CN111159814A - Design method and configuration of rectangular supersonic velocity spray pipe with turning inlet and high slenderness ratio - Google Patents
Design method and configuration of rectangular supersonic velocity spray pipe with turning inlet and high slenderness ratio Download PDFInfo
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Abstract
The invention relates to a design method and a configuration of a rectangular supersonic velocity spray pipe with a turning inlet and a high slenderness ratio, wherein the design method comprises the following steps: (1) determining the shapes of the upper wall surface and the lower wall surface from the nozzle inlet to the throat on the basis of the inlet height of the inlet section, and the section curves of the upper wall surface and the lower wall surface along the spanwise direction; (2) determining an optional range of the distance between the intersection position of the throat and the lower wall surface of the inlet section and the tangent point of the lower wall surface, namely an optional range of throat tangent distance; (3) determining molded lines of an upper wall surface and a lower wall surface of an outlet section of the supersonic velocity spray pipe by using a characteristic line method according to the throat height, the outlet height, the required outlet Mach number and the outlet section length, realizing the design of the spray pipe and meeting the performance requirement of the spray pipe; and the appropriate throat cutting distance and the combination of the types of the upper wall surface and the lower wall surface of the outlet section can be further designed, so that the performance of the spray pipe is improved.
Description
Technical Field
The invention discloses a design method and a configuration of a rectangular supersonic velocity spray pipe with a turning inlet and a high slenderness ratio, and belongs to the field of supersonic velocity spray pipe design.
Background
The high-speed aircraft encounters a severe aerodynamic heating effect in the flying process, the problems that the effective load is reduced due to the fact that the heat-proof layer is designed to be too thick, thermal deformation generated by an optical window is interfered by the aerodynamic optical effect and the like are easily caused, if local heat flow cannot be properly reduced, the high-speed aircraft is prevented from lifting the effective load, or optical guidance fails, and the design or task completely fails in severe cases. Therefore, local high-speed aircrafts can be cooled in specific areas on the surfaces of the aircrafts by using the supersonic jet flow air film formed by the spray pipes, the surface temperature of the aircrafts is reduced, and the effects of improving the effective load, weakening the negative effect of the aerodynamic heat effect and the like are achieved.
The research on the design details of the supersonic velocity spray pipe with the refrigerating effect at home and abroad is in a blank state or in an unpublished state, and particularly the supersonic velocity spray pipe with a turning inlet and a high slenderness ratio under the restriction of a narrow space is designed. The general supersonic velocity spray pipe mainly adopts a common characteristic line method to design an expansion section, and does not comprehensively design a single-curved wall surface or a double-curved wall surface of a contraction section, a throat and the expansion section, so that the supersonic velocity of the supersonic velocity air at the outlet of the spray pipe is extremely uneven, the purpose of effectively weakening the aerodynamic heat effect cannot be achieved, and the side effect of causing abnormal disorder of the surface flow field of an aircraft can be brought.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, the machine configuration of the design method of the rectangular supersonic velocity spray pipe with the turning inlet and the high slenderness ratio is provided, the purpose of obtaining a uniform supersonic velocity jet flow field is achieved, and the problem of uneven jet flow field caused by a common design method is effectively solved.
The technical scheme of the invention is as follows: a design method of a rectangular supersonic velocity spray pipe with a turning inlet and a high slenderness ratio comprises the following steps:
(1) determining the shapes of the upper wall surface and the lower wall surface from the nozzle inlet to the throat on the basis of the inlet height of the inlet section, and the section curves of the upper wall surface and the lower wall surface along the spanwise direction;
(2) determining an optional range of the distance between the intersection position of the throat and the lower wall surface of the inlet section and the tangent point of the lower wall surface, namely an optional range of throat tangent distance;
(3) and determining the molded lines of the upper wall surface and the lower wall surface of the outlet section of the supersonic velocity spray pipe by using a characteristic line method according to the height of the throat, the height of the outlet, the required Mach number of the outlet and the length of the outlet section.
