Parameterized sizing method for turbine blade mould cavity

Abstract

The invention discloses a parameterized sizing method for a turbine blade mould cavity. The parameterized sizing method comprises the following steps of: measuring an existing turbine blade to obtain a measurement model; performing registering positioning and precise registering on a computer-aided design (CAD) model and the corresponding measurement model to obtain geometric characteristic parameters of two-dimensional sections of the measurement model and the CAD model on the same height and calculating deformation vectors of the two-dimensional sections; conversely adjusting the deformation vectors and representing a middle arc model of a blade shape by using a cubic polynomial curve; then restoring the mould cavity; and repeatedly establishing at least four blade shape sections of the mould cavity at any height and finally reconstructing an entity of the mould cavity. By the parameterized sizing method, the product yield of the turbine blades is increased greatly and the period and the frequency of mould trail are reduced; and the parameterized sizing method has the characteristics of short design period, high precision and high efficiency.

Description

technical field [0001] The invention relates to the technical field of mold cavity shaping, in particular to a parametric shaping method for an aeroengine turbine blade mold cavity. Background technique [0002] Turbine blades are the core technology of high thrust-to-weight ratio engines, the core components of turbomachinery, and also vulnerable to failure. Its performance level, especially its ability to withstand high temperatures, is an important symbol of the advanced level of a type of engine, and in a certain sense, it is also a significant symbol of the level of a country's aviation industry. Due to the long-term service under the conditions of strong thermal shock and complex cyclic thermal stress, the structural design and manufacturing technology of turbine blades have become the core technology of high thrust-to-weight ratio aeroengines. [0003] At present, turbine blades generally adopt directional crystallization or single crystal precision casting without m...

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Problems solved by technology

[0007] In order to overcome the deficiencies of the prior art, the present invention provides a method for designing the cavity of precision casting molds based on geometric characteristic parameters. The design results can be directly used to guide the design of the cavity of precision casting molds for turbine blades, and solve the problems of current similar mold designs. Problems of long cycle, low efficiency and low precision

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