CN114352362A - Elastic support structure, bearing support using same and flexible rotor - Google Patents
Elastic support structure, bearing support using same and flexible rotor Download PDFInfo
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- CN114352362A CN114352362A CN202111487143.6A CN202111487143A CN114352362A CN 114352362 A CN114352362 A CN 114352362A CN 202111487143 A CN202111487143 A CN 202111487143A CN 114352362 A CN114352362 A CN 114352362A
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Abstract
An elastic support structure and a bearing support and a flexible rotor using the same belong to the technical field of elastic support structure design under the 3D printing and processing technology. The rotary part comprises a rotary part and a group of curved surface fins, wherein the group of curved surface fins are arranged on the outer side of the rotary part at intervals, the curved surface fins are arranged in a concentric circle along the radial direction of the rotary part, and the outer end parts of the group of curved surface fins are combined to form a circumferential supporting structure. In the elastic supporting structure, a group of curved surface fins are arranged on the outer side of the rotating piece, and a curved surface bending structure of the curved surface fins is utilized to form a deformation difference value between the curved surface fins and an external structure to be supported under the action of a rotating centrifugal force, and the deformation difference value is converted into a radial acting force to support the external structure; the bearing support and the flexible rotor which adopt the elastic supporting structure have simple structure, convenient installation and good supporting effect.
Description
Technical Field
The invention belongs to the field of elastic support structure design under the 3D printing processing technology, and particularly relates to an elastic support structure, and a bearing support and a flexible rotor using the structure.
Background
Gas turbines are high speed rotating equipment and rotor speeds can range from tens to hundreds of thousands of revolutions per minute. All loads of the gas turbine rotor are transmitted to the engine casing through the bearing and the support member, so the bearing and its corresponding support are very important parts of the gas turbine, and the bearing is one of the most vulnerable parts of the engine due to various problems such as uneven load bearing because it is a part connecting the rotor and the stator.
In the traditional design and manufacture, in the effort of prolonging the service life of the bearing, the bearing is concentrated, and in measures for preventing the bearing from being rubbed and damaged, the bearing play is reduced, and a bearing retainer is positioned and an inner ring is arranged. In the bearing cooling measure, the bearing inner ring is designed to be grooved.
Bearing inner race and axle, the cooperation of outer lane and shell is very important when the bearing installation, and when the assembly was loose, the fitting surface can produce relative slip, is called the creep, and the creep production can the wearing and tearing fitting surface cause the bearing to damage. In order to avoid creep, interference magnitude is required.
Generally, the working envelope of a rotor of a gas turbine or an aircraft engine is wide, the load condition is complex, the interference magnitude determined in the initial state cannot adapt to all working conditions, the creep phenomenon can occur under certain working conditions such as high rotating speed or extreme load, and the service life of a bearing is shortened. However, the excessive initial interference can cause the surface stress of the bearing ring to be excessive, so that the inner ring of the bearing is cracked, and the service life of the bearing is shortened.
Secondly, the traditional bearing matching mode provides higher difficulty for assembly, the heating and cooling modes are generally adopted, and the assembly process requirement and the cost are very high.
The bearing is stressed unevenly and is a main reason for causing the bearing to be easy to damage, although a bearing support is subjected to precision machining, absolute precision cannot be achieved, when the bearing support is assembled with the bearing, the whole cylindrical surface cannot be ensured to be in contact with the bearing, only a few lines or points are actually contacted, the rotor load born by the bearing is uneven, and the bearing can be damaged when the bearing is operated in an uneven state for a long time.
In addition, the traditional gas turbine rotor adopts a rigid connection mode, and the rigidity of the whole rotor meets the requirement, but the flexibility is insufficient. When the critical rotating speed is adjusted, only the supporting stator is used for structural treatment, such as a squirrel cage and a pull rod type elastic support, the structure is complex, the number of parts is large, and the assembly is difficult.
Disclosure of Invention
In view of the above problems in the prior art, an object of the present invention is to provide an elastic support structure with an elastic support function, uniform support member acting force, a simple structure, convenient processing and assembly, and low processing cost, and a bearing support and a flexible rotor using the same.
The invention provides the following technical scheme: an elastic supporting structure comprises a rotating part and a group of curved surface fins, wherein the group of curved surface fins are arranged on the outer side of the rotating part at intervals, the curved surface fins are arranged in a concentric circle mode along the radial direction of the rotating part, and the outer end parts of the group of curved surface fins are combined to form a circumferential supporting structure.
Preferably, the curved fin is curved.
