CN102927141A - Coupler assembly - Google Patents
Coupler assembly Download PDFInfo
- Publication number
- CN102927141A CN102927141A CN201210410057XA CN201210410057A CN102927141A CN 102927141 A CN102927141 A CN 102927141A CN 201210410057X A CN201210410057X A CN 201210410057XA CN 201210410057 A CN201210410057 A CN 201210410057A CN 102927141 A CN102927141 A CN 102927141A
- Authority
- CN
- China
- Prior art keywords
- coupling
- screw rod
- spline
- internal spline
- turbine rotor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a coupler assembly. A shell of the coupler assembly is provided with an internal spline and fixedly arranged on a gas compressor rotor through a pin, a screw rod is provided with an internal spline and is fixed with a turbine rotor through external threads, two ends of a coupler are respectively provided with a front external spline matched with the internal spline on the shell and a rear external spline matched with the internal spline on the screw rod, a regulating pad is arranged between end surfaces of the screw rod and the turbine rotor, and the turbine rotor and the gas compressor rotor are in matching connection through splines. The coupler assembly disclosed by the invention has the advantages of compact structure, simpleness in assembly and lower cost, realizes the stable connection after the assembly, and achieves the self locking; and meanwhile, due to the design, the machining accuracy of parts is not too high, and thus the cost is saved.
Description
Technical field
The present invention relates to a kind of coupling assembly.
Background technique
Usually be connected by coupling between the compressor rotor of aeroengine and the High Pressure Turbine Rotor.When gas compressor-High Pressure Turbine Rotor is only used two point supportings, generally adopt rigid coupling, such as the JT9D-74R turbofan engine; When adopting three fulcrum supports, generally adopt flexible connector.Coupling by torsion pass, locate and be fixedly connected with three part-structure key elements and form.
Rigid coupling generally has dual mode, the first is to adopt pin or key torsion pass or select the involute splines torsion pass, flank is felt relieved or is established in addition the cylndrical surface at the spline two ends and locate, this mode can realize locking voluntarily, but need establish in addition special-purpose fitting surface feels relieved, simultaneously, pin and key torsion pass moment are less; The mode of torsion pass and centering when the second way is employing circular arc end tooth, this mode requires machining accuracy very high, so cost is high, and can not realize locking voluntarily, needs supporting locking measure.
Flexible coupling is flexible or floats, and its spline answers length to reduce as far as possible, the requirement of the angle of declination when satisfying fan propeller and turbine rotor axis disalignment.Flexible coupling generally has the axial clearance requirement, should be provided with spacer, and flexible coupling need design axial linkage structure, and assembling is comparatively complicated, cannot lock voluntarily simultaneously, needs supporting locking measure.
Summary of the invention
The purpose of this invention is to provide a kind of coupling, can realize that compressor rotor is connected connection and moment of torsion transmission with turbine rotor, can transmit larger moment of torsion, the stable connection, compact structure is effective, and assembling is simple, cost is lower, and realizes voluntarily locking.
Concrete technological scheme of the present invention is: coupling assembly comprises coupling, housing, screw rod, pressure spring, spacer, described housing is provided with internal spline and is fixed by a pin on the compressor rotor, be provided with internal spline on the described screw rod and fix by outside thread and turbine rotor, the step of promising screw rod location is set on the described coupling external diameter, be provided with the step for pressure spring location on the internal diameter, the rear external splines that the two ends of coupling are respectively arranged with the front external splines that cooperates with internal spline on the housing and cooperate with internal spline on the screw rod, the other end of described spring is pressed on the compressor rotor, described screw rod leans against on the step that arranges on the external diameter of coupling, and and the end face of turbine rotor between be provided with spacer, described turbine rotor is connected by spline fitted with compressor rotor.Be provided with screw thread on the internal diameter of one end of the close rear external splines of described coupling, an end of the close internal spline of described screw rod is provided with diameter greater than the front spline of another section of this internal spline.
Turbine rotor of the present invention and compressor rotor are by the spline torsion pass, and flank is felt relieved; Spacer is adjusted the relative axial position of turbine shaft and compressorshaft, guarantees spline fitted; Screw flight and turbine shaft screw-internal thread fit play the spacing effect of axial connection, prevent that compressor rotor and turbine rotor from axially throwing off, and its internal spline cooperates with the coupling external splines and guarantees itself and coupling rotational synchronization; External splines is connected with screw rod before the coupling, guarantees to rotate synchronously, prevents the disengagement of screw rod internal thread and turbine shaft screw-thread fit; Rear spline cooperates with coupling housing internal spline, guarantees that itself and coupling housing synchronous rotating move; Coupling housing internal spline cooperates with coupling, guarantees to rotate synchronously, and is connected with compressor rotor by pin, guarantees to rotate synchronously with compressor rotor; Pin plays the effect that the coupling housing is connected with compressor rotor; Spring plays after finishing spline fitted coupling is upspring, and spline is in cooperates assembling.
