A guide structure of a turbine pump exhaust ring cavity
By using a specially designed vertical support plate and circumferential flow guide structure in the exhaust ring cavity of the turbopump, the gas passage is separated into upper and lower chambers, which solves the problem of large gas flow loss and improves the performance of the rocket engine.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- NORTHWESTERN POLYTECHNICAL UNIV
- Filing Date
- 2026-03-26
- Publication Date
- 2026-05-29
AI Technical Summary
Existing turbopumps suffer significant gas flow losses in the exhaust ring chamber, leading to a decrease in gas pressure entering the thrust chamber and affecting engine performance.
Multiple first and second vertical support plates and a circumferential flow guide structure are used, designed with a specific included angle and radius ratio, to separate the exhaust ring cavity into upper and lower chambers, thereby reducing the influence of swirling flow and weakening the flow around the circumference.
Significantly reduce gas flow loss and improve rocket engine performance.
Smart Images
Figure CN122106940A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of pumping device technology, and in particular to a flow guiding structure for the exhaust ring cavity of a turbopump. Background Technology
[0002] The turbopump is a core component of a liquid rocket engine, directly impacting its overall performance and reliability. In staged combustion cycle engines, the high-temperature, high-pressure combustion gas generated in the pre-combustion chamber performs work on the turbine rotor of the turbopump before being introduced into the thrust chamber via the exhaust ring cavity. For cantilevered turbopump layouts, the gas flow direction needs to be deflected by 90° within the exhaust ring cavity, resulting in significant flow losses and a reduction in the gas pressure entering the thrust chamber, thus affecting engine performance.
[0003] Most existing turbopumps incorporate vertical support plates within the exhaust ring chamber to guide the gas flow, reducing flow losses caused by gas swirl and propelling the gas towards the exhaust outlet. This also enhances the axial stiffness of the turbopump assembly. Furthermore, most existing turbopumps optimize the cross-sectional shape of the exhaust ring chamber, with the cross-sectional area gradually increasing from the inside to the exhaust outlet to prevent gas accumulation within the exhaust ring chamber.
[0004] However, the existing turbopump structure is unable to reduce the mixed effects of the main and secondary gas flows, and there is strong flow around the exhaust ring cavity in the vertical section, resulting in a large flow loss of the gas and limiting further improvement of engine performance. Summary of the Invention
[0005] This application provides a flow guiding structure for the exhaust ring cavity of a turbopump, which solves the technical problem of large flow loss of gas in the exhaust ring cavity and low gas pressure when entering the thrust chamber, resulting in reduced engine performance.
[0006] This application provides a flow guiding structure for the exhaust annular cavity of a turbopump. The flow guiding structure includes: a plurality of first vertical support plates, which are spaced apart around the central axis of the exhaust annular cavity, with their two ends connected to the top and bottom walls of the exhaust housing, respectively; wherein each first vertical support plate is offset from the radial direction of the exhaust annular cavity towards the thrust chamber by a first preset angle; a second vertical support plate, with its two ends connected to the top and bottom walls of the exhaust housing, and extending along the axis of the thrust chamber; and a circumferential flow guiding structure, which is connected to the plurality of first vertical support plates and the second vertical support plate, extends along the exhaust annular cavity and protrudes towards the bottom wall of the exhaust housing, with the leading edge of the circumferential flow guiding structure located at the gas inlet of the exhaust housing.
[0007] In one possible implementation, the front edge radius of the first vertical support plate is a first preset multiple of the rear edge radius of the first vertical support plate.
[0008] In one possible implementation, the front edge radius of the second vertical support plate is a second preset multiple of the rear edge radius of the second vertical support plate.
[0009] In one possible implementation, the length of the second vertical support plate is greater than the length of the first vertical support plate.
[0010] In one possible implementation, the first preset included angle is 45°.
[0011] In one possible implementation, the included angle between two adjacent first vertical support plates, and the included angle between the second vertical support plate and the adjacent first vertical support plate, are both second preset included angles.
[0012] In one possible implementation, the second preset included angle is 27.7°.
[0013] In one possible implementation, the leading edge of the circumferential flow guide structure is located at the middle of the gas inlet of the exhaust housing, and the trailing edge of the circumferential flow guide structure is at the same height as the center of the exhaust outlet section of the exhaust housing.
[0014] In one possible implementation, both the leading edge and the trailing edge of the circumferential flow guide structure are circular arc surfaces, and the leading and trailing radii of the circumferential flow guide structure are equal.
[0015] In one possible implementation, the leading and trailing radii of the circumferential guide structure are 3 mm.
