End wall molded line modeling method for intermediate case of gas compressor

Abstract

The invention provides an end wall molded line modeling method for an intermediate case of a gas compressor. Fitting and adjusting of a hub and a molded line of the intermediate case of the gas compressor are completed through the Nom-Uniform Rational B-Spline curve and perpendicularity equal-division point moving method, the problem that a general method does not exist in the existing geometric design field of the intermediate case is solved, and complicated geometric molded lines such as the intermediate case with the large curvature change characteristic can be described mathematically and accurately. Meanwhile, the number of a plurality of free parameters needed in a traditional experience method is decreased to two, and therefore two-dimensional parameterized modeling is faster, simpler, more efficient and higher in generality, and good aerodynamic design indexes can be met.

Description

technical field [0001] The invention relates to a method for designing an intermediary casing of a compressor, in particular to a molding method for an end wall of an intermediary casing of a compressor. Background technique [0002] As the stator part connecting the high-pressure compressor and the low-pressure compressor of the turbofan engine, the intermediary casing of the compressor has a very important transitional role: on the one hand, it must rectify the airflow compressed by the upstream low-pressure compressor, and reduce its circumferential direction as much as possible. Inhomogeneity and circumferential and radial pressure gradients; on the other hand, two severe airflow deflections in the S-shaped flow channel must be completed to provide the best possible inlet conditions for the downstream high-pressure compressor stage. The current research on the intermediary casing of the compressor mainly focuses on the internal flow field analysis, aerodynamic performanc...

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Problems solved by technology

[0003] Literature [1] (Que Xiaobin, Hou Anping, Zhou Sheng. Axisymmetric Equivalent Method for Transition Section of Axial Flow Compression System with Support Plate, Acta Aeronautica Sinica, 2010, Vol31, No.9.) Expressed as a quartic polynomial curve, the fitting effect on the concave and convex curvature transition areas of the geometric profile is not ideal (almost linear distribution), and the hub and casing profiles have as many as 10 free control variables respectively. Calculate and solve inconvenient

Literature [2] (Wallin F, Arroyo Osso, C., Johansson, T.G. Experimental and Numerical Investigation of an Aggressive Intermediate Turbine Duct: Part1—Flowfield at Design Inlet Conditions. AIAA paper AIAA-2008-7055, 2008.) try to The intermediary casing parameterization method of arc plus height distribution uses the combination of polynomial basis function and weight to regulate the geometric shape line, but the given basis function depends too much on the experience of the designer, and the implementation method is also relatively Complicated and limited in scope

Therefore, the current field of intermediary casing research lacks a simple (simple mathematical principle), high-efficiency (few free control variables), and strong versatility (the modeling method is suitable for most complex large-curvature geometric lines) end wall molding method

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