Gas collection structure, turbine pump and rocket engine

Abstract

The invention provides a gas collection structure, a turbine pump and a rocket engine. The gas collecting structure comprises a gas collecting ring and a nozzle disc, the gas collecting ring comprises an annular body and a gas inlet formed in the outer wall of the annular body, and a gas collecting groove communicated with the gas inlet is formed in one side of the annular body; the nozzle disc covers a notch of the gas collecting groove, a plurality of nozzles are arranged on the nozzle disc, inlet ends of the nozzles are communicated with the gas inlet, outlet ends of the nozzles are configured to be communicated with the turbine, the nozzles comprise a group of first nozzles and a group of second nozzles, and the second nozzles are far away from the gas inlet relative to the first nozzles; the cross-sectional area of the inlet end of the first nozzle is smaller than that of the inlet end of the second nozzle, and the cross-sectional area of the outlet end of the first nozzle is smaller than that of the outlet end of the second nozzle, so that the airflow attack angles of the first nozzle and the second nozzle at the outlet ends are equal or the difference value of the airflow attack angles is smaller than a design threshold value. The circumferential uniformity of airflow sprayed out of the nozzle disc can be improved, and the turbine efficiency is improved.

Description

Technical Field

[0001] The present application relates to the technical field of turbine nozzles, and more specifically, to an air collecting structure, a turbine pump, and a rocket engine. Background Art

[0002] The turbopump is a key component of a pump-type liquid rocket engine. It's a linkage device that uses a turbine to drive a pump, thereby pressurizing the propellant. The turbopump's operating principle is primarily that the gas blown from the gas generator drives the turbine, which in turn drives the coaxial pump, pressurizing the fuel and oxidizer and injecting them into the thrust chamber for combustion.

[0003] The turbopump's air inlet is equipped with a gas collecting ring, which connects to a nozzle disk with multiple nozzles arranged evenly around the circumference. When the gas passes through the gas collecting ring and enters the nozzle inlets, the velocity distribution at the inlet is asymmetrical along the circumference, with higher velocities near the gas collecting ring inlet. Furthermore, the gas velocity constantly changes as it flows through the flow channel within the casing. This results in inconsistent angles of attack for the turbine nozzles at different locations at the turbine inlet, reducing turbine efficiency. Summary of the Invention

[0004] In view of the shortcomings of the existing methods, the present application proposes an air collection structure, a turbopump and a rocket engine to solve the technical problem of inconsistent turbine attack angles of nozzles at different positions at the turbine inlet in the related art.

[0005] In a first aspect, an embodiment of the present application provides a gas collecting structure, comprising: An air collecting ring, comprising an annular body and an air inlet provided on an outer wall of the annular body, an air collecting groove formed on one side of the annular body, and the air inlet being in communication with the air collecting groove; A nozzle disk covers the slot of the air collecting groove, and a plurality of nozzles are provided on the nozzle disk. The plurality of nozzles are distributed at intervals around the circumference of the nozzle disk, the inlet end of the nozzle is connected to the air inlet, and the outlet end of the nozzle is constructed to be connected to the turbine. The plurality of nozzles include a group of first nozzles and a group of second nozzles, the second nozzles are away from the air inlet relative to the first nozzle, the cross-sectional area of ​​the inlet end of the first nozzle is smaller than the cross-sectional area of ​​the inlet end of the second nozzle, and the cross-sectional area of ​​the outlet end of the first nozzle is smaller than the cross-sectional area of ​​the outlet end of the second nozzle, so that the airflow attack angle of the first nozzle and the second nozzle at the outlet end, or the difference in the airflow attack angle, is smaller than the design threshold.

[0006] Optionally, the first nozzles include at least two, and the at least two first nozzles are arranged on both sides close to the air inlet.

[0007] Optionally, a group of the first nozzles occupies an angle ranging from 30 degrees to 60 degrees corresponding to the arc length of the circumference of the nozzle plate.

[0008] Optionally, the cross-sectional areas of the inlet ends of the plurality of first nozzles are equal, and the cross-sectional areas of the outlet ends of the plurality of first nozzles are equal.

