Aerospace turbine with hole type damping sealing structure

Abstract

The utility model discloses a spaceflight turbine with a hole type damping sealing structure, and relates to the technical field of turbine pumps of liquid rocket engines. The spaceflight turbine comprises a turbine shell, a two-stage turbine disc, a guide vane ring, an outlet pipe and a turbine main shaft. A two-stage turbine disc blade grid is arranged on the outer edge of the two-stage turbine disc in the radial direction, a two-stage hole type damping sealing structure is arranged on the inner side of the guide vane ring, and the hole type damping sealing structure is composed of a plurality of round hole grooves formed in the inner side of the guide vane ring. According to the spaceflight turbine with the hole type damping sealing structure, the hole type damping sealing structure is arranged, so that gas enters the circular hole groove to form vortex motion, kinetic energy is consumed, and the effects of tight sealing, resistance to gas exciting force and improvement of the stability of a rotor system are achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of liquid rocket engine turbine pumps, in particular to an aerospace turbine with a hole-type damping sealing structure. Background Art

[0002] Liquid rocket engines generally use labyrinth-type seal turbines, and most of them are single-stage bladed turbine disc structures. Due to the labyrinth-type seal structure, the gas in the sealing gap has a significant circumferential rotation speed, which can easily cause the risk of overall instability of the engine turbine pump rotor system under high speed conditions. The labyrinth-type seal has limited gas sealing capacity. At the same time, the gas has a large residual speed loss after passing through the single-stage bladed turbine disc, resulting in low overall efficiency of the turbine. Utility Model Content

[0003] The purpose of the utility model is to solve the deficiencies of the above-mentioned prior art and to provide an aerospace two-stage turbine with excellent rotor dynamics, strong gas sealing capability, high efficiency and high reliability.

[0004] The technical solutions adopted by the present invention to solve the technical problems are as follows.

[0005] An aerospace turbine with a hole-type damping seal structure comprises a turbine housing, a two-stage turbine disc, a guide vane ring, an outlet pipe, and a turbine main shaft; the outlet pipe is fixed to the turbine housing; the guide vane ring is located in the outlet pipe and fixed to the turbine housing; the two-stage turbine disc is located in the guide vane ring, and the two-stage turbine disc is fixedly connected to the turbine main shaft;

[0006] The outer edge of the two-stage turbine disk is provided with two stages of turbine disk blade cascades in the radial direction, and a guide vane ring blade cascade accommodating cavity is formed between the two stages of turbine disk blade cascades; the inner side of the guide vane ring is provided with two stages of hole-type damping sealing structures, and the two stages of hole-type damping sealing structures correspond to the two stages of turbine disk blade cascades; a guide vane ring blade cascade is provided between the two stages of hole-type damping sealing structures and extends into the guide vane ring blade cascade accommodating cavity;

[0007] The hole-type damping sealing structure is composed of a plurality of circular hole grooves arranged on the inner side of the guide vane ring.

[0008] In some other embodiments, the circular hole has a diameter of 1-10 mm and a depth of 1-10 mm.

[0009] Preferably, the spacing between adjacent circular holes of the hole-type damping sealing structure is 1-10 mm.

[0010] In some other embodiments, the turbine housing is composed of an air collecting ring and a nozzle ring, and nozzles are provided circumferentially inside the nozzle ring; the air collecting ring is located on one side of the nozzle ring, and the guide vane ring is fixed to the other side of the nozzle ring through a detachable part.

[0011] In some other embodiments, the nozzle ring and the guide vane ring are further provided with external stops for radial positioning.

[0012] Preferably, the detachable parts are flanges and bolts.

[0013] In some other embodiments, the turbine housing is integrally formed by 3D printing.

[0014] In some other embodiments, the outlet pipe is fixed to the turbine casing by welding.

[0015] In some other embodiments, the two-stage turbine disk is fixedly connected to the turbine main shaft via an involute spline and / or a flange.

[0016] In some other embodiments, the guide vane ring is composed of multiple parts.

[0017] The aerospace turbine with a hole-type damping seal structure of this utility model, through the arrangement of the hole-type damping seal structure, causes the gas entering the circular hole groove to form a vortex motion and consume kinetic energy, thereby achieving a tight seal, resisting the gas excitation force, and improving the stability of the rotor system. Furthermore, by arranging a two-stage turbine disk, the aerospace turbine fully utilizes the residual gas velocity energy to improve turbine efficiency. The gas energy is then used to output axial work energy to generate partial thrust, effectively enhancing the overall stability of the rocket engine turbopump rotor, and improving the turbine's energy conversion efficiency and operational reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] 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.

[0019] Figure 1 It is a partial cross-sectional view of an aerospace turbine having a hole-type damping seal structure according to an embodiment.

[0020] Figure 2 2 is a front view of the guide vane ring in the embodiment.

[0021] Figure 3 2 is a cross-sectional view of the guide vane ring in the embodiment.

[0022] Figure 4 Schematic diagram of the hole-type damping seal structure in the embodiment.

