CN109209641B - A kind of connection structure of engine rotor assemblies - Google Patents
A kind of connection structure of engine rotor assemblies Download PDFInfo
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- CN109209641B CN109209641B CN201811289987.8A CN201811289987A CN109209641B CN 109209641 B CN109209641 B CN 109209641B CN 201811289987 A CN201811289987 A CN 201811289987A CN 109209641 B CN109209641 B CN 109209641B
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- 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
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a kind of connection structure of engine rotor assemblies, it can be achieved that compressor rotor and turbine rotor are reliably connected.It can be applied in the core machine rotor connection area of ground gas turbine, aero-engine.The requirement such as the transmitting of rotor axial power, the bearing of rotor, reliable assembling/decomposition of rotor and dynamic balancing of rotor assembly may be implemented in the structure.And rotor assembly has the characteristics that number of parts is few and component good rigidity, will have important engineer application meaning in ground gas turbine or aero-engine field.Further, which is not limited to the pattern of axial flow compressor and axial flow turbine, is also not limited to the series of compressor or turbine, and pull rod can be adjusted in the starting tightened position for generator terminal of calming the anger according to the series (length) of corresponding component.
Description
Technical field
The invention belongs to ground gas turbine, Core Engine field, it is related to a kind of engine rotor assemblies
The connection structure of connection structure more particularly to a kind of compressor rotor and turbine rotor.
Background technique
Modular construction design problem suitable for small size gas turbine and Core Engine rotor is in combustion gas wheel
Machine, aero-engine field have the engineering problem of important practical usage.
Gas turbine, aero-engine structure design in, due to rotor blade tip gap high-precision requirement and
The problems such as rigors of rotor dynamics, the fulcrum layout of rotor assembly, connection between rotor torsion pass route, rotor, is equal
It will affect the requirement that high performance gas-turbine engine, aero-engine performance are further promoted and reliability further increases.Thus
There is an urgent need to propose a kind of rotor component construction layout method more preferably and suitable for core engine.
In addition, the failure of gas turbine, aero-engine is frequently experienced in high-speed rotating rotor assembly, and is often gone out
Under the transition state environment of present engine.Therefore, transition state lower rotor part how is improved, the axial/radial gap of stator keeps energy
Power is the actual requirement for influencing gas turbine, aero-engine reliability and further being promoted.
Summary of the invention
It is in view of the above drawbacks of the prior art and insufficient, the present invention is intended to provide a kind of connection knot of engine rotor assemblies
Structure, the structure can realize being reliably connected for compressor rotor and turbine rotor, and can meet the transmitting of rotor axial power, rotor
Bearing, reliable assembling/decomposition of rotor and dynamic balancing of rotor assembly etc. require, and rotor assembly have number of parts few and
The characteristics of component good rigidity, has important engineer application meaning in ground gas turbine or aero-engine field.
The present invention is technical solution used by solving its technical problem are as follows:
A kind of connection structure of engine rotor assemblies, the engine are gas turbine or turbojet, institute
Stating rotor assembly includes at least two stage compressor rotor and at least one level turbine rotor sequentially coaxially arranged along engine axis,
It is characterized by:
-- the rotor assembly integrally uses the supporting way of 1-0-1, and front fulcrum uses deep groove ball bearing, and rear fulcrum is adopted
With stick roller bearing, wherein
The inner ring of the deep groove ball bearing is arranged on the extension axle journal of first order compressor rotor wheel disc, and outer ring setting exists
On the primary load bearing casing of engine；The front end of the extension axle journal of first order compressor rotor wheel disc is equipped with external screw thread I, the outer spiral shell
Line I is equipped with a front nut and a nut locking plate I to prevent the front nut from loosening；
The extending back on axle journal of final stage turbine rotor wheel disc is arranged in the inner ring of the stick roller bearing, and outer ring is arranged in engine
Auxiliary support case on；
By the deep groove ball bearing, by the axial force of the rotor assembly and partially radially power passes to the front fulcrum
The primary load bearing casing, the rear fulcrum are passed to the partially radially power of the rotor assembly by the stick roller bearing described
Assist support case；
-- for centering and the torsion pass requirement for realizing final stage compressor rotor and first order turbine rotor, final stage compressor rotor
