CN210105926U - Turbine disk, liquid rocket engine and liquid rocket - Google Patents
Turbine disk, liquid rocket engine and liquid rocket Download PDFInfo
- Publication number
- CN210105926U CN210105926U CN201920205330.2U CN201920205330U CN210105926U CN 210105926 U CN210105926 U CN 210105926U CN 201920205330 U CN201920205330 U CN 201920205330U CN 210105926 U CN210105926 U CN 210105926U
- Authority
- CN
- China
- Prior art keywords
- blades
- turbine
- liquid rocket
- blade
- turbine disc
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model provides a turbine disc, a liquid rocket engine and a liquid rocket, wherein the turbine disc comprises a turntable; at least two stages of blades are formed on the periphery of the rotary table; wherein the blades and the turntable are integrally formed for additive manufacturing. Compare with processing technology such as traditional electric spark, when the range between the interval undersize of two-stage blade or blade at the same level is inseparable, traditional technology receives the influence of operating space and machining precision etc, and the turbine dish under the above-mentioned parameter condition is difficult to process, nevertheless the utility model provides a turbine dish adopts vibration material disk integrated into one piece, piles up the shape of printing into the design with raw and other materials melting during vibration material disk manufacturing technique, and its course of working is the pile up shaping, and is lower to the requirement of structure, can very convenient processing out the turbine dish of above-mentioned description, and the course of working is simple, and the time is short.
Description
Technical Field
The utility model relates to an aerospace technical field, concretely relates to turbine disc, liquid rocket engine, liquid rocket.
Background
The turbine disc is one of key parts in a liquid rocket engine turbine pump, and the function of the turbine disc is to convert the internal energy of high-temperature and high-pressure fuel gas into kinetic energy to provide input power for the pump. To improve turbine efficiency, the prior art typically employs shrouded blades, with the shroud of all blades typically being an integral annulus, known as a shroud.
At present, most turbine disks are formed by adopting a forging machine and combining electric spark machining, the order period of forging blanks is long, the machining amount is large, and meanwhile, because the turbine disks are provided with shroud rings, turbine blades can only adopt electric spark machining. The electric spark machining has long blade period, and particularly for a two-stage or multi-stage turbine disk, the traditional machining is difficult to realize due to the fact that the turbine structure of the liquid rocket engine is compact and the distance between blades is small.
SUMMERY OF THE UTILITY MODEL
Therefore, the to-be-solved technical problem of the utility model lies in overcoming among the prior art multistage turbine dish because of the less problem that leads to the processing difficulty of blade interval at different levels to a turbine dish, liquid rocket engine, liquid rocket are provided.
In order to solve the above problems, the utility model provides a turbine disc, which comprises a rotary disc;
at least two stages of blades are formed on the periphery of the rotary table;
wherein the blades and the turntable are integrally formed for additive manufacturing.
Further, the blades are straight blades.
Further, the blade includes a first-stage blade and a second-stage blade coaxially arranged with the first-stage blade.
Further, the ratio of the axial chord length of the blade to the turbine pitch diameter of the blade is [0.03, 0.07 ].
Further, the axial chord A of the first-stage blade is 9.96mm, and the radial spacing B is 2.22 mm.
Further, the axial chord length C of the secondary blades is 10.96mm, and the radial distance D is 4.66 mm.
Further, the axial distance E between the primary blade and the secondary blade is 16 mm.
The utility model also provides a liquid rocket engine includes: a turbine disc as claimed in any one of the preceding claims.
The utility model also provides a liquid rocket includes: a turbine disk as described in any preceding claim, or a liquid rocket engine as described in any preceding claim.
The utility model discloses technical scheme has following advantage:
1. the utility model provides a turbine disc which comprises a turntable; at least two stages of blades are formed on the periphery of the rotary table; wherein the blades and the turntable are integrally formed for additive manufacturing.
