Cooling effect test device for gas turbine blades at full temperature and equal expansion ratio

Abstract

The invention provides a total-temperature equal expansion ratio cooling effect test device of a turbine blade of a gas turbine.A turbine blade test mainstream system is composed of a centrifugal air compressor, a mainstream air inlet emptying valve, an air inlet regulating valve, a mainstream flow nozzle, a an electric heater, a metal expansion joint, a combustor, a turbine blade test section, an exhaust desuperheater and a noise reduction tower, all of which are connected in sequence.A cooling air system comprises a roots blower, a cooling air emptying valve, a cooling air regulating valve, a Venturi meter and a cooling air electric heater, all of which are connected in sequence.The cooling air electric heater is connected with the turbine blade test section.A cooling water system comprises a cooling tower, an outlet of the combustor and an inlet of the exhaust desuperheater are connected with the cooling tower through water inlet pipelines, an inlet and an outlet of the turbine blade test section are connected with the cooling tower through water outlet pipelines, and the cooling tower is further connected with a water replenishing pipeline.According to the total-temperature equal expansion ratio cooling effect test device, a turbine blade total-temperature equal expansion ratio cooling effect test can be accurately and conveniently carried out at low cost.

Description

technical field [0001] The invention relates to a full-temperature equal expansion ratio cooling effect test device for heavy-duty gas turbine turbine blades and a parameter design method thereof, belonging to the technical field of gas turbines. Background technique [0002] The turbine inlet temperature of F-class gas turbine reaches 1400°C, the turbine inlet temperature of H-class gas turbine reaches 1500°C, and the turbine inlet temperature of J-class gas turbine reaches 1600°C. The working temperature of the directional crystallization or single crystal nickel-based alloy base metal of the turbine blade is about 900°C to 1000°C, and the temperature drop between the turbine inlet temperature and the working temperature of the turbine blade base metal is 500°C to 600°C. This is achieved by adopting blade cooling structure design and surface thermal barrier coating. The heat insulation temperature of the thermal barrier coating of the turbine blade is about 50°C to 100°C,...

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Problems solved by technology

[0003] Turbine blade cooling effect test is a necessary link in the development of high-temperature turbine blades for gas turbines. In the prior art and public literature reports, there is no cooling effect test device and parameter design method for full-temperature and equal expansion ratio of heavy-duty gas turbine blades.

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