[0009] Optionally, the first angle between two adjacent first nozzles is equal to the second angle between two adjacent second nozzles, the first angle is the angle formed by the axis of the nozzle disk and the line connecting the axis of the two adjacent first nozzles, and the second angle is the angle formed by the axis of the nozzle disk and the line connecting the axis of the two adjacent second nozzles.

[0010] Optionally, the circumferential spacing between two adjacent first nozzles is greater than the circumferential spacing between two adjacent second nozzles; The circumferential distance between two adjacent first nozzles is equal, and the circumferential distance between two adjacent second nozzles is equal.

[0011] Optionally, the circumferential spacing between two adjacent first nozzles is proportional to the radius of the nozzle disk and inversely proportional to the number of the nozzles.

[0012] Optionally, the gas collecting structure further comprises at least one of the following: The nozzle comprises a contraction section, a narrow throat section, and an expansion section which are sequentially away from the air inlet, the inlet end is located at an end of the contraction section away from the narrow throat section, and the outlet end is located at an end of the expansion section away from the narrow throat section; The axis of the first nozzle inlet end is parallel to the axis of the second nozzle inlet end, and the axis of the first nozzle outlet end is parallel to the axis of the second nozzle outlet end.

[0013] In a second aspect, an embodiment of the present application provides a turbo pump, comprising: a turbine pump housing having a turbine disposed therein; a pump connected to the turbine shaft; As described in the above embodiment, the air collecting structure includes an air inlet, which is constructed to be connected to the combustion chamber of the rocket engine. The air collecting structure includes a nozzle disk and a plurality of nozzles arranged circumferentially around the nozzle disk. The outlet end of the nozzle is connected to the turbine pump housing, so that the air flow generated by the combustion in the combustion chamber flows through the air collecting structure to the turbine pump housing to drive the turbine to rotate.

[0014] In a third aspect, an embodiment of the present application provides a rocket engine, comprising: a combustion chamber containing an air flow generated by combustion; And, the turbopump as described in the above embodiment is connected to the combustion chamber.

[0015] The beneficial technical effects brought about by the technical solutions provided in the embodiments of the present application include: In an embodiment of the present application, by designing multiple nozzles on the nozzle disk, the cross-sectional area of ​​a group of first nozzles relatively close to the air inlet of the gas collecting ring is reduced, including the cross-sectional area of ​​the inlet end and the cross-sectional area of ​​the outlet end of the first nozzle, or the cross-sectional area of ​​the inlet end and the cross-sectional area of ​​the outlet end of a group of second nozzles relatively far from the air inlet of the gas collecting ring are both increased, so that the cross-sectional area of ​​the inlet end of the first nozzle is smaller than the cross-sectional area of ​​the inlet end of the second nozzle, and the cross-sectional area of ​​the outlet end of the first nozzle is smaller than the cross-sectional area of ​​the outlet end of the second nozzle, so that the airflow velocity in the first nozzle relatively close to the air inlet of the gas collecting ring can be reduced, or the airflow velocity in the second nozzle relatively far from the air collecting ring inlet can be increased, so that the airflow velocities of the gas flow flowing into the first nozzle and the second nozzle through the air inlet of the gas collecting ring are equal, and when the airflow flows into the turbine from the outlet ends of the first nozzle and the second nozzle, the airflow attack angles of the first nozzle and the second nozzle at the outlet end can be equal, or the difference between the airflow attack angles of the first nozzle and the second nozzle at the outlet end can be less than the design threshold, thereby improving the turbine efficiency.

