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Turbine guider blade adopting efficient cooling structure

A turbine guider and cooling structure technology, which is applied in the direction of blade support elements, machines/engines, stators, etc., can solve the problems of not being able to meet the use requirements of the engine and short durability, and achieve the effect of meeting the use requirements and improving the service life

Pending Publication Date: 2020-11-13
中国航发贵阳发动机设计研究所
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] Purpose of the invention: To propose a turbine guide vane with a high-efficiency cooling structure to solve the problem that the high-pressure turbine guide blade of the existing aviation gas turbofan engine has a short service life and cannot meet the needs of the engine.

Method used

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  • Turbine guider blade adopting efficient cooling structure
  • Turbine guider blade adopting efficient cooling structure
  • Turbine guider blade adopting efficient cooling structure

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Embodiment Construction

[0026] Referring to the accompanying drawings, through the description of the embodiments, the specific implementation of the present invention, such as the shape, structure, mutual position and connection relationship between the various parts, the function and working principle of each part, and the manufacturing process And the method of operation and use, etc., are described in further detail to help those skilled in the art have a more complete, accurate and in-depth understanding of the concept and technical solutions of the present invention.

[0027] Such as figure 1 As shown, a turbine guide blade adopting a high-efficiency cooling structure includes a blade body 3, an upper edge plate 1, a lower edge plate 2, and a guide vane 4. The upper edge plate 1 and the lower edge plate 2 are arranged on the blade body 3 sides, such as figure 2 , 3 As shown, the inside of the blade body 3 is provided with a front chamber 5, a middle chamber one 6, a middle chamber two 7, and...

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Abstract

The invention discloses a turbine guider blade adopting an efficient cooling structure. The turbine guider blade adopting the efficient cooling structure comprises a blade body, an upper edge plate, alower edge plate and flow deflectors, the upper edge plate and the lower edge plate are arranged on the two sides of the blade body, and a front cavity, a first middle cavity, a second middle cavityand a rear cavity are formed in the blade body. Under the condition that the using state of an existing aviation gas turbine fan engine is not changed, calculation and test verification show that theservice life of the turbine guider blade is obviously prolonged by 5 times or above, and the using requirement for the whole service life of the existing aviation gas turbine fan engine is met.

Description

technical field [0001] The invention relates to the technical field of turbomachinery, and in particular to a turbine guide vane adopting a high-efficiency cooling structure. Background technique [0002] The turbine is one of the key core components of the aviation gas turbofan engine. Its function is to convert the thermal energy and kinetic energy of the engine into mechanical energy. The turbine guide vane is a core part of the turbine component. It is above 1500°C, bears huge thermal stress, is scoured and corroded by high temperature gas, and is also affected by high and low frequency vibration stress. Therefore, the turbine guide blade is required to be resistant to high temperature, corrosion resistance, high strength and good durability. [0003] The improvement of the thrust of modern gas turbine engines largely depends on the increase of the total temperature before the turbine. The increase of the total temperature before the turbine puts forward higher requireme...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F01D5/18
CPCF01D9/02F01D5/187F01D5/186F05D2260/2212F05D2260/22141F05D2240/12F05D2240/127
Inventor 康清亮栗尼娜赵熙林莉焦嫦丽
Owner 中国航发贵阳发动机设计研究所
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