CN108412553B - Shaft structure for optimizing running stability of high-speed rotor and high-speed rotor - Google Patents
Shaft structure for optimizing running stability of high-speed rotor and high-speed rotor Download PDFInfo
- Publication number
- CN108412553B CN108412553B CN201810384635.4A CN201810384635A CN108412553B CN 108412553 B CN108412553 B CN 108412553B CN 201810384635 A CN201810384635 A CN 201810384635A CN 108412553 B CN108412553 B CN 108412553B
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- Prior art keywords
- shaft
- supporting
- rotating
- speed rotor
- supporting part
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- 238000009434 installation Methods 0.000 claims abstract description 7
- 230000007704 transition Effects 0.000 claims description 13
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000008901 benefit Effects 0.000 description 4
- 238000001816 cooling Methods 0.000 description 4
- 239000000112 cooling gas Substances 0.000 description 3
- 230000004323 axial length Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000013011 mating Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000001934 delay Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- 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
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a shaft structure for optimizing the running stability of a high-speed rotor, wherein at least two connected rotating component mounting parts are arranged on the shaft, a raised supporting part is arranged on at least one rotating component mounting part, and the connecting parts of the supporting parts and adjacent rotating component mounting parts are arranged at intervals; the support portion surrounds the outer surface of the shaft, and the center line of the support portion coincides with the center line of the shaft. According to the invention, on the basis of the original shaft, the supporting part near the installation part of the rotating part is added, the supporting part uniformly surrounds the outer surface of the shaft, and when the rotor runs at a high speed, the rotor can normally work even if the connecting part loses the self-centering function or the detachable connecting part is worn, so that the purpose that the rotor can still stably and normally work under a severe working condition is achieved.
Description
Technical Field
The invention relates to the technical field of a shaft structure and a rotor comprising the shaft structure, in particular to a shaft structure for optimizing the running stability of a high-speed rotor and the high-speed rotor.
Background
Currently, most gas turbine rotor stages are connected by end tooth connections, which function to achieve automatic centering and torque transfer during operation. But the meshing between teeth at two ends is tightly pressed by the pretightening force of bolts at two ends, when looseness occurs or the end teeth are severely worn, the connection effect of the end teeth can be invalid, the rotor is rubbed when the rotor runs at a high speed, and the serious accident of scrapping the rotor occurs when the rotor is heavy.
Disclosure of Invention
The invention aims to solve the technical problems that the existing rotor is easy to loose or severely worn at the joint of the stages during high-speed operation, and the rotor is rubbed or even scrapped.
The invention adopts the following technical scheme to solve the technical problems:
the shaft structure for optimizing the running stability of the high-speed rotor is characterized in that at least two connected rotating component mounting parts are arranged on the shaft, a raised supporting part is arranged on at least one rotating component mounting part, and the joint of the supporting part and the adjacent rotating component mounting part is arranged at intervals; the support portion surrounds the outer surface of the shaft, and the center line of the support portion coincides with the center line of the shaft.
Further, the shaft is a variable-inner-diameter hollow shaft and comprises a large-diameter section and a small-diameter section which are communicated with each other, the inner diameter of the large-diameter section is larger than that of the small-diameter section, the large-diameter section corresponds to the position on the shaft where the rotary part mounting part is arranged, and the small-diameter section corresponds to the position on the shaft where the rotary part mounting part is not arranged.
Further, the number of the rotating component mounting parts is the same as that of the supporting parts, and the rotating component mounting parts and the supporting parts are in one-to-one correspondence.
Further, the rotating component mounting part comprises a transition section, two ends of the transition section are respectively connected with the matching part and the supporting part, and the outer diameter of the transition section is smaller than that of the matching part. Further, the supporting portion is provided with a groove penetrating along the axial direction.
Further, the rotary member mounting portion and the support portion are integrally formed with the shaft.