[0016] Additional aspects and advantages of the present application will be given in part in the following description, which will become apparent from the following description, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which: Figure 1 A schematic structural diagram of a gas collecting structure provided in an embodiment of the present application; Figure 2 A schematic structural diagram of the annular body provided in an embodiment of the present application; Figure 3 A schematic diagram of the structure of the nozzle plate at the inlet end provided in an embodiment of the present application; Figure 4 This is a schematic structural diagram of the nozzle plate at the outlet end provided in an embodiment of the present application. Description of the accompanying drawings: 10-gas collecting ring; 11-annular body; 12-gas inlet; 13-gas collecting groove; 131-first channel; 132-second channel; 20 - nozzle plate; 21 - nozzle; 211 - first nozzle; 212 - second nozzle; 201 - inlet end; 202 - outlet end. DETAILED DESCRIPTION

[0018] The following describes the embodiments of the present application in conjunction with the accompanying drawings. It should be understood that the embodiments described below in conjunction with the accompanying drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0019] Those skilled in the art will understand that, unless otherwise stated, the terms "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of this application refers to the presence of the described features, integers, steps, operations, elements and / or components, but does not exclude the implementation of other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" can be implemented as "A", or as "B", or as "A and B".

[0020] In order to make the objectives, technical solutions and advantages of this application clearer, the implementation methods of this application will be further described in detail below with reference to the accompanying drawings.

[0021] First, a few words of technical jargon.

[0022] The turbopump is a key component of a pump-type liquid rocket engine. It's a linkage device that uses a turbine to drive a pump, thereby pressurizing the propellant. The turbopump's operating principle is primarily that the gas blown from the gas generator drives the turbine, which in turn drives the coaxial pump, pressurizing the fuel and oxidizer and injecting them into the thrust chamber for combustion.

[0023] Turbine efficiency: The ratio of input energy to useful work during the operation of the turbine.

[0024] Shock wave: A strong compression wave formed in supersonic gas, also called a shock wave.

[0025] In related technologies, a gas collecting ring is installed at the turbine pump's air inlet, connecting to a nozzle disk with multiple nozzles arranged evenly around the circumference. When the gas passes through the gas collecting ring and enters the nozzle inlets, the velocity distribution at the inlet is asymmetrical along the circumference, with higher velocities near the gas collecting ring inlet. Furthermore, the gas velocity constantly fluctuates as it flows along the flow path within the casing, resulting in uneven circumferential airflow at the turbine inlet and inconsistent turbine angles of attack for nozzles at different locations, which reduces turbine efficiency.

[0026] Reference Figures 1-4 The embodiment of the present application provides an air collection structure to solve the technical problem mentioned above that the airflow ejected from the nozzles 21 at different positions at the turbine inlet is not uniform, resulting in inconsistent turbine attack angles of the nozzles 21 at different positions.

[0027] Reference Figure 1 The gas collecting structure of the present application includes a gas collecting ring 10 and a nozzle disk 20 arranged on one side of the gas collecting ring 10.

[0028] Reference Figure 2 The gas collecting ring 10 includes an annular body 11 and an air inlet 12 arranged on the outer wall of the annular body 11 . A gas collecting groove 13 is formed on one side of the annular body 11 , and the air inlet 12 is connected to the gas collecting groove 13 .

[0029] Reference Figures 1-4 The nozzle disk 20 fits over the notch of the gas collecting groove 13. Multiple nozzles 21 are provided on the nozzle disk 20, spaced apart circumferentially around the nozzle disk 20. The inlet ends 201 of the multiple nozzles 21 are connected to the air inlet 12 of the gas collecting ring 10, and the outlet ends 202 of the multiple nozzles 21 are configured to communicate with the turbine. The multiple nozzles 21 include a set of first nozzles 211 and a set of second nozzles 212. The set of first nozzles 211 includes at least one nozzle, and the set of second nozzles 212 includes a plurality of nozzles. The second nozzles 212 are located farther from the air inlet 12 than the first nozzles 211. The cross-sectional area of ​​the inlet end 201 of the first nozzle 211 is smaller than that of the inlet end 201 of the second nozzle 212, and the cross-sectional area of ​​the outlet end 202 of the first nozzle 211 is smaller than that of the second nozzle 212. This ensures that the airflow angles of attack at the outlet ends 202 of the first and second nozzles 211 and 212 are equal, or the difference in angles of attack is less than a design threshold.

[0030] The airflow attack angle of the nozzle 21 generally refers to the angle between the geometric axis of the nozzle 21 and the actual airflow direction entering the nozzle 21. When the airflow attack angles of multiple nozzles 21 are inconsistent, part of the airflow will be separated, thereby reducing the turbine efficiency.

