Blade leading edge double-rotational-flow impingement cooling experiment testing system and method

Abstract

The invention discloses a blade leading edge double-rotational-flow impingement cooling experiment testing system and method. The system comprises a main flow channel, a blade leading edge experiment section, a secondary flow cooling system and an infrared thermal imaging system. Heated air is introduced into an inner cavity of the main flow channel, and an outlet of the main flow channel is connected with the blade leading edge experiment section; a blade leading edge double-rotational-flow impact experiment piece is placed in an inner cavity of the blade leading edge experiment section; the secondary flow cooling system comprises an air branch and a high-density gas branch, an outlet of the air branch and an outlet of the high-density gas branch are connected with a gas collection chamber, an outlet of the gas collection chamber extends into an inner cavity of the blade leading edge double-rotational-flow impact experiment piece, and a first ball valve is arranged on the outlet of the gas collection chamber; and the infrared thermal imaging system monitors the surface temperature field distribution of the blade leading edge double-rotational-flow impact experiment piece. The system is simple in structure, low in cost and convenient to build, and provides a reference basis for advanced cooling design of gas turbines in the future.

Description

technical field [0001] The invention belongs to the technical field of gas turbine leading edge cooling and heat exchange, in particular to a blade leading edge double swirl flow impact cooling experimental testing system and method. Background technique [0002] Gas turbine is an advanced and complex complete set of power machinery equipment, and it is a typical high-tech intensive product. The initial gas temperature is an important factor affecting the efficiency of the gas turbine, and the increase of the initial gas temperature is of great significance for improving the efficiency of the gas turbine. At present, the turbine inlet temperature of aero-engines exceeds 1800°C, and the initial turbine inlet temperature of future heavy-duty gas turbines fueled by pure hydrogen will also reach 1700°C, which puts higher demands on the temperature resistance of the hot-end components of the gas turbine. requirements, especially the cooling performance of the leading edge of the...

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problems existing in the prior art, the present invention provides an experimental test system and method for double-swirl impingement cooling at the leading edge of the blade, which solves the problem that there is currently no experimental means to effectively reveal the cooling mechanism of the double-swirl cooling technology, and fills in the experimental means Revealing the Blank of the Cooling Mechanism of the Double Swirl Cooling Technology

Images