Bag type sealing structure and spaceflight turbine

Abstract

The invention discloses a bag type sealing structure and a space turbine, and belongs to the field of space engines. The bag type sealing structure comprises a structure body. The first baffles are arranged on the structure body in a protruding mode and arranged at intervals in the first direction, and the structure body and the first baffles are matched with each other to form a bag-shaped sealing structure; in the first direction, the two adjacent first baffles and the structure body jointly form a first cavity. And the second baffle is located in the first cavity and can prevent the gas from moving in the circumferential direction. The bag type sealing structure can seal the turbine pump, prevent gas from circumferentially moving in a sealing gap, resist fluid cross exciting force and effectively improve the stability of a rotor system of the turbine pump.

Description

Technical Field

[0001] The present invention relates to the field of aerospace engines, and in particular to a bag-type sealing structure and an aerospace turbine. Background Art

[0002] In the prior art, the turbine of a liquid rocket engine generally adopts a labyrinth seal. However, since the gas in the sealing gap of the labyrinth bag seal structure has a significant circumferential rotation speed, it is easy to cause the risk of overall instability of the engine rotor system under high speed conditions. Summary of the invention

[0003] The present application provides a bag-type sealing structure and an aerospace turbine, which can seal a turbine pump, block the circumferential movement of the combustion gas in the sealing gap, resist the cross-excitation force of the fluid, and effectively improve the stability of the turbine pump rotor system.

[0004] To achieve the above objectives, the embodiments of the present application adopt the following technical solutions:

[0005] In a first aspect, the present application discloses a bag-type sealing structure, comprising:

[0006] Structural body;

[0007] A plurality of first baffles are protrudingly provided on the structural body and arranged at intervals along a first direction, the structural body and the plurality of the first baffles cooperate with each other to form a bag-shaped sealing structure; in the first direction, two adjacent first baffles and the structural body jointly form a first cavity; and

[0008] The second baffle, located in the first cavity, can hinder the circumferential movement of the combustion gas.

[0009] In some embodiments, it further comprises:

[0010] The third baffle is arranged on the structural body, and the third baffle divides the first cavity into a second cavity and a third cavity along the first direction, and the volume of the second cavity is greater than the volume of the third cavity.

[0011] In some embodiments, a notch is provided on the top of the third baffle.

[0012] In some embodiments, a notch is disposed on the top of the first baffle or the second baffle.

[0013] In some embodiments, the structural body and the first baffle, the second baffle and the third baffle are integrally formed.

[0014] In some embodiments, the second baffle extends along the first direction to separate the first cavity along the second direction.

[0015] In the second aspect, the present application also discloses a guide vane ring, comprising a guide vane ring flange, a bag-type sealing structure as described in any one of the first aspects above, and a guide vane ring blade grid, wherein the guide vane ring flange and the guide vane ring blade grid are respectively located on both sides of the bag-type sealing structure, the guide vane ring blade grid is used to change the direction of the gas, and the guide vane ring flange is used to fix the guide vane ring.

[0016] In a third aspect, the present application further discloses an aerospace turbine, comprising the bag-type sealing structure described in any one of the first aspect or the guide vane ring described in the second aspect.

[0017] The beneficial effects of the present invention compared with the prior art are:

[0018] The bag-type sealing structure disclosed in the present invention allows the gas to enter the sealing hole groove of the bag-type sealing structure to form a vortex motion, thereby consuming the kinetic energy of the gas, and the second baffle plate provided can hinder the circumferential motion of the gas, thereby achieving the effects of sealing the turbine pump, resisting the gas excitation force and improving the stability of the rotor system;

[0019] The various cavities formed in the bag-type sealing structure disclosed in the present invention can consume the kinetic energy of the gas and seal the gas tightly;

[0020] The aerospace turbine disclosed in the present invention fully utilizes the residual speed energy of the combustion gas and improves the turbine efficiency by designing a two-stage turbine disk;

[0021] The aerospace turbine disclosed in the present invention utilizes fuel gas energy to output shaft work energy outwards to generate partial thrust, thereby effectively enhancing the overall stability of the rocket engine turbine pump rotor and improving the turbine energy conversion efficiency and turbine operating reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying any creative work.