[0031] The embodiment of the present application performs matching design of the nozzle 21 based on the simulation results of the turbine design point operating conditions, and adjusts the areas of the inlet end 201 and the outlet end 202 of the nozzle 21 according to the size of the incoming flow velocity (i.e., the velocity of the airflow when it flows into the nozzle inlet end). It is known that the incoming flow velocity is proportional to the area of ​​the nozzle 21, that is, (Expression 1) In expression 1, represents the incoming flow velocity, represents the nozzle area, and k represents a constant.

[0032] Based on the above-mentioned proportional relationship between the air flow velocity and the area of ​​the nozzle 21, the present application designs the multiple nozzles 21 on the nozzle plate 20, reduces the cross-sectional area of ​​a group of first nozzles 211 relatively close to the air inlet 12 of the gas collecting ring 10, including the cross-sectional area of ​​the inlet end 201 and the cross-sectional area of ​​the outlet end 202 of the first nozzle 211, or increases the cross-sectional area of ​​the inlet end 201 and the cross-sectional area of ​​the outlet end 202 of a group of second nozzles 212 relatively far from the air inlet 12 of the gas collecting ring 10, thereby making the cross-sectional area of ​​the inlet end 201 of the first nozzle 211 smaller than the cross-sectional area of ​​the inlet end 201 of the second nozzle 212, and the cross-sectional area of ​​the outlet end 202 of the first nozzle 211 smaller than the cross-sectional area of ​​the outlet end 202 of the second nozzle 212. The cross-sectional area of ​​202 can reduce the air flow velocity in the first nozzle 211 which is relatively close to the air inlet 12 of the gas collecting ring 10, or increase the air flow velocity in the second nozzle 212 which is relatively far from the inlet of the gas collecting ring 10, so that the air flow velocities of the fuel gas flow flowing into the first nozzle 211 and the second nozzle 212 through the air inlet 12 of the gas collecting ring 10 are equal. When the air flow flows into the turbine from the outlet end 202 of the first nozzle 211 and the second nozzle 212, the air flow attack angles of the first nozzle 211 and the second nozzle 212 at the outlet end 202 can be equal, or the difference between the air flow attack angles of the first nozzle 211 and the second nozzle 212 at the outlet end 202 can be less than the design threshold, thereby improving the turbine efficiency.

[0033] It should be noted that the cross-sectional area of ​​the inlet end 201 of the nozzle 21 (including the first nozzle 211 and the second nozzle 212) represents the area of ​​a plane cut at the inlet end 201 of the nozzle 21 with a first plane perpendicular to the extension direction of the inlet end 201 of the nozzle 21; the cross-sectional area of ​​the outlet end 202 of the nozzle 21 represents the area of ​​a plane cut at the outlet end 202 of the nozzle 21 with a second plane perpendicular to the extension direction of the outlet end 202 of the nozzle 21.

[0034] Optionally, refer to Figure 3 The first nozzles 211 include at least two, and the at least two first nozzles 211 are arranged on both sides close to the air inlet 12 .

[0035] Because the nozzle plate 20 covers the notch of the gas collecting groove 13, the gas collecting groove 13 and the inner wall of the nozzle plate 20 enclose an airflow channel that connects to both the air inlet 12 and the nozzle 21. The airflow channel includes a first channel 131 and a second channel 132 distributed along the circumference of the airflow channel. The first end of the first channel 131 is connected to the first end of the second channel 132. A connecting point between the first channel 131 and the second channel 132 is connected to the air inlet 12, so that a first portion of the airflow from the combustion chamber flows into the first channel 131, and a second portion flows into the second channel 132.

[0036] The present application distributes at least two first nozzles 211 on both sides of the air inlet 12 of the gas collecting ring 10, wherein at least one first nozzle 211 corresponds to the first channel 131, and at least one first nozzle 211 corresponds to the second channel 132, so that the gas flow flowing in from the air inlet 12 can be bidirectionally fed, thereby improving the flow efficiency of the gas flow in the air flow channel, and improving the circumferential uniformity of the air flow ejected from the outlet end 202 of the nozzle disk 20.

