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A Boundary Layer Forced Transition Method for Low Pressure Turbine Based on Macroscopic Pore Structure

A pore structure, low pressure turbine technology, which is applied to the supporting elements of blades, machines/engines, mechanical equipment, etc., can solve problems such as shortening the service life of the engine, failure of composite materials, and decline in the mechanical properties of the hole edge, so as to reduce aerodynamic losses. , The effect of good fatigue resistance and strong structural designability

Active Publication Date: 2022-04-08
XIAMEN UNIV
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Problems solved by technology

At present, for the manufacture of low-pressure turbine blades with composite materials, by considering the transition mechanism under the condition of low Reynolds number, a related forced transition device design method has been established. This method only considers the preparation of composite material preforms, and the pores formed by it The main problem of this design method is the decrease in the mechanical properties of the hole edge, which may cause the failure of the composite material and shorten the service life of the engine

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  • A Boundary Layer Forced Transition Method for Low Pressure Turbine Based on Macroscopic Pore Structure
  • A Boundary Layer Forced Transition Method for Low Pressure Turbine Based on Macroscopic Pore Structure
  • A Boundary Layer Forced Transition Method for Low Pressure Turbine Based on Macroscopic Pore Structure

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[0030] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer and clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0031] see Figure 1-8 , the low-pressure turbine boundary layer transition method in advance based on the macroscopic pore structure described in this embodiment, the steps include:

[0032] 1) Selection of prefabricated body parameters

[0033] The braiding angle of the braided prefabricated body is 25°-45°, the average fiber diameter is 9-15 μm, and the fiber volume fraction is 30%-45%. Superalloy materials require cooling system limitations, and thermal expansion coefficient matching can be considered for corresponding size adjustments. Considering comprehensively, the length of the airfoil of the low-pressure turbine blade 2 is designed to increase by 0.3% to 0.6% compared with the airfoil of the...

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Abstract

A method of forced transition of low-pressure turbine boundary layer based on macroscopic pore structure, 1) Selection of prefabricated body parameters: the prefabricated body adopts an integral design, and the blade body length of the designed low-pressure turbine blade is compared to that of the low-pressure turbine blade made of superalloy. 2) The design of the spatial distribution of the pore structure, the pore structure is arranged on the entire blade surface; 3) The selection of the pore structure parameters: the porosity is 0.5% to 2%, and the pore diameter is 0.1 to 2mm. The distance between adjacent pores is 0.1-2 mm, and the pore depth is 0.1-2 mm; 4) Two-step method to weave the prefabricated body and form a pore structure. By designing a reasonable pore structure, the early transition of the boundary layer of the low-pressure turbine is realized, and the effect of improving the engine performance is achieved.

Description

technical field [0001] The invention relates to the field of low-pressure turbines, in particular to a method for forced transition of a boundary layer of a low-pressure turbine based on a macroscopic pore structure. Background technique [0002] Aeroengine is an important component of the aircraft, known as the "heart" of the aircraft, its performance directly affects or even determines the overall performance of the aircraft. The low-pressure turbine is one of the core components of an aero-engine. It is usually used to drive the fan and booster stage. Its aerodynamic efficiency directly affects the overall performance of the engine. Due to the relative rotation between the blade rows, the flow on the surface of the blades inside the low-pressure turbine is in a very complex environment, which has both its own unsteady effects and disturbances such as upstream wakes and incoming flow turbulence. In practical applications, the size of the engine of some aircraft is small, ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/14F01D5/28
CPCF01D5/145F01D5/147F01D5/282
Inventor 朱剑锋张扬闻尤延铖
Owner XIAMEN UNIV
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