Bag type sealing structure and spaceflight turbine

Abstract

The utility model 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 utility model relates to the field of aerospace engines, in particular to a bag-type sealing structure and an aerospace turbine Background Art

[0002] In existing technology, liquid rocket engine turbines generally use labyrinth seals. However, because the gas within the sealing gap of the labyrinth bag seal structure has a significant circumferential rotational speed, high speed conditions can easily cause the risk of overall engine rotor system instability. Utility Model Content

[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 protruding from the structural body and spaced apart along a first direction, the structural body and the plurality of first baffles cooperating with each other to form a bag-shaped sealing structure; in the first direction, two adjacent first baffles and the structural body together form a first cavity; and

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

[0009] In some embodiments, further comprising:

[0010] The third baffle is provided on the structural body, and the third baffle divides the first cavity into a second cavity and a third cavity along a first direction, wherein 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 provided 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 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.

[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 utility model 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. The second baffle 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 utility model can consume the kinetic energy of the gas and seal the gas tightly;

[0020] The aerospace turbine disclosed in the utility model is designed with a two-stage turbine disc to fully utilize the residual speed energy of the combustion gas and improve the turbine efficiency;

[0021] The aerospace turbine disclosed by the utility model 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 following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0023] Figure 1 A schematic diagram of the expanded 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 in an embodiment of the present application;

[0025] Figure 3 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. Outlet pipe;

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

[0035] The following description provides specific application scenarios and requirements for this specification, with the goal of enabling those skilled in the art to make and use the contents of this specification. Various modifications to the disclosed embodiments will be readily 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 is intended to be accorded the broadest scope consistent with the claims.

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

[0037] In this application, terms such as "upper," "lower," "left," "right," "front," "back," "top," "bottom," "inner," "outer," "vertical," "horizontal," "transverse," and "longitudinal" indicate positions or locations based on the positions or locations shown in the accompanying drawings. These terms are primarily intended to better describe this application and its embodiments and are not intended to limit the devices, elements, or components indicated to having a specific orientation, or to being constructed or operated in a specific orientation.

[0038] Furthermore, some of the above terms may be used to express other meanings besides indicating a position or location. For example, the term "on" may also be used to indicate a dependency or connection in certain circumstances. Those skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances.

[0039] Furthermore, the terms "installed," "disposed," "provided with," "connected," and "connected" should be interpreted broadly. For example, they can refer to fixed connections, removable connections, or integral structures; mechanical connections or electrical connections; direct connections, indirect connections through an intermediary, or internal communication between two devices, elements, or components. Those skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances.

[0040] These and other features of this specification, as well as the operation and function of the associated elements of the structure, and the economical assembly and manufacture of the components, can be significantly improved with consideration of the following description. Reference is made to the accompanying drawings, all of which form a part of this specification. However, it should be expressly 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. For example, in a bipropellant pump-type liquid rocket engine, when the engine is operating, the propellant and fuel are squeezed out of the tanks and fed into the thrust chamber via a propellant delivery line. The propellant is mixed and atomized by the injectors at the head of the thrust chamber, forming fine droplets. These droplets are heated by the flame in the combustion chamber, vaporize, and burn violently, becoming high-temperature, high-pressure combustion gas. The gas is accelerated through the nozzle into a supersonic flow and ejected backward, generating thrust on the engine and propelling the rocket forward. In the prior art, the turbines of liquid rocket engines generally use labyrinth seals. However, because the gas within the sealing gap of the seal structure has a significant circumferential rotational velocity, high speeds can easily cause overall instability in the engine's turbine pump rotor system.

[0042] In view of this, the 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-type sealing structure of the turbine is described in detail below through a specific embodiment:

[0044] like Figure 1The figure shows an expanded schematic diagram of the bag-type sealing structure 32. The bag-type sealing structure 32 is composed of a series of regularly arranged bag-type sealing holes and slots on the stator surface, 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 protruded from the structural body 3220 and is arranged at intervals along the first direction. The first baffle 3221 extends in a direction perpendicular to the first direction to form a rectangular cube, 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. However, since the gas has a significant circumferential rotation speed in the first cavity 3211, the risk of overall instability 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, intersecting with the first baffle 3221, dividing the first cavity 3211 along the second direction and defining a plurality of first cavities 3211. It is understood that in another embodiment, the first baffles 3221 may be arranged in a comb-like, discontinuous pattern on the structural body 3220. In this case, the first cavities 3211 formed are not enclosed, but still achieve the effect of consuming gas kinetic energy and sealing the gas. Similarly, in another embodiment, the first baffles 3221 may be sheet-like baffles, arranged in groups on the structural body 3220.

