Experimental system and method for turbine blade leading edge cooling test under rotating condition

Abstract

The invention discloses an experimental system and method for turbine blade leading edge cooling test under a rotating condition. A whole blade leading edge cooling system is imitated, a real airflowimpact boundary condition is provided, and the comprehensive influence of the mixing of heating incoming flow at external relative speed and internal cooling air flow, the arrangement mode of air flowimpact channels, the arrangement of shower head air film cooling holes at the front edge target surface and the rotation of different areas (blade root, blade body and blade top) of the blade is considered. In the experiment process, temperature, pressure and flow signals are monitored, controlled and adjusted, so that the interior-air film coupling cooling performance of the rotary turbine bladeis accurately evaluated, and reliable reference is provided for design and application of an actual blade cooling structure.

Description

technical field [0001] The invention belongs to the technical field of turbine blade cooling and heat exchange, in particular to an experimental system and method for testing the cooling of the leading edge of a turbine blade under a rotating condition. Background technique [0002] In the design process of a gas turbine, increasing the cycle temperature ratio is an important means to improve the cycle efficiency and power output of the gas turbine; however, an increase in the temperature ratio will lead to an increase in the inlet temperature of the turbine, making the turbine blades and end walls to withstand higher gas temperatures; The thermal load on the blade increases and the thermal stress increases. The continuous increase of turbine inlet temperature has far exceeded the limit temperature of blade materials, so it is necessary to develop efficient blade cooling technology to ensure the performance requirements and safe use of gas turbine blades. [0003] Due to th...

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Problems solved by technology

Most of the early experiments were jet impact experiments under static conditions, and the leading edge of the concave blade was simplified to a flat surface. The blade model does not consider the mixing effect of high-temperature heat flow and cooling air flow, resulting in large differences in experimental results obtained by different simplified models and even opposite conclusions. It is not universal and cannot truly reflect the internal-gas film coupling cooling structure of rotating turbine blades. And fully explore its heat transfer characteristics and influencing factors

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