CN114673562B - Multi-rotor-piece robustness connecting structure of aeroengine - Google Patents
Multi-rotor-piece robustness connecting structure of aeroengine Download PDFInfo
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- CN114673562B CN114673562B CN202210354348.5A CN202210354348A CN114673562B CN 114673562 B CN114673562 B CN 114673562B CN 202210354348 A CN202210354348 A CN 202210354348A CN 114673562 B CN114673562 B CN 114673562B
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- rotor
- spigot
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- rotor piece
- interference
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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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application belongs to the field of aeroengine design, and relates to a multi-rotor-piece robustness connecting structure of an aeroengine, which comprises a long bolt, and a first rotor piece, a second rotor piece, a third rotor piece and a fourth rotor piece which are sequentially arranged from the tail end to the head of the long bolt; the interference spigot fitting positions of the different rotor pieces are staggered by adding three spigot connecting mechanisms at different positions of the third rotor piece respectively; when the rotor pieces are connected with the long bolts, no overlapping part exists in the axial direction, mutual interference between the rabbets is avoided, and due to different interference fit positions of different rotor pieces, additional damage or rabbet disconnection is prevented, and the stability of rotor connection is higher; meanwhile, as the interference spigot matching positions of the rotor pieces are staggered, the axial matching positions of the rotor pieces cannot be affected mutually, the axial length of the rotor pieces on the interference cylindrical surface spigot matching surface is moderate, the circumferential tightness is uniform, the assembly is convenient, and the continuity and the stable work of the rotor are ensured.
Description
Technical Field
The application belongs to the field of aeroengine design, and particularly relates to a multi-rotor-piece robustness connecting structure of an aeroengine.
Background
The rotor system of an aeroengine has high working rotation speed and very severe working environment, and a plurality of rotor parts are often connected together in order to meet the functional requirements in a small space. Whether the connection of a plurality of rotor parts is stable and reliable can seriously influence the connection rigidity between the rotors and the contact state of the connecting surface, and then can influence the dynamic characteristics, vibration characteristics and safety of the whole machine structure.
When the design of the multi-rotor-piece connecting structure is carried out, a connecting and positioning structure is required to be designed according to the whole working environment of the engine, so that the assembled rotor is ensured to meet the requirements of safe working and performance maintenance of the engine.
At present, a plurality of rotor pieces of an aeroengine are connected, and an interference cylindrical surface spigot is often adopted to realize radial and circumferential positioning, and the structure is axially pressed through a common bolt. The interference seam allowance is always overlapped together in the axial direction due to space limitation, so that the seam allowance has an overlapped part in the axial direction, and great difficulty is brought to assembly.
Therefore, how to achieve a simple and efficient assembly of the rotor elements is a problem to be solved.
Disclosure of Invention
The application aims to provide a multi-rotor-piece robustness connecting structure of an aeroengine, which is used for solving the problem that in the prior art, the seam allowance of a plurality of rotor pieces are mutually overlapped to cause difficult assembly.
The technical scheme of the application is as follows: a multi-rotor-piece robustness connecting structure of an aeroengine comprises a long bolt, and a first rotor piece, a second rotor piece, a third rotor piece and a fourth rotor piece which are sequentially arranged from the tail end to the head of the long bolt; the third rotor piece is provided with first tang connection structure, second tang connection structure and third tang connection structure respectively in different positions, all be provided with two at least groups tang cooperation positions on first rotor piece, second rotor piece and the fourth rotor piece to two at least groups tang cooperation positions of every group rotor piece are located the upper and lower both sides of stock bolt respectively, first tang connection structure and the cooperation of a tang cooperation position interference tang of first rotor piece, second tang connection structure and second rotor piece are located the tang cooperation position interference tang cooperation of the opposite side of the relative first rotor piece tang junction of stock bolt, third tang connection structure and the cooperation of tang cooperation of the tang cooperation position interference tang of the opposite side of the relative second rotor piece tang junction of stock bolt.
