Fiber winding prestress turbine rotor

A turbine rotor and prestressing technology, which is applied to the support components of blades, climate sustainability, engine components, etc., can solve the problems of steel wire strength decline and the inability to meet the high temperature working environment of turbine rotors, so as to reduce working stress and improve fatigue Effect of lifetime or operating temperature

Active Publication Date: 2014-04-02
TSINGHUA UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At the same time, the strength of the steel wire will drop sharply at high temperature, which cannot meet the high temperature working environment of the turbine rotor.

Method used

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  • Fiber winding prestress turbine rotor
  • Fiber winding prestress turbine rotor
  • Fiber winding prestress turbine rotor

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] The specific structure of a prestressed fiber wound turbine rotor of the present invention is as follows: figure 1 , figure 2 with image 3 shown. The turbine rotor consists of a turbine disc 1 and a set of blades 2, which are assembled with a light-weight high-temperature-resistant material (such as titanium-aluminum intermetallic compound or carbon / carbon composite material) outside the blade shroud 7 with a gap of 0.001mm to 0.01mm. The ring groove 3 is made, and the high-temperature high-strength fiber is wound in the ring groove 3 layer by layer with a tensile stress of 0-10.0GPa; when the preset number of turns and layers are wound, the prestressed fiber winding layer 5 The thickness can reach 0.5mm ~ 100mm. After the preset prestress is generated on the turbine disk 1 and blade 2, the winding layer is covered with a sealing cover plate 4, and a closed structure is formed by connecting the seam 6 and the ring groove 3 to isolate the prestress. The stress windi...

Embodiment 2

[0039] The specific structure of a prestressed fiber wound turbine rotor of the present invention is as follows: Figure 4 with Figure 5 shown. The turbine rotor is composed of a turbine disk 1 and a set of blades 2. The winding groove 8 is directly processed on the blade crown 7 of the blade, and the high-temperature and high-strength fibers are wound on the winding groove layer by layer with a tensile stress of 0-10.0GPa. 8; when the preset number of turns and layers are wound, the thickness of the prestressed fiber winding layer 5 can reach 0.5 mm to 100 mm. After the preset prestress is generated on the turbine disk 1 and blade 2, seal the The plate 4 covers the wrapping layer and forms a closed structure through the connection of the seam 6 and the wrapping groove 8 to isolate the prestressed wrapping layer 5 from contact with the external airflow.

Embodiment 3

[0041] The specific structure of a prestressed fiber wound turbine rotor of the present invention is as follows: Image 6 with Figure 7 shown. The turbine rotor is composed of a turbine disk 1 and a set of blades 2. The winding groove 8 processed on the blade crown 7 of the blade is made of fibers (silicon carbide fibers) with strong high-temperature oxidation resistance or reliable oxidation resistance on the surface. Coated (such as carbon fiber surface prepared with silicon carbide coating or aluminum oxide coating) fibers are wound in the winding groove 8 layer by layer with a tensile stress of 0-10.0 GPa. After the preset number of turns and layers are wound, the thickness of the prestressed fiber winding layer 5 can reach 0.5 mm to 100 mm, and a preset prestress is generated on the turbine disk 1 and the blade 2 .

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PUM

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Abstract

Disclosed is a turbine rotor device for a gas turbine, the turbine rotor device comprising a turbine rotor body (1), and a pre-stressed fiber-wound layer (2), wherein the pre-stressed fiber-wound layer (2) is wound on the periphery of the turbine rotor body (1) to exert a predetermined pre-loading force on the turbine rotor body (1). Additionally, a rotor, and a gas turbine and a turbine engine having the turbine rotor device are also provided.

Description

technical field [0001] The invention relates to a turbine rotor of a gas turbine, in particular to a prestressed wound turbine rotor of a gas turbine. Background technique [0002] Turbine rotors are the key working parts of aerospace engines and gas turbines. Under the harsh working conditions of high temperature and high speed, it is required to work stably for a long time. Centrifugal force generated by high speed, thermal stress, aerodynamic force of gas or steam, vibration load and other complex loads act comprehensively on the turbine disk and blades of the turbine rotor, forming a stress state dominated by tensile stress. As a result, turbine materials must have high strength and excellent fatigue resistance at high temperatures. Once the blades or turbine discs of the turbine rotor fail and fail, the centrifugal force of high-speed rotation causes the debris to fly out at high speed, causing serious damage to other parts of the engine. [0003] In order to improve...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/02F01D5/28
CPCF01D5/282F01D5/225F05D2300/603F01D5/288Y02T50/672Y02T50/673F01D5/34Y02T50/60F01D5/03
Inventor 林峰张人佶巩前明张磊张婷袁宵闫文涛
Owner TSINGHUA UNIV
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