Aero-engine turbine air-cooled blade strength evaluation method

The invention belongs to the technical field of aero-engine turbine air-cooled blade strength evaluation, and particularly relates to an aero-engine turbine air-cooled blade strength evaluation method which comprises the steps that a typical section of a turbine air-cooled blade is extracted; import...

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Bibliographic Details
Main Authors YI FENG, LIU YIXIONG, WU YUNWU, ZHANG CUIHUA, SU SHOULI
Format Patent
LanguageChinese
English
Published 11.11.2022
Subjects
CALCULATING
COMPUTING
COUNTING
ELECTRIC DIGITAL DATA PROCESSING
PHYSICS
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Summary:The invention belongs to the technical field of aero-engine turbine air-cooled blade strength evaluation, and particularly relates to an aero-engine turbine air-cooled blade strength evaluation method which comprises the steps that a typical section of a turbine air-cooled blade is extracted; importing the geometric model of the typical section of the turbine air-cooled blade into finite element software, defining a unit type as a generalized plane unit, and performing grid division to obtain a generalized plane strain analysis model of the turbine air-cooled blade; and in the generalized plane strain analysis model of the turbine air-cooled blade, adding a centrifugal load, an aerodynamic load and a temperature load suffered by the typical section of the turbine air-cooled blade to obtain stress distribution on the typical section of the turbine air-cooled blade, and evaluating the strength of the turbine air-cooled blade of the aero-engine. 本申请属于航空发动机涡轮气冷叶片强度评估技术领域，具体涉及一种航空发动机涡轮气冷叶片强度评估方法，包括：提取涡轮气冷叶片典型截面；将涡
Bibliography:Application Number: CN202210976226