The connection structure of circular arc end tooth is used between first order turbine rotor；
The end for extending back axle journal of the first order compressor rotor wheel disc is formed with band internal thread inner hole, described interior
The front end of a center pull rod is threadedly coupled in hole, the center pull rod extends along engine axis and sequentially passes through intermediate pressures at different levels
The centre bore of the centre bore of mechanism of qi rotor disk and turbine rotor wheel disc at different levels, the rear end of the center pull rod stretch out in end
The rear end surface in the outside for extending back axle journal of grade turbine rotor wheel disc, the center pull rod is equipped with external screw thread II, the outer spiral shell
A tightening nut, a clamp nut of nut locking plate II and one are set gradually on line II, wherein
The inner face of the tightening nut is pressed against on the outer end face for extending back axle journal of final stage turbine rotor wheel disc, to draw
Tight compressor rotors at different levels and turbine rotor at different levels；
The inside of the nut locking plate II is simultaneously outside the outer end face of the tightening nut, the inner ring of the stick roller bearing
End face, the nut locking plate II is to prevent the tightening nut from loosening；
The outside of the nut locking plate II is arranged in the clamp nut, and the clamp nut passes through the nut locking plate II
It is pressed against on the inner ring outer end face of the stick roller bearing, to compress the inner ring of the stick roller bearing.
Preferably, the center pull rod is to realize the axis of the compressor rotor and turbine rotor when cold conditions is assembled
To pretension function.
In the connection structure of engine rotor assemblies of the invention, in compressor, turbine rotor connection, synthesis is used
A variety of connection types such as circular arc end tooth and center pull rod, while the compressing structure of double nut is used in the rear end of center pull rod.
Compressor and turbine rotor component use the supporting way of 1-0-1, and the front fulcrum positioned at generator terminal of calming the anger is using deep groove ball bearing
Thrust bearing scheme, the fulcrum of turbine end are the stick roller bearing support scheme for being subjected only to radial force load.
Selectively, it is contemplated that the assembly and disassembly of component needs, and center pull rod uses in the position of turbine end and adds drawing
Bar internal screw thread increases the two ways of external thread length to realize the use of hydraulic disassembling tool.
It more preferably, should be in such a way that material selection, heat treatment process and structure design, to increase at screw position
Hardness, in the case where ensuring to bear larger pulling force, the reliably working of center pull rod.
More preferably, at center pull rod screw thread, using the special warfare processing method that screw thread is silver-plated, prevent nut thread and
Adhesion of the center pull rod screw thread under hot working condition.
More preferably, in order to avoid center pull rod tightening force is excessive biggish so as to cause the generation of turbine end stick roller bearing inner ring
Deformation, turbo-side use double nut scheme in the position of center pull rod.The relatively small nut of diameter mainly undertakes tension and calms the anger
The function of machine rotor and turbine rotor applies biggish screw-down torque to it.The relatively large nut of diameter undertakes compression roller
The purpose of bearing inner ring, screw-down torque are relatively small.
It selectively, can also be by thickening in the case where the DN value level of turbine end stick roller bearing has sufficient fund
The mode of the inner ring thicknesses of stick roller bearing will not be deformed with ensuring itself, thus cancel the lesser nut structure of diameter,
Turbine end becomes single nut structure at this time.Selectively, according to engine performance demand, compressor series can 2~8 grades it
Between choose.
Selectively, compressor can be integral blade disk or other leaf dish connection types.
Selectively, circular arc end tooth, rectangular teeth or length/lag bolt can be used in the torsion pass positioning between different compressor stages
Connection type.
Preferably, between compressor stage axle journal diameter dimension choose it is larger, to improve the rigidity of rotor assembly.
Preferably, according to the design of the structure of part each in rotor component construction and Position Design, in suitable axial position
Place increases axially adjustable mat structure, to adjust the rotor blade tip gap of oblique flow/centrifugal compressor or centripetal turbine.
More preferably, according to the design of the structure of part each in rotor component construction and Position Design, in suitable axial position
Place increases axially adjustable mat structure, to adjust the axial gap between rotor and stator.
Preferably, the series of multistage turbine grade is recommended between 1~2 grade.