[0037] This application is described by taking an example in which five first nozzles 211 are provided on the nozzle plate 20 and ten second nozzles 212 are provided on the nozzle plate 20 .

[0038] Optionally, refer to Figure 3 The angle range corresponding to the arc length of the circumference of the nozzle plate 20 occupied by a group of first nozzles 211 is 30 degrees to 60 degrees.

[0039] In the present application, the circumferential angle corresponding to the circumferential arc length occupied by the first nozzle 211 on the nozzle disk 20 is defined as θ. According to the simulation results of the turbine design point operating conditions, it can be seen that in the area where the circumferential angles corresponding to the circumferential arc lengths on both sides of the air inlet 12 of the air collecting ring 10 are approximately 15 degrees to 30 degrees, the air flow velocity of the nozzle 21 is relatively large. Therefore, the embodiment of the present application specifically designs the nozzle 21 in the area where the circumferential angles on both sides of the air inlet 12 of the air collecting ring 10 are 15 degrees to 30 degrees (the total angle range of the occupied nozzle disk 20 is 30 degrees to 60 degrees), so that the fluid can be more evenly distributed when entering the turbine pump or combustion chamber, thereby improving the stability of the fluid flow and reducing shock waves and unnecessary energy losses.

[0040] The size of the nozzle 21 is affected by the pressure distribution in front of the nozzle 21. The area of ​​the inlet end 201 of the nozzle 21 is calculated according to the following formula: (Expression 2) In Expression 2, A is the area of ​​the nozzle; is the flow rate in the gas gathering ring; is the gas pressure at the nozzle inlet; is the gas specific volume at the nozzle inlet; is the gas pressure at any cross section in the nozzle channel, is the gas adiabatic index.

[0041] From the analysis of expression 2, we can see that: (Expression 3) Expression 3 shows that when the gas pressure at the inlet end 201 of the nozzle 21 is higher, the area of ​​the nozzle 21 needs to be reduced to maintain flow balance.

[0042] (Expression 4) Expression 4 shows that when the gas specific volume (gas expansion degree) at the inlet end 201 is larger, the area of ​​the nozzle 21 needs to be expanded to reduce the flow rate.

[0043] The size of the nozzle 21 is nonlinearly related to the area of ​​the nozzle 21 and needs to be dynamically adjusted according to the flow state (subsonic / supersonic). For the area with the same pressure at the inlet end 201 of the nozzle 21, the size of the nozzle 21 is designed to be the same.

[0044] Optionally, refer to Figure 3-Figure 4 The cross-sectional areas of the inlet ends 201 of the plurality of first nozzles 211 are equal, and the cross-sectional areas of the outlet ends 202 of the plurality of first nozzles 211 are equal.

[0045] Through the simulation of the turbine design point operating conditions of the embodiment of the present application, it can be known that the pressure at the inlet end 201 of the first nozzle 211 is in the area of ​​±0.5 MPa (megapascals). At this time, the cross-sectional areas of the inlet ends 201 of multiple first nozzles 211 can be designed to be the same, and the cross-sectional areas of the outlet ends 202 of multiple first nozzles 211 can also be the same, thereby making the airflow ejected from the first nozzle 211 and the second nozzle 212 at the outlet end 202 more uniform, and ensuring that the airflow attack angles of each group of airflows of the first nozzle 211 and the second nozzle 212 at the outlet end 202 are equal, or the difference between the airflow attack angles of the first nozzle 211 and the second nozzle 212 at the outlet end 202 is less than the design threshold.

[0046] Optionally, a first angle between two adjacent first nozzles 211 is equal to a second angle between two adjacent second nozzles 212. The first angle is the angle formed by a line connecting the axis of the nozzle plate 20 and the axis of the two adjacent first nozzles 211, and the second angle is the angle formed by a line connecting the axis of the nozzle plate 20 and the axis of the two adjacent second nozzles 212.

