“…Experienced blade designers use specialized skills to determine optimal blade geometries. Blade designers represent the blade geometry as a grid of points on the surface of the blade (Figure 1) or with non-standard algebraic equations (Crouse, 1981). In order to manufacture the blade using contemporary computer-aided manufacturing technology it must be represented in a portable format.…”

Section: Motivationmentioning

confidence: 99%

“…Axial blade design typically begins with two-dimensional stream line curvature through-flow algorithms that aid in determining the blade cross-section geometry from aerodynamic requirements (Law and Puterbaugh, 1982;Crouse, 1981). Input to these programs includes overall aerodynamic performance and basic blade section information.…”

Section: Motivationmentioning

confidence: 99%

BladeCAD: An Interactive Geometric Design Tool for Turbomachinery Blades

Miller

Oliver

Miller

et al. 1996

Volume 1: Turbomachinery

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A new methodology for interactive design of turbomachinery blades is presented. Software implementation of the methods provides a user interface that is intuitive to aero-designers while operating with standardized geometric forms. The primary contribution is that blade sections may be defined with respect to general surfaces of revolution which may be defined to represent the path of fluid flow through the turbomachine. The completed blade design is represented as a non-uniform rational B-spline (NURBS) surface and is written to a standard IGES file which is portable to most design, analysis, and manufacturing applications.

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“…The main-frame version of the code was documented in NASA TP-1946(Crouse & Gorrell, 1981). An improved PC-version, available from and supported by James E. Crouse, was used in this design.…”

Section: Streamline-curvaturementioning

confidence: 99%

Design of a Low Aspect Ratio Transonic Compressor Stage Using CFD Techniques

Sanger

1996

Journal of Turbomachinery

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A transonic compressor stage has been designed for the Naval Postgraduate School Turbopropulsion Laboratory. The design relied heavily on CFD techniques while minimizing conventional empirical design methods. The low aspect ratio (1.2) rotor has been designed for a specific head ratio of 0.25 and a tip relative inlet Mach number of 1.3. Overall stage pressure ratio is 1.56. The rotor was designed using an Euler code augmented by a distributed body force model to account for viscous effects. This provided a relatively quick-running design tool, and was used for both rotor and stator calculations. The initial stator sections were sized using a compressible, cascade panel code. In addition to being used as a case study for teaching purposes, the compressor stage will be used as a research stage. Detailed measurements, including nonintrusive LDV, will be compared with the design computations, and with the results of other CFD codes, as a means of assessing and improving the computational codes as design tools.

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Computer Program for Aerodynamic and Blading Design of Multistage Axial-Flow Compressors.

Cited by 19 publications

References 0 publications

The Use of Optimization Techniques to Design-Controlled Diffusion Compressor Blading

The Use of Optimization Techniques to Design-Controlled Diffusion Compressor Blading

BladeCAD: An Interactive Geometric Design Tool for Turbomachinery Blades

Design of a Low Aspect Ratio Transonic Compressor Stage Using CFD Techniques

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