Preferably, the torsion pass between multistage turbine grade uses the type of attachment of lag bolt.
Selectively, the torsion pass between multistage turbine grade can also be connected by spline or end tooth frame mode.
Preferably, stage of turbine turbo blade and wheel disk of turbine are proposed with tongue-and-groove/tenon tooth connection type, avoid blade to
The heat transfer in wheel disc core direction.
Preferably, settable two balanced surfaces under the modular construction assembled state, go when for rotor assembly dynamic balancing
Material requirements.
Preferably, the deep groove ball bearing is thrust deep groove ball bearing, is also set between the front nut and deep groove ball bearing
A bevel gear is set, is equipped with an annular groove at the rear end face center of the bevel gear, and arrangement one is adjusted in the annular groove
Whole pad I, axial position of the adjusting pad I to adjust the bevel gear.
Preferably, an oil scraper ring abutted with it, the gear are also set up at the rear end face of the inner ring of the deep groove ball bearing
One labyrinth seal ring is set at the rear end face of oil ring.
Preferably, extending back for the final stage turbine rotor wheel disc also sets up a graphite annulus runway, the graphite annulus on axle journal
One adjusting pad II is set between the rear end face of runway and the stick roller bearing inner ring front end face, and the adjusting pad II is to adjust heat
Position to axial under state working condition between the stick roller bearing runway and rolling element.
Preferably, a labyrinth seal ring abutted with it is also set up at the front end face of the graphite annulus runway.
Preferably, the import side surface of the first order compressor rotor wheel disc and/or final stage turbine rotor wheel disc go out
Mouthful side surface is equipped with continuously in a circumferential or intermittent balance boss, for adjusting the computing ballance correction of rotor assembly.
Preferably, under the premise of maintaining fulcrum support location layout, the compressor rotor, turbine rotor series can
Arbitrarily to choose, the tightened position of center pull rod is also adjustable；The compressor can be oblique flow, axis stream or centrifugal, institute
Stating turbine can be axis stream or radial inflow.
Preferably, under the premise of maintaining structure type and fulcrum is laid out, by increasing adjustment mat structure in corresponding position,
To adjust compressor rotor blade blade tip radial clearance.
Preferably, the diameter of the extension axle journal of the first order compressor rotor wheel disc is according to the DN value design result of bearing
It is adjusted, and the length for the axis that protracts is adjusted according to the layout and the mode of obturaging of bearing bore；Between other compressor stages and grade
Journal diameter parameter interconnected is adjusted according to the rotor dynamics of rotor component construction.
Preferably, it is also set up between the front end of the center pull rod and the centre bore of the first order compressor rotor wheel disc
One support baffle ring, and sealing ring is equipped between support baffle ring and the centre bore of the first order compressor rotor wheel disc, it is excellent
It is selected as O-shaped rubber ring.
Compared with the compressor and turbine rotor connection structure of conventional gas turbine and Core Engine, the present invention
The connection structure of engine rotor assemblies, it can be achieved that being reliably connected for compressor rotor and turbine rotor, and rotor can be met
The requirement such as the transmitting of axial force, the bearing of rotor, reliable assembling/decomposition of rotor and dynamic balancing of rotor assembly；And it is all
Rotor is freely-supported pattern, therefore rotor assembly rotor dynamics are excellent；And in view of rotor transmitting torque in the structure
" axis " radial location it is relatively high, therefore rotor assembly rigidity preferably, substantially increase rotor blade tip gap protect
Ability is held, there is huge application potential.
Detailed description of the invention
Fig. 1 is the attachment structure schematic diagram of engine rotor assemblies of the invention；
Fig. 2 is the attachment structure schematic diagram of generator terminal of calming the anger in Fig. 1；
Fig. 3 is the attachment structure schematic diagram of turbine end in Fig. 1；
Fig. 4 is the dynamic balancing schematic diagram of compressor of the invention and turbine rotor connection structure.
Specific embodiment
The present invention will be further described in detail below with reference to the embodiments, following embodiment be explanation of the invention and
The invention is not limited to following embodiments.
