An ejector nozzle with double bell-shaped ejector sleeves

Abstract

The invention discloses an injection spray pipe with a double-bell type injection casing pipe. The injection spray pipe comprises a main spray pipe and the injection casing pipe. The main spray pipe is a fixed throat shrinkage and expansion spray pipe. The injection casing pipe comprises an injection casing pipe convergence section, an injection casing pipe first expansion section and an injectioncasing pipe second expansion section. The area of a throat of the injection casing pipe is determined according to the work characteristics of an engine air inlet way so as to control the injection suction flow under various flight states. A break point is formed through the difference of the injection casing pipe first expansion section and the injection casing pipe second expansion section, andaccordingly it is guaranteed that when the injection spray pipe works at the low blow-down ratio, airflow is separated at the break point, and excessive expansion of the airflow is prevented; and atthe high blow-down ratio, an injection channel enters a jamming state, the airflow is constantly expanded to a spray pipe outlet along the injection casing pipe second expansion section, and the thrust performance at the high blow-down ratio is guaranteed. Through control over the wall face separation position of airflow of the injection spray pipe, the continuous high thrust performance of the injection spray pipe within the wide blow-down ratio range is effectively guaranteed.

Description

technical field [0001] The invention relates to the field of aerospace technology, and more specifically relates to an ejector nozzle with double bell-shaped ejector sleeves, which is mainly used in aero-engines with wide drop pressure ratio and high thrust performance requirements. Background technique [0002] Horizontal take-off and landing hypersonic vehicle has been the focus of aerospace research in recent years, and hypersonic power plant is the key technology of hypersonic vehicle. The horizontal take-off and landing hypersonic power plant, based on considerations of safety, economy and other factors, must be able to take into account higher efficiency in a very large speed range from take-off, subsonic, transonic, hyposonic and finally to hypersonic flight This requires the exhaust nozzle of the hypersonic engine to maintain high thrust performance in a wide range of drop pressure ratios. [0003] At present, researches on tail nozzles with fixed throat area of ​​h...

AI Technical Summary

Problems solved by technology

[0006] In view of this, the present invention provides an ejector nozzle with double bell-shaped ejector sleeves, which solves the problem that the existing geometrically non-adjustable tail nozzle cannot maintain high thrust performance in a relatively high drop pressure ratio range. question

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