Preferably, the supporting acting force formula of the outer end part of the curved surface fin is as follows:
wherein F represents a bearing force in Newton; fr represents the radial load in Newton; n represents the rotation speed, and the unit of the rotation speed is revolution per minute; n represents the number of curved fins, and the unit of n is one; r represents the distance between the center of the rotating piece and the outer end part of the curved surface fin, and the unit of the distance is millimeter; r represents the radius of the rotating member in millimeters; δ represents fin thickness in millimeters; k represents the stiffness coefficient of the curved fin.
The bearing support is characterized in that the rotating part is a rotor, a bearing and a stator are arranged on the outer side of a curved surface fin, the bearing is limited and arranged between the rotating part and the stator, and the curved surface fin is in contact with an inner ring of the bearing.
The bearing support is characterized in that a stator axial positioning end face is arranged on the stator, a rotor axial positioning end face is arranged on the rotating piece, and the bearing is axially positioned and installed through the stator axial positioning end face and the rotor axial positioning end face.
A bearing support applying an elastic supporting structure is characterized in that the thickness delta of each fin is 0.5-1.0 mm, the entering angle alpha of each fin is 15-45 degrees, the exiting angle beta of each fin is 60-110 degrees, R is larger than 50 mm, R is 5-15 mm, and the number n of curved-surface fins is 15-35; so as to ensure that the required deformation difference is formed between the curved surface fin and the external structure to be supported under the action of the rotating centrifugal force.
The utility model provides an use flexible rotor of elastic support structure, the rotating member is the pivot, and rotating member one end is equipped with the rotor dish, be equipped with rotor blade on the rotor dish, rotating member, curved surface fin, rotor dish and the integrative 3D of rotor blade print the shaping.
A flexible rotor applying an elastic supporting structure is characterized in that the thickness delta of each fin is 0.8-2.5 mm, the entering angle alpha of each fin is 15-45 degrees, the exiting angle beta of each fin is 60-110 degrees, R is 20-50 mm, R is 10-40 mm, and the number n of curved-surface fins is 15-35; so as to ensure that the required deformation difference is formed between the curved surface fin and the external structure to be supported under the action of the rotating centrifugal force.
By adopting the technology, compared with the prior art, the invention has the following beneficial effects:
1) in the elastic supporting structure, a group of curved surface fins are arranged on the outer side of the rotating piece, and a curved surface bending structure of the curved surface fins is utilized to form a deformation difference value between the curved surface fins and an external structure to be supported under the action of a rotating centrifugal force, and the deformation difference value is converted into a radial acting force to support the external structure;
2) when the elastic supporting structure is applied to a bearing support structure, the bearing inner ring can be supported, the supporting acting force is dynamically changed and adjusted along with the change of the working condition, the creep margin of the bearing is widened, and the service life of the bearing can be effectively prolonged in the all-working-condition envelope curve;
4) when the elastic supporting structure is applied to a bearing support structure, the problem that the stress of the inner ring of a bearing is uneven due to the processing problem of the traditional bearing support is avoided; the structure does not need to adopt a complex and high-cost cold and hot process during assembly, is convenient to assemble and has low cost;
5) when the elastic supporting structure is applied to a bearing support structure, the distributed fin support is adopted, the size shrinkage center of the structural processing is adjusted to the center of each curved surface fin, the integral processing size shrinkage of the bearing support is reduced, and the error between the processed structural size and the design value is reduced;
3) when the elastic supporting structure is applied to the flexible rotor structure, the complex and high-cost cold and hot process is not needed during the assembly of the rotor, the assembly is convenient, and the cost is low; and the elastic support is arranged on the rotor, so that the structure size is small and the structure is simple.
Drawings
FIG. 1 is a schematic perspective view of a bearing support according to the present invention;
FIG. 2 is a schematic sectional front view of the bearing support of the present invention;
FIG. 3 is a side cross-sectional structural view of the bearing support of the present invention;
FIG. 4 is a schematic perspective view of one side of a flexible rotor according to the present invention;
fig. 5 is a schematic perspective view of the other side of the flexible rotor according to the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
On the contrary, the invention is intended to cover alternatives, modifications, equivalents and alternatives which may be included within the spirit and scope of the invention as defined by the appended claims. Furthermore, in the following detailed description of the present invention, certain specific details are set forth in order to provide a better understanding of the present invention. It will be apparent to one skilled in the art that the present invention may be practiced without these specific details.
An elastic supporting structure comprises a rotating part 1 and a group of curved surface fins 2, wherein the group of curved surface fins 2 are arranged in a concentric circle along the radial direction of the rotating part 1, and the outer end parts of the curved surface fins 2 are combined to form a circumferential supporting structure; the curved fin 2 is curved.
