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Gas turbine stationary blade insert installation method and application

An installation method and plug-in technology, which are applied to the installation method and application field of a gas turbine turbulent and stationary blade plug-in, can solve the problems of ineffective cooling, safety accidents, and shortened blade life, and achieve the effect of ensuring the cooling effect.

Active Publication Date: 2021-02-05
DONGFANG TURBINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The internal cooling performance of turbine turbine stator blades is closely related to the bottom clearance. If the clearance is too large, it may easily cause over-temperature failure, lead to high-temperature scrapping of the stator blades, and even cause serious safety accidents
[0004] For the cooling of the stationary blade, the cooling gas is shot to the surface of the blade through the impact hole on the insert to cool the metal of the blade. If the assembly gap between the insert and the bottom of the blade is too large, the cold air will enter the chamber through the gap and no cooling will be achieved. As a result, the cold air leaks, the cooling flow of the gas turbine increases, and the temperature of the blades increases
The gas turbine efficiency is reduced, and the blade life is reduced, which affects the safe operation of the gas turbine

Method used

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  • Gas turbine stationary blade insert installation method and application

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Effect test

Embodiment 1

[0032] The present invention is realized through the following technical solutions, a method for installing a gas turbine turbine vane plug-in, specifically comprising steps:

[0033] Calculate the relationship between the plug-in assembly gap and the cooling gas leakage to obtain the plug-in assembly gap; the plug-in assembly gap is 0-1.0mm;

[0034] The relationship between the calculation plug-in assembly clearance and cooling gas leakage; specifically refers to:

[0035] Through three-dimensional CFD calculation, the cold air leakage of the static blades under different installation clearances is obtained, and the corresponding assembly clearance is found according to the requirements of different blades on the cold air leakage;

[0036] Reserve cavity grooves in the inner cavity of the vane;

[0037] Plug-in orthopedics: orthopedize the completed plug-in, and the length of the exposed part of the plug-in is controlled at 3-20mm.

[0038] Orthopedics refers to the use of...

Embodiment 2

[0047] A method for installing a gas turbine turbine stator blade plug-in. The temperature of the first and second-stage stator blades of a gas turbine is very high, requiring efficient internal cooling, and the installation requirements for the plug-in are also relatively high. The specific installation method for the first and second-stage stator blade plug-ins The steps are:

[0048] In the manufacture of hollow stators, a cavity groove is reserved at the bottom of the inner cavity insert to facilitate the assembly of the insert;

[0049] According to the internal structure of the blade and the cooling airflow conditions, the relationship between the plug-in assembly clearance and the cooling gas leakage is calculated, and a reasonable plug-in assembly clearance requirement is put forward. The theoretical analysis and full three-dimensional CFD calculation and analysis of the first and second stages of a certain gas turbine are carried out to evaluate the plug-in leakage fl...

Embodiment 3

[0054] A method for installing a gas turbine turbine stator blade plug-in. Although the temperature of the third-stage stator blade of a gas turbine is not as high as that of the first and second stages, internal cooling is still required. The specific steps for installing the third-stage stator blade plug-in of a gas turbine are as follows:

[0055] In the manufacture of hollow stators, a cavity groove is reserved at the bottom of the inner cavity insert to facilitate the assembly of the insert;

[0056] According to the internal structure of the blade and the cooling airflow conditions, the theoretical analysis and full three-dimensional CFD calculation and analysis of the third-stage stator blade of a certain gas turbine are carried out to evaluate the plug-in leakage flow, and it is concluded that the assembly clearance of the third-stage stator blade plug-in assembly is required to be 0.5mm.

[0057] Orthopedically improve the finished plug-in, reduce assembly interference...

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Abstract

The invention relates to the technical field of gas turbine hollow blade cooling, and particularly discloses a gas turbine stationary blade insert installation method which is applied to installationof heavy-duty gas turbine hollow blade inserts or aviation turbine engine hollow blade inserts. The method specifically comprises the following steps of calculating a relation between the insert assembling clearance and cooling gas leakage to obtain the insert assembling clearance, wherein the insert assembling clearance is 0-1.0 mm; reserving inner cavity grooves in inner cavities of stationary blades; correcting the shape of inserts; performing repairing and polishing; performing assembling; and completing assembling. According to the method, the leakage of cooling gas is effectively controlled within a reasonable range, and the service life of the blades is prolonged.

Description

technical field [0001] The invention relates to the technical field of gas turbine hollow blade cooling, in particular to an installation method and application of a gas turbine stator vane plug-in. Background technique [0002] Gas turbines play an irreplaceable role in aircraft propulsion, power generation and industry. Both modern gas turbine engines and heavy-duty gas turbines are developing toward higher thermal efficiency and higher power. The gas inlet temperature of turbines is getting higher and higher, and the working conditions are getting worse. However, the development of materials is difficult to meet the needs of the development of modern advanced gas turbines. , therefore, effective cooling of turbine blades is the key to efficient operation and further development of gas turbines. Cooling of gas turbine blades includes external cooling and internal cooling, among which jet impingement cooling and column rib cooling are often used for internal cooling. [0...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P21/00
CPCB23P21/00
Inventor 苏鹏飞蔡国煌赵世全孔祥林尹正发罗涛卢航周娜李金鸿
Owner DONGFANG TURBINE CO LTD
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