Blade leading edge double-rotational-flow impingement cooling experiment testing system and method
A technology for the leading edge of the blade and the test system, which is applied to the supporting elements of the blade, the engine element, the machine/engine, etc., can solve the problem of effectively revealing the cooling mechanism of the double swirl cooling technology without experimental means, and achieves simple structure and convenient construction. , the effect of low cost
Active Publication Date: 2021-06-22
XI AN JIAOTONG UNIV
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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
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[0035] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.
[0036] Such as figure 1 As shown, the present invention provides a kind of blade leading edge dual-swirl impingement cooling experiment test system, including main flow channel, blade leading edge experiment section 11, secondary flow cooling system and infrared thermal imaging system; wherein, the outlet of main flow channel and The inlet of the blade leading edge test section 11 is connected by a flange; the frame of the blade leading edge test section 11 is made of plexiglass, and a blade leading edge double swirl impact test piece 12 and a temperature measuring device 10 are arranged inside; the front side of the test piece 45 An infrared shooting window 26 is arranged in the direction, and the infrared optical thermal imager 27 can measure the temperature directly to the experimental observation area through the window; the secondary flow ...
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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...
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IPC IPC(8): F01D5/18F01D5/14F01D21/00
CPCF01D5/186F01D5/141F01D5/147F01D21/003
Inventor 刘学斌宋立明张超
Owner XI AN JIAOTONG UNIV
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