The first embodiment is as follows:
referring to fig. 1-3, a bearing support using an elastic support structure includes an elastic support structure, in which a rotating member 1 is a rotor, a bearing 3 and a stator 4 are disposed outside the elastic support structure, the bearing 3 is disposed between the stator 4 and a curved fin 2 in a limited manner, and an outer end of the curved fin 2 contacts an inner ring of the bearing 3.
Specifically, stator 4 is provided with a stator axial positioning end face 401, rotor axial positioning end face 101 is provided on rotating member 1, and bearing 3 is axially positioned and mounted through stator axial positioning end face 401 and rotor axial positioning end face 101.
Specifically, when the rotating element 1 rotates, the outer end part of the curved surface fin 2 supports the inner ring of the bearing 3, and the calculation formula of the supporting acting force is as follows:
wherein F represents a bearing force in Newton; fr represents the radial load in Newton; n represents the rotation speed, and the unit of the rotation speed is revolution per minute; n represents the number of curved fins 2 in units of one; r represents the distance between the center of the rotary member 1 and the outer end of the curved fin 2 in millimeters; r denotes the radius of the rotating member 1 in millimeters; δ represents fin thickness in millimeters; k represents the rigidity coefficient of the curved surface fin 2, and the k is in a functional relation with the fin entrance angle alpha and the fin exit angle beta.
Wherein the thickness delta of the fins is 0.5-1.0 mm, the entering angle alpha of the fins is 15-45 degrees, the leaving angle beta of the fins is 60-110 degrees, R is more than 50 mm, R is 5-15 mm, and the number n of the curved surface fins 2 is 15-35.
The principle of the structure of the embodiment is as follows:
the rotor rotates to drive the curved surface fins 2 and the inner ring of the bearing 3 to rotate, the curved surface fins 2 and the inner ring of the bearing 3 generate deformation difference values under the action of rotating centrifugal force, and the difference values are converted into radial acting force of the curved surface fins 2 on the inner ring of the bearing 3; when the size of the whole structure is stable, the acting force of the curved surface fin 2 on the inner ring of the bearing 3 is in direct proportion to the square of the rotating speed, under the working conditions of different rotating speeds of the rotor, the acting force can be correspondingly changed, and the bearing creep is directly related to the acting force. Through the structural design of the curved surface fin 2, the dynamic matching adjustment of the inner rings of the curved surface fin 2 and the bearing 3 along with the change of working conditions can be achieved, the creep margin of the bearing is widened, the full-working-condition envelope curve is realized, and the service life of the bearing is effectively prolonged.
Example two:
referring to fig. 4-5, in a flexible rotor using an elastic supporting structure, a rotating member 1 is a rotating shaft, a rotor disc 5 is disposed at one end of the rotating member 1, a rotor blade 6 is disposed on the rotor disc 5, and the rotating member 1, a curved fin 2, the rotor disc 5, and the rotor blade 6 are integrally formed by 3D printing.
Specifically, when the rotary member 1 rotates, the calculation formula of the supporting acting force of the outer end portion of the curved surface fin 2 is as follows:
wherein F represents a bearing force in Newton; fr represents the radial load in Newton; n represents the rotation speed, and the unit of the rotation speed is revolution per minute; n represents the number of curved fins 2 in units of one; r represents the distance between the center of the rotary member 1 and the outer end of the curved fin 2 in millimeters; r denotes the radius of the rotating member 1 in millimeters; δ represents fin thickness in millimeters; k represents the rigidity coefficient of the curved surface fin 2, and the k is in a functional relation with the fin entrance angle alpha and the fin exit angle beta.
Wherein the thickness delta of the fins is 0.8-2.5 mm, the entering angle alpha of the fins is 15-45 degrees, the leaving angle beta of the fins is 60-110 degrees, R is 20-50 mm, R is 10-40 mm, and the number n of the curved surface fins 2 is 15-35.
