CN111335966A - Variable blade tip size control mounting structure of high-speed engine compressor - Google Patents
Variable blade tip size control mounting structure of high-speed engine compressor Download PDFInfo
- Publication number
- CN111335966A CN111335966A CN202010221163.8A CN202010221163A CN111335966A CN 111335966 A CN111335966 A CN 111335966A CN 202010221163 A CN202010221163 A CN 202010221163A CN 111335966 A CN111335966 A CN 111335966A
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- shaft
- balance
- test piece
- nut
- mounting structure
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- 238000004040 coloring Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 5
- 230000000694 effects Effects 0.000 abstract description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract description 3
- 229910002804 graphite Inorganic materials 0.000 abstract description 3
- 239000010439 graphite Substances 0.000 abstract description 3
- 238000007790 scraping Methods 0.000 abstract 1
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
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Classifications
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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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/601—Mounting; Assembling; Disassembling specially adapted for elastic fluid pumps
- F04D29/602—Mounting in cavities
Abstract
A variable-blade-tip size control mounting structure of a high-rotation-speed engine compressor comprises a transfer shaft, a connecting nut and a balance nut, wherein one end of the transfer shaft is fixedly connected with an output shaft of a rotator, the other end of the transfer shaft is fixedly connected with the connecting shaft through a connecting screw, an external spline is designed on the outer diameter of the connecting shaft and is matched with an internal spline of a test piece, the other end, which is not contacted with the transfer shaft, of the connecting shaft is provided with the connecting nut, and the connecting nut fixes the connecting shaft and the test piece; the balance nut is assembled at the right end of the test piece and used for dynamic balance; the balance nut and the end part of the transfer shaft are provided with a plurality of balance screws for dynamic balance; when the device is used for installing an engine compressor, the device can ensure that the outer diameters of the rotor blades of the compressor in a working state are more consistent, and the increase of blade tip gaps caused by the extension and scraping of graphite of individual blades is avoided, so that the loss of the compressor is reduced, and the efficiency and the pressure ratio of the compressor are improved; the invention has simple structure, reliable installation, safe operation and good use effect, and can be repeatedly used.
Description
Technical Field
The invention belongs to the technical field of mechanical structures, relates to a mounting structure, and particularly relates to a variable blade tip size control mounting structure of a high-speed engine compressor.
Background
The compressor of the small engine has small size and compact structure, and generally adopts a T-shaped ring mortise structure to connect a rotor blade and a rotor disk, as shown in figure 1. This kind of structure is because reasons such as blade tenon, rim plate tongue-and-groove tolerance accumulation, during the assembly, can have radial clearance H between tenon, the tongue-and-groove, and the blade tenon of difference is inconsistent with the clearance between the tongue-and-groove moreover. After the grinding of the rotor blade tips is finished in the state, the blade tips have the same diameter, but in the working state, the rotor blades are thrown out under the action of centrifugal force, the tenon-mortise gap is eliminated, and the elongation of each blade is different (the maximum elongation is about 0.2 mm-0.3 mm generally) due to different initial gaps. Therefore, after the first test run, the situation that the blade tips of partial rotor blades extend and graphite on the outer ring of the rotor is scraped is inevitably generated, so that the blade tip gaps of the partial rotor blades are increased, some rotor blades can reach 2 times of the designed gaps, such as the designed gaps are 0.2 mm-0.4 mm, and the gaps can reach 0.4 mm-0.7 mm after being increased, and finally, the loss of the blade tip gaps of the gas compressor is increased, and the efficiency and the pressure ratio of the gas compressor are reduced. The above problems are temporarily not solved by known solutions.
Disclosure of Invention
In order to solve the problems, the invention provides a variable blade tip size control mounting structure of a high-speed engine compressor, which is used for controlling the size of a blade tip of a rotor blade of the compressor and can realize the connection of the rotor of the engine compressor and an over-rotation tester so as to complete the pre-rotation test of the rotor of the compressor and realize the control of the size of the blade tip of the blade in a working state.
The technical scheme of the invention is as follows: a variable-blade-tip size control mounting structure of a high-rotation-speed engine compressor comprises a transfer shaft, a connecting nut and a balance nut, wherein one end of the transfer shaft is fixedly connected with an output shaft of a rotator, the other end of the transfer shaft is fixedly connected with the connecting shaft through a connecting screw, an external spline is designed on the outer diameter of the connecting shaft and is matched with an internal spline of a test piece, the other end, which is not contacted with the transfer shaft, of the connecting shaft is provided with the connecting nut, and the connecting nut fixes the connecting shaft and the test piece; the balance nut is assembled at the right end of the test piece and used for dynamic balance; the balance nut and the end of the transfer shaft are fitted with a plurality of balance screws for dynamic balancing.
