Corrugated turbulent flow plane cooling device and application

Abstract

The invention discloses a corrugated turbulent flow plane cooling device and application, and belongs to the field of aero-engines. Comprising a cold side corrugated plate, a hot side flat plate and hollow turbulent flow columns, the cold side corrugated plate is located on one side of a cold air channel, and the hot side flat plate is located on one side of a high-temperature fuel gas channel; a hill-shaped middle channel with the sectional area changing periodically is formed between the cold side corrugated plate and the hot side flat plate. A plurality of hollow turbulent flow columns are arranged between the cold side corrugated plate and the hot side flat plate to form a middle channel containing the hollow turbulent flow columns, and the cold air channel is communicated with the high-temperature fuel gas channel through hollow holes in the hollow turbulent flow columns; the hollow turbulent flow columns are connected with wave troughs of the hot side flat plate and the cold side corrugated plate; and a gas film protection layer is formed on the hot-side flat plate by utilizing outflow of a trough high-pressure area of the cold-side corrugated plate. According to the invention, the amount of cold air near the wall surface of the spray pipe is reduced, and the thrust loss of the engine caused by cold air mixing is reduced under the condition of achieving higher cooling efficiency.

Description

technical field [0001] The invention belongs to the field of aero-engines, and in particular relates to a corrugated spoiler plane cooling device and its application. Background technique [0002] When military fighters take off at short distances and maneuver quickly, they often obtain additional thrust through afterburner beyond the maximum throttle opening of the engine. Due to the limited space in the afterburner, the still-burning gas acts on the nozzle wall of the converging section of the engine in the form of oblique impact, which is likely to cause gas backflow and cause serious consequences. Studies have shown that the gas temperature of the tail nozzle will be as high as 2000K at this time. In addition, the pressure gradient from the inlet to the outlet of the engine nozzle is relatively large, which is likely to cause a strong suction of the gas in the expansion section, which aggravates the occurrence of the backflow phenomenon in the convergent section. [00...

AI Technical Summary

Problems solved by technology

On the other hand, excessive use of cold air to cool the wall will form a thicker air film boundary layer on the wall, which will cause loss of engine thrust

In addition, due to the low-pressure suction of gas in the expansion section, most of the cooling air is drawn to the expansion section with milder working conditions, which to some extent causes waste of cooling air

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