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A Turbine Blade Vibration Fatigue Simulator and Its Design Method

A turbine blade and vibration fatigue technology is applied in the field of turbine blade vibration fatigue simulation parts and its design.

Active Publication Date: 2022-03-25
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Abstract
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Problems solved by technology

[0004] On the one hand, the present invention provides a turbine blade vibration fatigue simulation part to solve the technical problems of long evaluation period and high cost in the current turbine blade vibration fatigue test due to the use of full-scale designed turbine blades

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  • A Turbine Blade Vibration Fatigue Simulator and Its Design Method
  • A Turbine Blade Vibration Fatigue Simulator and Its Design Method
  • A Turbine Blade Vibration Fatigue Simulator and Its Design Method

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Embodiment Construction

[0042] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0043] like figure 1 and figure 2 As shown, a turbine blade vibration fatigue simulation, including:

[0044] Clamping section 1, used for fixing on the test bench during the test;

[0045] The airfoil section 2 is fixed on the clamping section 1 and has a symmetrical cross-sectional shape. The vibration stress ratio of the blade back root 6 and the leading edge root 7 in the root of the airfoil section 2 is the same as that of the designed turbine blade model. The vibration stress ratio of the blade basin / back dangerous point in the vibration modal analysis is equal, and the length L of the airfoil section 2 makes the first-order bending natural frequency of the turbine blade vibration fat...

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Abstract

The invention discloses a turbine blade vibration fatigue simulation part and a design method thereof. The turbine blade vibration fatigue simulation part comprises: a clamping section; an airfoil section fixed on the clamping section and having a symmetrical cross-sectional shape, The vibration stress ratio of the blade back root and the leading edge root in the root of the airfoil section is equal to the blade pot / back dangerous point vibration stress ratio of the designed turbine blade model in the vibration modal analysis, and the length L of the airfoil section is such that The first-order bending natural frequency of the turbine blade vibration fatigue simulation part is the same as the first-order bending natural frequency of the designed turbine blade model; the simulated blade root fillet is set at the connection between the root of the airfoil section and the clamping section, and the radius is the same as The root rounding radii of the designed turbine blade models are the same. The vibration fatigue simulation part of the turbine blade designed by the invention has a simple structure, no complex high-order curved surface, low manufacturing, processing and testing costs, quick acquisition of the vibration fatigue performance of the blade, short evaluation period and low cost.

Description

technical field [0001] The invention relates to the technical field of turbine blade detection, in particular to a turbine blade vibration fatigue simulation part and a design method thereof. Background technique [0002] At present, the research on the vibration fatigue performance of turbine blades is realized through the vibration fatigue tests of full-scale designed turbine blades. However, turbine blades require a long process from drawing design to mold manufacturing to blade casting, and the designed turbine blades are expensive, resulting in high test costs. In order to reduce the test cost, only a very limited number of tests can be carried out, which limits the vibration fatigue reliability evaluation of turbine blades. [0003] The existing technology needs to use full-scale designed turbine blades for testing, and full-scale turbine blades require a long process from design drawings to mold manufacturing to blade casting, and the manufacturing, processing and te...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M7/02G01N3/30
CPCG01M7/025G01N3/30G01N2203/0032G01N2203/0073
Inventor 蒋康河陈晓龙陈竞炜
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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