Design method of TBCC exhaust nozzle adjusting mechanism based on double-shifting-piece type sliding block principle

Abstract

The invention relates to the technical field of TBCC exhaust nozzles, in particular to a design method of a TBCC exhaust nozzle adjusting mechanism based on the double-shifting-piece type sliding block principle. The method comprises the steps that 1) a round-to-square exhaust nozzle overall structure is adopted; 2) a double-shifting-piece type sliding block is designed, and the airflow performance is guaranteed during rotation; 3) a rotating shaft is hinged to the outer end of the double-shifting-piece type sliding block, continuous adjustment is achieved in the door body opening process, and starting and stopping are achieved at any time; and 4) the upper and lower edges of the double-shifting-piece type sliding block are tightly attached to the upper and lower wall contours of the square area of the exhaust nozzle in shape design, and the sealing characteristic of the ventilation opening is ensured during closing. The exhaust nozzle adjusting mechanism adopts a translation and rotation mode, the two sides of the exhaust nozzle are respectively provided with a push rod, a rotating rod and a shifting piece type sliding block, a motor drives connecting rods on the two sides to translate, the connecting rods drive the rotating rods to rotate, the shifting piece type sliding block with one end fixed is made to rotate, and opening and closing of the exhaust nozzle are achieved. The throat area of the convergent type exhaust nozzle can be changed, starting and stopping can be conducted at any time, continuous adjustment is achieved, the thrust requirement is met, and the air tightness condition is met when the exhaust nozzle is completely closed.

Description

Technical field [0001] The present invention relates to TBCC tailpipe technology, and particularly relates to a design method based on the adjustment mechanism TBCC tailpipe principle double slider type paddles. Background technique [0002] Achieve hypersonic flight is to enhance my country's comprehensive national strength important technological means, but only by a single air-breathing engine is difficult to achieve hypersonic flight. Therefore, in order to meet the hypersonic flight, combined engine came into being. [0003] Combined engine comprises of RBCC (rocket-based combined cycle) engines and TBCC (Turbine-Based-Combined-Cycle, a turbine based combined cycle) engines two categories. TBCC wherein the engine is a turbine engine (including turbojet, turbofan engine) and the ramjet two techniques (including sub-combustion, combustion and dual-mode ultra-combustion ramjet) combining developed, which incorporates a turbine engine and ramjet advantage in their respective app...

AI Technical Summary

Problems solved by technology

Only relying on the way of rotating a single diaphragm to realize the mode conversion of the tail nozzle has the problem of air leakage, and there is separation of the airflow boundary layer at the straight corner, which aggravates the flow loss, and the splitter plate will withstand high temperature and excessive air load during the conversion process

Images