{"id":5396,"date":"2025-03-07T17:02:54","date_gmt":"2025-03-07T09:02:54","guid":{"rendered":"https:\/\/turbineblade.net\/?p=5396"},"modified":"2025-04-25T13:15:02","modified_gmt":"2025-04-25T05:15:02","slug":"crack-analysis-method-for-integral-blade-ring-of-aeroengine","status":"publish","type":"post","link":"https:\/\/turbineblade.net\/ar\/crack-analysis-method-for-integral-blade-ring-of-aeroengine\/","title":{"rendered":"Crack analysis method for integral blade ring of aeroengine"},"content":{"rendered":"

With the continuous improvement of aircraft engine performance, high thrust-to-weight ratio has become an important indicator of advanced aircraft engine performance. Therefore, the development of advanced high structural efficiency and high-performance materials with lightweight overall structure has become the main development trend. The integral blade ring structure using continuous fiber reinforced titanium-based <\/a>composite materials has significant advantages in weight reduction and can also withstand circumferential loads. It is the development direction of advanced aircraft engine materials. At present, the integral blade ring <\/a>is mostly made of continuous single silicon carbide long fiber reinforced titanium-based composite materials, which has the advantages of high strength, high operating temperature and good fatigue and creep properties. Its manufacturing process generally forges ordinary titanium alloy into a blank, then processes it into a blade, and at the same time processes a ring groove on the inside of the blade ring, loads the composite material, and covers the plug-in with ordinary titanium alloy, and then performs hot isostatic pressing, and finally makes it composite into one.<\/p>

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This study mainly conducts vibration fatigue life assessment tests on integral blade rings with two different manufacturing processes: forging heat treatment (FHT) + hot isostatic pressing (HIP) and FHT. Among them, the integral blade ring blade in the FHT+HIP process state is blade I, and the integral blade ring blade in the FHT process state is blade II. The test blade matrix material is TC17 titanium alloy, and the test target for the number of cycles is 3\u00d7107. The relevant information of the test piece is shown in Table 1. When blade I cycles to 1.8\u00d7107 times, cracks appear near the tip of the blade, and the test is terminated; blade II passes the test assessment. This study analyzes the crack properties and initiation causes of blade I through macroscopic inspection, fracture macro-micro analysis, material analysis, mechanical properties test, and finite element stress simulation to determine the failure cause and failure mode of the blade.<\/p>

Experimental process and results<\/strong><\/h2>

Macroscopic inspection<\/strong><\/h2>

The fluorescence detection results of the crack of blade I are shown in Figure 1. There is a crack fluorescence near the tip of the blade, and the crack has penetrated the thickness of the blade. The crack is about 33 mm away from the air inlet edge of the blade.<\/p>

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