[0047] Reference Figure 4 In the embodiment of the present application, the first angle between two adjacent first nozzles 211 is β, and the second angle between two adjacent second nozzles 212 is α. Designing the first angle β between two adjacent first nozzles 211 to be equal to the second angle α between two adjacent second nozzles 212 ensures that, after the gas flow expands and accelerates through the first and second nozzles 211, 212, its velocity at the outlets 202 of the first and second nozzles 211, 212 is consistent. This results in a more uniform circumferential velocity of the gas ejected from the multiple nozzles 21 on the nozzle plate 20, significantly improving the uniformity of the gas flow distribution and thereby reducing impact losses or gas separation losses.

[0048] Optionally, refer to Figure 4The circumferential spacing between two adjacent first nozzles 211 is greater than the circumferential spacing between two adjacent second nozzles 212. The circumferential spacing between two adjacent first nozzles 211 is equal, and the circumferential spacing between two adjacent second nozzles 212 is equal.

[0049] It should be noted that the circumferential spacing between two adjacent first nozzles 211 in this application refers to the spacing between the centers of adjacent first nozzles 211 along the circumference of the nozzle plate 20, which is usually calculated as arc length. The same applies to the circumferential spacing between two adjacent second nozzles 212.

[0050] In the embodiment of the present application, the circumferential spacing between the first nozzles 211 with smaller sizes is designed to be larger than the circumferential spacing between two adjacent second nozzles 212 with larger sizes. This allows the centers of the first nozzles 211 and the second nozzles 212 to be evenly distributed on the nozzle disk 20, thereby significantly optimizing the uniformity of the circumferential airflow velocity on the nozzle disk 20.

[0051] Optionally, the distance between two adjacent first nozzles 211 is proportional to the radius of the nozzle plate 20 and inversely proportional to the number of the nozzles 21 .

[0052] The circumferential spacing between adjacent first nozzles 211 (or second nozzles 212) is applicable to the following formula: (Expression 5) Wherein, L is the circumferential spacing between adjacent nozzles; is the dispersion; D is the turbine median diameter; n is the number of nozzles.

[0053] Since the turbine mid-diameter is proportional to the radius of the nozzle disk 20, it can be concluded that the circumferential spacing between two adjacent first nozzles 211 is proportional to the turbine mid-diameter and inversely proportional to the total number of nozzles 21; the circumferential spacing between two adjacent second nozzles 212 is proportional to the turbine mid-diameter and inversely proportional to the total number of nozzles 21.

[0054] In the embodiment of this application, it is necessary to ensure <1, it avoids the first nozzle 211 and the second nozzle 212 from overlapping or being arranged apart on the nozzle plate 20, thereby improving the uniformity of the circumferential airflow velocity on the nozzle plate 20.

[0055] Optionally, the nozzle 21 includes a contraction section, a narrow throat section and an expansion section which are sequentially away from the air inlet 12 , the inlet end 201 is located at the end of the contraction section away from the narrow throat section, and the outlet end 202 is located at the end of the expansion section away from the narrow throat section.

[0056] The cross-sectional area of ​​the nozzle 21 changes continuously from the inlet end 201 to the outlet end 202, and the flow speed of the airflow in the nozzle 21 also changes due to the change of the cross-sectional area at different positions, so that the airflow is accelerated from subsonic to sonic and finally to supersonic.

[0057] Optionally, the axis of the inlet end 201 of the first nozzle 211 is parallel to the axis of the inlet end 201 of the second nozzle 212 , and the axis of the outlet end 202 of the first nozzle 211 is parallel to the axis of the outlet end 202 of the second nozzle 212 .

[0058] In the embodiment of the present application, by rationally arranging multiple nozzles 21 and ensuring that their axes at the inlet end 201 are parallel, and their axes at the outlet end 202 are also parallel, the fluid entering the turbine pump can be more evenly distributed, flow resistance and turbulence can be reduced, and the pressure balance of the fluid flowing into and out of the turbine pump can be better ensured, thereby improving the overall fluid transmission efficiency.

[0059] Based on the same inventive concept, the present application also provides a turbine pump (not shown in the figure), including a turbine pump housing, a pump and the gas collecting structure described in the above embodiment.

