Experimental system for measuring comprehensive cooling efficiency of turbine blade tip of gas turbine

Abstract

The invention discloses an experimental system for measuring comprehensive cooling efficiency of a turbine blade tip of a gas turbine. The experimental system comprises a mainstream system and a cooling gas system, the mainstream system comprises a variable-frequency fan and a pipeline which is connected with an outlet of the fan and is provided with a corner, the corner of the pipeline is a test section, and a to-be-measured blade is arranged on the test section; infrared glass is arranged on a cover plate of the upper end wall of the test section and is opposite to the blade top of the to-be-measured blade, an infrared thermal imager is arranged above the infrared glass and is used for measuring temperature distribution on the surface of the blade top through the infrared glass, and a total pressure probe, a Pitot tube and a mainstream thermocouple are arranged at the inlet end of the test section and are used for monitoring mainstream working conditions; a gas supply cavity thermocouple is arranged in a gas supply cavity of the blade to be measured; the cooling gas system comprises a cooling gas source, the cooling gas source is connected with a gas inlet connector of a blade to be measured, a heat exchanger is arranged on a connecting pipeline, and by means of the gas turbine blade tip dimensionless temperature distribution testing device, blade tip dimensionless temperature distribution matched with the real working condition of a gas turbine can be obtained, and the design of a blade tip cooling structure is assisted.

Description

technical field [0001] The invention belongs to the technical field of gas turbines, and relates to blade cooling technology, in particular to an experimental system for measuring the comprehensive cooling efficiency of turbine blade tops of gas turbines. Background technique [0002] Gas turbines are widely used in modern industrial society. In order to design more advanced gas turbines, data are often obtained through experimental measurements to assist the design process. The inlet temperature of the gas turbine is extremely high, and the internal hot-end parts need cooling gas protection to maintain the safe and stable operation of the gas turbine, and the flow laws of these cooling gases need to be studied through experiments. The thermal load on the tip of the gas turbine moving blade in the hot end part is extremely high, and ablation occurs from time to time, which is one of the important reasons for the failure of gas turbine components. Therefore, cooling gas is ...

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Problems solved by technology

[0003] The current experimental research on the cooling efficiency of the blade tip has the following limitations: 1. The experimental measurement of the adiabatic cooling efficiency of the blade tip can only obtain the temperature distribution on the surface of the blade tip, but cannot obtain the temperature distribution inside the blade tip; 2. Measure the comprehensive cooling of the blade tip Efficiency can obtain the temperature distribution inside the blade tip, but such an experimental system is currently lacking

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