As shown in figures 1-4, the present embodiment is compressor in certain Core Engine, turbine rotor component structure
Design scheme.In this embodiment, the rotor in rotor assembly except inclined flow air compressor 1, axial flow compressor 12, the turbine disk 14 with
Outside, it is contemplated that the demand obturaged between bearing bore is obturaged, starting generates electricity and grade, also comprising bevel gear 5, oil scraper ring 7, castor ring gear 8,
11 and 17, the structures such as graphite annulus runway 18 and various adjusting pads 4 and 19.In the rotor assembly, front and rear fulcrum is respectively adopted
Deep groove ball bearing 6 and stick roller bearing 20, and in order to realize the locking of front nut 2, using the structure of nut locking plate 3.Turbine
The solution of center pull rod 13 tightening force and bearing axially position pretightning force is then realized by the way of double nut 21 and 22 in end
Coupling.
In component assembly, center pull rod 13 extendes back axle journal inner hole with inclined flow air compressor and uses the side being threadedly coupled
Formula, and by the internal thread structure of its rear end, realize the use of assembly hydraulic tool.By two stage compressor machine rotor and turbine
Rotor tenses.The general active force is at 6~10 tons or so.The pressing force for compressing turbine end stick roller bearing inner ring is then typically small.
Specifically, as shown in Figures 1 to 3, the connection structure of engine rotor assemblies of the invention, engine are gas turbine
Or turbojet, rotor assembly include the inclined flow air compressor rotor 1 sequentially coaxially arranged along engine axis, axis stream pressure
Mechanism of qi rotor 12, turbine rotor, turbine rotor include that the turbine disk 14 and the turbine being fixed on the turbine disk 14 by locking plate 15 turn
Blades 16.
Rotor assembly integrally uses the supporting way of 1-0-1, and front fulcrum uses deep groove ball bearing 6, and rear fulcrum is using rolling
Mandrel holds 20, wherein the inner ring of deep groove ball bearing 6 is arranged on the extension axle journal of inclined flow air compressor rotor disk, outer ring setting
On the primary load bearing casing of engine；The front end of the extension axle journal of inclined flow air compressor rotor disk is equipped with external screw thread I, external screw thread I
It is equipped with a front nut 2 and a nut locking plate I 3 to prevent front nut 2 from loosening；The inner ring setting of stick roller bearing 20 exists
The turbine disk 14 extendes back on axle journal, and outer ring is arranged on the auxiliary support case of engine；Front fulcrum will by deep groove ball bearing 6
The axial force of rotor assembly and partially radially power pass to primary load bearing casing, and rear fulcrum passes through stick roller bearing for the portion of rotor assembly
Point radial force passes to auxiliary support case.
For centering and the torsion pass requirement for realizing axial flow compressor rotor 12 and turbine rotor, axial flow compressor rotor 12 and whirlpool
Take turns the connection structure that circular arc end tooth is used between rotor；The end for extending back axle journal of inclined flow air compressor rotor disk, which is formed with, to be had
The inner hole of internal screw thread, is threadedly coupled the front end of a center pull rod 13 in inner hole, center pull rod 13 extend along engine axis and according to
The centre bore of the secondary centre bore for passing through intermediate compressor rotor wheel discs at different levels and the turbine disk 14, the rear end of center pull rod 13 is stretched
For the outside for extending back axle journal of the turbine disk 14, the rear end surface of center pull rod 13 is equipped with external screw thread II, on external screw thread II according to
One tightening nut 21 of secondary setting, a clamp nut of nut locking plate II and one 23, wherein the inner face of tightening nut 21 is pressed against whirlpool
On the outer end face for extending back axle journal of wheel disc 14, to tense compressor rotors and turbine rotor at different levels；The inside of nut locking plate II
Simultaneously against the outer end face of tightening nut 21, the inner ring outer end face of stick roller bearing 20, nut locking plate II is to prevent tightening nut
21 loosen；The outside of nut locking plate II is arranged in clamp nut 23, and clamp nut 23 is pressed against roller axis by nut locking plate II
It holds on 20 inner ring outer end face, to compress the inner ring of stick roller bearing.
