Single-duct ejector device for aero-engine

Abstract

The invention discloses a single-duct ejector device for an aero-engine. Six flow stabilizing supporting plates are evenly distributed and fixed in an ejector middle section, and the airflow inlet end of each flow stabilizing supporting plate is made to communicate with an annular high-pressure air source plenum chamber on the ejector middle section. Three variable Mach number nozzles are installed on one surface of each flow stabilizing supporting plate, and outlets of the variable Mach number nozzles all face the ejector rear section. According to the single-duct ejector device, the air inlet channel of the ejector is designed into the subsonic air inlet channel, the smooth wall surface increases the wall adhesion of inlet airflow, the boundary layer separation of the air inlet wall surface is inhibited, and the quality of an air inlet flow field is improved. Each flow stabilizing supporting plate with the oval head is adopted, so that disturbance vortex caused by the flow stabilizing supporting plate is reduced, the nozzles spray in a low-pressure area behind the supporting plates, and noise generated when the ejector works is reduced. Centrosymmetric multi-point distributed ejection is adopted, so that the ejection area between a high-energy ejection flow and a low-energy ejected flow is greatly increased, and the ejection efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of aero-engine testing, in particular to a variable-working-condition multi-nozzle distributed single-duct injection device for aero-engines. Background technique [0002] With the extensive application of new concepts, new layouts, and new technologies such as combined power supersonic free air intake, vector thrust engine exhaust, and large bypass ratio engine mass flow in aero-engine tests, the test envelope continues to expand. Costs are rising, and trials are becoming more technically risky. Therefore, it is necessary to develop low-cost, low-risk and high-efficiency model test simulation technology. For the simulation of the engine power plant, the ejector is the core component. Two streams of different pressures mix and exchange energy in the ejector to form a fluid of mixed pressure. [0003] The ejector can obtain the intake and exhaust effects of the engine power plant with lower test cost and h...

AI Technical Summary

Problems solved by technology

[0003] The ejector can obtain the intake and exhaust effects of the engine power plant with lower test cost and higher efficiency, but the material exchange area between the high-energy fluid and the low-energy fluid of the traditional ejector is not large, and the ejection efficiency is low; usually The mixing section of the primary and secondary fluids is long, and the working conditions cannot be changed because the nozzles used are fixed nozzles

In the invention with the publication number CN111911465A, a binary nozzle injector device is disclosed, which injects through multiple high-pressure hollow injection channels, but the device cannot change the area of ​​the injection outlet, and cannot change the aerodynamic force of the mixed flow. parameter

In the invention with the notification number CN110411704B, a low-speed wind tunnel aircraft is disclosed in the exhaust simulation test. The ejector module is ejected through a plurality of short distribution nozzles, but the mixed exhaust velocity of the device is low. And there is no mixing section, the ejection efficiency of high-energy fluid is low

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