CN110805476A - Turbine disc with cavity structure of obturaging - Google Patents
Turbine disc with cavity structure of obturaging Download PDFInfo
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- CN110805476A CN110805476A CN201910987701.1A CN201910987701A CN110805476A CN 110805476 A CN110805476 A CN 110805476A CN 201910987701 A CN201910987701 A CN 201910987701A CN 110805476 A CN110805476 A CN 110805476A
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- disc
- turbine
- sealing ring
- static
- static disc
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/028—Blade-carrying members, e.g. rotors the rotor disc being formed of sheet laminae
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a turbine disc with a cavity sealing structure, which comprises a turbine static disc and a turbine dynamic disc, wherein the turbine static disc is provided with a cavity; the inner and outer sealing rings of the static disc extend outwards from the side of the static disc between the edges of the static disc of the turbine wheel, and the inner sealing ring of the dynamic disc extends outwards from the side of the dynamic disc of the turbine wheel; wherein, the head end or the position close to the wall surface of the static disc of the sealing ring in the static disc is provided with a circular boss ring which is convex towards the high radius direction, and the tail end or the position close to the tail end of the sealing ring in the static disc is provided with a circular boss ring which is convex towards the high radius direction; the static disc outer containing cavity formed by the sealing structure enables gas to generate vortex between the static disc outer sealing ring and the movable disc inner sealing ring on one hand, effectively prevents part of high-temperature gas from invading at the sealed cold air outflow port, and consumes part of invading high-temperature gas; on the other hand, standing vortex is generated in the groove between the boss ring and the convex ring by the fuel gas, so that the fuel gas in the deep cavity is further blocked, and the fuel gas is prevented from invading the sealed inner cavity; on the premise of certain sealing air consumption, the fuel gas can be better blocked in the outer containing cavity of the static disc, so that the sealing performance is greatly improved.
Description
Technical Field
The invention belongs to the technical field of engines, and particularly relates to the technical field of rotating parts, such as gas turbines and aero-engines.
Background
The research on the pneumatic heat transfer problem of the gas turbine has important significance in the fields of science and technology.
The increasing inlet parameters and the decreasing quality of cooling air of gas turbines result in increasing thermal loads on hot end components, and therefore, advanced secondary air cooling systems are required to prevent overheating and reduce the thermal stress level of rotating components such as disks, blades and rotors. The structural design of the rim seal, which is one of the important components of the advanced secondary air cooling system of the gas turbine, is also one of the key technologies for the development of the gas turbine.
Gas intrusion is a serious problem that may be encountered by the rotating-stationary disk cavity of a turbine. High-temperature gas goes deep into the center of the disc along the rotating-static disc cavity, so that uncontrollable deformation and fatigue of the wheel disc, serious damage to nearby bearings and the like are caused, and the like. The main way of reducing the gas intrusion is to increase the gas supply of a disc cavity, the cooling gas introduced from the gas compressor can effectively prevent the main flow gas intrusion, but the excessive extraction of cold gas from the gas compressor inevitably leads to the reduction of the overall heat efficiency of the engine; another measure is to arrange a rim seal on the outer diameter of the turbine disk to increase the flow resistance of the invading gas. Therefore, the reasonable design of the sealing structure of the disc edge can obviously reduce the amount of cooling air pumped from the compressor side, improve the overall efficiency of the gas turbine, and is one of the key technologies developed in the field of modern high-parameter and high-power gas turbines.
Disclosure of Invention
The purpose of the invention is as follows: the invention relates to a turbine disc with a cavity sealing structure, aiming at achieving good sealing performance of disc edge sealing under the condition of small amount of cold air by adopting a relatively simple structure.