Compare with processing technology such as traditional electric spark, when the range between the interval undersize of two-stage blade or blade at the same level is inseparable, traditional technology receives the influence of operating space and machining precision etc, and the turbine dish under the above-mentioned parameter condition is difficult to process, nevertheless the utility model provides a turbine dish adopts vibration material disk integrated into one piece, piles up the shape of printing into the design with raw and other materials melting during vibration material disk manufacturing technique, and its course of working is the pile up shaping, and is lower to the requirement of structure, can very convenient processing out the turbine dish of above-mentioned description, and the course of working is simple, and the time is short.
2. The utility model provides an in the turbine dish the blade be straight blade, straight blade structure is for other complicated high-order curved surface blades, its structure is simple relatively, and the processing calculated amount is little, can improve machining efficiency.
3. The utility model provides a blade include the one-level blade and with the second grade blade of the coaxial setting of one-level blade. The turbine disk with the two-stage blades is relatively simple in structure and short in material increase manufacturing time.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic structural view of a turbine disk provided in embodiment 1 of the present invention;
fig. 2 is a schematic structural view of a primary blade provided in embodiment 1 of the present invention;
fig. 3 is a schematic structural view of a secondary blade provided in embodiment 1 of the present invention;
fig. 4 is a schematic pitch structure diagram of a two-stage blade provided in embodiment 1 of the present invention.
Description of reference numerals:
1-a turntable;
2-a blade; 21-first stage blades; 22-secondary blades.
Detailed Description
The technical solution of the present invention will be described clearly and completely with reference to the accompanying drawings, and obviously, the described embodiments are some, but not all embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Furthermore, the technical features mentioned in the different embodiments of the invention described below can be combined with each other as long as they do not conflict with each other.
Example 1
As shown in fig. 1 to 4, a turbine disk provided for the embodiment 1 includes: a turntable 1; at least two stages of blades 2 are formed on the periphery of the rotary table 1; wherein the blades 2 and the rotating disk 1 are integrally formed by additive manufacturing.
Compare with processing technology such as traditional electric spark, when the range between the interval undersize of two-stage blade 2 or blade 2 at the same level is inseparable, traditional technology receives the influence of operating space and machining precision etc, and the turbine dish under the above-mentioned parameter condition is difficult to process, nevertheless the utility model provides a turbine dish adopts vibration material disk integrated into one piece, piles up the shape of printing into the design with raw and other materials melting during vibration material disk manufacturing technique, and its course of working is the pile up shaping, and is lower to the requirement of structure, can very convenient processing out the turbine dish of above-mentioned description, and the course of working is simple, and the time is short.
The blade 2 in the embodiment is a straight blade, the structure is relatively simple, the processing calculated amount is small, and the processing efficiency can be improved.
Further, the blade 2 comprises a first-stage blade 21 and a second-stage blade 22 which is coaxially arranged with the first-stage blade 21, the structure of the turbine disk of the two-stage blade is relatively simple, and the additive manufacturing time is short.
Typically, the ratio of the axial chord length of the blade 2 to the turbine pitch diameter F of the blade 2 is [0.03, 0.07 ].
As shown in fig. 2, the turbine pitch diameter F in the present embodiment is 200mm, the axial chord length a of the first-stage blades 21 is 9.96mm, the radial distance B is 2.22mm, the blade height is 10mm, the number of the first-stage blades is 85, as shown in fig. 3, the axial chord length C of the second-stage blades 22 is 10.96mm, the radial distance D is 4.66mm, the blade height is 12mm, the number of the blades is 88, and as shown in fig. 4, the axial distance E between the first-stage blades 21 and the second-stage blades 22 is 16 mm. The technical parameters in this embodiment, that is, the distance between the blades at the same stage is small, and particularly, the radial distance between the blades at the first stage is only 2.22mm, if the conventional electric discharge machining is adopted, firstly, the electric discharge machining is used as a special machining process, so that the machining cost is high, and the machining difficulty is large, the machining period is long, the time cost investment is huge, the machining difficulty is large, the reject ratio of the product is high, and the production efficiency is seriously affected.