Preferably, the first rotor piece includes first kink and first head, first kink is located between the main part of first rotor piece and the first head, first tang connection structure includes the first boss of an organic whole connection on the third rotor piece, first head and first boss interference tang cooperation.
Preferably, the second rotor piece includes second kink and second head, the second kink is located between the main part of second rotor piece and the second head, first kink and second kink are located the homonymy of stock, second tang connection structure includes the second boss of an organic whole connection on the third rotor piece, second kink and second boss interference tang cooperation.
Preferably, the fourth rotor piece includes fourth kink and fourth head, the fourth kink is located between the main part of fourth rotor piece and the fourth head, fourth kink and first kink are located the upper and lower both sides of stock respectively, third tang connection structure includes the third boss of an organic whole connection on the third rotor piece, fourth kink and third boss interference tang cooperation.
Preferably, the first boss and the third boss are located on left and right sides of the third rotor member, respectively.
Preferably, the long bolt comprises a threaded section, a first outer convex section, a first inner concave section, a second outer convex section and a second inner concave section, the diameters of the first outer convex section and the second outer convex section are larger than those of the first inner concave section and the second inner concave section, the first rotor piece is sleeved on the first outer convex section, the second rotor piece is sleeved on the first inner concave section, the third rotor piece is sleeved on the second outer convex section, and the fourth rotor piece is sleeved on the second inner concave section.
The application relates to a multi-rotor-piece robustness connecting structure of an aeroengine, which comprises a long bolt, and a first rotor piece, a second rotor piece, a third rotor piece and a fourth rotor piece which are sequentially arranged from the tail end to the head of the long bolt; the third rotor piece is provided with three spigot connecting mechanisms at different positions respectively, interference spigot matching positions of different rotor pieces are staggered, and when two rotor pieces led out from the same side are matched with the spigot of the third rotor piece, spigot connecting mechanisms corresponding to the two rotor pieces arranged on the third rotor piece are distributed at different positions; when the rotor pieces are connected with the long bolts, the axial direction has no overlapping part, mutual interference between the rabbets is avoided, and due to different interference fit positions of different rotor pieces, enough space between each rotor piece and the third rotor piece is designed into proper interference, so that additional damage or rabbet disconnection is prevented, and the stability of rotor connection is higher; meanwhile, as the interference spigot matching positions of the rotor pieces are staggered, the axial matching positions of the rotor pieces cannot be affected mutually, the axial length of the rotor pieces on the interference cylindrical surface spigot matching surface is moderate, the circumferential tightness is uniform, the assembly is convenient, and the continuity and the stable work of the rotor are ensured.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
FIG. 1 is a schematic diagram of the overall structure of the present application.
1. A first rotor member; 2. a first bending part; 3. a first head; 4. a second rotor member; 5. a second bending part; 6. a second head; 7. a third rotor member; 8. a first boss; 9. a second boss; 10. a third boss; 11. a fourth rotor member; 12. a fourth bending part; 13. a fourth head; 14. a self-locking nut; 15. a long bolt; 16. a first concave section.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
The utility model provides a multi-rotor piece robustness connection structure of aeroengine, as shown in fig. 1, includes long bolt 15 and first rotor piece 1, second rotor piece 4, third rotor piece 7, fourth rotor piece 11 that set gradually from long bolt 15 end to head. The long bolt 15 is preferably a D-head long bolt, and the tail end of the long bolt 15 is connected with a self-locking nut 14 in a threaded manner.
The third rotor piece 7 is provided with first tang connection structure, second tang connection structure and third tang connection structure respectively in different positions, all be provided with two at least groups tang cooperation positions on first rotor piece 1, second rotor piece 4 and fourth rotor piece 11, and two at least groups tang cooperation positions of every group rotor piece are located the upper and lower both sides of stock 15 respectively, first tang connection structure and the cooperation of one tang cooperation position interference tang of first rotor piece 1, second tang connection structure and second rotor piece 4 are located the tang cooperation position interference tang cooperation of the opposite side of stock 15 relative first rotor piece 1 tang junction, third tang connection structure and the cooperation of tang cooperation position interference tang of the opposite side of fourth rotor piece 11 are located the opposite side of stock 15 relative second rotor piece 4 tang junction.