The technical scheme is as follows: in order to achieve the purpose, the invention adopts the following technical scheme:
a turbine disc with a composite disc edge sealing structure comprises a turbine casing, a turbine static disc and a turbine dynamic disc; the turbine static disc and the turbine movable disc are coaxially arranged, and the turbine movable disc rotates relative to the turbine static disc; a rotating and static disc cavity is formed between the turbine static disc and the turbine dynamic disc; a main flow channel is formed among the turbine casing, the turbine static disc and the turbine dynamic disc; the inner side wall surface of the turbine static disc, the inner side wall surface of the turbine movable disc and the main flow channel form a cold air channel; the outer edge of the turbine static disc is provided with a circular outer sealing ring extending towards the turbine movable disc; the surface of the turbine static disc, which faces the turbine movable disc, extends towards the turbine movable disc to form an annular static disc inner sealing ring; the side, facing the turbine static disc, of the turbine movable disc extends to the turbine static disc to form an annular movable disc inner sealing ring; wherein, the head end or the position close to the wall surface of the static disc of the sealing ring in the static disc is provided with a circular boss ring which is convex towards the high radius direction, and the tail end or the position close to the tail end of the sealing ring in the static disc is provided with a circular boss ring which is convex towards the high radius direction; a groove with an open surface facing the high radius direction is formed between the boss ring and the convex ring; the outer sealing ring of the static disc and the inner sealing ring of the static disc form an outer cavity of the static disc.
Has the advantages that: the sealing structure forms a novel static disc outer cavity, the cavity structure effectively reduces the flowing speed of the invading gas, and the high-temperature gas is prevented from deeply invading the static disc cavity. In the static disc outer cavity, high-temperature gas flows into the cavity along the outer inclined plane of the dynamic disc inner sealing ring; after leaving the inclined plane, most of flowing fuel gas flows back to the high radius and along the inner wall surface of the static disc outer sealing ring, and clockwise vortex is generated between the static disc outer sealing ring and the dynamic disc inner sealing ring, so that on one hand, the invasion of part of high-temperature fuel gas to a static disc cavity is blocked, on the other hand, a large amount of invaded high-temperature fuel gas is consumed, and the rotation induced invasion effect is weakened to a certain extent; in addition, standing vortex can be generated in the groove between the boss ring and the convex ring, and the standing vortex and cold airflow flowing along the inner wall surface of the sealing ring in the movable disc can effectively block the other part of gas flowing into the deep cavity in the deep cavity of the outer cavity of the static disc; higher sealing efficiency can be obtained on the premise of not increasing the sealing air consumption.
Further, the turbine engine also comprises an outermost annular turbine casing, guide vanes and movable blades; the method is characterized in that: a main flow channel is formed among the turbine casing, the turbine static disc and the turbine movable disc, one end of each of a plurality of guide vanes in the main flow channel is fixed on the annular turbine casing at the outermost side, and the other end of each guide vane in the main flow channel is fixed on the turbine static disc; a plurality of movable blades in the main flow channel are fixedly connected with the turbine movable disc. Because the movable turbine disc rotates coaxially relative to the stationary turbine disc, a gap is reserved between the movable turbine disc and the turbine casing. The shape surfaces of the static disc wall surface and the movable disc wall surface jointly form a rotating and static disc cavity cold air channel. The existence of the sealing ring on the wall surface of the dynamic and static discs makes the flow passage of the disc cavity become tortuous.
Furthermore, the ratio S of the axial length of the sealing ring in the movable disc to the axial distance of the rotating and static disc cavities1S should be more than 0.5, the radial projection of the outer sealing ring of the static disc and the inner sealing ring of the movable disc should be overlapped, and the ratio S of the distance from the inner sealing ring of the static disc to the disc surface of the movable disc to the axial distance of the cavity of the static disc5S should be less than 0.5 to ensure that there is some overlap of the sealing rings in the stationary and moving discs and their radial thickness h2Is 3-5 mm.
Furthermore, the cross section of the head end of the boss ring or the part close to the wall surface of the static disc is smoothly connected with the wall surface of the static disc by adopting an arc, and the cross section of the tail end of the boss ring is connected with the sealing ring in the static disc by adopting a convex arc or a concave arc; the cross section of a convex ring at the tail end of the sealing ring in the static disc is in a right trapezoid shape, and the lower bottom of the right trapezoid shape of the section of the convex ring is connected with the sealing ring in the static disc.