[0046] In this embodiment, the first direction is the same as the gas direction and 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 through the first cavity 3211. It is 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 further provided on the bag-type sealing structure 32. 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 movement distance of the gas in the bag-type sealing structure 32 and facilitating the consumption of the gas kinetic energy.

[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 notches on the aforementioned baffles can enhance the stability of the sealing performance, i.e., a notch is provided on the top of each third baffle 3223. In this embodiment, a first notch 3231 is provided on the top of the first baffle 3221. The first notch 3231 expands the space connecting the second cavity 3212 and the third cavity 3213, thereby facilitating 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. 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, connecting the bag-type sealing structure 32 to the outlet.

[0055] like Figure 2 Figure 1 shows a cross-sectional view of an aerospace turbine structure, comprising a gas collecting ring 1, a nozzle ring 2, a guide vane ring 3, an outlet pipe 4, and a two-stage turbine disk 5. The gas collecting ring 1 and nozzle ring 2 are integrally formed using 3D printing, reducing machining steps and improving precision. Conical or cascade nozzles are arranged circumferentially within the nozzle ring 2 to cool, pressure, and increase the speed of the gas.

[0056] The guide vane ring 3 is fixed to the nozzle ring 2 by means of a guide vane ring flange 31 and a full circle of bolts. The guide vane ring 3 is divided into three lobes in the circumferential direction, has a simple structure, and is easy to assemble and disassemble. The outlet pipe 4 is welded and fixedly connected to the nozzle ring 2, which not only reduces 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 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 enters the bag-type sealing hole groove to form a vortex motion and fully consume kinetic energy, thereby achieving a sealing effect.

[0057] When high-temperature combustion gas enters gas collecting ring 1, it is rectified and distributed to the nozzles within nozzle ring 2. Within the nozzles, the gas rapidly expands, reducing its temperature and pressure while increasing its velocity. The gas is discharged from nozzle ring 2 backward along the engine axis at high speed, much faster than the speed at which the air enters the engine, converting thermal energy into kinetic energy. Simultaneously, some of the high-speed combustion gas enters the leaf channels of the two-stage turbine disk 5, performing work and driving the two-stage turbine disk 5 at high speed. This converts the combustion gas's kinetic energy into mechanical shaft work output, which in turn drives the turbine pump.

[0058] like Figure 2 Figure 2 shows 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-mentioned embodiment. The guide vane ring flange 31 and the guide vane ring cascade 33 are located on either side of the bag-type sealing structure 32. The guide vane ring cascade 33, located between the two-stage turbine disk 5, is used to change the direction of the combustion gas, while the guide vane ring flange 31 is used to secure the guide vane ring 3.

[0059] Because the two-stage turbine disk 5 is a rotating component, its rotation inevitably creates a gap between it and the corresponding engine casing. This allows a small amount of combustion gas to enter the pocket seal 32 between the two-stage turbine disk 5 and the guide vane ring 3. This pocket seal 32 seals the combustion gas, dissipates its kinetic energy, resists the excitation force of the combustion gas, and stabilizes the rotor system. Ultimately, the combustion gas flowing from the blades of the two-stage turbine disk 5 enters the channel of the outlet pipe 4, where it continues to expand and accelerate, and is discharged into the environment through the outlet pipe 4, generating some thrust.

[0060] The aerospace turbine provided in this embodiment fully utilizes the fuel gas energy to output shaft work energy outward, thereby generating partial thrust, effectively enhancing the overall stability of the rocket engine turbopump rotor, and improving the turbine energy conversion efficiency.

[0061] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and such modifications or substitutions are intended to be within the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be subject to the scope of protection of the claims.

Claims

1. A bag-type sealing structure, characterized in that: include: Structural body; A plurality of first baffles are protrudingly provided on the structural body and arranged at intervals along a first direction, wherein the structural body and the plurality of 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 together 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, wherein: Also includes: The third baffle is provided on the structural body, and the third baffle divides the first cavity into a second cavity and a third cavity along a first direction, wherein 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, wherein: A notch is provided on the top of the third baffle.

4. The bag-type sealing structure according to claim 3, wherein: 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, wherein: 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, wherein: The second baffle extends along the first direction and divides the first cavity along the second direction.

7. A guide vane ring, characterized in that: It includes a guide vane ring flange, a bag-type sealing structure according to 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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