The turbine disc in the embodiment is prepared by an additive manufacturing technology, specifically, the turbine disc is printed and molded by a 3D printer, a three-dimensional model of the three-dimensional turbine disc is firstly drawn by three-dimensional software, three-dimensional model data is input into the 3D printer, and the three-dimensional data model data is printed and molded by a selective laser melting and molding process. The material used by the turbine disc in the embodiment is Inconel718 high-temperature alloy, is in a powder shape, can pass through a No.200 sieve, and has a one-time passing rate of not less than 95%. The method comprises the following steps of machining and forming a rough blank of the turbine disc through a 3D printer, removing redundant high-temperature alloy powder in the rough blank, removing the redundant high-temperature alloy powder through blowing and polishing, removing internal stress through solution heat treatment, and performing fine polishing treatment on a turbine blade.
Meanwhile, the turbine disc is one of key parts of the turbine pump, works under the conditions of high temperature, high pressure, high rotating speed and the like, bears complex loads such as centrifugal load, thermal load, vibration and the like, is very severe in stress condition, and is relatively small in strength safety margin. Because the 3D printing technology is adopted for the turbine disc for the first time, in order to verify the feasibility of the application of the 3D printing technology on the turbine disc, the strength safety margin of the turbine disc and the blades needs to be discovered, and an over-rotation test needs to be carried out on the turbine disc and the blades.
Before the over-rotation test, the dynamic balance test is firstly carried out on the turbine disc in the implementation. The dynamic balance test is a process of detecting and correcting the dynamic balance of a rotating piece and meeting the use requirement. In an ideal case, when the rotating member rotates and does not rotate, the pressure generated on the bearing is the same, and the rotating body is a balanced rotating body. However, various rotating parts in engineering have asymmetric geometric shapes due to various factors such as uneven material, blank defects, errors generated in processing and assembly, and even design, so that centrifugal inertia force generated by each tiny mass point on the rotating parts cannot be counteracted mutually when the rotating parts rotate. Centrifugal inertia force acts on machinery and the foundation through the bearing, vibration is caused, noise is generated, bearing abrasion is accelerated, the service life of the machinery is shortened, and destructive accidents can be caused in severe cases. For this purpose, the rotor must be subjected to a balancing test to an acceptable level of precision of the balancing or to an acceptable range of amplitude of the mechanical vibrations generated thereby. According to the requirements of a test bed of a tester, the final unbalance amount after the dynamic balance test is less than 100mg, the over-rotation test is carried out for multiple times of normal-temperature over-rotation tests and multiple times of high-temperature over-rotation tests respectively in order to find out the strength of the turbine disc at normal temperature and at high temperature, the total over-rotation time is as long as eight thousand seconds, after each over-rotation test, the size inspection and the coloring inspection are respectively carried out, all indexes are normal through inspection, and the feasibility of the processing mode of 3D printing the turbine disc is verified.
Example 2
This embodiment provides a liquid rocket engine, which includes the turbine disk of embodiment 1, and has all the technical advantages, and therefore, the detailed description is omitted here.
Example 3
This embodiment provides a liquid rocket, which includes the turbine disk in embodiment 1 or the liquid rocket in embodiment 2, and has all the technical advantages, and therefore, the details are not repeated herein.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications can be made without departing from the scope of the invention.
Claims (9)
1. A turbine disk for a rocket engine, comprising:
a turntable (1);
at least two stages of blades (2) are formed on the periphery of the rotary table (1);
wherein the blades (2) and the turntable (1) are integrally formed by additive manufacturing.
2. A turbine disc according to claim 1, characterized in that the blades (2) are straight blades.
3. A turbine disc according to claim 2, characterized in that the blades (2) comprise primary blades (21) and secondary blades (22) arranged coaxially to the primary blades (21).
4. A turbine disc according to claim 3, characterized in that the ratio of the axial chord length of the blades (2) to the turbine pitch diameter F of the blades (2) is [0.03, 0.07 ].
