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Centrifugal impeller and turbine blade profile cold and hot state rapid conversion method

A technology of turbine blades and impellers is applied in the field of rapid conversion of cold and hot states of centrifugal impellers and turbine blades, which can solve the problems of large amount of calculation, long time consumption, and difficulty in ensuring the accuracy of centrifugal impellers and centripetal turbine blades. Conversion accuracy, solving the effect of large amount of calculation

Inactive Publication Date: 2022-05-06
泸州懋威科技有限公司
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Problems solved by technology

[0004] Although these two methods can obtain high-precision cold-state models, the first conversion method can basically guarantee the accuracy of axial flow blades, but it is difficult to guarantee the accuracy of centrifugal impellers and centripetal turbine blades; although the second method has high accuracy However, the amount of calculation is large and time-consuming, and it is difficult to meet the needs of rapid conversion in engineering practice

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  • Centrifugal impeller and turbine blade profile cold and hot state rapid conversion method
  • Centrifugal impeller and turbine blade profile cold and hot state rapid conversion method
  • Centrifugal impeller and turbine blade profile cold and hot state rapid conversion method

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[0020] The specific embodiments of the present invention are described below so that those skilled in the art can understand the present invention, but it should be clear that the present invention is not limited to the scope of the specific embodiments. For those of ordinary skill in the art, as long as various changes Within the spirit and scope of the present invention defined and determined by the appended claims, these changes are obvious, and all inventions and creations using the concept of the present invention are included in the protection list.

[0021] Such as Figure 1 ~ Figure 3 As shown, the present invention provides a method for quickly changing the hot and cold state of the compressor impeller or turbine blade. Considering the aerodynamic load, temperature field and centrifugal load, the deformation of the control points of each modeling section is obtained by calculating the deformation of the arc in each modeling section and linear interpolation. This not ...

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Abstract

The invention discloses a centrifugal impeller and turbine blade profile cold and hot state rapid conversion method, which mainly aims at the problem of large deformation calculation amount of control points of each modeling cross section of a blade profile in an iteration process, comprehensively considers aerodynamic load, temperature field and centrifugal load, and calculates the cold and hot state of the blade profile by calculating the deformation of a mean camber line of each modeling cross section. And carrying out linear interpolation to obtain deformation of each modeling section control point. Therefore, the conversion precision is ensured, and the problem of large calculation amount of a deformation output point can be solved.

Description

technical field [0001] The invention relates to the technical field of design of a centrifugal impeller and a turbine blade, in particular to a method for quickly changing the cold and hot states of a centrifugal impeller and a turbine blade. Background technique [0002] After the aerodynamic design of the centrifugal impeller compressor or turbine of the engine is completed, the given flow passage and airfoil are the hot state dimensions of the design point, and the parts processed according to the design model should be cold state models. If processed directly according to the thermal model, the centrifugal impeller compressor or the turbine rotor will be deformed in the working state, especially the turbine rotor will be significantly deformed under aerodynamic load, high temperature and centrifugal load, and these deformations will affect the aerodynamic performance of the component , performance that deviates from the design point. [0003] Existing conventional metho...

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Application Information

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IPC IPC(8): G06F30/23G06F30/17
CPCG06F30/23G06F30/17Y02T90/00
Inventor 邹果
Owner 泸州懋威科技有限公司
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