[0016] The technical solutions provided in the embodiments of the present invention have at least the following technical effects or advantages: This invention provides a flow guiding structure for the exhaust ring cavity of a turbopump. Multiple first vertical support plates, second vertical support plates, and a circumferential flow guiding structure reduce the influence of swirling flow. The circumferential flow guiding structure divides the gas passage in the exhaust ring cavity into two small channels, weakening the flow of gas around the vertical section of the exhaust ring cavity, significantly reducing the flow loss of gas, and thus further improving the performance of the rocket engine. Attached Figure Description
[0017] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments of this application will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0018] Figure 1 A cross-sectional view of the flow guiding structure of the turbopump exhaust annular cavity provided in the embodiments of this application. Figure 1 ; Figure 2 A cross-sectional view of the flow guiding structure of the turbopump exhaust annular cavity provided in the embodiments of this application. Figure 2 ; Figure 3 A schematic cross-sectional view of the first vertical support plate provided in an embodiment of this application; Figure 4 A schematic cross-sectional view of the second vertical support plate provided in an embodiment of this application; Figure 5 This is a cross-sectional schematic diagram of the annular flow guide structure provided in an embodiment of this application.
[0019] Reference numerals: 100-First vertical support plate; 200-Second vertical support plate; 300-Circular flow guide structure; 400-Exhaust casing; 401-Exhaust annular cavity; 402-Thrust chamber; 403-Gas inlet; 404-Exhaust outlet. Detailed Implementation
[0020] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0021] In the description of the embodiments of this application, it should be noted that the terms "center," "upper," "lower," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the embodiments of this application and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.
[0022] This application provides a flow guiding structure for the exhaust annular cavity of a turbopump, such as... Figure 1 and Figure 2As shown, the flow guiding structure of the exhaust ring cavity of the turbopump includes multiple first vertical support plates 100, second vertical support plates 200, and an circumferential flow guiding structure 300.
[0023] Multiple first vertical support plates 100 are spaced apart around the central axis of the exhaust ring cavity 401, and the two ends of the multiple first vertical support plates 100 are respectively connected to the top wall and the bottom wall of the exhaust housing 400. Each first vertical support plate 100 is offset from the exhaust ring cavity 401 radially toward the thrust chamber 402 by a first preset angle.
[0024] Since the multiple first vertical support plates 100 are all offset radially from the exhaust annular cavity 401 towards the thrust chamber 402, the multiple first vertical support plates 100 guide the gas entering from the gas inlet 403 of the exhaust housing 400 to flow towards the exhaust outlet 404. For example, as... Figure 2 As shown, the first preset angle between the first vertical support plate 100 and the radial direction of the exhaust ring cavity 401 is θ1, where θ1 is 45°.
[0025] The two ends of the second vertical support plate 200 are respectively connected to the top wall and bottom wall of the exhaust casing 400, and the second vertical support plate 200 extends along the axis of the thrust chamber 402.
[0026] The second vertical support plate 200 and the plurality of first vertical support plates 100 can guide the airflow within the exhaust ring cavity 401, reducing the swirling flow within the exhaust ring cavity 401. Furthermore, with Figure 2 Taking the orientation shown as an example, the airflow in the upper half of the exhaust ring cavity 401 flows clockwise, and the airflow in the lower half of the exhaust ring cavity 401 flows counterclockwise. The second vertical support plate 200 can prevent the clockwise airflow and the counterclockwise airflow from colliding, thus avoiding the generation of more swirling flow and reducing flow loss.
[0027] The circumferential flow guide structure 300 is connected to a plurality of first vertical support plates 100 and second vertical support plates 200. The circumferential flow guide structure 300 extends along the exhaust ring cavity 401 and protrudes toward the bottom wall of the exhaust housing 400. The leading edge of the circumferential flow guide structure 300 is located at the gas inlet 403 of the exhaust housing 400.
[0028] The circumferential flow guide structure 300 can guide the airflow at the gas inlet 403 of the exhaust housing 400 to the exhaust ring cavity 401, further reducing the swirling flow within the exhaust ring cavity 401. Furthermore, the circumferential flow guide structure 300 divides the exhaust ring cavity 401 into upper and lower chambers, weakening the gas flow around the annular cavity cross-section and reducing gas flow losses.
[0029] Therefore, in the flow guiding structure of the turbopump exhaust ring cavity provided in this application embodiment, the multiple first vertical support plates 100, second vertical support plates 200 and the circumferential flow guiding structure 300, on the basis of reducing the influence of swirling flow, divide the gas passage in the exhaust ring cavity 401 into upper and lower chambers, weaken the flow of gas around the vertical section of the exhaust ring cavity 401, greatly reduce the flow loss of gas, and thus further improve the performance of the rocket engine.
[0030] like Figure 3 As shown, in this embodiment, the leading edge radius of the first vertical support plate 100 is a first preset multiple of the trailing edge radius of the first vertical support plate 100, thereby ensuring that the leading edge of the first vertical support plate 100 has a strong load-bearing capacity. Multiple first vertical support plates 100 cooperate with the second vertical support plate 200 to transfer the load on the turbine assembly and other structures in the upstream portion of the exhaust housing 400 to a ring of bolts at the bottom of the exhaust housing 400.
[0031] For example, the first preset multiple is 2.
[0032] In some other embodiments of this application, the leading edge radius of the first vertical support plate 100 is equal to the trailing edge radius of the first vertical support plate 100.