[0023] Figure 1 A schematic diagram of the development of a bag-type sealing structure provided in an embodiment of the present application;

[0024] Figure 2 A cross-sectional view of an aerospace turbine structure provided for an embodiment of the present application;

[0025] Figure 3 A schematic diagram of the guide vane ring structure provided in an embodiment of the present application.

[0026] The reference numerals in the figures are:

[0027] 1. Gas collecting ring;

[0028] 2. Nozzle ring;

[0029] 3. Guide vane ring;

[0030] 31. Guide vane ring flange;

[0031] 32. Bag-type sealing structure; 3211. First cavity; 3212. Second cavity; 3213. Third cavity; 3220. Structural body; 3221. First baffle; 3222. Second baffle; 3223. Third baffle; 3224. Fourth baffle; 3231. First notch; 3232. Second notch;

[0032] 33. Guide vane ring cascade;

[0033] 4. Export pipe;

[0034] 5. Two-stage turbine disc. DETAILED DESCRIPTION

[0035] The following description provides specific application scenarios and requirements of this specification, with the purpose of enabling those skilled in the art to make and use the contents of this specification. Various local modifications to the disclosed embodiments will be apparent to those skilled in the art, and the general principles defined herein may be applied to other embodiments and applications without departing from the spirit and scope of this specification. Therefore, this specification is not limited to the embodiments shown, but to the widest scope consistent with the claims.

[0036] The terms used herein are only used for the purpose of describing specific example embodiments and are not restrictive. For example, unless the context clearly indicates otherwise, as used herein, the singular forms "a", "an" and "the" may also include plural forms. When used in this specification, the terms "include", "comprise" and / or "contain" mean that the associated integers, steps, operations, elements and / or components exist, but do not exclude the existence of one or more other features, integers, steps, operations, elements, components and / or groups or that other features, integers, steps, operations, elements, components and / or groups may be added in the system / method.

[0037] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0038] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0039] In addition, the terms "installed", "set", "provided with", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be an internal connection between two devices, elements, or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0040] In view of the following description, these and other features of the present specification, as well as the operation and function of the related elements of the structure, and the economy of the combination and manufacture of the parts can be significantly improved. Reference is made to the accompanying drawings, all of which form a part of this specification. However, it should be clearly understood that the drawings are for illustration and description purposes only and are not intended to limit the scope of this specification. It should also be understood that the drawings are not drawn to scale.

[0041] A liquid rocket engine is a chemical rocket engine that uses liquid propellant. Taking a two-component pump-type liquid rocket engine as an example, when the liquid rocket engine is working, the propellant and fuel are squeezed out of the tank respectively and enter the thrust chamber through the propellant delivery pipe. The propellant is mixed and atomized by the injector at the head of the thrust chamber to form fine droplets, which are heated and vaporized by the flame in the combustion chamber and burn violently, turning into high-temperature and high-pressure combustion gas in the combustion chamber. The combustion gas is accelerated into a supersonic airflow through the nozzle and ejected backward, generating thrust acting on the engine and driving the rocket forward. In the prior art, the turbine of the liquid rocket engine generally adopts a labyrinth seal. However, since the combustion gas in the sealing gap of the sealing structure has an obvious circumferential rotation speed, it is easy to cause the overall instability of the engine turbine pump rotor system under high speed conditions.

[0042] In view of this, an embodiment of the present invention provides a bag-type sealing structure and an aerospace turbine, which can seal the turbine pump, block the circumferential movement of the combustion gas in the sealing gap, resist the cross-excitation force of the fluid, and effectively improve the stability of the turbine pump rotor system.

[0043] The bag seal structure of the turbine is described in detail below through a specific embodiment:

[0044] like Figure 1As shown, it is a schematic diagram of the development of the bag-type sealing structure 32. The bag-type sealing structure 32 is composed of a series of regularly arranged bag-type sealing hole slot stator surfaces, and its structure is divided into a structural body 3220, a first baffle 3221, a second baffle 3222 and a first cavity 3211. The first baffle 3221 is convexly arranged on the structural body 3220, and is arranged at intervals from each other along the first direction. The first baffle 3221 extends in a direction perpendicular to the first direction to form a long cube shape, and the first baffle 3221 forms a gas path sealing structure. The two first baffles 3221 adjacent to each other in the first direction and the structural body 3220 together form a first cavity 3211. The first cavity 3211 can consume the kinetic energy of the gas and seal the gas, but because the gas has an obvious circumferential rotation speed in the first cavity 3211, the overall instability risk of the engine rotor system is high. A second baffle 3222 is provided in the first cavity 3211 , and the second baffle 3222 can hinder the circumferential movement of the combustion gas, thereby improving the vibration stability of the rotor system.