5. A turbine disc according to claim 4, wherein the axial chord A of the primary blades (21) is 9.96mm and the radial pitch B is 2.22 mm.
6. A turbine disc according to claim 4, wherein the secondary blades (22) have an axial chord length C of 10.96mm and a radial pitch D of 4.66 mm.
7. A turbine disc according to claim 4, characterized in that the axial spacing E of the primary blades (21) from the secondary blades (22) is 16 mm.
8. A liquid rocket engine, comprising:
a turbine disk as claimed in any one of claims 1 to 7.
9. A liquid rocket, comprising:
a turbine disk as claimed in any one of claims 1 to 7, or
A liquid rocket engine as recited in claim 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920205330.2U CN210105926U (en) | 2019-02-15 | 2019-02-15 | Turbine disk, liquid rocket engine and liquid rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920205330.2U CN210105926U (en) | 2019-02-15 | 2019-02-15 | Turbine disk, liquid rocket engine and liquid rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210105926U true CN210105926U (en) | 2020-02-21 |
Family
ID=69532233
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920205330.2U Active CN210105926U (en) | 2019-02-15 | 2019-02-15 | Turbine disk, liquid rocket engine and liquid rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210105926U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109826670A (en) * | 2019-02-15 | 2019-05-31 | 北京星际荣耀空间科技有限公司 | The turbine disk, liquid-propellant rocket engine, liquid rocket |
-
2019
- 2019-02-15 CN CN201920205330.2U patent/CN210105926U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109826670A (en) * | 2019-02-15 | 2019-05-31 | 北京星际荣耀空间科技有限公司 | The turbine disk, liquid-propellant rocket engine, liquid rocket |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3660282B1 (en) | Containment system for gas turbine engine | |
| JP2017522488A (en) | Manufacturing turbomachinery impellers by assembling multiple tubular parts | |
| CN210105926U (en) | Turbine disk, liquid rocket engine and liquid rocket | |
| JP2012021526A (en) | Dovetail connection for turbine rotating blade and rotor wheel | |
| WO2011018413A1 (en) | Turbine diaphragms | |
| US20190128126A1 (en) | Turbine blisk and method of manufacturing thereof | |
| US1399816A (en) | Rotor for multistage high-speed engines | |
| CN109977537B (en) | Turbine blade and method for producing a turbine blade | |
| US20140140849A1 (en) | Gas turbine engine compressor rotor assembly and balancing system | |
| CN206419067U (en) | A kind of Gas Turbine Power turbine structure based on friction torsion pass | |
| WO2012048957A1 (en) | Turbomachine rotor with blade roots with adjusting protrusions | |
| EP2955329A1 (en) | Integrally formed rotor assembly with shaft and blisks | |
| US10914174B2 (en) | Method for the construction of bladed discs for radial turbomachines and a bladed disc obtained by means of this method | |
| CN109826670A (en) | The turbine disk, liquid-propellant rocket engine, liquid rocket | |
| CN106224016B (en) | Turbine rotor, engine and the method for improving engine rotor centering reliability | |
| CN209743041U (en) | Novel gas turbine rotor | |
| EP3674517B1 (en) | Kinetic disassembly of support structure system for additively manufactured rotating components | |
| JP2011157965A (en) | Shaped rotor wheel capable of carrying multiple blade stages | |
| CN111379738A (en) | Impeller, turbo compressor equipped with an impeller, and method for manufacturing an impeller | |
| JP5220314B2 (en) | Gas turbine disk rotor disk | |
| EP3054108B1 (en) | Gas turbine engine containment structures | |
| CN107206468B (en) | The manufacturing method and ring-shaped material of cyclic annular formed body | |
| CN211343127U (en) | Turbine and rotor system with gland | |
| EP2708697A1 (en) | Method of coupling two rotor sections and turbine rotor | |
| US7524566B2 (en) | Composite material, method for the production of a composite material and the utilization thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Patentee after: Beijing Star glory Space Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Patentee before: BEIJING XINGJIRONGYAO SPACE TECHNOLOGY Co.,Ltd. |