[0023] Description of the symbols in the figure:

[0024] 1-gas collecting ring; 2-nozzle ring; 3-guide vane ring; 301-first component, 302-second component, 303-third component; 31-flange; 32-hole-type damping sealing structure; 321-first-stage hole-type damping sealing structure; 322-second-stage hole-type damping sealing structure; 3201-circular hole groove; 33-guide vane ring blade grid; 34-external stop; 4-outlet pipe; 5-two-stage turbine disk; 51-first-stage turbine disk blade grid; 52-second-stage turbine disk blade grid; 53-guide vane ring blade grid accommodating cavity; 6-gasket; 7-bolt; 8-weld; 9-turbine pump housing. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0026] It should also be understood that the terms used in this utility model specification are only for the purpose of describing specific embodiments and are not intended to limit the utility model. As used in this utility model specification and the appended claims, the singular forms "a", "an" and "the" are intended to include plural forms unless the context clearly indicates otherwise.

[0027] It should be further understood that the term “and / or” used in the present specification and the appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes these combinations.

[0028] Example

[0029] See also Figures 1-4 The aerospace turbine with a hole-type damping seal structure shown includes a turbine casing, a guide vane ring 3, an outlet pipe 4, a two-stage turbine disk 5 and a turbine main shaft.

[0030] The turbine housing consists of a gas collecting ring 1 and a nozzle ring 2, both of which are integrally formed using 3D printing, reducing machining steps and improving precision. Nozzles are circumferentially arranged within the nozzle ring 2. These nozzles can be conical or cascade-shaped, reducing gas pressure and increasing speed.

[0031] The outlet pipe 4 is fixed to the turbine housing. In this embodiment, the outlet pipe 4 is directly welded to the nozzle ring 2. Figure 1 The weld 8 shown in the figure can reduce the assembly and manufacturing cost by welding and play a role in reliably sealing the gas.

[0032] The guide vane ring 3 is located within the outlet pipe 4 and is fixed to the turbine casing. Specifically, the gas collecting ring 1 is located on one side of the nozzle ring 2, and the guide vane ring 3 is fixed to the other side of the nozzle ring 2 via a removable component. In this embodiment, the guide vane ring 3 is provided with a flange 31, which is fixed to the nozzle ring 2 via bolts 7. The flange 31 and bolts 7 are the removable components. It can be understood that to achieve a fixed connection between the guide vane ring 3 and the nozzle ring 2, multiple bolts 7 are provided at equal intervals along the circumference of the nozzle ring 2 to secure the guide vane ring 3 and the nozzle ring 2, and gaskets 6 are provided between the bolts 7 and the flange 31 to enhance firmness.

[0033] An external stop 34 for radial positioning is provided between the guide vane ring 3 and the nozzle ring 2. In this embodiment, the external stop 34 is provided on the nozzle ring 2, and the guide vane ring 3 is provided with an abutment that matches the external stop 34. The matching of the external stop 34 and the abutment enables rapid positioning and installation of the nozzle ring 2 and the guide vane ring 3. It will be appreciated that in other embodiments, the external stop 34 may be provided on the guide vane ring 3, and the abutment that matches the external stop 34 may be provided on the nozzle ring 2.

[0034] The guide vane ring 3 can be composed of multiple parts. In this embodiment, the guide vane ring 3 is processed as a whole and then divided into three parts by wire cutting. Figure 2 As shown, the guide vane ring 3 is composed of a first component 301, a second component 302, and a third component 303, each of which has a central angle of 120°. The positioning of the outer stop 34 and the splicing structure of the three components facilitate the installation and removal of the guide vane ring 3.

[0035] The inner side of the guide vane ring 3 is provided with a two-stage hole-type damping sealing structure 32, which is composed of a plurality of circular hole grooves 3201 arranged on the inner side of the guide vane ring (such as Figure 4 The diameter of the circular holes is 1-10 mm, the depth is 1-10 mm, and the spacing between adjacent circular holes is 1-10 mm.

[0036] In this embodiment, the diameter of the circular holes is specifically 2 mm, the depth is specifically 3 mm, and the spacing between adjacent circular holes is specifically 2.5 mm.

[0037] The hole-type damping seal structure 32 consists of a series of regularly spaced circular slots 3201. Its function is to cause the gas passing through the gaps at the top of the two-stage turbine disk cascade 5 to enter the circular slots 3201, forming a vortex motion and dissipating kinetic energy, thus achieving a sealing effect. This has the advantages of low gas leakage. The densely distributed circular slots 3201 along the circumference and axial direction block the circumferential motion of the gas within the gap, reducing the cross-fluid excitation force and effectively enhancing the stability of the turbopump rotor system. Furthermore, the circular slot structure of the hole-type damping seal simplifies its manufacturing process.

[0038] like Figure 3 As shown, the two-stage hole-type damping sealing structure 32 is respectively a primary hole-type damping sealing structure 321 and a secondary hole-type damping sealing structure 322 , and a guide vane ring cascade 33 is provided between the primary hole-type damping sealing structure 321 and the secondary hole-type damping sealing structure 322 .