Furthermore, the included angle β between the surface of the static disc outer sealing ring facing the dynamic disc inner sealing ring and the wall surface of the static disc is 100-120 degrees, the connection is smooth transition, the root part of the movable blade, the end surface of the hub and the movable disc inner sealing ring are in smooth transition, and the movable disc inner sealing ring and the end surface of the movable disc are in smooth transition.
Furthermore, the distance between the upper bottom surface of the section of the convex ring at the tail end surface of the sealing ring in the static disc and the sealing ring in the movable disc is 2-4 mm, the tooth height is not more than 4mm, and the upper bottom S is30.5-1.5 mm, and 100-120 degrees of upper vertex angle α.
Further, the thickness h of the boss ring at the head end of the inner seal ring of the static disc1Should be higher than trapezoidal tooth, but should be lower than the dynamic disc inner seal ring, and the axial length S of the boss at the head end of the static disc inner seal ring4From the outer cavity of the static disc to the inner cavity of the dynamic discDistance S of end face of sealing ring2Ratio S of4/S20.5 to 1.
Furthermore, the minimum radial distance of the tail end of the sealing ring in the movable disc facing the end face of the static disc is 1-2 mm, and the outer surface of the sealing ring in the movable disc can adopt a convex inclined surface or a concave inclined surface besides a straight inclined surface. When the convex inclined surface is adopted, the minimum radial clearance for sealing is relatively reduced, and high-temperature gas entering the sealing cavity is reduced, so that the sealing efficiency is improved; when the concave inclined surface is adopted, the vortex system between the outer sealing ring of the static disc and the inner sealing ring of the movable disc can be strengthened, the fuel gas flowing into the deep cavity can be lifted and blown to the high-radius wall surface of the deep cavity, and the fuel gas can be limited in the deep cavity for a long time.
Furthermore, in the overlapped part of the sealing ring in the movable disc and the sealing ring outside the static disc, the radial distance between the outer surface of the sealing ring in the movable disc and the inner surface of the sealing ring outside the static disc is 2-4 mm.
Drawings
FIG. 1 is an isometric view of the overall structure of a turbine disk, partially cut away to show internal structure.
Fig. 2 is a schematic view of a turbine disk structure.
Fig. 3 is an enlarged partial cross-sectional view of the portion of the isometric view of fig. 1 indicated by the dashed box.
FIG. 4 is a schematic view of the vector streamline of the outer cavity of the stator disc of the turbine disc.
Detailed Description
The accompanying drawings are only schematic structural views of a preferred embodiment, and the following detailed description of the present invention is given in conjunction with the accompanying drawings, which are included for explanation of the present invention and are not intended to limit the present invention.