The high-speed rotor comprises the shaft structure, and further comprises at least two rotating parts sleeved on the shaft, wherein the rotating parts correspond to the positions of the mounting parts of the rotating parts one by one, and the end parts of the adjacent rotating parts are detachably connected.
Further, the rotating member includes a turbine and a compressor, the ends of which are engaged by end teeth.
Further, the support portion is in interference fit with the rotating member.
Further, the contact point of the rotating member and the edge of the supporting portion is spaced from the edge of the rotating member.
The invention has the following beneficial effects:
according to the invention, on the basis of the original shaft, the supporting part near the installation part of the rotating part is added, the supporting part uniformly surrounds the outer surface of the shaft, and the centering function is realized, so that the automatic centering function of the connecting part of the adjacent rotating parts is weakened, and even if the connecting part of the rotating parts loses the automatic centering function or the detachable connecting part is worn during high-speed operation, the rotor can work normally, and the purpose that the rotor can still work stably and normally under severe working conditions is achieved.
The shaft is arranged to be a hollow shaft with a variable inner diameter, and the mass distribution of the rotor is balanced, so that the rigidity matrix distribution of the shaft is more reasonable.
After the rotating component is assembled on the shaft, a clearance channel is formed between the inner wall surface of the rotating component and the outer wall surface of the shaft and is used for cooling air flow to enter and flow out, so that the temperature of the components around the shaft is more uniform, the comprehensive performance of the rotor is improved, and the service life is prolonged.
The supporting part is provided with a groove which is convenient for cooling air to enter and flow out.
The contact point of the rotating part and the supporting part is arranged at intervals with the edge of the rotating part to form a cantilever, so that the contact surface of the shaft supporting part and the rotating part is delayed to slide when the rotor runs at high speed.
Drawings
FIG. 1 is a cross-sectional view of a central shaft in an embodiment of the invention;
FIG. 2 is a block diagram of a high speed rotor in an embodiment of the invention;
FIG. 3 is a cross-sectional view taken along the A-A plane in FIG. 2;
fig. 4 is an enlarged view of a portion B in fig. 3;
FIG. 5 is a cross-sectional view of an embodiment of the present invention at a first support of a high speed rotor;
fig. 6 is a sectional view of the second support portion of the high-speed rotor in the embodiment of the present invention.
The device comprises a 1-shaft, a 11-rotating part mounting part, a 111-turbine mounting part, a 112-compressor mounting part, a 113-connecting part, a 12-supporting part, a 120-groove, a 121-first supporting part, a 1211-supporting convex surface, a 122-second supporting part, a 1221-annular convex surface, a 13-large-diameter section, a 14-small-diameter section, a 15-transition section, a 16-matching part, a 17-round angle, a 2-rotating part, a 21-turbine, a 210-first clearance channel, a 211-exhaust hole, a 22-compressor, a 220-second clearance channel, a 23-inner hole clearance gap, a 231-first inner hole clearance gap, a 232-second inner hole clearance gap, a 24-overhang, a 241-first overhang, a 242-second overhang and 25-end teeth.
Detailed Description
For a further understanding and appreciation of the structural features and advantages achieved by the present invention, the following description is provided in connection with the accompanying drawings, which are presently preferred embodiments and are incorporated in the accompanying drawings, in which:
the present embodiment provides a shaft structure that optimizes the running stability of a high-speed rotor, and as shown in fig. 1, the outer surface of the shaft 1 is integrally formed with a rotary member mounting portion 11 and a supporting portion 12.
The shaft 1 is provided with at least two connected rotary component mounting parts 11, at least one rotary component mounting part 11 is provided with a raised supporting part 12, and the supporting part 12 is arranged at intervals at the joint 113 of the adjacent rotary component mounting parts 11. The support portion 12 uniformly surrounds the outer surface of the shaft 1, and the center line of the support portion coincides with the center line of the shaft 1, so that the support portion 12 has a good centering function while supporting the rotating member 11, thereby ensuring the stability of high-speed operation of the rotor.