Furthermore, a plurality of balance screws are circumferentially arranged on the balance nut, so that better dynamic balance is realized.
Furthermore, after the device is assembled, the center of mass of the test piece is ensured to coincide with the axis by adjusting the balance screw and the balance nut of the transfer shaft and the connecting shaft, so that dynamic balance is realized.
Furthermore, one end of the transfer shaft is in a circular ring shape, the inner diameter of the transfer shaft is matched with the bearing mounting position of the test piece, the coaxial and centering of the transfer shaft and the bearing mounting position are guaranteed, and the balance screws are assembled on the end portion of the circular ring shape.
Furthermore, the threads matched with the connecting shaft and the connecting nut are high-precision fine threads so as to ensure the stability of the device in a working state, and the connecting nut is required to be assembled according to a specified torque requirement during assembly so as to ensure sufficient axial pretightening force during the operation of a test piece.
Furthermore, the smoothness and the precision of the matching surfaces of the transfer shaft and the test piece are the same as those of the surface of the bearing seat, so that the test piece is ensured to be assembled concentrically and stably.
Furthermore, the external spline of the connecting shaft is tightly matched with the internal spline of the test piece, the coloring area of the external spline and the internal spline is not less than 90%, the impact load of torque transmission is reduced, and vibration is reduced.
Furthermore, the connecting shaft is coaxial with the cylindrical surface matched with the front matching surface and the rear positioning surface of the test piece, so that the rotation stability is ensured.
The invention has the advantages that:
when the device is used for installing the compressor of the engine, the outer diameters of the rotor blades of the compressor in the working state can be more consistent, and the increase of blade tip gaps caused by the fact that individual blades extend to scrape graphite is avoided, so that the loss of the compressor is reduced, and the efficiency and the pressure ratio of the compressor are improved; the invention has simple structure, reliable installation, safe operation and good use effect, and can be repeatedly used.
Drawings
FIG. 1 is a schematic diagram of a problem description structure of the background art;
FIG. 2 is a schematic structural diagram of an embodiment of the present invention;
the test device comprises a connecting shaft 1, a connecting shaft 2, a connecting nut 3, a test piece 4, a balance nut 5 and a balance screw 6.
Detailed Description
This section is an example of the present invention for explaining and illustrating the objects and technical solutions of the present invention.
A variable blade tip size control mounting structure of a high-speed engine compressor comprises a transfer shaft 1, a connecting shaft 2, a connecting nut 3 and a balance nut 5, wherein one end of the transfer shaft 1 is fixedly connected with an output shaft of a rotator, the other end of the transfer shaft is fixedly connected with the connecting shaft 2 through a connecting screw, the outer diameter of the connecting shaft 2 is provided with an external spline and matched with an internal spline of a test piece 4, the other end of the connecting shaft 2, which is not in contact with the transfer shaft 1, is provided with the connecting nut 3, and the connecting shaft 2 and the test piece 4 are fixed through the connecting nut 3; the balance nut 5 is assembled at the right end of the test piece 4 and used for dynamic balance; the balance nut 5 and the end of the adapter shaft 1 are fitted with a plurality of balance screws 6 for dynamic balancing. A plurality of balance screws 6 are circumferentially arranged on the balance nut 5 for realizing better dynamic balance. After the device is assembled, the center of mass of a test piece is ensured to coincide with the axis by adjusting the balance screw 6 and the balance nut 5 of the adapting shaft 1 and the connecting shaft 2, so that dynamic balance is realized. One end of the adapter shaft 1 is in a ring shape, the inner diameter of the adapter shaft is matched with the bearing mounting position of the test piece 4, the coaxial and centering of the adapter shaft and the bearing mounting position are guaranteed, and a plurality of balance screws are assembled on the end portion of the ring shape. The threads matched with the connecting shaft 2 and the connecting nut 3 are high-precision fine threads so as to ensure the stability of the device under the working state, and meanwhile, the connecting nut is required to be assembled according to the specified torque requirement during assembly, so that the sufficient axial pre-tightening force of the test piece during operation is ensured. The smoothness and the precision of the matching surfaces of the adapter shaft 1 and the test piece 4 are the same as those of the surfaces of the bearing seats, so that the test piece assembly is concentric and stable. The external spline of the connecting shaft 2 is tightly matched with the internal spline of the test piece, the coloring area of the external spline and the internal spline is not less than 90%, the impact load of torque transmission is reduced, and vibration is reduced. The connecting shaft 2 is coaxial with the cylindrical surfaces matched with the front matching surface and the rear positioning surface of the test piece 4, so that the rotation stability is ensured.