Referring to fig. 1 and 3, the present embodiment is a turbine disk with a composite disk edge sealing structure, and is used for products related to turbine components, such as aircraft engines or gas turbines. Said invention mainly includes: a turbine case 1; a turbine vane 2; turbine buckets 3; a turbine stationary disk 4; a turbine rotor disk 5; a static disc outer sealing ring 6; a static disc outer cavity 7; a dynamic disc inner sealing ring 8; a convex ring cross-section 9; a stationary disc inner sealing ring 10; a static disc inner cavity 11; a main flow gas channel 12; rotating and static disc cavity13. The two ends of the guide vane 2 in the turbine main flow gas channel 12 are respectively fixed between the turbine casing 1 and the turbine static disc 4, the movable vane 3 is fixedly connected with the turbine movable disc 5, a certain gap is left between the high-radius end of the movable vane 3 and the turbine casing, the turbine static disc 4 and the movable disc 5 form a rotating and static system, the gap between the two wheels is called as a rotating and static disc cavity 13, the wall surface of the static disc 4, the wall surface of the movable disc 5 and the main flow channel form a cold air channel, and cold air introduced from the compressor flows between the cold air channel and the cold air channel. An annular outer sealing ring 6 and an annular inner sealing ring 10 are arranged on the side of the turbine static disc 4 in the cavity of the rotating static disc, and an annular inner sealing ring 8 is arranged on the side of the turbine movable disc 5 in the cavity of the rotating static disc; wherein, the position of the head end of the sealing ring 10 in the static disc or close to the wall surface of the static disc 4 is provided with a circular boss ring 14 which is convex towards the high radius direction, and the position of the tail end of the sealing ring 10 in the static disc or close to the tail end is provided with a circular boss ring 9 which is convex towards the high radius direction; the outer static disc sealing ring 6 and the inner static disc sealing ring 10 form an outer static disc accommodating cavity 7. The sealing rings are arranged in a staggered manner and are in a covering shape, high-temperature gas flows into the cavity along the surface of the straight inclined surface on the outer side of the sealing ring in the movable disc, most of the gas flows back to a high-radius position and along the inner wall surface of the sealing ring outside the static disc after leaving the straight inclined surface, and clockwise vortexes are generated between the sealing ring outside the static disc and the sealing ring inside the movable disc; standing vortex can be generated in the groove between the boss ring and the convex ring, and high-temperature gas is completely blocked in the outer cavity 7 of the static disc under the condition that the flow of cold gas is not increased. Therefore, the novel sealing structure for the disc edge can improve the sealing efficiency and the turbine efficiency under the condition of not increasing the use amount of cold air. To achieve the above result, in the present embodiment, the ratio S of the axial length of the dynamic disk inner seal ring 8 to the axial spacing of the static disk cavities1S should be more than 0.5, the radial projection of the static disc outer sealing ring 6 and the movable disc inner sealing ring 8 should be overlapped, and the ratio S of the distance from the static disc inner sealing ring 10 to the disc surface of the movable disc 5 to the axial distance of the rotating and static disc cavity5S should be less than 0.5 to ensure that there is some overlap of the sealing rings in the stationary and moving discs and their radial thickness h2Is within 3-5 mm.
In the embodiment, the cross section of the head end of the boss ring 14 or the position close to the wall surface of the static disc 4 is smoothly connected with the wall surface of the static disc by adopting an arc, and the cross section of the tail end of the boss ring is smoothly connected with the static discThe sealing rings 10 in the disc are connected by adopting convex circular arcs or concave circular arcs; the cross section of a convex ring 9 at the tail end of the static disc inner sealing ring 10 is in a right trapezoid shape, and the lower bottom of the right trapezoid shape of the cross section of the convex ring 9 is connected with the static disc inner sealing ring 10. The distance between the upper bottom surface of the convex ring section 9 at the tail end of the static disc inner sealing ring 10 and the movable disc inner sealing ring 8 is 2-4 mm, the tooth height is not more than 4mm, and the upper bottom S is30.5-1.5 mm, and 100-120 degrees of upper vertex angle α, the thickness h of the boss ring 14 at the head end of the inner seal ring 10 of the static disc1Should be higher than the trapezoidal teeth 9, but lower than the dynamic disc inner sealing ring 8, and the axial length S of the boss at the head end of the static disc inner sealing ring 104The distance S from the outer cavity 7 of the static disc to the end face of the inner sealing ring of the dynamic disc2Ratio S of4/S20.5-1, in the overlapped part of the movable disc inner sealing ring 8 and the static disc outer sealing ring 6, the radial distance between the outer surface of the movable disc inner sealing ring 8 and the inner surface of the static disc outer sealing ring 6 is between 2-4 mm, the included angle β between the surface of the static disc outer sealing ring facing the movable disc inner sealing ring 8 and the wall surface of the static disc 4 is 100-120 degrees, smooth transition connection is adopted between the surfaces, the root part of the movable blade 3, the end surface of the hub and the movable disc inner sealing ring 8 are in smooth transition, the smooth transition between the movable disc inner sealing ring 8 and the end surface of the movable disc 5 is adopted, the minimum radial distance between the tail end of the movable disc inner sealing ring 8 facing the end surface of the static disc is 1-2 mm, the outer surface of the movable disc inner sealing ring 8 adopts a straight inclined surface, as shown in figure 3 in the embodiment, a convex inclined surface 16 or a concave inclined surface 17 is also adopted, when the convex inclined surface 16 is adopted, the minimum radial clearance of the sealing is relatively reduced, the high-temperature gas entering the sealing cavity is reduced, and the sealing efficiency is improved, and when the concave inclined surface 17 is adopted, the outer surface of the vortex sealing ring 6 and the vortex ring is deeply blown to the vortex chamber, the high-pressure sealing ring is limited.