The present invention is owing to having adopted the spline transmitting torque between turbine rotor and the compressor rotor, and spline can bear very large moment of torsion, has therefore realized larger moment of torsion transmission; Adopt spline structure at the coupling two ends, be provided with screw thread in the coupling, screw rod is provided with front spline, when assembling, only need one can with coupling jack-up, the spline at coupling two ends be thrown off, the telescopic frock of screw rod rotation can be able to be finished assembling simultaneously, thereby make compact structure of the present invention, assembling is simple, and cost is lower; After the assembling, the screw thread between turbine rotor and screw rod can guarantee the axially play not of position turbine shaft, and the spline of turbine rotor can guarantee that screw thread can not automatic rotary then throw off simultaneously, thereby has realized stable connection, voluntarily locking.Simultaneously above-mentioned design provides cost savings also so that make the part processing precision of the present invention need not be too high.
Description of drawings
Fig. 1 is structural representation of the present invention.
Embodiment
As shown in the figure, coupling assembly comprises coupling 1, housing 2, screw rod 3, pressure spring 4, spacer 8, described housing 2 is provided with internal spline and is fixed on the compressor rotor 6 by pin 5, be provided with internal spline and fixing by outside thread and turbine rotor 7 on the described screw rod 3, the step of promising screw rod 3 location is set on described coupling 1 external diameter, be provided with the step for pressure spring 4 location on the internal diameter, the rear external splines that the two ends of coupling 1 are respectively arranged with the front external splines that cooperates with internal spline on the housing 2 and cooperate with internal spline on the screw rod 3, the other end of described spring 4 is pressed on the compressor rotor 6, described screw rod 3 leans against on the step that arranges on the external diameter of coupling 1, and and the end face of turbine rotor 7 between be provided with spacer 8, described turbine rotor 7 and compressor rotor 6 are connected by spline fitted.Be provided with screw thread on the internal diameter of one end of the close rear external splines of described coupling 1, an end of the close internal spline of described screw rod 3 is provided with diameter greater than the front spline 10 of another section of this internal spline.
Claims (2)
1. coupling assembly, it is characterized in that, coupling assembly comprises coupling (1), housing (2), screw rod (3), pressure spring (4), spacer (8), described housing (2) is provided with internal spline and is fixed on the compressor rotor (6) by pin (5), be provided with internal spline and fixing by outside thread and turbine rotor (7) on the described screw rod (3), the step of promising screw rod (3) location is set on described coupling (1) external diameter, be provided with the step for pressure spring (4) location on the internal diameter, the rear external splines that the two ends of coupling (1) are respectively arranged with the front external splines that cooperates with internal spline on the housing (2) and cooperate with internal spline on the screw rod (3), the other end of described spring (4) is pressed on the compressor rotor (6), described screw rod (3) leans against on the step that arranges on the external diameter of coupling (1), and and the end face of turbine rotor (7) between be provided with spacer (8), described turbine rotor (7) is connected by spline fitted with compressor rotor (6).
2. coupling assembly as claimed in claim 1, it is characterized in that, be provided with screw thread on the internal diameter of one end of the close rear external splines of described coupling (1), an end of the close internal spline of described screw rod (3) is provided with diameter greater than the front spline (10) of another section of this internal spline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210410057XA CN102927141A (en) | 2012-10-24 | 2012-10-24 | Coupler assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210410057XA CN102927141A (en) | 2012-10-24 | 2012-10-24 | Coupler assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102927141A true CN102927141A (en) | 2013-02-13 |
Family
ID=47642031