[0060] A turbine is housed within the turbopump housing; the pump and turbine are axially connected. The gas collection structure includes an air inlet 12, which is configured to communicate with the rocket engine's combustion chamber. The gas collection structure includes a nozzle disk 20 and multiple nozzles 21 arranged circumferentially around the nozzle disk 20. The outlet ends 202 of the nozzles 21 communicate with the turbopump housing, allowing the airflow generated by combustion in the combustion chamber to flow through the gas collection structure into the turbopump housing, driving the turbine.

[0061] The embodiment of the present application adopts the air collecting structure of the above-mentioned embodiment. By carrying out targeted design of some nozzles 21 on the nozzle disk 20 in the air collecting structure, the multiple groups of air flows flowing from the outlet end 202 of the nozzle disk 20 into the turbine are more uniform, thereby making the turbine pump of the embodiment of the present application have higher turbine efficiency.

[0062] Based on the same inventive concept, the present application also provides a rocket engine (not shown in the figure), including a combustion chamber and the turbopump described in the above embodiment.

[0063] There is an airflow generated by combustion in the combustion chamber, and the turbine pump is communicated with the combustion chamber.

[0064] The rocket engine of the present application embodiment utilizes a turbopump with higher turbine efficiency. This high-efficiency turbopump can more effectively pump fuel and oxidizer into the combustion chamber. With the same input energy, higher pressures and flow rates can be achieved, thereby enhancing combustion efficiency and ultimately improving the overall propulsion efficiency of the rocket engine.

[0065] The beneficial technical effects brought about by the technical solutions provided in the embodiments of the present application include: By designing the multiple nozzles 21 on the nozzle plate 20, the cross-sectional area of ​​a group of first nozzles 211 relatively close to the air inlet 12 of the gas collecting ring 10 is reduced, including the cross-sectional area of ​​the inlet end 201 and the cross-sectional area of ​​the outlet end 202 of the first nozzle 211, or the cross-sectional area of ​​the inlet end 201 and the cross-sectional area of ​​the outlet end 202 of a group of second nozzles 212 relatively far from the air inlet 12 of the gas collecting ring 10 are increased, so that the cross-sectional area of ​​the inlet end 201 of the first nozzle 211 is smaller than the cross-sectional area of ​​the inlet end 201 of the second nozzle 212, and the cross-sectional area of ​​the outlet end 202 of the first nozzle 211 is smaller than the cross-sectional area of ​​the outlet end 202 of the second nozzle 212, thereby The air flow velocity in the first nozzle 211 which is relatively close to the air inlet 12 of the gas collecting ring 10 can be reduced, or the air flow velocity in the second nozzle 212 which is relatively far from the inlet of the gas collecting ring 10 can be increased, so that the air flow velocities of the gas flow flowing into the first nozzle 211 and the second nozzle 212 through the air inlet 12 of the gas collecting ring 10 are equal. When the air flow flows into the turbine from the outlet end 202 of the first nozzle 211 and the second nozzle 212, the air flow attack angles of the first nozzle 211 and the second nozzle 212 at the outlet end 202 can be equal, or the difference between the air flow attack angles of the first nozzle 211 and the second nozzle 212 at the outlet end 202 can be less than the design threshold, thereby improving the turbine efficiency.

[0066] The first angle between two adjacent first nozzles 211 is designed to be equal to the second angle between two adjacent second nozzles 212, which can ensure as much as possible that the gas flow, after expanding and accelerating through the first nozzle 211 and the second nozzle 212, reaches the same gas flow velocity at the outlet end 202 of the first nozzle 211 and the second nozzle 212, so that the circumferential velocity of the multiple nozzles 21 on the nozzle plate 20 is relatively uniform, which significantly improves the uniformity of the gas flow distribution, thereby reducing the impact loss or gas separation loss.

[0067] The distance between two adjacent first nozzles 211 is proportional to the radius of the nozzle disk 20 and inversely proportional to the number of nozzles 21, and ensures that γ<1, thereby avoiding the first nozzles 211 and the second nozzles 212 from overlapping or being arranged apart on the nozzle disk 20, thereby improving the uniformity of the circumferential airflow velocity on the nozzle disk 20.

[0068] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0069] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. Throughout this application, unless otherwise specified, "plurality" means two or more.