Various other modifications and changes may be made by those skilled in the art based on the above-described technical solutions and concepts, and all such modifications and changes should fall within the scope of the claims of the present invention.
Claims (9)
1. A turbine disc with a composite disc edge sealing structure comprises a turbine casing (1), a turbine static disc (4) and a turbine movable disc (5); the turbine static disc (4) and the turbine movable disc (5) are coaxially arranged, and the turbine movable disc (5) rotates relative to the turbine static disc (4); a rotating static disc cavity (13) is formed between the turbine static disc (4) and the turbine movable disc (5); a main flow channel (12) is formed among the turbine casing (1), the turbine static disc (4) and the turbine movable disc (5); the inner side wall surface of the turbine static disc (4), the inner side wall surface of the turbine movable disc (5) and the main flow channel form a cold air channel; the method is characterized in that: the outer edge of the turbine static disc (4) is provided with a circular outer sealing ring (6) extending towards the turbine movable disc (5); the turbine static disc (4) faces the turbine movable disc (5), and a circular ring-shaped static disc inner sealing ring (10) extends towards the turbine movable disc (5); the turbine moving disc (5) faces the turbine static disc (4), and a circular moving disc inner sealing ring (8) extends towards the turbine static disc (4); wherein, the head end of the sealing ring (10) in the static disc or the position close to the wall surface of the static disc (4) is provided with a circular boss ring (14) protruding towards the high radius direction, and the tail end of the sealing ring (10) in the static disc or the position close to the tail end is provided with a circular boss ring (9) protruding towards the high radius direction; a groove with an open surface facing the high radius direction is formed between the boss ring (14) and the convex ring (9); an outer sealing ring (6) of the static disc and an inner sealing ring (10) of the static disc form an outer cavity (7) of the static disc.
2. The turbine disk of claim 1, wherein: the turbine engine further comprises an annular turbine casing (1) positioned at the outermost side, a guide vane (2) and a movable vane (3); one end of a plurality of guide vanes (2) in the main flow channel (12) is fixed on the annular turbine casing (1) at the outermost side, and the other end is fixed on the turbine static disc (4); a plurality of movable blades (3) in the main flow channel (12) are fixedly connected with the turbine movable disc (5); a gap is reserved between the movable blade (3) and the turbine casing (1).
3. The turbine disk of claim 1 or 2, wherein: the ratio S of the axial length of the sealing ring (8) in the moving disc to the axial distance of the rotating and static disc cavities1S is more than 0.5, the radial projection of the static disc outer sealing ring (6) and the moving disc inner sealing ring (8) is overlapped, and the ratio S of the distance from the static disc inner sealing ring (10) to the disc surface of the moving disc (5) to the axial distance of the rotating and static disc cavity5S is less than 0.5, and the static disc is sealedThe ring and the inner sealing ring of the movable disc have certain overlap, while the radial thickness h of the inner sealing ring of the static disc2Is 3-5 mm.