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210410057XA Pending CN102927141A (en) | 2012-10-24 | 2012-10-24 | Coupler assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102927141A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105757130A (en) * | 2016-04-19 | 2016-07-13 | 哈尔滨东安发动机（集团）有限公司 | Engine turbine and compressor rotor connection and torque transmission device |
| CN109595265A (en) * | 2018-11-26 | 2019-04-09 | 中国航发南方工业有限公司 | Axile connection structure |
| CN111946403A (en) * | 2020-07-31 | 2020-11-17 | 中国航发贵阳发动机设计研究所 | Coupling for connecting aviation rotors |
| CN114278606A (en) * | 2021-12-28 | 2022-04-05 | 北京动力机械研究所 | Multi-working-medium helium gas compressor main shaft structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4915589A (en) * | 1988-05-17 | 1990-04-10 | Elektroschmelzwerk Kempten Gmbh | Runner with mechanical coupling |
| CN1212320A (en) * | 1997-09-19 | 1999-03-31 | 亚瑞亚·勃朗勃威力有限公司 | Blade-fixing device of compressor for high speed worm-gear machine |
| CN101100958A (en) * | 2007-07-10 | 2008-01-09 | 刘天成 | Mini size gas turbine |
| CN102691576A (en) * | 2012-06-14 | 2012-09-26 | 中国科学院工程热物理研究所 | Power transmission mechanism of gas compressor and turbine |
| CN202851706U (en) * | 2012-10-24 | 2013-04-03 | 哈尔滨东安发动机（集团）有限公司 | Coupling assembly |
-
2012
- 2012-10-24 CN CN201210410057XA patent/CN102927141A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4915589A (en) * | 1988-05-17 | 1990-04-10 | Elektroschmelzwerk Kempten Gmbh | Runner with mechanical coupling |
| CN1212320A (en) * | 1997-09-19 | 1999-03-31 | 亚瑞亚·勃朗勃威力有限公司 | Blade-fixing device of compressor for high speed worm-gear machine |
| CN101100958A (en) * | 2007-07-10 | 2008-01-09 | 刘天成 | Mini size gas turbine |
| CN102691576A (en) * | 2012-06-14 | 2012-09-26 | 中国科学院工程热物理研究所 | Power transmission mechanism of gas compressor and turbine |
| CN202851706U (en) * | 2012-10-24 | 2013-04-03 | 哈尔滨东安发动机（集团）有限公司 | Coupling assembly |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105757130A (en) * | 2016-04-19 | 2016-07-13 | 哈尔滨东安发动机（集团）有限公司 | Engine turbine and compressor rotor connection and torque transmission device |
| CN105757130B (en) * | 2016-04-19 | 2018-07-17 | 哈尔滨东安发动机（集团）有限公司 | A kind of engine turbine connect torsion transmitter with compressor rotor |
| CN109595265A (en) * | 2018-11-26 | 2019-04-09 | 中国航发南方工业有限公司 | Axile connection structure |
| CN109595265B (en) * | 2018-11-26 | 2020-03-24 | 中国航发南方工业有限公司 | Shaft connecting structure |
| CN111946403A (en) * | 2020-07-31 | 2020-11-17 | 中国航发贵阳发动机设计研究所 | Coupling for connecting aviation rotors |
| CN111946403B (en) * | 2020-07-31 | 2022-09-02 | 中国航发贵阳发动机设计研究所 | Coupling for connecting aviation rotors |
| CN114278606A (en) * | 2021-12-28 | 2022-04-05 | 北京动力机械研究所 | Multi-working-medium helium gas compressor main shaft structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102927141A (en) | Coupler assembly | |
| EP2884124B1 (en) | Bidirectional bearing, drive train, planetary gear and wind generator | |
| US11078989B2 (en) | Reduction gear and electromechanical device | |
| JP2019019751A (en) | Gas turbine rotor and gas turbine generator | |
| US10221932B2 (en) | Gear wheel having helical toothing and segment for a gear wheel | |
| EP2910740B1 (en) | Variable vane sychronization ring transmission mechanisms | |
| US20200067382A1 (en) | Speed reduction apparatus and electromechanical device | |
| CN106767650B (en) | A kind of zero-bit position limiting structure of double redundancy gear drive angular displacement sensor | |
| CN202851706U (en) | Coupling assembly | |
| CN203412971U (en) | Connecting structure between speed reducer and motor | |
| EP3209873B1 (en) | Accessory assembly of a turbine engine | |
| CN102042345A (en) | Axial adjustable diaphragm coupler | |
| CN105466691A (en) | Testing installation structure for rotor tip of gas compressor | |
| CN103528818B (en) | A kind of electric synchronization loader | |
| CN105757130B (en) | A kind of engine turbine connect torsion transmitter with compressor rotor | |
| CN201875008U (en) | Axial adjustable membrane coupling | |
| CN207300132U (en) | A kind of drive mechanism of triplex redundance angular displacement sensor | |
| CN106989117B (en) | Mechanical contrate-gear-type clutch | |
| CN211180307U (en) | Photoelectric combined micro slip ring | |
| CN109831059B (en) | Linear driver | |
| CN112240226B (en) | Rotor assembly, aircraft engine and assembly method of rotor assembly | |
| CN208719273U (en) | Speed changer and vehicle | |
| CN207437614U (en) | A kind of manual transmission direct high synchronization structure | |
| CN112882221A (en) | Periscopic periscope optical image eliminating rotation mechanism | |
| CN105151279A (en) | Synchronization mechanism with changeable mounting angle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130213 |