As a further preferable embodiment, the shaft 1 is integrally formed with two rotary member mounting portions 11, which are respectively a turbine mounting portion 111 and a compressor mounting portion 112. The turbine installation department 111 is last to be equipped with first supporting part 121, is equipped with the second supporting part 122 on the compressor installation department 112, and turbine installation department 111 and compressor installation department 112 are connected at junction 113, and first supporting part 121, second supporting part 122 all set up in the vicinity of junction 113, and with junction 113 interval 2-4mm, make the support centering effect of supporting part better.
As a further preferable solution, the shaft 1 is a hollow shaft with a variable inner diameter, and includes a large diameter section 13 and a small diameter section 14 that are mutually communicated, the inner diameter of the large diameter section 13 is larger than the inner diameter of the small diameter section 14, the large diameter section 13 corresponds to the position of the rotating component mounting portion 11 on the shaft, the small diameter section 14 corresponds to the position of the rotating component mounting portion on the shaft, in this embodiment, the rotating component mounting portion 11 is located on the right side of the shaft 1, the large diameter section 13 extends from the right end of the shaft 1 to the left end of the rotating component mounting portion 11 from the left end of the shaft 1 to the right end of the rotating component mounting portion 11. The hollow shaft has the advantages that compared with a solid shaft, the hollow shaft saves more materials under the condition of transmitting the same torque, and balances the mass distribution of the high-speed rotor, so that the rigidity matrix distribution of the shaft 1 is more reasonable.
As a further preferable technical scheme, the connection part of the large diameter section 13 and the small diameter section 14 is in smooth fillet transition, so that stress concentration at the connection part is avoided.
The present embodiment further provides a high-speed rotor including the above-mentioned shaft structure, as shown in fig. 2-3, the high-speed rotor further includes at least two rotating members 2 sleeved on the shaft 1, the positions of the rotating members 2 and the rotating member mounting portions 11 are in one-to-one correspondence, the end portions of adjacent rotating members 2 are detachably connected, and the connection positions of the adjacent rotating members are corresponding to the connection positions 113 on the shaft.
As a further preferable embodiment, the rotary part 2 includes a turbine 21 and a compressor 22, the turbine 21 and the compressor 22 are engaged with each other by end teeth 25, and an exhaust hole 211 is provided at the end of the inner wall surface of the turbine 21. Referring to fig. 1, the turbine 21 is sleeved on the outer surface of the turbine mounting portion 111, and the compressor 22 is sleeved on the outer surface of the compressor mounting portion 112.
As a further preferred solution, the support 12 is an interference fit with the rotating part 2. I.e. the first support 121 is in an interference fit with the turbine 21 and the second support 122 is in an interference fit with the compressor 22.
As a further preferable solution, as shown in fig. 1 and fig. 4, the rotary component mounting portion 11 is provided with a transition portion 15, two ends of the transition portion 15 are respectively connected with the mating portion 16 and the supporting portion 12 through a rounded corner 17, and an outer diameter of the transition portion 15 is smaller than an outer diameter of the mating portion 16 and an outer diameter of the supporting portion 12. The function is to create a clearance channel between the transition piece 15 and the rotating part 2 for the cooling air flow in and out after the assembly of the rotating part 2 on the shaft 1. As shown in fig. 3, a first clearance passage 210 is formed between the inner wall surface of the turbine 21 and the transition section 15, and a second clearance passage 220 is formed between the inner wall surface of the compressor 22 and the transition section 15.
As a further preferable solution, as shown in fig. 5-6, the supporting portion 12 is provided with 2-5 grooves 120 penetrating along the axial direction for the cooling air flow to enter and exit, which is not limited to the grooves, or a plurality of through holes may be formed.
