Double-working medium refrigeration experiment system used for turbine blade of gas turbine

A technology of turbine blades and gas turbines, which is applied in the direction of gas turbine engine testing, jet engine testing, machine/structural component testing, etc., and can solve problems such as data reliability and accuracy cannot be guaranteed, steam cooling cannot be realized, and duration is short, etc.

Inactive Publication Date: 2009-04-08
XI AN JIAOTONG UNIV
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Problems solved by technology

The structure and function of the above-mentioned existing experimental system are relatively simple, and can only study the relevant characteristics of the air-cooled turbine blades, and the experimental process is basically transient, the duration is very short, and the data acquisition needs to be completed in a very short time. The

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  • Double-working medium refrigeration experiment system used for turbine blade of gas turbine
  • Double-working medium refrigeration experiment system used for turbine blade of gas turbine
  • Double-working medium refrigeration experiment system used for turbine blade of gas turbine

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Embodiment Construction

[0026] The working principle and operation method of the experimental system of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0027] Referring to Figure 1, the experimental system mainly includes the following parts: ① Mainstream air source unit; ② Experimental section unit; ③ Cooling air unit; ④ Cooling steam unit; ⑤ Data acquisition unit; ⑥ Control unit; ⑦ Exhaust unit.

[0028] The experimental section unit mainly includes an air intake rectifying device 302 and an experimental section 304 . The air intake rectifying device 302 is equipped with a honeycomb 301 and a damping net. The air intake rectification device is equipped with a honeycomb 301 and a damping net, so that the quality of the mainstream air flow passing through the rectification device is better, and a turbulent grid is also installed at the entrance of the test section 304 to adjust the gas turbulence entering the test section degree is within the ...

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Abstract

The invention discloses a duplex working medium cooling experimental system used for gas turbine blades. The system comprises an experiment section unit including an intake rectifying device and an experiment section in which the turbine blades to be tested are arranged; a main air-supply unit generating the main air which is required by the experiment section and is rectified in the intake rectifying section and enters the experiment section; a cooling air unit generating the cooling air required by the turbine blades to be tested; an exhausting unit exhausting the main air and cooling air of the experiment section and a data collecting unit collecting both the temperature and pressure parameters of the turbine blades to be tested in the experiment section and the parameters of working medium injected into the experiment section and the turbine blades to be tested and also store and analyze the collected data. The system is characterized in that the system also comprises a cooling steam unit comprising a water disposal device, a water-supply device and a steam generator which are sequentially connected through pipelines; the cooling steam generated by the steam generator firstly passes the turbine blades to be tested in the experiment section and then is exhausted from the experiment section.

Description

technical field [0001] The invention relates to the research field of gas turbine blades, in particular to a dual substance cooling experiment system for gas turbine blades. technical background [0002] Heavy-duty gas turbine is one of the important power generation equipment in modern power plants. The higher the gas inlet temperature, the higher the thermal efficiency of single unit and combined cycle. At present, the efficiency of the combined cycle unit has reached 60%, and the turbine inlet temperature of the gas turbine has reached 1500°C, or even higher. In the modern era of energy shortage, it is particularly important to improve the thermal efficiency of gas turbines. However, as the gas inlet temperature of the gas turbine increases, the strength and life of the turbine blades will decrease rapidly. In recent decades, the gas temperature at the turbine inlet has increased by an average of about 20°C per year, while the metal temperature resistance is only Approx...

Claims

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Application Information

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IPC IPC(8): G01M15/14G01M19/00G01M99/00
Inventor 高建民高铁瑜陈富民张英杰刘加增王昭黄军辉
Owner XI AN JIAOTONG UNIV
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