[0033] like Figure 4 As shown in this embodiment, the leading edge radius of the second vertical support plate 200 is a second preset multiple of the trailing edge radius of the second vertical support plate 200, thereby ensuring that the leading edge of the second vertical support plate 200 has a strong load-bearing capacity. The second vertical support plate 200 cooperates with multiple first vertical support plates 100 to transfer the load on the turbine assembly and other structures in the upstream part of the exhaust housing 400 to a ring of bolts at the bottom of the exhaust housing 400.
[0034] For example, the second preset multiple is 2.
[0035] In some other embodiments of this application, the leading edge radius of the second vertical support plate 200 is equal to the trailing edge radius of the second vertical support plate 200.
[0036] like Figure 3 and Figure 4 As shown in the embodiment of this application, the length of the second vertical support plate 200 is greater than the length of the first vertical support plate 100, which improves the rigidity of the structure of the exhaust housing 400 near the exhaust outlet 404 and also ensures that the clockwise and counterclockwise airflows do not collide.
[0037] In some other embodiments of this application, while ensuring the structural rigidity of the exhaust housing 400, the length of the second vertical support plate 200 is less than or equal to the length of the first vertical support plate 100.
[0038] like Figure 2 As shown, in this embodiment of the application, the included angle between two adjacent first vertical support plates 100, and the included angle between the second vertical support plate 200 and the adjacent first vertical support plate 100, are both second preset included angles. For example, in... Figure 2 The second preset included angle is θ2, which is 27.7°.
[0039] In the above structure, the second vertical support plate 200 and the plurality of first vertical support plates 100 can uniformly divide the airflow in the exhaust ring cavity 401.
[0040] The leading edge of the circumferential guide structure 300 is located in the middle of the gas inlet 403 of the exhaust housing 400, and the trailing edge of the circumferential guide structure 300 is at the same height as the center of the cross-section of the exhaust outlet 404 of the exhaust housing 400, so as to improve the flow uniformity of the gas at the exhaust outlet 404 and further improve the performance of the guide structure with the exhaust annular cavity of the turbopump.
[0041] Both the leading and trailing edges of the circumferential flow guide structure 300 are arc surfaces, and the radii of the leading and trailing edges are equal. The circumferential flow guide structure 300 mainly bears the pressure load from the combustion gas, and the pressure loads on the upper and lower surfaces are similar, thus giving the exhaust casing 400 high strength.
[0042] For example, the leading and trailing radii of the circumferential guide structure 300 are 3 mm.
[0043] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.
Claims
1. A flow guiding structure for the exhaust annular cavity of a turbopump, characterized in that, include: Multiple first vertical support plates are spaced apart around the central axis of the exhaust ring cavity, and the two ends of the multiple first vertical support plates are respectively connected to the top wall and bottom wall of the exhaust housing; wherein, each first vertical support plate is offset from the radial direction of the exhaust ring cavity towards the thrust chamber by a first preset angle; A second vertical support plate, the two ends of which are respectively connected to the top and bottom walls of the exhaust casing, and the second vertical support plate extends along the axis of the thrust chamber; and A circumferential flow guide structure is connected to the plurality of first vertical support plates and second vertical support plates. The circumferential flow guide structure extends along the exhaust annular cavity and protrudes toward the bottom wall of the exhaust housing. The leading edge of the circumferential flow guide structure is located at the gas inlet of the exhaust housing.
2. The flow guiding structure of the turbine pump exhaust annular cavity according to claim 1, characterized in that, The front edge radius of the first vertical support plate is a first preset multiple of the rear edge radius of the first vertical support plate.
3. The flow guiding structure of the turbine pump exhaust annular cavity according to claim 1 or 2, characterized in that, The front edge radius of the second vertical support plate is a second preset multiple of the rear edge radius of the second vertical support plate.
4. The flow guiding structure of the turbine pump exhaust annular cavity according to claim 1, characterized in that, The length of the second vertical support plate is greater than the length of the first vertical support plate.
5. The flow guiding structure of the turbine pump exhaust annular cavity according to claim 1, characterized in that, The first preset included angle is 45°.
6. The flow guiding structure of the turbine pump exhaust annular cavity according to claim 1, characterized in that, The included angle between two adjacent first vertical support plates, and the included angle between the second vertical support plate and the adjacent first vertical support plate are both second preset included angles.
7. The flow guiding structure of the turbine pump exhaust annular cavity according to claim 6, characterized in that, The second preset included angle is 27.7°.
8. The flow guiding structure of the turbine pump exhaust annular cavity according to claim 1, characterized in that, The leading edge of the circumferential flow guide structure is located in the middle of the gas inlet of the exhaust housing, and the trailing edge of the circumferential flow guide structure is at the same height as the center of the exhaust outlet section of the exhaust housing.
9. The flow guiding structure of the turbine pump exhaust annular cavity according to claim 1, characterized in that, Both the leading edge and the trailing edge of the circumferential flow guide structure are circular arc surfaces, and the leading edge radius and trailing edge radius of the circumferential flow guide structure are equal.
10. The flow guiding structure of the turbine pump exhaust annular cavity according to claim 9, characterized in that, The leading and trailing radii of the circumferential guide structure are 3 mm.