As shown in fig. 5, a first supportThe depth of the groove 120 on the portion 121 is the same as or similar to the height of the supporting portion 12, the groove 120 divides the first supporting portion 121 into 2-5 supporting convex surfaces 1211 uniformly surrounding the outer wall of the shaft 1, and the turbine 21 needs to largely introduce air and then spray out, at this time, the flow rate of the cooling gas passing through the groove 120 is large, so that the size of the groove 120 on the first supporting portion 121 is large, and the contact area between the single supporting convex surface 1211 and the inner wall surface of the turbine 21 is 40-55mm 2 The axial length is 8-14mm. As shown in fig. 6, the groove 120 on the second supporting portion 122 is smaller in size, and the outer surface of the second supporting portion 122 is an annular convex surface 1221 with an axial length of 8-14mm.
As a further preferable embodiment, the first supporting part 121 includes 3 supporting convex surfaces 1211.
In use, the cooling gas required for the turbine 21 is injected from the exhaust holes 211 at the tail of the turbine 21 through the first clearance channel 210 at the engagement of the end teeth 25. The cooling gas required by the compressor 22 passes through the grooves 120 and the second clearance passages 220 in the second support portion in sequence from the engagement of the end teeth 25 to cool the compressor 22 and the shaft 1. The temperature of the rotor formed by the shaft 1, the turbine 21, the compressor 22 and other parts is more uniform, and the service life of the rotor is further prolonged.
As a further preferable solution, as shown in fig. 3-4, an inner hole avoidance space 23 is provided on the inner wall surface of the rotating member 2 at the position where the inner end point of the supporting portion is matched. That is, a first inner hole clearance gap 231 is formed on the inner wall surface of the turbine 21 at the position where the right end point of the first supporting portion 121 is matched, and a second inner hole clearance gap 232 is formed on the inner wall surface of the compressor 22 at the position where the left end point of the second supporting portion 122 is matched. The arrangement of the inner hole avoidance spaces 23 is beneficial to processing.
As a further preferable solution, as shown in fig. 3-4, the contact point between the rotating member 2 and the supporting portion 12 is spaced from the edge of the rotating member 2, so as to form an overhang 24. That is, the left edge of the inner wall surface of the turbine 21 protrudes leftward with respect to the left edge of the first support 121, forming a first overhang 241; the right edge of the inner wall surface of the compressor 22 protrudes rightward with respect to the right edge of the second supporting portion 122, forming a second overhang 242. The overhang arrangement delays the slippage of the contact surface of the shaft support 12 with the turbine 21 or the compressor 22 during high-speed operation of the rotor.
The invention has simple structure, easy processing and low transformation cost, realizes multiple functions of centering, supporting and the like only through the supporting part, reduces the deformation quantity of the rotor, reduces the rubbing probability of the rotor component and the stator component, optimizes the stability of the whole rotor and obtains the best comprehensive benefit under the condition of consuming little useful work.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made therein without departing from the spirit and scope of the invention, which is defined by the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. The shaft structure is characterized in that at least two connected rotating component mounting parts are arranged on the shaft, raised supporting parts are arranged on the rotating component mounting parts, and the connecting parts of the supporting parts and the adjacent rotating component mounting parts are arranged at intervals; the supporting part surrounds the outer surface of the shaft, and the central line of the supporting part coincides with the central line of the shaft; the rotating component mounting part comprises a turbine mounting part and a compressor mounting part, a first supporting part is arranged on the turbine mounting part, and a second supporting part is arranged on the compressor mounting part; the first supporting part and the second supporting part are arranged near the connecting part; the supporting part is provided with a groove penetrating along the axial direction; the groove on the first supporting part is larger than the groove on the second supporting part; the rotating part installation part comprises a transition section, two ends of the transition section are respectively connected with the matching part and the supporting part, and the outer diameter of the transition section is smaller than that of the matching part and the supporting part.