That is, when the spigot fitting position of the first rotor member 1 at the upper portion of the long bolt 15 is fitted with the spigot connecting structure spigot of the third rotor member 7, the spigot fitting position of the second rotor member 4 at the lower portion of the long bolt 15 is spigot fitted with the spigot connecting structure of the third rotor member 7; when the spigot fitting position of the first rotor member 1 on the lower portion of the long bolt 15 is fitted with the spigot connecting structure spigot of the third rotor member 7, the spigot fitting position of the second rotor member 4 on the upper portion of the long bolt 15 is spigot fitted with the spigot connecting structure of the third rotor member 7. The same applies to the selection of the location of the spigot connection of the fourth rotor member 11 to the third rotor member 7.
The third rotor piece 7 is provided with three spigot connecting mechanisms at different positions, interference spigot matching positions of different rotor pieces are staggered, the positions of the spigot connecting mechanisms are guaranteed to be far away as far as possible in design, and when two rotor pieces led out from the same side are matched with the spigot of the third rotor piece 7, spigot connecting mechanisms corresponding to the two rotor pieces arranged on the third rotor piece 7 are distributed at different positions; when the rotor pieces are connected with the long bolts 15, the axial direction has no overlapping part, mutual interference between the rabbets is avoided, and due to different interference fit positions of different rotor pieces, enough space is designed between each rotor piece and the third rotor piece 7 to be proper interference, so that additional damage or rabbet disconnection is prevented, and the stability of rotor connection is higher; meanwhile, as the interference spigot matching positions of the rotor pieces are staggered, the axial matching positions of the rotor pieces cannot be affected mutually, the axial length of the rotor pieces on the interference cylindrical surface spigot matching surface is moderate, the circumferential tightness is uniform, the assembly is convenient, and the continuity and the stable work of the rotor are ensured.
In the process of connecting the rotor members, not limited to the connection of four rotor members in the present application, the spigot connection structure may be appropriately increased or decreased for the connection of more or fewer rotor members, thereby achieving similar effects.
Preferably, the first rotor member 1 includes a first bending part 2 and a first head 3, both parts can be selected as spigot fitting positions, and the two positions are respectively located at the upper part and the lower part of the long bolt 15, the first bending part 2 is arranged between the main body part of the first rotor member 1 and the first head 3, the first spigot connecting structure includes a first boss 8 integrally connected to the third rotor member 7, and the first head 3 is in interference spigot fitting with the first boss 8. The first boss 8 is arranged on the third rotor piece 7 to realize the spigot matching with the first rotor piece 1, and the first boss 8 is matched with the first head 3 of the first rotor piece 1 by designing two groups of spigot matching positions of the first rotor piece 1, so that other rotor pieces at similar positions can be subjected to interference spigot matching by using another position, mutual interference of spigot matching positions is avoided, and reliable radial and axial positioning of the first rotor piece 1 is ensured.
Preferably, the second rotor member 4 includes a second bending portion 5 and a second head portion 6, both portions can be selected as spigot fitting positions, and the two positions are respectively located at an upper portion and a lower portion of the long bolt 15, the second bending portion 5 is disposed between a main body portion of the second rotor member 4 and the second head portion 6, the first bending portion 2 and the second bending portion 5 are located at the same side of the long bolt 15, the second spigot connecting structure includes a second boss 9 integrally connected to the third rotor member 7, and the second bending portion 5 is in interference spigot fitting with the second boss 9. The second boss 9 is arranged on the third rotor piece 7 to realize the spigot matching with the second rotor piece 4, and the second boss 9 is matched with the second bending part 5 of the second rotor piece 4 by designing two groups of spigot matching positions of the second rotor piece 4, so that other rotor pieces at similar positions can be subjected to interference spigot matching by using another position, mutual interference of spigot matching positions is avoided, and reliable radial and circumferential positioning of the second rotor piece 4 is ensured.