[0070] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to direct connections, indirect connections through an intermediate medium, or internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0071] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0072] The above is only part of the implementation methods of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the solution of the present application, other similar implementation methods based on the technical ideas of the present application also fall within the protection scope of the embodiments of the present application.

Claims

1. A gas collecting structure, characterized in that: include: An air collecting ring, comprising an annular body and an air inlet provided on an outer wall of the annular body, an air collecting groove formed on one side of the annular body, and the air inlet being in communication with the air collecting groove; A nozzle disk covers the slot of the air collecting groove, and a plurality of nozzles are provided on the nozzle disk. The plurality of nozzles are distributed at intervals around the circumference of the nozzle disk, the inlet end of the nozzle is connected to the air inlet, and the outlet end of the nozzle is constructed to be connected to the turbine. The plurality of nozzles include a group of first nozzles and a group of second nozzles, the second nozzles are away from the air inlet relative to the first nozzle, the cross-sectional area of ​​the inlet end of the first nozzle is smaller than the cross-sectional area of ​​the inlet end of the second nozzle, and the cross-sectional area of ​​the outlet end of the first nozzle is smaller than the cross-sectional area of ​​the outlet end of the second nozzle, so that the airflow attack angles of the first nozzle and the second nozzle at the outlet end are equal, or the difference in the airflow attack angles is smaller than the design threshold.

2. The gas collecting structure according to claim 1, characterized in that: The first nozzles include at least two, and the at least two first nozzles are arranged on both sides close to the air inlet.

3. The gas collecting structure according to claim 2, characterized in that: The angle range corresponding to the arc length of the circumference of the nozzle plate occupied by a group of the first nozzles is 30 degrees to 60 degrees.

4. The gas collecting structure according to claim 1, characterized in that: The cross-sectional areas of the inlet ends of the plurality of first nozzles are equal, and the cross-sectional areas of the outlet ends of the plurality of first nozzles are equal.

5. The gas collecting structure according to claim 2, characterized in that: The first angle between two adjacent first nozzles is equal to the second angle between two adjacent second nozzles. The first angle is the angle formed by the axis of the nozzle disk and the line connecting the axis of the two adjacent first nozzles. The second angle is the angle formed by the axis of the nozzle disk and the line connecting the axis of the two adjacent second nozzles.

6. The gas collecting structure according to claim 1, characterized in that: The circumferential spacing between two adjacent first nozzles is greater than the circumferential spacing between two adjacent second nozzles; The circumferential distance between two adjacent first nozzles is equal, and the circumferential distance between two adjacent second nozzles is equal.

7. The gas collecting structure according to claim 6, characterized in that: The circumferential distance between two adjacent first nozzles is proportional to the radius of the nozzle plate and inversely proportional to the number of the nozzles.

8. The gas collecting structure according to claim 1, characterized in that: Also includes at least one of the following: The nozzle comprises a contraction section, a narrow throat section, and an expansion section which are sequentially away from the air inlet, the inlet end is located at an end of the contraction section away from the narrow throat section, and the outlet end is located at an end of the expansion section away from the narrow throat section; The axis of the first nozzle inlet end is parallel to the axis of the second nozzle inlet end, and the axis of the first nozzle outlet end is parallel to the axis of the second nozzle outlet end.

9. A turbo pump, characterized in that: include: a turbine pump housing having a turbine disposed therein; a pump connected to the turbine shaft; The air collecting structure according to any one of claims 1 to 8, wherein the air collecting structure includes an air inlet, wherein the air inlet is configured to be connected to a combustion chamber of a rocket engine, and the air collecting structure includes a nozzle disk and a plurality of nozzles arranged circumferentially around the nozzle disk, wherein the outlet end of the nozzle is connected to the turbine pump housing, so that the airflow generated by the combustion in the combustion chamber flows through the air collecting structure into the turbine pump housing to drive the turbine to rotate.

10. A rocket engine, characterized in that: include: a combustion chamber containing an air flow generated by combustion; And, the turbopump according to claim 9, wherein the turbopump is in communication with the combustion chamber.

Images