Another embodiment of the present invention is described below with reference to the drawings.
The structure of the invention is shown in figure 2, the air compressor rotor is driven by the over-rotation tester, the working condition is simulated to rotate at a high speed, the rotor blades are thrown out by centrifugal force, the gap between the tenon and the mortise is eliminated, meanwhile, each rotor blade of the air compressor rotor completes stress balance again through the complicated stress action between dozens of blade flanges and the tenon and the mortise edges, and the tenon and the mortise are always attached. And then, a common grinding machine is used for grinding, and because the radial force is very small during grinding, the joint state of the tenon and the mortise is not changed any more after grinding, so that the working clearance of the blade tip of the rotor of the gas compressor is ensured, the loss of the blade tip clearance is reduced, and the efficiency and the pressure ratio of the gas compressor are improved. When the rotor of the air compressor rotates, the rotating speed is very high, so the invention has higher requirement on the coaxiality of the output shaft of the over-rotation tester and the rotating shaft of the air compressor and is matched with the working state as much as possible.
The torque of the over-rotation tester is transmitted to the connecting shaft through the adapter shaft, the compressor rotor is driven to rotate under the action of the spline, meanwhile, the circular inner diameter of the adapter shaft is matched with the bearing installation position of the compressor rotor shaft, the radial positioning effect is achieved on the installation of the compressor rotor, the compressor rotor shaft is ensured to be coaxial with the output shaft of the over-rotation tester, and meanwhile, the condition that the compressor rotor is consistent in the use working state is simulated, namely single-point support through the bearing. The mounting structure ensures that the working condition of the compressor rotor is consistent with the working state when the compressor rotor is tested, thereby ensuring that the loss of the compressor is avoided and the efficiency and the pressure ratio of the compressor are ensured after the blades are ground. The invention has the characteristics of simple structure, reliable installation, safe operation and good use effect.
Claims (8)
1. The variable-blade-tip size control mounting structure of the high-rotation-speed engine compressor is characterized by comprising a transfer shaft (1), a connecting shaft (2), a connecting nut (3) and a balance nut (5), wherein one end of the transfer shaft (1) is fixedly connected with an output shaft of a rotator, the other end of the transfer shaft is fixedly connected with the connecting shaft (2) through a connecting screw, the outer diameter of the connecting shaft (2) is provided with an external spline and matched with an internal spline of a test piece (4), the other end, which is not contacted with the transfer shaft (1), of the connecting shaft (2) is provided with the connecting nut (3), and the connecting shaft (2) and the test piece (4) are fixed by the connecting nut (3); the balance nut (5) is assembled at the bracket end of the test piece (4); the balance nut (5) and the end part of the transfer shaft (1) are provided with a plurality of balance screws (6).
2. The variable tip size control mounting structure of the compressor of the high-speed engine as claimed in claim 1, wherein a plurality of balance screws (6) are circumferentially arranged on the balance nut (5).
3. The variable tip size control mounting structure of the compressor of the high-speed engine according to claim 1, wherein one end of the adapter shaft (1) is in a circular ring shape, the inner diameter of the adapter shaft is matched with the bearing mounting position of the test piece (4), the adapter shaft and the test piece are coaxial and centered, and a plurality of balance screws are assembled on the end of the circular ring.
4. The variable tip size control mounting structure of the high-speed engine compressor according to claim 1, wherein the threads matched with the connecting shaft (2) and the connecting nut (3) are high-precision fine threads.
5. The variable-tip size control mounting structure of the high-speed engine compressor as claimed in claim 1, wherein the smoothness and accuracy of the matching surface of the adapter shaft (1) and the test piece (4) are the same as those of the bearing seat surface.
6. The variable tip size control mounting structure of the high-speed engine compressor according to claim 1, wherein the external spline of the connecting shaft (2) is tightly matched with the internal spline of the test piece, and the coloring area of the external spline and the internal spline is not less than 90%.