Further, deep groove ball bearing 6 is thrust deep groove ball bearing, also sets up one between front nut 2 and deep groove ball bearing 6
Bevel gear 5 is equipped with an annular groove at the rear end face center of bevel gear 5, and arranges an adjusting pad I 4 in annular groove, adjusts
Axial position of the pad I 4 to adjust bevel gear 5.A gear abutted with it is also set up at the rear end face of the inner ring of deep groove ball bearing 6
A labyrinth seal ring 8 is arranged at the rear end face of oil scraper ring 7 for oil ring 7.Extending back for final stage turbine rotor wheel disc also sets up one on axle journal
An adjusting pad II 19 is arranged between the 20 inner ring front end face of rear end face and stick roller bearing of graphite annulus runway 18 in graphite annulus runway 18,
Adjusting pad II 19 is to adjust the position to axial under hot working condition between stick roller bearing runway and rolling element.It is preferred that
Ground also sets up a labyrinth seal ring 17 abutted with it at the front end face of graphite annulus runway 18.The front end of center pull rod 13 and the
A support baffle ring 10 is also set up between the centre bore of level-one compressor rotor wheel disc, and baffle ring 10 and first order compressor is supported to turn
Sealing ring 9, preferably O-shaped rubber ring are equipped between the centre bore of sub- wheel disc.
Compared with the compressor and turbine rotor connection structure of conventional gas turbine and Core Engine, the present invention
The connection structure of engine rotor assemblies, it can be achieved that being reliably connected for compressor rotor and turbine rotor, and rotor can be met
The requirement such as the transmitting of axial force, the bearing of rotor, reliable assembling/decomposition of rotor and dynamic balancing of rotor assembly；And it is all
Rotor is freely-supported pattern, therefore rotor assembly rotor dynamics are excellent；And in view of rotor transmitting torque in the structure
" axis " radial location it is relatively high, therefore rotor assembly rigidity preferably, substantially increase rotor blade tip gap protect
Ability is held, there is huge application potential.
As shown in figure 4, illustrating that component in above-described embodiment goes the illustrated position of material.Remove the selection principle of positions of materials
Are as follows: apart from both ends, position of the fulcrum is closer, while diameter should be chosen at the larger diameter position of disk edge.Remove the range needs of material
It is obtained after Strength co-mputation.In figure, A is to calm the anger at generator terminal de-material material；B is that turbine end is gone at material.
In addition, it should be noted that, the specific embodiments described in this specification, the shape of parts and components are named
Title etc. can be different.The equivalent or simple change that all structure, feature and principles described according to the invention patent design are done, is wrapped
It includes in the scope of protection of the patent of the present invention.Those skilled in the art can be to described specific implementation
Example is done various modifications or additions or is substituted in a similar manner, and without departing from structure of the invention or surmounts this
Range as defined in the claims, is within the scope of protection of the invention.
Claims (21)
1. a kind of connection structure of engine rotor assemblies, the engine is gas turbine or turbojet, described
Rotor assembly includes at least two stage compressor rotor and at least one level turbine rotor sequentially coaxially arranged along engine axis,
It is characterized in that:
-- the rotor assembly integrally uses the supporting way of 1-0-1, and front fulcrum uses deep groove ball bearing, and rear fulcrum is using rolling
Mandrel is held, wherein
The inner ring of the deep groove ball bearing is arranged on the extension axle journal of first order compressor rotor wheel disc, and outer ring setting is being started
On the primary load bearing casing of machine；The front end of the extension axle journal of first order compressor rotor wheel disc is equipped with external screw thread I, the external screw thread I
It is equipped with a front nut and a nut locking plate I to prevent the front nut from loosening；
The extending back on axle journal of final stage turbine rotor wheel disc is arranged in the inner ring of the stick roller bearing, and the auxiliary of engine is arranged in outer ring
It helps on support case；
The front fulcrum is passed to the axial force of the rotor assembly and partially radially power by the deep groove ball bearing described
The partially radially power of the rotor assembly is passed to the auxiliary by the stick roller bearing by primary load bearing casing, the rear fulcrum
Support case；
-- the end for extending back axle journal of the first order compressor rotor wheel disc is formed with band internal thread inner hole, the inner hole
The middle front end for being threadedly coupled a center pull rod, the center pull rod, which extends along engine axis and sequentially passes through centre, at different levels calms the anger
The centre bore of the centre bore of machine rotor wheel disc and turbine rotor wheel disc at different levels, the rear end of the center pull rod stretch out in final stage
The rear end surface in the outside for extending back axle journal of turbine rotor wheel disc, the center pull rod is equipped with external screw thread II, the external screw thread
A tightening nut, a clamp nut of nut locking plate II and one are set gradually on II, wherein
The inner face of the tightening nut is pressed against on the outer end face for extending back axle journal of final stage turbine rotor wheel disc, each to tense
Grade compressor rotor and turbine rotor at different levels；
The inside of the nut locking plate II is simultaneously against the inner ring outer end of the outer end face of the tightening nut, the stick roller bearing
Face, the nut locking plate II is to prevent the tightening nut from loosening；
The outside of the nut locking plate II is arranged in the clamp nut, and the clamp nut is compressed by the nut locking plate II
On the inner ring outer end face of the stick roller bearing, to compress the inner ring of the stick roller bearing.