[0039] The two-stage turbine disk 5 is located within the guide vane ring 3 and is fixedly connected to the turbine main shaft. In this embodiment, the two-stage turbine disk 5 and the turbine main shaft are fixedly connected via an involute spline, which ensures reliable torque transmission and drives the turbine main shaft to rotate.

[0040] Two stages of turbine disk blades are radially arranged along the outer edge of the two-stage turbine disk 5: a first-stage turbine disk blade cascade 51 and a second-stage turbine disk blade cascade 52. A guide vane ring blade cascade accommodating cavity 53 is formed between the first-stage turbine disk blade cascade 51 and the second-stage turbine disk blade cascade 52. The first-stage turbine disk blade cascade 51 corresponds to the first-stage hole-type damping seal structure 321, and the second-stage turbine disk blade cascade 52 corresponds to the second-stage hole-type damping seal structure 322. The guide vane ring blade cascade 33 extends into the guide vane ring blade cascade accommodating cavity 53.

[0041] This aerospace turbine operates as follows: high-temperature combustion gas enters the gas collecting ring 1, where it is rectified and distributed to the nozzles within the nozzle ring 2. Within the nozzles, the combustion gas rapidly expands, reducing its temperature and pressure while increasing its velocity, converting thermal energy into kinetic energy. The high-speed combustion gas then enters the cascade channels of the two-stage turbine disk 5, performing work and driving the two-stage turbine disk 5 to rotate at high speed. The guide vane ring cascade channels between the two-stage turbine disk 5 serve to divert the combustion gas flow. A small portion of the combustion gas enters the hole-type damping seal gap between the two-stage turbine disk 5 and the guide vane ring 3. The hole-type damping seal structure seals the combustion gas, reduces leakage, resists combustion excitation forces, and stabilizes the rotor system. Finally, the combustion gas exiting the cascade channels of the two-stage turbine disk 5 enters the outlet pipe 4, where it continues to expand and accelerate before being discharged into the environment, generating some thrust. This aerospace turbine fully utilizes the combustion gas energy to output axial work energy, generating some thrust and effectively enhancing the overall stability of the rocket engine turbopump rotor and improving turbine energy conversion efficiency.

[0042] The aerospace turbine with a hole-type damping seal structure of this embodiment can be used for the turbine pump of aerospace rocket engines. The turbine pump housing 9 is sleeved on the turbine main shaft, and the turbine pump housing 9 is fixedly connected to the turbine housing (such as Figure 1 As shown), the rotation of the two-stage turbine disk 5 can drive the turbine main shaft to rotate, thereby driving the turbine pump.

[0043] 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. An aerospace turbine with a hole-type damping seal structure, characterized in that: It includes a turbine housing, a two-stage turbine disc, a guide vane ring, an outlet pipe and a turbine main shaft; the outlet pipe is fixed to the turbine housing; the guide vane ring is located in the outlet pipe and fixed to the turbine housing; the two-stage turbine disc is located in the guide vane ring, and the two-stage turbine disc is fixedly connected to the turbine main shaft; The outer edge of the two-stage turbine disk is provided with two stages of turbine disk blade cascades in the radial direction, and a guide vane ring blade cascade accommodating cavity is formed between the two stages of turbine disk blade cascades; the inner side of the guide vane ring is provided with two stages of hole-type damping sealing structures, and the two stages of hole-type damping sealing structures correspond to the two stages of turbine disk blade cascades; a guide vane ring blade cascade is provided between the two stages of hole-type damping sealing structures and extends into the guide vane ring blade cascade accommodating cavity; The hole-type damping sealing structure is composed of a plurality of circular hole grooves arranged on the inner side of the guide vane ring.

2. The aerospace turbine with a hole-type damping seal structure according to claim 1, characterized in that: The circular hole has a diameter of 1-10 mm and a depth of 1-10 mm.

3. The aerospace turbine with a hole-type damping seal structure according to claim 2, characterized in that: The spacing between adjacent circular slots of the hole-type damping sealing structure is 1-10 mm.

4. The aerospace turbine with a hole-type damping seal structure according to claim 1, characterized in that: The turbine housing is composed of an air collecting ring and a nozzle ring, and nozzles are arranged circumferentially inside the nozzle ring; the air collecting ring is located on one side of the nozzle ring, and the guide vane ring is fixed to the other side of the nozzle ring through a detachable part.

5. The aerospace turbine with a hole-type damping seal structure according to claim 4, characterized in that: The nozzle ring and the guide vane ring are also provided with external stops for radial positioning.

6. The aerospace turbine with a hole-type damping seal structure according to claim 4, characterized in that: The detachable parts are flanges and bolts.

7. The aerospace turbine with a hole-type damping seal structure according to claim 4, characterized in that: The turbine housing is integrally formed by 3D printing.

8. The aerospace turbine with a hole-type damping seal structure according to claim 1, characterized in that: The outlet pipe is fixed on the turbine housing by welding.

9. The aerospace turbine with a hole-type damping seal structure according to claim 1, characterized in that: The two-stage turbine disc is fixedly connected to the turbine main shaft via an involute spline and / or a flange.

10. The aerospace turbine with a hole-type damping seal structure according to claim 1, characterized in that: The guide vane ring is composed of multiple parts.

Images