Thrust measuring structure of double-duct spray pipe with sealing gas

Abstract

The invention belongs to the field of aero-engine double-duct spray pipes, and particularly relates to a thrust measuring structure of a double-duct spray pipe with sealing gas. The structure comprises an inner duct pressure stabilizing cavity (3), an inner duct air inlet pipe (2), an inner duct sealing air pressure stabilizing cabin (11), an outer duct pressure stabilizing cavity (6), an outer duct air inlet pipe (4), an outer duct sealing air pressure stabilizing cabin (12), a double-duct spray pipe test piece (10) and a thrust measuring balance (7). According to the thrust measurement structure of the double-duct spray pipe with the sealing gas, the inner duct and the outer duct simultaneously, horizontally and symmetrically feed gas, and a non-contact sealing and sealing gas structure is adopted, so that thrust and flow can be accurately measured, and interference of gas feeding in thrust measurement can be eliminated at the same time; influence of the structure on thrust measurement is smaller, and the interference caused by the structure can be quantitatively calculated; coaxial air supply of a double-duct spray pipe test piece can be realized, secondary switching is reduced, a straight pipe section is longer, and air flow pressure stabilization and rectification are facilitated; and the structure is compact and efficient, the thrust measuring platform is convenient to arrange, and the test efficiency is improved.

Description

technical field [0001] The application belongs to the field of dual-duct nozzles of aero-engines, and in particular relates to a thrust measurement structure of a double-duct nozzle with sealing gas. Background technique [0002] At present, civil aviation aero-engines all adopt a large bypass ratio structure, and most of the exhaust devices are exhaust nozzles with inner and outer cores separated. In order to evaluate the thrust characteristics and thrust-fuel consumption rate characteristics of the engine, it is necessary to accurately measure the thrust of the nozzle and the flow through the inner and outer cores. How to simultaneously measure the flow and thrust of a large nozzle is a technical problem. [0003] The existing structure of the nozzle dynamometer test bench mainly has three forms: 1) no sealing structure is used, such as the flexible connection method; 2) both the inner and outer streams are sealed, but the thrust and flow need to be measured separately; ...

AI Technical Summary

Problems solved by technology

However, the existing technology still has the following disadvantages: Both the flexible structure and the semi-sealed structure have force measurement interference that is difficult to calculate quantitatively and cannot be eliminated, which affects the accuracy of force measurement; in order to reduce interference, it is necessary to make the force measurement system As close as possible to the state in which it is located, this virtually increases the adjustment workload, resulting in increased test costs and reduced efficiency

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