7. The variable blade tip size control mounting structure of the high-speed engine compressor according to claim 1, wherein the connecting shaft (2) is coaxial with a cylindrical surface matched with a front matching surface and a rear locating surface of the test piece (4), so that the rotational stability is ensured.
8. A dynamic balance method of a variable tip size control mounting structure of a high-speed engine compressor is characterized in that after the variable tip size control mounting structure of the high-speed engine compressor is assembled according to claim 1, the center of mass of a test piece is enabled to coincide with the axis by adjusting balance screws (6) and balance nuts (5) of a transfer shaft (1) and a connecting shaft (2), and dynamic balance is achieved.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010221163.8A CN111335966A (en) | 2020-03-25 | 2020-03-25 | Variable blade tip size control mounting structure of high-speed engine compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010221163.8A CN111335966A (en) | 2020-03-25 | 2020-03-25 | Variable blade tip size control mounting structure of high-speed engine compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111335966A true CN111335966A (en) | 2020-06-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010221163.8A Pending CN111335966A (en) | 2020-03-25 | 2020-03-25 | Variable blade tip size control mounting structure of high-speed engine compressor |
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| CN (1) | CN111335966A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112179564A (en) * | 2020-09-29 | 2021-01-05 | 中国航发动力股份有限公司 | Balancing device and method for multistage blisk |
| CN112936016A (en) * | 2021-02-09 | 2021-06-11 | 中国航发哈尔滨东安发动机有限公司 | Engine rotor blade tip processingequipment |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4117742A (en) * | 1977-07-29 | 1978-10-03 | Stein Philip C | Permanent automatic rotor balancer for shafts operating above critical speed |
| US4767272A (en) * | 1987-10-14 | 1988-08-30 | United Technologies Corporation | Method for reducing blade tip variation of a bladed rotor |
| CN202710311U (en) * | 2012-06-12 | 2013-01-30 | 中国南方航空工业(集团)有限公司 | Over-running test clamp |
| KR20150066360A (en) * | 2013-12-06 | 2015-06-16 | 주식회사 포스코 | Bolt for repairing hole and Method for repairing hole with the same |
| CN105466691A (en) * | 2015-12-11 | 2016-04-06 | 哈尔滨东安发动机（集团）有限公司 | Testing installation structure for rotor tip of gas compressor |
| CN105570187A (en) * | 2015-12-11 | 2016-05-11 | 哈尔滨东安发动机（集团）有限公司 | Control method for dimensions of rotor tips of gas compressor |
| CN109322848A (en) * | 2018-08-30 | 2019-02-12 | 中国航发湖南动力机械研究所 | The rotor assembly and Compressor test part of Compressor test part |
-
2020
- 2020-03-25 CN CN202010221163.8A patent/CN111335966A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4117742A (en) * | 1977-07-29 | 1978-10-03 | Stein Philip C | Permanent automatic rotor balancer for shafts operating above critical speed |
| US4767272A (en) * | 1987-10-14 | 1988-08-30 | United Technologies Corporation | Method for reducing blade tip variation of a bladed rotor |
| CN202710311U (en) * | 2012-06-12 | 2013-01-30 | 中国南方航空工业(集团)有限公司 | Over-running test clamp |
| KR20150066360A (en) * | 2013-12-06 | 2015-06-16 | 주식회사 포스코 | Bolt for repairing hole and Method for repairing hole with the same |
| CN105466691A (en) * | 2015-12-11 | 2016-04-06 | 哈尔滨东安发动机（集团）有限公司 | Testing installation structure for rotor tip of gas compressor |
| CN105570187A (en) * | 2015-12-11 | 2016-05-11 | 哈尔滨东安发动机（集团）有限公司 | Control method for dimensions of rotor tips of gas compressor |
| CN109322848A (en) * | 2018-08-30 | 2019-02-12 | 中国航发湖南动力机械研究所 | The rotor assembly and Compressor test part of Compressor test part |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112179564A (en) * | 2020-09-29 | 2021-01-05 | 中国航发动力股份有限公司 | Balancing device and method for multistage blisk |
| CN112936016A (en) * | 2021-02-09 | 2021-06-11 | 中国航发哈尔滨东安发动机有限公司 | Engine rotor blade tip processingequipment |
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Application publication date: 20200626 |