Preferably, the step (3) is followed by the following steps:
(4) in the selectable range of the throat cutting distance, under the condition of different throat cutting distances, based on given inlet pressure and outlet pressure, calculating a flow field of the spray pipe to obtain corresponding actual outlet Mach number curves under the condition of different throat cutting distances;
(5) determining a proper throat cutting distance according to the Mach number curve of the outlet in the step (4) and a set selection standard;
(6) the profile lines of the upper wall surface and the lower wall surface of the outlet section can be designed into two types, namely straight lines or curves, and under each combination condition of the profile lines of the upper wall surface and the lower wall surface of the outlet section, the flow field of the spray pipe is calculated based on the given inlet pressure and temperature according to the determined proper throat tangential distance to obtain the corresponding actual outlet Mach number curve under each combination condition;
(7) and (4) determining the combination of the profile types of the upper wall surface and the lower wall surface of the outlet section according to the outlet Mach number curve in the step (6) and the set selection standard.
Preferably, due to space constraints, the gas flow cannot flow into the nozzle in a direction perpendicular to the cross-section of the nozzle throat, and therefore the inlet section of the nozzle needs to be arranged to turn, preferably at a turn angle θ of less than 90 °.
Preferably, the ratio of the length to the width of the rectangular supersonic nozzle outlet is called slenderness ratio, and in order to produce a thin refrigerant gas film, a high slenderness ratio is adopted, preferably in the range of 10: 1 or more.
Preferably, the ratio of the maximum cross-sectional area of the inlet section of the nozzle to the minimum cross-sectional area of the throat is a contraction ratio, and the contraction ratio is made as large as possible under the condition of space limitation, so that the flow field is more favorably stabilized.
Preferably, the distance from the intersection point of the throat and the lower wall surface to the tangent point of the lower surface is called throat tangential distance, and the throat tangential distance is not too small and is at least more than one time of the height of the throat.
Preferably, the expansion section of the nozzle adopts an upper wall surface molded line and a lower wall surface molded line as much as possible, and a single wall surface molded line is avoided.
Preferably, the expansion angle of the molded line of the single wall surface is decomposed to an upper wall surface and a lower wall surface without changing the size of the throat and the size of an outlet, so that the effect of reducing the expansion angle is achieved, the transverse movement amplitude of the airflow in the expansion process is small, and the flow field is more easily stabilized.
Preferably, as shown in fig. 4, a rectangular supersonic nozzle configuration with a corner inlet and a high slenderness ratio comprises: an inlet section and an outlet section; the connecting surface of the inlet section and the outlet section is used as a throat; the inlet section comprises an upper wall surface and a lower wall surface; the outlet section comprises an upper wall surface and a lower wall surface; the distance between the intersection position H of the throat CH and the lower wall surface HI of the outlet section and the tangent point G of the second straight line segment GH of the inlet section and the arc FG of the lower wall surface of the inlet section is used as throat tangent distance;
the upper wall surface of the inlet section comprises an inlet first straight line section AB and an inlet first curve section BC which are connected at a point B in a smooth and sliding manner, and the lower wall surface of the inlet section comprises an inlet second straight line section EF, an inlet circular arc section FG and an inlet third straight line section GH; (preferably, the upper wall surface of the inlet section has a cross section in the spanwise direction including a first straight line section and a first curved line section, the first straight line section is connected with the first curved line section, the first straight line section is close to the inlet, and the first curved line section is close to the throat)
The upper wall of the outlet section comprises a curved section CD and the lower wall of the outlet section comprises a straight section HI.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention uses the molded line with optimized contraction ratio, throat tangential distance and double-wall surface expansion to adjust the flow of the spray pipe, and solves the problems that the flow field at the outlet of the spray pipe is not uniform due to simple design, so that the jet flow heat reduction effect cannot reach or even brings serious disordered flow fields to an aircraft.
(2) The invention ensures the uniformity of the outlet flow field by the design of numerical simulation of optimized contraction ratio, the range of throat tangential distance and double-wall surface expansion.
(3) The invention provides uniform and stable air flow and provides powerful guarantee for the refrigeration effect of supersonic jet flow.
(4) The invention can form a stable supersonic flow field by optimizing the shrinkage ratio, the throat tangential distance and the double-wall surface profile design with the assistance of numerical calculation.
(5) The invention mainly aims at the design problem of a rectangular supersonic velocity spray pipe with a turning inlet and a high slenderness ratio, and completes the design of the supersonic velocity spray pipe by optimizing and analyzing the expansion modes of a contraction section, a throat section and an expansion section to obtain a uniform emergent flow field.