Preferably, the fourth rotor member 11 includes a fourth bending portion 12 and a fourth head portion 13, both portions can be selected as spigot fitting positions, and the two positions are respectively located at an upper portion and a lower portion of the long bolt 15, the fourth bending portion 12 is disposed between a main body portion of the fourth rotor member 11 and the fourth head portion 13, the fourth bending portion 12 and the first bending portion 2 are respectively located at two sides of the long bolt 15, the third spigot connecting structure includes a third boss 10 integrally connected to the third rotor member 7, and the fourth bending portion 12 is in interference spigot fitting with the third boss 10. The fourth bending part 12 and the second bending part 5 are respectively positioned at the upper side and the lower side of the long bolt 15, the first head part 3 and the fourth bending part 12 are spaced from the second rotor part 4 and the third rotor part 7, and the same distance is long, so that the radial and circumferential reliable positioning of the fourth rotor part 11 is ensured, and therefore, the spigot matching positions of the first rotor part 1, the second rotor part 4 and the fourth rotor part 11 are not mutually interfered.
Preferably, the first boss 8 and the third boss 10 are located on the left and right sides of the third rotor member 7, respectively. Mutual interference is prevented by arranging the first boss 8 and the third boss 10 farther to separate the spigot positions of the first rotor member 1 and the fourth rotor member 11.
Preferably, the long bolt 15 comprises a threaded section, a first male section, a first female section 16, a second male section and a second female section; the thread section is connected with the self-locking nut 14, the diameters of the first outer convex section and the second outer convex section are larger than those of the first inner concave section 16 and the second inner concave section, the first rotor piece 1 is sleeved on the first outer convex section, the second rotor piece 4 is sleeved on the first inner concave section 16, the third rotor piece 7 is sleeved on the second outer convex section, and the fourth rotor piece 11 is sleeved on the second inner concave section. The first to fourth rotor members 11 with the stepped structures are more convenient to axially position by designing the long bolts 15, so that the compression amount is ensured, and the rotor members under the whole envelope working condition of the whole machine are axially compressed and the spigot cannot be separated.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (3)
1. A multi-rotor robustness connection structure of an aeroengine is characterized in that: the motor comprises a long bolt (15) and a first rotor piece (1), a second rotor piece (4), a third rotor piece (7) and a fourth rotor piece (11) which are sequentially arranged from the tail end to the head of the long bolt (15); the third rotor piece (7) is provided with a first spigot connecting structure, a second spigot connecting structure and a third spigot connecting structure at different positions, at least two groups of spigot matching positions are arranged on the first rotor piece (1), the second rotor piece (4) and the fourth rotor piece (11), the at least two groups of spigot matching positions of each group of rotor pieces are respectively positioned at the upper side and the lower side of the long bolt (15), the first spigot connecting structure is in interference spigot fit with one spigot matching position of the first rotor piece (1), the second spigot connecting structure is in interference spigot fit with one spigot matching position of the second rotor piece (4) positioned at the other side of the long bolt (15) opposite to the spigot connecting position of the first rotor piece (1), and the third spigot connecting structure is in interference fit with one spigot matching position of the fourth rotor piece (11) positioned at the other side of the long bolt (15) opposite to the spigot connecting position of the second rotor piece (4);
The mounting edge of the first rotor piece (1) comprises a first bending part (2) and a first head part (3), the first bending part (2) is arranged between the main body part of the first rotor piece (1) and the first head part (3), the first spigot connecting structure comprises a first boss (8) integrally connected to the third rotor piece (7), and the first head part (3) is in interference spigot fit with the first boss (8);
the mounting edge of the second rotor piece (4) comprises a second bending part (5) and a second head part (6), the second bending part (5) is arranged between the main body part of the second rotor piece (4) and the second head part (6), the first bending part (2) and the second bending part (5) are positioned on the same side of the long bolt (15), the second spigot connecting structure comprises a second boss (9) integrally connected to the third rotor piece (7), and the second bending part (5) is matched with the second boss (9) through an interference spigot;
The installation limit of fourth rotor spare (11) includes fourth kink (12) and fourth head (13), between the main part and the fourth head (13) of fourth rotor spare (11) are located in fourth kink (12), fourth kink (12) and first kink (2) are located upper and lower both sides of stock (15) respectively, third tang connection structure includes third boss (10) of body coupling on third rotor spare (7), fourth kink (12) and third boss (10) interference tang cooperation.