2. The shaft structure for optimizing running stability of a high-speed rotor according to claim 1, wherein the shaft is a variable-inner-diameter hollow shaft, and comprises a large-diameter section and a small-diameter section which are communicated with each other, wherein the inner diameter of the large-diameter section is larger than that of the small-diameter section, the large-diameter section corresponds to a rotary part mounting part on the shaft, and the small-diameter section corresponds to a position on the shaft where the rotary part mounting part is not arranged.
3. The shaft structure for optimizing operation stability of a high-speed rotor according to claim 1, wherein the number of the rotary member mounting portions is the same as the number of the supporting portions, and the rotary member mounting portions are in one-to-one correspondence with the supporting portions.
4. A shaft structure for optimizing the operational stability of a high speed rotor as defined in claim 1, wherein the number of said grooves is 2-5.
5. The shaft structure for optimizing operational stability of a high-speed rotor of claim 1, wherein said rotary member mounting portion and said support portion are integrally formed with said shaft.
6. A high-speed rotor comprising the shaft structure according to any one of claims 1 to 5, further comprising at least two rotating members fitted around the shaft, the rotating members being in one-to-one correspondence with positions of the rotating member mounting portions, and end portions of the adjacent rotating members being detachably connected.
7. The high speed rotor of claim 6 wherein the rotating components include a turbine and a compressor, the ends of the turbine and compressor being engaged by end teeth.
8. The high speed rotor of claim 6, wherein the support portion is an interference fit with the rotating component.
9. The high-speed rotor according to claim 6, wherein an inner hole clearance is provided on the inner wall surface of the rotating member at a position where the inner end point of the supporting portion is engaged.
10. The high-speed rotor of claim 6, wherein the contact point of the rotating member with the edge of the support is spaced from the edge of the rotating member.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810384635.4A CN108412553B (en) | 2018-04-26 | 2018-04-26 | Shaft structure for optimizing running stability of high-speed rotor and high-speed rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810384635.4A CN108412553B (en) | 2018-04-26 | 2018-04-26 | Shaft structure for optimizing running stability of high-speed rotor and high-speed rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108412553A CN108412553A (en) | 2018-08-17 |
| CN108412553B true CN108412553B (en) | 2023-11-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810384635.4A Active CN108412553B (en) | 2018-04-26 | 2018-04-26 | Shaft structure for optimizing running stability of high-speed rotor and high-speed rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108412553B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2011967A1 (en) * | 2007-07-06 | 2009-01-07 | Lindenmaier AG | Rotor shaft assembly and manufacturing method therefore |
| CN104213981A (en) * | 2013-05-31 | 2014-12-17 | 西安统领动力有限公司 | Novel minisize gas turbine |
| CN208153065U (en) * | 2018-04-26 | 2018-11-27 | 贵州智慧能源科技有限公司 | A kind of axle construction and high speed rotor optimizing high speed rotor operation stability |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8186939B2 (en) * | 2009-08-25 | 2012-05-29 | Pratt & Whitney Canada Corp. | Turbine disc and retaining nut arrangement |
| EP2837769B1 (en) * | 2013-08-13 | 2016-06-29 | Alstom Technology Ltd | Rotor shaft for a turbomachine |
| FR3026774B1 (en) * | 2014-10-07 | 2020-07-17 | Safran Aircraft Engines | TURBOMACHINE COMPRISING A BLOWER ROTOR BRAKING DEVICE. |
-
2018
- 2018-04-26 CN CN201810384635.4A patent/CN108412553B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2011967A1 (en) * | 2007-07-06 | 2009-01-07 | Lindenmaier AG | Rotor shaft assembly and manufacturing method therefore |
| CN104213981A (en) * | 2013-05-31 | 2014-12-17 | 西安统领动力有限公司 | Novel minisize gas turbine |
| CN208153065U (en) * | 2018-04-26 | 2018-11-27 | 贵州智慧能源科技有限公司 | A kind of axle construction and high speed rotor optimizing high speed rotor operation stability |
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| Publication number | Publication date |
|---|---|
| CN108412553A (en) | 2018-08-17 |
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