Drawings
FIG. 1 is a schematic cross-sectional view of a nozzle of the present invention;
FIG. 2 is a comparison of the distribution of the number of the flow field Ma at the outlet of the nozzle before and after the optimization of the inlet area according to the present invention;
FIG. 3 is a graph of the effect of single wall expansion and double wall expansion designs of the present invention on the distribution of the Ma number of the nozzle exit flow field;
FIG. 4 is a line drawing of the outer shape of the nozzle designed according to the present invention.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
For an aircraft flying at a high speed for a long time, the wall surface is continuously heated by airflow, so that the temperature of the wall surface reaches very high, guidance and safety of the aircraft are not facilitated, and the surface of the aircraft can be cooled by a refrigeration spray pipe generally. However, the nozzles used do not allow new interfering objects to be formed on the aircraft surface, and therefore the nozzle orifices of the nozzles typically use elongated slots. In order to adapt to an aircraft flying at a high speed, the speed of jet airflow is generally determined to be high, and the Mach number can reach 2-4. With the design of the long and narrow rectangular nozzle, if the curves of the inlet section and the outlet section are randomly established, a uniform flow field is often not obtained, so that the refrigeration efficiency is reduced, a more complex flow field is seriously formed, and the guidance and safety of an aircraft are threatened inadequately. The invention is specially designed for the special spray pipe, the designed spray pipe can form a high-speed flow field with uniform outlet Mach number, the refrigeration purpose can be effectively finished, and the problems of guidance and safety of the aircraft caused by high temperature on the wall surface are solved.
The invention relates to a design method and a configuration of a rectangular supersonic velocity spray pipe with a turning inlet and a high slenderness ratio, wherein the design method comprises the following steps: (1) determining the shapes of the upper wall surface and the lower wall surface from the nozzle inlet to the throat on the basis of the inlet height of the inlet section, and the section curves of the upper wall surface and the lower wall surface along the spanwise direction; (2) determining an optional range of the distance between the intersection position of the throat and the lower wall surface of the inlet section and the tangent point of the lower wall surface, namely an optional range of throat tangent distance; (3) determining molded lines of an upper wall surface and a lower wall surface of an outlet section of the supersonic velocity spray pipe by using a characteristic line method according to the throat height, the outlet height, the required outlet Mach number and the outlet section length, realizing the design of the spray pipe and meeting the performance requirement of the spray pipe; and the appropriate throat cutting distance and the combination of the types of the upper wall surface and the lower wall surface of the outlet section can be further designed, so that the performance of the spray pipe is improved.
The invention relates to a design method of a rectangular supersonic velocity spray pipe with a turning inlet and a high slenderness ratio, which comprises the following steps:
(1) determining the shapes of the upper wall surface and the lower wall surface from the nozzle inlet to the throat on the basis of the inlet height of the inlet section, and the section curves of the upper wall surface and the lower wall surface along the spanwise direction;
(2) determining an optional range of a distance GH between an intersection position H of the throat CH and the lower wall surface HI of the outlet section and a tangent point G of an arc FG of the inlet section and a second straight line section GH of the inlet section, namely an optional range of throat tangent distance; the length of GH is determined empirically, and is preferably 1-2 times of the length of the throat height CH;
(3) determining molded lines of an upper wall surface and a lower wall surface of an outlet section of the supersonic velocity spray pipe by using a characteristic line method according to the height of a throat, the height of the outlet, the required Mach number of the outlet and the length of the outlet section;
preferably, the method further comprises the following steps after the step (3)
(4) In the selectable range of the throat cutting distance, under the condition of different throat cutting distances, based on given inlet pressure and outlet pressure, calculating a flow field of the spray pipe to obtain corresponding actual outlet Mach number curves under the condition of different throat cutting distances;
(5) determining a proper throat cutting distance according to the Mach number curve of the outlet in the step (4) and a set selection standard;
(6) the profile lines of the upper wall surface and the lower wall surface of the outlet section can be designed into two types, namely straight lines or curves, and under each combination condition of the profile lines of the upper wall surface and the lower wall surface of the outlet section, the flow field of the spray pipe is calculated based on the given inlet pressure and outlet pressure according to the determined proper throat tangential distance to obtain the corresponding actual outlet Mach number curve under each combination condition;
(7) determining the combination of the profile types of the upper wall surface and the lower wall surface of the outlet section according to the outlet Mach number curve in the step (6) and the set selection standard;
preferably, the preferable scheme in the specific design process further includes:
(1) the cross sections of the inlet section and the outlet section are rectangular and have the same width;
(2) the upper wall surface comprises a straight line segment AB, a curve segment BC and a curve segment CD, which are respectively tangent at a point B and a point C and are required to be smoothly connected, the curve segment BC is usually formed by two reverse arcs, and the curve segment CD is obtained by design calculation of a characteristic line method;
(3) the lower wall surface comprises a straight line section EF, an arc section FG and a straight line section GHI which are respectively tangent with the Gdian at the point F, and preferably required to be smoothly connected.
