Vacuum-pumping ejector and vacuum-pumping method for engine
An ejector and vacuuming technology, which is applied in the directions of machines/engines, rocket engine devices, jet pumps, etc., can solve the problems of no self-contained vacuuming ejection device, etc., to improve the use and maintenance performance, shorten the axial length, The effect of reducing the weight of the structure
Active Publication Date: 2020-05-08
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
[0004] At present, the domestic liquid oxygen kerosene engine does not have its own vacuum ejection device
Method used
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[0023] The present invention will be further described in detail through the drawings and examples below. Through these descriptions, the features and advantages of the present invention will become more apparent.
[0024] According to a first aspect of the present invention, a vacuum ejector is provided, such as figure 1 As shown, the ejector is a cylindrical structure with variable cross-sectional area in the axial direction and connected, including the first-stage nozzle section 1, the first-stage mixing section 2, the second-stage nozzle section 3, and the second-stage mixing section 4 connected in sequence , and the expansion section 5, wherein,
[0025] The first-stage nozzle section 1 integrates the first-stage injection nozzle 11 and the engine vacuum port 12. The first-stage injection nozzle 11 is connected to a high-pressure air source to convert the static pressure of the injection air flow into a dynamic pressure, so that the first-stage nozzle section 1 forms a n...
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The invention provides a vacuum-pumping ejector and a vacuum-pumping method for an engine. The vacuum-pumping ejector comprises a primary nozzle segment, a primary mixing segment, a secondary nozzle segment, a secondary nozzle segment and an expansion segment, wherein the primary nozzle segment is internally provided with a primary ejection nozzle and an engine vacuum-pumping mouth, the primary ejection nozzle is connected with a high-pressure air source to transform ejection air-flow static pressure into dynamic pressure, and vacuum-pumping of an inner cavity of the engine is conducted through the engine vacuum-pumping mouth; the secondary nozzle segment is provided with a secondary ejection nozzle to further accelerate the air flows which flow through the secondary ejection nozzle; the air flows are fully mixed through the first mixing segment and the secondary mixing segment; the air flows mixed through the secondary mixing segment are accelerated by the expansion segment and then ejected to enter the atmosphere. In the method, a two-stage ejection way is adopted, and the limiting ejection ability is high and can be up to 2.7KPa or below; the vacuum-pumping mouth and the primaryejection nozzle are vertically arranged, compared with a through way, the structural length can be effectively shortened, the primary nozzle segment is prevented from being suspended in the air in aflow field, the processing difficulty of the primary nozzle segment is reduced, and the quality of the flow field can be effectively improved.
Description
technical field [0001] The invention relates to a small-scale vacuuming device and a vacuuming method, in particular to a vacuuming ejector and an engine vacuuming method, which can be used for vacuuming a liquid rocket engine. Background technique [0002] Before starting the liquid oxygen kerosene engine, in order to ensure that the propellant fuel path can be quickly filled after entering the engine to avoid cavitation in the engine due to residual gas in the engine cavity, the engine fuel path must be vacuumed before the test . [0003] At present, in order to ensure the thrust-to-mass ratio of the liquid oxygen kerosene engine, considering the influence of the size and weight of the vacuuming equipment, the vacuuming process mainly depends on the ground maintenance equipment. The ground vacuum equipment needs to be connected to the engine in the shooting range, and the long connecting pipeline increases the possibility of seal failure, and affects the maintenance perfo...
Claims
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IPC IPC(8): F04F5/22F04F5/46F04F5/44F02K9/44
CPCF04F5/22F04F5/46F04F5/44F02K9/44
Inventor 巨龙高玉闪张晓光王猛张晟秦红强杨飒
Owner XIAN AEROSPACE PROPULSION INST