[0045] like Figure 1 As shown, in this embodiment, the first direction is the direction of the gas. The second baffle 3222 extends along the same first direction as the gas and intersects with the first baffle 3221 to separate the first cavity 3211 along the second direction and define a plurality of first cavities 3211. It can be understood that in another embodiment, the first baffle 3221 can be comb-shaped and discontinuously arranged on the structural body 3220. In this case, the first cavity 3211 formed is non-enclosed, but can still achieve the effect of consuming the kinetic energy of the gas and sealing the gas. Similarly, in another embodiment, the first baffle 3221 can be a sheet-like baffle, which is arranged in groups on the structural body 3220.

[0046] In this embodiment, the first direction is the same as the gas direction and is perpendicular to the second direction. It can be understood that in another embodiment, the first direction is the same as the gas direction, but the second direction may form an acute angle with the first direction.

[0047] It can be understood that there can be multiple second baffles 3222, and in order to facilitate modular production, multiple second baffles 3222 are set accordingly. At the same time, there are also multiple first cavities 3211 formed between the multiple second baffles 3222 and the multiple first baffles 3221, which can maximize the reduction of gas leakage.

[0048] In this embodiment, the second baffle 3222 is fixed on the structural body 3220 . In another embodiment, the second baffle 3222 may be fixed on the first baffle 3221 and fixedly connected to the side wall of the first baffle 3221 .

[0049] Similarly, if Figure 1As shown, in this embodiment, the second baffle 3222 is a structure extending to penetrate the first cavity 3211. It can be understood that in another embodiment, the second baffle 3222 can be a discontinuous structure, for example, it is separately provided in the first cavity 3211 and is not connected to the first baffle 3221.

[0050] A third baffle 3223 is also provided on the bag-type sealing structure 32, and the third baffle 3223 divides the first cavity 3211 into a second cavity 3212 and a third cavity 3213 along the first direction, thereby increasing the moving distance of the gas in the bag-type sealing structure 32 and facilitating the consumption of the kinetic energy of the gas.

[0051] It is understandable that the volume between the second cavity 3212 and the third cavity 3213 can be changed and can be adaptively adjusted according to different materials, engine types, engine rotor types, etc. In this embodiment, the volume of the second cavity 3212 is greater than the volume of the third cavity 3213.

[0052] Providing a notch on the baffle can enhance the stability of the sealing performance, that is, a notch is provided on the top of the third baffle 3223. In this embodiment, a first notch 3231 is provided on the top of the first baffle 3221, and the first notch 3231 expands the connecting space between the second cavity 3212 and the third cavity 3213, which is conducive to the flow of gas.

[0053] In order to simplify the manufacturing process and improve the production accuracy and repeatability of parts, the structural body 3220 and the first baffle 3221, the second baffle 3222 and the third baffle 3223 are integrally formed.

[0054] A fourth baffle 3224 is provided at the air outlet of the bag-type sealing structure 32, and the width of the fourth baffle 3224 is greater than the widths of the first baffle 3221, the second baffle 3222 and the third baffle 3223. A second notch 3232 is provided at the top of the fourth baffle 3224, and the second notch 3232 connects the bag-type sealing structure 32 with the outlet.

[0055] like Figure 2 The figure shows a cross-sectional view of the aerospace turbine structure, which includes an air collecting ring 1, a nozzle ring 2, a guide vane ring 3, an outlet pipe 4, and a two-stage turbine disk 5. The air collecting ring 1 and the nozzle ring 2 are integrally formed by 3D printing, which reduces the processing steps and improves the processing accuracy. Conical or cascade-shaped nozzles are arranged circumferentially in the nozzle ring 2 to reduce the temperature, pressure and speed of the gas.