(4) The exit mach number is a dimensionless velocity of the gas stream at the exit, and is calculated as the exit mach number equal to the exit velocity divided by the exit sonic velocity, preferably as follows:
the Ma number is an outlet Mach number, V is an outlet speed, and a is an outlet sound speed;
(5) and the flow field is preferably calculated by adopting Fluent software to obtain a Mach number curve of the outlet. In the process of calculating the flow field, the inlet pressure is given according to the maximum pressure of the airflow which can be stably provided by the upstream equipment, and the inlet temperature is given according to the maximum temperature of the airflow which can be stably provided by the upstream equipment;
(6) the optimization standard of the design result is that the height range corresponding to the straight part of the variation curve of the Mach number of the outlet along with the height of the outlet is larger.
(7) The upper wall surface curve CD of the outlet section is a curve calculated according to a characteristic line method, and the characteristic line method is a general basic calculation method for solving the molded line of the spray pipe in aerodynamics.
(8) In the process of designing the spray pipe profile by using the characteristic line method, three parameters are mainly included: exit mach number, exit height, and maximum expansion angle. The Mach number and the height of the outlet are determined according to design requirements, and the maximum expansion angle is determined by designers according to the following two points: the Mach number uniformity of the flow field outlet and the length of the outlet section reserved for design in the design requirement are achieved. Generally, the smaller the maximum expansion angle, the more uniform the exit mach number, but the greater the exit section length. Thus, there is always an optimum maximum expansion angle for any one practical design requirement. In general, the optimum range of the maximum expansion angle is 4 ° to 15 °.
(9) The optimization of the outlet section upper and lower wall molded line combination mainly comprises two combinations, wherein one combination is that the upper and lower wall surfaces are molded lines, and the other combination is that the upper wall surface is a molded line and the lower wall surface is a straight line. In both combinations, the maximum expansion angle can be designed smaller when both the upper and lower walls are molded lines, so the convection field is better.
FIG. 2 shows a comparison of the distribution of the number of the nozzle exit flow fields Ma before and after the optimization of the inlet area;
the inlet section is preferably rectangular and the outlet section is preferably rectangular, the junction surfaces of the inlet section and the outlet section forming a throat.
The upper wall surface comprises a first arc line segment and a second arc line segment; two ends of arc line are connected
The shape of the lower wall surface is a third arc segment
Exit mach number, meaning: mach number of gas at exit location.
The length of the outlet section is the distance from the surface of the throat to the surface of the outlet.
As shown in FIG. 1, the invention provides a design method of a rectangular supersonic velocity spray pipe with a turning inlet and a high slenderness ratio, which comprises the following steps:
(1) determining the molded line of the inlet section of the spray pipe: and determining the molded line of the upper wall surface of the inlet section of the spray pipe from the inlet to the throat on the basis of the height of the inlet of the spray pipe, the height of the throat, the throat tangential distance, the arc radius of the lower wall surface of the inlet section and the included angle theta of the air flow in the flow direction of the inlet and the outlet.
(2) Determining the throat cutting distance: under the condition of meeting the design requirement, the distance GH between the intersection position H of the throat and the lower wall surface and the tangent point G of the third straight line segment of the inlet section and the arc of the lower wall surface of the inlet section is properly prolonged. The throat cutting distance GH is larger than or equal to the height CH of the throat, and is generally 1-2 times of CH.