The principle of the structure of the embodiment is as follows:
the side of the curved surface fin 2 on the structure is inserted into a rotor centering hole 7 on a rotor disc 5 at the next stage, when the rotor disc 5 rotates, rotors which are axially connected in series rotate at high speed according to the direction shown in the attached drawing 4, the curved surface fin 2 and the rotor centering hole 7 on the rotor disc 5 at the next stage generate a deformation difference under the action of a rotating centrifugal force, and the deformation difference is converted into a radial acting force of the curved surface fin 2 on the rotor centering hole 7. After the structure size is stable, the acting force of the curved surface fin 2 on the rotor centering hole 7 is in direct proportion to the square of the rotating speed, and under the different rotating speed working conditions of the rotor disc 5, the acting force can be correspondingly changed, so that a dynamic flexible rotor connecting structure is realized, and a good effect is achieved on adjusting the critical rotating speed of the rotor and relieving the vibration of an engine.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (8)
1. An elastic support structure characterized by: the novel rotary fin structure comprises a rotary piece (1) and a group of curved fins (2), wherein the group of curved fins (2) are arranged on the outer side of the rotary piece (1) at intervals, the curved fins (2) are arranged in a concentric circle mode along the radial direction of the rotary piece (1), and the outer end portions of the group of curved fins (2) are combined to form a circumferential supporting structure.
2. A flexible support structure according to claim 1, wherein said curved fins (2) are curved.
3. A flexible support structure according to claim 2, wherein the support force formula for the outer end of said curved fin (2) is:
wherein F represents a bearing force in Newton; fr represents the radial load in Newton; n represents the rotation speed, and the unit of the rotation speed is revolution per minute; n represents the number of the curved surface fins (2), and the unit of the number is one; r represents the distance between the center of the rotating piece (1) and the outer end part of the curved surface fin (2), and the unit of the distance is millimeter; r represents the radius of the rotating element (1) in millimeters; δ represents fin thickness in millimeters; k represents the rigidity coefficient of the curved surface fin (2).
4. The bearing support of an elastic supporting structure applied to any one of claims 1 to 3, characterized in that the rotating member (1) is a rotor, the bearing (3) and the stator (4) are arranged on the outer side of the curved surface fin (2), the bearing (3) is limited and arranged between the rotating member (1) and the stator (4), and the curved surface fin (2) is contacted with the inner ring of the bearing (3).
5. A bearing support using elastic supporting structure according to claim 4, characterized in that said stator (4) is provided with a stator axial positioning end face (401), said rotating member (1) is provided with a rotor axial positioning end face (101), and said bearing (3) is axially positioned and installed through said stator axial positioning end face (401) and said rotor axial positioning end face (101).
6. The bearing support applying the elastic support structure as claimed in claim 5, wherein the fin thickness δ is 0.5-1.0 mm, the fin entrance angle α is 15-45 degrees, the fin exit angle β is 60-110 degrees, R is more than 50 mm, R is 5-15 mm, and the number n of the curved fins (2) is 15-35.
7. The flexible rotor applying the elastic support structure according to any one of claims 1 to 3, wherein the rotating member (1) is a rotating shaft, a rotor disc (5) is arranged at one end of the rotating member (1), rotor blades (6) are arranged on the rotor disc (5), and the rotating member (1), the curved fins (2), the rotor disc (5) and the rotor blades (6) are integrally formed by 3D printing.
8. The flexible rotor using elastic support structure according to claim 7, wherein said fin thickness δ is 0.8-2.5 mm, fin entrance angle α is 15-45 degrees, fin exit angle β is 60-110 degrees, R is 20-50 mm, R is 10-40 mm, and the number n of curved fins (2) is 15-35.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111487143.6A CN114352362A (en) | 2021-12-07 | 2021-12-07 | Elastic support structure, bearing support using same and flexible rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111487143.6A CN114352362A (en) | 2021-12-07 | 2021-12-07 | Elastic support structure, bearing support using same and flexible rotor |
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| Publication Number | Publication Date |
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| CN114352362A true CN114352362A (en) | 2022-04-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111487143.6A Pending CN114352362A (en) | 2021-12-07 | 2021-12-07 | Elastic support structure, bearing support using same and flexible rotor |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012193834A (en) * | 2011-03-18 | 2012-10-11 | Shimadzu Corp | Dynamic pressure gas bearing |
| EP3088754A1 (en) * | 2015-04-28 | 2016-11-02 | Rolls-Royce Corporation | Cage for a high speed bearing assembly |
| CN111637149A (en) * | 2020-05-27 | 2020-09-08 | 西安交通大学 | Foil gas bearing with elastic damping structure |
-
2021
- 2021-12-07 CN CN202111487143.6A patent/CN114352362A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012193834A (en) * | 2011-03-18 | 2012-10-11 | Shimadzu Corp | Dynamic pressure gas bearing |
| EP3088754A1 (en) * | 2015-04-28 | 2016-11-02 | Rolls-Royce Corporation | Cage for a high speed bearing assembly |
| CN111637149A (en) * | 2020-05-27 | 2020-09-08 | 西安交通大学 | Foil gas bearing with elastic damping structure |
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