[0056] The guide vane ring 3 is fixed to the nozzle ring 2 by means of the guide vane ring flange 31 and a full circle of bolts. The guide vane ring 3 is divided into three petals in the circumferential direction, with a simple structure and convenient assembly and disassembly. The outlet pipe 4 is welded and fixedly connected to the nozzle ring 2, which not only reduces the assembly and manufacturing costs, but also improves the reliability and sealing of the device. The two-stage turbine disk 5 is fixedly connected to the turbine main shaft by means of an involute spline or a flange structure, which plays a role in reliable torque transmission. When the combustion gas passes through the gap at the top of the blade grid of the two-stage turbine disk 5, it will enter the bag-type sealing hole groove to form a vortex motion and fully consume kinetic energy, thereby achieving a sealing effect.

[0057] When the high-temperature combustion gas enters the gas collecting ring 1, it is rectified by the gas collecting ring 1 and distributed to the nozzle in the nozzle ring 2. The combustion gas expands rapidly in the nozzle, the temperature and pressure decrease, and the speed increases. The combustion gas is discharged backward from the nozzle ring 2 along the engine axis at a high speed, which is much faster than the speed of the airflow entering the engine, converting thermal energy into kinetic energy. At the same time, part of the high-speed combustion gas enters the leaf channel of the two-stage turbine disk 5 to do work, driving the two-stage turbine disk 5 to rotate at a high speed, converting the combustion gas kinetic energy into mechanical shaft work output and driving the turbine pump.

[0058] like Figure 2 As shown, it is a schematic diagram of the structure of the guide vane ring 3. The guide vane ring 3 includes the bag-type sealing structure 32, the guide vane ring flange 31 and the guide vane ring cascade 33 provided in the above embodiment. The guide vane ring flange 31 and the guide vane ring cascade 33 are respectively located on both sides of the bag-type sealing structure 32, the guide vane ring cascade 33 in the middle of the two-stage turbine disk 5 is used to change the direction of the gas, and the guide vane ring flange 31 is used to fix the guide vane ring 3.

[0059] Since the two-stage turbine disk 5 is a rotating part, there must be a gap between it and the corresponding engine housing when it rotates, resulting in a small amount of gas entering the bag-type sealing structure 32 between the two-stage turbine disk 5 and the guide vane ring 3. The bag-type sealing structure 32 can seal the gas, consume the kinetic energy of the gas, resist the gas excitation force and stabilize the rotor system. Finally, the gas flowing out of the blade grid of the two-stage turbine disk 5 enters the outlet pipe 4 channel to continue to expand and increase in speed, and is discharged from the outlet pipe 4 to the environment, generating some thrust.

[0060] The aerospace turbine provided in this embodiment fully utilizes the fuel gas energy, outputs shaft work energy outward, generates partial thrust, and effectively enhances the overall stability of the rocket engine turbine pump rotor, thereby improving the turbine energy conversion efficiency.

[0061] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed by the present invention, and these modifications or replacements should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. A bag-type sealing structure, characterized in that: include: Structural body; A plurality of first baffles are convexly disposed on the structural body and arranged at intervals along a first direction, the structural body and the plurality of the first baffles cooperate with each other to form a bag-shaped sealing structure; in the first direction, two adjacent first baffles and the structural body jointly form a first cavity; as well as The second baffle is located in the first cavity and can hinder the circumferential movement of the combustion gas.

2. The bag-type sealing structure according to claim 1, characterized in that: Also includes: The third baffle is arranged on the structural body, and the third baffle divides the first cavity into a second cavity and a third cavity along the first direction, and the volume of the second cavity is greater than the volume of the third cavity.

3. The bag-type sealing structure according to claim 2, characterized in that: A notch is arranged on the top of the third baffle.

4. The bag-type sealing structure according to claim 3, characterized in that: A notch is provided on the top of the first baffle or the second baffle.

5. The bag-type sealing structure according to claim 2, characterized in that: The structural body and the first baffle, the second baffle and the third baffle are integrally formed.

6. The bag-type sealing structure according to claim 1, characterized in that: The second baffle extends along the first direction to separate the first cavity along the second direction.

7. A guide vane ring, characterized in that: It comprises a guide vane ring flange, a bag-type sealing structure as described in any one of claims 1 to 6, and a guide vane ring cascade, wherein the guide vane ring flange and the guide vane ring cascade are respectively located on both sides of the bag-type sealing structure, the guide vane ring cascade is used to change the direction of the gas, and the guide vane ring flange is used to fix the guide vane ring.

8. An aerospace turbine, characterized in that: It comprises the bag-type sealing structure according to any one of claims 1 to 6 or the guide vane ring according to claim 7.

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