(3) Determining the molded line of the expansion section of the spray pipe: the molded lines of the upper wall surface and the lower wall surface of the expansion section of the spray pipe are calculated by adopting a double-wall surface molded line design with the molded lines of the upper wall surface and the lower wall surface and utilizing a conventional design method of the supersonic velocity spray pipe, namely a characteristic line method. And smoothly connecting the molded line of the expansion section of the spray pipe with the molded line of the inlet section of the spray pipe at the throat to obtain the complete molded line of the spray pipe.
(4) And calculating a flow field by utilizing numerical simulation aiming at different throat tangential distances and profile parameters based on given inlet pressure and temperature, and performing comparison optimization through a calculation result.
(5) And comparing the calculation results under different throat tangential distances to determine the proper throat tangential distance.
(6) And comparing the calculation results of the single-wall molded line and the double-wall molded line to determine a proper molded line design result.
(7) Based on the design and optimization results, the rectangular supersonic velocity spray pipe suitable for the inlet with the turning and the high slenderness ratio is finally obtained. FIG. 3 illustrates the effect of the single wall expansion and double wall expansion designs of the present invention on the nozzle exit flow field Ma number distribution;
the preferable scheme of the invention is as follows: by adopting the design method related to the method, a long and narrow bend is required to be obtained, the Mach number of an outlet is 3.1, the bend angle theta is 77 degrees, the whole width of the spray pipe is 100mm, the inlet height is 10mm, the outlet height is 5mm, the length of the outlet section is 30mm, and the total distance from the end point I of the lower wall surface of the outlet of the spray pipe to the leftmost AB straight line section is not more than 50 mm.
According to known conditions, in the first step, according to the turning angle theta and the length of the outlet section, the horizontal length of the outlet section can be calculated, and then the length ranges of an arc section FG of the lower wall surface of the inlet section and a third straight line section GH can be estimated by combining the inlet height and the total distance limit;
secondly, calculating the throat height CH according to the outlet Mach number and the outlet height;
thirdly, according to the ranges of the throat heights CH, FG and GH, determining FG and GH according to experience, and completing the design of the lower wall surface;
the fourth step determines the location of points B and C (where AB is EF) based on the entrance height AE, throat height CH, arc FG and straight line segment GH. And the BC section is designed through two sections of circular arcs.
And fifthly, calculating a CD section curve by using a characteristic line method.
The upper wall curve ABCD and the lower wall curve EFGHI are obtained.
And calculating a flow field by using a fluid general calculation software Fluent, setting the pressure at an inlet AE to be preferably 2MPa and the temperature to be preferably 293K, and performing numerical calculation to obtain a curve of the Mach number of the outlet flow field along the height direction.
And changing the length of the throat cutting distance GH, repeating the design and calculation, and comparing outlet Mach number curves with different GH values, wherein the GH value corresponding to the result that the width corresponding to the straight section of the curve is larger is better.
And changing the form of CD and HI from the form that CD is a bent profile and HI is a straight line to the form that CD and HI are both bent profiles, wherein the design of the lower wall surface from F to H is changed from the mode of FG circular arc + GH straight line to an integral curve from F to H, and the smooth transition is ensured at the points F and H. The other design steps and calculation are repeated, and compared with the outlet Mach number curve obtained by calculation under the condition of different CD and HI combination forms, the outlet Mach number curve is better in the form that the double wall surfaces are both of the bent molded lines.
The invention has not been described in detail in part of the common general knowledge of those skilled in the art.
Claims (9)
1. A design method of a rectangular supersonic velocity spray pipe with a turning inlet and a high slenderness ratio is characterized by comprising the following steps:
(1) determining the shapes of the upper wall surface and the lower wall surface from the nozzle inlet to the throat on the basis of the inlet height of the inlet section, and the section curves of the upper wall surface and the lower wall surface along the spanwise direction;
(2) determining an optional range of the distance between the intersection position of the throat and the lower wall surface of the inlet section and the tangent point of the lower wall surface, namely an optional range of throat tangent distance;
(3) and determining the molded lines of the upper wall surface and the lower wall surface of the outlet section of the supersonic velocity spray pipe by using a characteristic line method according to the height of the throat, the height of the outlet, the required Mach number of the outlet and the length of the outlet section.