4. A turbine disc according to claim 1 or 3, wherein: the cross section of the head end of the boss ring (14) or the part close to the static disc (4) is smoothly connected with the wall surface of the static disc by adopting an arc, and the cross section of the tail end of the boss ring is connected with the sealing ring (10) in the static disc by adopting a convex arc or a concave arc; the cross section of a convex ring (9) at the tail end of the static disc inner sealing ring (10) is in a right trapezoid shape, and the lower bottom of the right trapezoid shape of the cross section of the convex ring (9) is connected with the static disc inner sealing ring (10).
5. A turbine disc according to claim 1 or 3, characterized in that the included angle β between the surface of the outer sealing ring of the static disc facing the inner sealing ring (8) of the movable disc and the wall surface of the static disc (4) is 100-120 degrees, the root of the movable vane (3), the end surface of the hub and the inner sealing ring (8) of the movable disc are in smooth transition, and the inner sealing ring (8) of the movable disc and the end surface of the movable disc (5) are in smooth transition.
6. The turbine disk of claim 4, wherein: the distance between the upper bottom surface of the convex ring section (9) at the tail end surface of the static disc inner sealing ring (10) and the movable disc inner sealing ring (8) is 2-4 mm, the tooth height is not more than 4mm, and the upper bottom S is30.5-1.5 mm, and 100-120 degrees of upper vertex angle α.
7. The turbine disk of claim 4, wherein: thickness h of boss ring (14) at head end of inner seal ring (10) of static disc1Is higher than the trapezoidal teeth (9) but lower than the movable disc inner sealing ring (8), and the axial length S of the boss at the head end of the static disc inner sealing ring (10)4A distance S from an outer containing cavity (7) of the static disc to the tail end face of the inner sealing ring of the dynamic disc2Ratio S of4/S20.5 to 1.
8. The turbine disk of claim 5, wherein: the minimum radial distance of the tail end of the movable disc inner sealing ring (8) facing the end face of the static disc is 1-2 mm, and the outer surface of the movable disc inner sealing ring (8) adopts a straight inclined plane, a convex inclined plane (16) or a concave inclined plane (17).
9. The turbine disk of claim 5, wherein: in the overlapped part of the movable disc inner sealing ring (8) and the static disc outer sealing ring (6), the radial distance between the outer surface of the movable disc inner sealing ring (8) and the inner surface of the static disc outer sealing ring (6) is 2-4 mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910987701.1A CN110805476B (en) | 2019-10-17 | 2019-10-17 | Turbine disc with cavity structure of obturaging |
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| CN201910987701.1A CN110805476B (en) | 2019-10-17 | 2019-10-17 | Turbine disc with cavity structure of obturaging |
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| CN110805476A true CN110805476A (en) | 2020-02-18 |
| CN110805476B CN110805476B (en) | 2022-04-12 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112431639A (en) * | 2020-11-27 | 2021-03-02 | 北京化工大学 | Can restrain rim seal structure of inhomogeneous multiscale gas invasion |
| CN112594014A (en) * | 2020-12-15 | 2021-04-02 | 中国科学院工程热物理研究所 | Sealing air supply device for transonic turbine plane cascade experiment |
| CN112922673A (en) * | 2021-02-04 | 2021-06-08 | 南京航空航天大学 | Turbine disc with T-shaped disc edge sealing structure |
| CN115075893A (en) * | 2021-03-12 | 2022-09-20 | 斗山重工业建设有限公司 | Turbine engine |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112431639A (en) * | 2020-11-27 | 2021-03-02 | 北京化工大学 | Can restrain rim seal structure of inhomogeneous multiscale gas invasion |
| CN112594014A (en) * | 2020-12-15 | 2021-04-02 | 中国科学院工程热物理研究所 | Sealing air supply device for transonic turbine plane cascade experiment |
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| CN112922673A (en) * | 2021-02-04 | 2021-06-08 | 南京航空航天大学 | Turbine disc with T-shaped disc edge sealing structure |
| CN115075893A (en) * | 2021-03-12 | 2022-09-20 | 斗山重工业建设有限公司 | Turbine engine |
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|---|---|
| CN110805476B (en) | 2022-04-12 |
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