2. The multi-rotor robust connection structure of claim 1, wherein: the first boss (8) and the third boss (10) are respectively positioned at the left side and the right side of the third rotor piece (7).
3. The multi-rotor robust connection structure of claim 1, wherein: the long bolt (15) comprises a threaded section, a first outer convex section, a first inner concave section (16), a second outer convex section and a second inner concave section, the diameters of the first outer convex section and the second outer convex section are larger than those of the first inner concave section (16) and the second inner concave section, the first outer convex section is sleeved with the first rotor piece (1), the first inner concave section (16) is sleeved with the second rotor piece (4), the second outer convex section is sleeved with the third rotor piece (7), and the second inner concave section is sleeved with the fourth rotor piece (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210354348.5A CN114673562B (en) | 2022-04-06 | 2022-04-06 | Multi-rotor-piece robustness connecting structure of aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210354348.5A CN114673562B (en) | 2022-04-06 | 2022-04-06 | Multi-rotor-piece robustness connecting structure of aeroengine |
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| Publication Number | Publication Date |
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| CN114673562A CN114673562A (en) | 2022-06-28 |
| CN114673562B true CN114673562B (en) | 2024-07-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210354348.5A Active CN114673562B (en) | 2022-04-06 | 2022-04-06 | Multi-rotor-piece robustness connecting structure of aeroengine |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116562106B (en) * | 2023-07-04 | 2023-10-03 | 中国航发四川燃气涡轮研究院 | Method for designing tightness of rotor spigot of aero-engine compressor |
| CN117744284B (en) * | 2024-02-21 | 2024-05-03 | 中国航发四川燃气涡轮研究院 | Method and device for designing length of pressure surface of spigot of compressor rotor |
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| JPH10121903A (en) * | 1996-10-21 | 1998-05-12 | Toshiba Corp | Gas tubine rotor |
| CN104533532A (en) * | 2014-11-26 | 2015-04-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Wheel disc spigot locating structure of gas turbine rotor and gas turbine rotor |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3621523B2 (en) * | 1996-09-25 | 2005-02-16 | 株式会社東芝 | Gas turbine rotor blade cooling system |
| EP0844369B1 (en) * | 1996-11-23 | 2002-01-30 | ROLLS-ROYCE plc | A bladed rotor and surround assembly |
| CN105765168B (en) * | 2013-11-26 | 2017-10-24 | 通用电气公司 | Radial direction tie bolt supports spring |
| US10273972B2 (en) * | 2015-11-18 | 2019-04-30 | United Technologies Corporation | Rotor for gas turbine engine |
| CN205135719U (en) * | 2015-11-26 | 2016-04-06 | 中国航空动力机械研究所 | Rim plate connection structure and aeroengine |
| DE102016218285A1 (en) * | 2016-09-23 | 2018-03-29 | MTU Aero Engines AG | Rotor stage for a turbomachine, rotor drum and rotor |
| GB201800511D0 (en) * | 2018-01-12 | 2018-02-28 | Rolls Royce Plc | Fan disc assembly |
| US11215056B2 (en) * | 2020-04-09 | 2022-01-04 | Raytheon Technologies Corporation | Thermally isolated rotor systems and methods |
| CN112282853B (en) * | 2020-10-29 | 2022-06-03 | 中国航发湖南动力机械研究所 | Two-stage turbine and engine |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10121903A (en) * | 1996-10-21 | 1998-05-12 | Toshiba Corp | Gas tubine rotor |
| CN104533532A (en) * | 2014-11-26 | 2015-04-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Wheel disc spigot locating structure of gas turbine rotor and gas turbine rotor |
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| CN114673562A (en) | 2022-06-28 |
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