2. The design method of the rectangular supersonic velocity spray pipe with the turning inlet and the high slenderness ratio as the claim 1, is characterized in that: the method also comprises the following steps in sequence after the step (3):
(4) in the selectable range of the throat cutting distance, under the condition of different throat cutting distances, based on given inlet pressure and outlet pressure, calculating a flow field of the spray pipe to obtain corresponding actual outlet Mach number curves under the condition of different throat cutting distances;
(5) determining a proper throat cutting distance according to the Mach number curve of the outlet in the step (4) and a set selection standard;
(6) the profile lines of the upper wall surface and the lower wall surface of the outlet section can be designed into two types, namely straight lines or curves, and under each combination condition of the profile lines of the upper wall surface and the lower wall surface of the outlet section, the flow field of the spray pipe is calculated based on the given inlet pressure and temperature according to the determined proper throat tangential distance to obtain the corresponding actual outlet Mach number curve under each combination condition;
(7) and (4) determining the combination of the profile types of the upper wall surface and the lower wall surface of the outlet section according to the outlet Mach number curve in the step (6) and the set selection standard.
3. The method of claim 1 for designing a rectangular supersonic nozzle with a corner inlet and a high slenderness ratio is characterized in that: due to space constraints, the air flow cannot flow into the nozzle in a direction perpendicular to the cross-section of the nozzle throat, and therefore the inlet section of the nozzle needs to be arranged to turn.
4. The method of claim 1 for designing a rectangular supersonic nozzle with a corner inlet and a high slenderness ratio is characterized in that: the ratio of the length to the width of the rectangular supersonic nozzle outlet is called slenderness ratio, and a high slenderness ratio is adopted for generating a thin refrigeration air film.
5. The method of claim 1 for designing a rectangular supersonic nozzle with a corner inlet and a high slenderness ratio is characterized in that: the ratio of the maximum cross-sectional area of the inlet section of the spray pipe to the minimum cross-sectional area of the throat is a contraction ratio, and the contraction ratio is made as large as possible under the condition of space limitation, so that the flow field is more favorably stabilized.
6. The method of claim 1 for designing a rectangular supersonic nozzle with a corner inlet and a high slenderness ratio is characterized in that: the distance from the intersection point of the throat and the lower wall surface to the tangent point of the lower surface is called throat tangent distance, and the throat tangent distance is not too small and is at least more than one time of the height of the throat.
7. The method of claim 1 for designing a rectangular supersonic nozzle with a corner inlet and a high slenderness ratio is characterized in that: the expansion section of the spray pipe adopts upper and lower double-wall molded lines as much as possible, and the single-wall molded line is avoided.
8. The design method of the rectangular supersonic nozzle with the turning inlet and the high slenderness ratio as claimed in one of the claims 1 to 6, characterized in that: the expansion angle of the single-wall molded line is decomposed to the upper wall and the lower wall without changing the sizes of the throat and the outlet, so that the effect of reducing the expansion angle is achieved, the transverse movement amplitude of the airflow in the expansion process is small, and the flow field is more stable.
9. A rectangular supersonic nozzle configuration with a turning inlet and a high slenderness ratio is characterized by comprising: an inlet section and an outlet section; the connecting surface of the inlet section and the outlet section is used as a throat; the inlet section comprises an upper wall surface and a lower wall surface; the outlet section comprises an upper wall surface and a lower wall surface; the distance between the intersection position H of the throat CH and the lower wall surface HI of the outlet section and the tangent point G of the second straight line segment GH of the inlet section and the arc FG of the lower wall surface of the inlet section is used as throat tangent distance;
the upper wall surface of the inlet section comprises an inlet first straight line section AB and an inlet first curve section BC which are connected at a point B in a smooth and sliding manner, and the lower wall surface of the inlet section comprises an inlet second straight line section EF, an inlet circular arc section FG and an inlet third straight line section GH;
the upper wall of the outlet section comprises a curved section CD and the lower wall of the outlet section comprises a straight section HI.
Priority Applications (1)
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| CN112035952A (en) * | 2020-08-21 | 2020-12-04 | 南京航空航天大学 | Design method of ejector nozzle experimental device for simulating outflow of aircraft |
| CN112591134A (en) * | 2020-12-24 | 2021-04-02 | 中国航空工业集团公司西安飞机设计研究所 | Design method for section of air inlet of nacelle |
| CN112727634A (en) * | 2020-12-07 | 2021-04-30 | 西安航天动力研究所 | Rectangular cross-section spray pipe |
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