An ejector nozzle device for simulating sub/transonic outflow
An injection nozzle, transonic technology, applied in the direction of jet propulsion devices, machines/engines, etc., can solve the problems of sub/transonic airflow that cannot simulate the flow field outside the aircraft, the small scale of the test model, and the congestion of the wind tunnel flow field, etc. , to save test cost and workload, avoid extremely congested wind tunnel, and simple aerodynamic principle
Active Publication Date: 2022-04-19
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS +1
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Problems solved by technology
However, its device is limited to simulate the supersonic airflow of the external flow field of the aircraft, and cannot simulate the sub / transonic airflow of the external flow field of the aircraft.
[0006] However, the simulation of the sub / transonic air flow outside the aircraft, especially the simulation of the transonic incoming flow, is very difficult, mainly because the wind tunnel flow field is easily blocked in the transonic state, which makes the scale of the test model very large. Small, and its corresponding clogging degree is usually between 1% and 3%, which makes it difficult to conduct sub / transonic outflow and ejection nozzle internal flow interference tests, and even if it can be carried out, the cost is very high
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[0023] Such as figure 1 with figure 2 As shown, in the invention of an ejector nozzle device for simulating sub / transonic outflow, in the transonic wind tunnel test of aircraft outflow, it is necessary to ensure that the congestion degree of the wind tunnel is between 1% and 3%, and the size of the test device The need is very small. In this injection nozzle device, the size of the test device does not have this limitation, and it can be processed into a reasonable size, which greatly simplifies the difficulty of processing. This device includes a circular main nozzle section 1, a secondary flow nozzle section 2, and a tertiary flow nozzle section. 3 and support plate 4; support plate 4 is used for fixing the position of main nozzle section 1, secondary flow nozzle section 2 and tertiary flow nozzle section 3, and main nozzle section 1, secondary flow nozzle section 2, and tertiary flow nozzle section 3 are An annular pipe with a common central axis, the secondary flow nozz...
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The invention discloses an injection nozzle device for simulating sub / transonic outflow, which comprises a circular main nozzle section, a secondary flow nozzle section and a tertiary flow nozzle section surrounding the main nozzle section; The direction is extended and is located behind the outlet of the secondary flow nozzle. By designing the intake structure of the tertiary flow and adjusting the equivalent expansion ratio of the ejector nozzle, the ejector nozzle of sub / transonic outflow is simulated under the condition of static outflow on the ground Flow field, to ensure that the flow field in the injection nozzle of the ground test is similar to the flow field in the real injection nozzle. The aerodynamic principle of the present invention is simple, and the structure is easy to realize. It does not need to carry out tests in the free-jet wind tunnel, and does not need to modify the structure of the wind tunnel. The accurate simulation of the sub / transonic outflow can be realized only through the conventional nozzle ground test bench, which can effectively Avoid the problem of extremely congested wind tunnel in the transonic state, effectively saving test cost and workload.
Description
technical field [0001] The invention relates to the field of aircraft aerodynamic experiments, in particular to an ejector nozzle device capable of simulating sub / transonic outflow. Background technique [0002] TBCC has the characteristics of wide application, high durability, good economy, good low-speed performance, low environmental pollution, good reusability, and conventional take-off and landing, and has very good engineering application prospects. The main function of the TBCC exhaust pipe is to fully expand the gas at the outlet of the engine in the exhaust pipe, and convert the heat energy and pressure energy carried by it into kinetic energy, so as to increase the impulse of the engine outlet airflow, thereby increasing the thrust of the engine. Since the TBCC tail nozzle works in a large range of falling pressure ratio, its expansion ratio changes from 2 in the take-off state to 15-20 in the supersonic cruise state. Certain technical means must be used to realize...
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IPC IPC(8): F02K1/78
CPCF02K1/78
Inventor李子杰蔡佳黄河峡林正康谭慧俊刘金楠雷鸣
OwnerNANJING UNIV OF AERONAUTICS & ASTRONAUTICS