2. connection structure according to claim 1, which is characterized in that the center pull rod is real to when cold conditions is assembled
The axial pretension function of the existing compressor rotor and turbine rotor.
3. connection structure according to claim 1, which is characterized in that described in view of the assembly and disassembly of component needs
Internal screw thread is equipped in the rear end inner hole of center pull rod or makes the external screw thread of the rear end of the center pull rod that there is certain length, with
Realize the use of hydraulic disassembling tool.
4. connection structure according to claim 1, which is characterized in that pass through material selection, heat treatment process and structure
The mode of design increases the hardness at each screw position, in the case where ensuring to bear larger pulling force, the center pull rod can
By work.
5. connection structure according to claim 1, which is characterized in that at the external screw thread of center pull rod rear end, using spiral shell
The silver-plated special warfare processing method of line, prevents the adhesion of nut thread and center pull rod screw thread under hot working condition.
6. connection structure according to claim 1, which is characterized in that the diameter of the clamp nut is greater than the tension spiral shell
Female diameter, the lesser tightening nut of diameter mainly undertake the function of tensing compressor rotor and turbine rotor, apply to it
Add biggish screw-down torque；The clamp nut being relatively large in diameter mainly undertakes the function of compressing stick roller bearing inner ring, tightens
Torque is relatively small.
7. connection structure according to claim 1, which is characterized in that have in the DN value level of the stick roller bearing enough
In the case where deposit, to ensure itself to deform by way of the inner ring thicknesses for thickening stick roller bearing, to take
The lesser tightening nut of the diameter that disappears, is only arranged the clamp nut in the rear end of the center pull rod at this time.
8. connection structure according to claim 1, which is characterized in that according to engine performance demand, compressor series is 2
~8 grades.
9. connection structure according to claim 1, which is characterized in that the compressor rotor is integral blade disk connection side
Formula.
10. connection structure according to claim 1, which is characterized in that use arc end between adjacent compressor rotors at different levels
Tooth, spline, rectangle flute profile or length/lag bolt torsion pass connection type.
11. connection structure according to claim 1, which is characterized in that the torsion pass between adjacent turbine rotors at different levels is using short
The type of attachment of bolt.
12. connection structure according to claim 1, which is characterized in that the torsion pass between adjacent turbine rotors at different levels passes through flower
Key or the connection of end tooth frame mode.
13. connection structure according to claim 1, which is characterized in that in each turbine rotor, turbo blade and turbine
Tongue-and-groove/tenon tooth connection type is used between wheel disc, avoids blade to the heat transfer in wheel disc core direction.
14. connection structure according to claim 1, which is characterized in that realize final stage compressor rotor and first order whirlpool
The centering and torsion pass requirement for taking turns rotor, use the connection knot of circular arc end tooth between final stage compressor rotor and first order turbine rotor
Structure.
15. connection structure according to claim 1, which is characterized in that the deep groove ball bearing is thrust deep groove ball bearing,
A bevel gear is also set up between the front nut and deep groove ball bearing, and it is recessed that an annular is equipped at the rear end face center of the bevel gear
Slot, and an adjusting pad I is arranged in the annular groove, axial position of the adjusting pad I to adjust the bevel gear.
16. connection structure according to claim 15, which is characterized in that at the rear end face of the inner ring of the deep groove ball bearing
An oil scraper ring abutted with it is also set up, a labyrinth seal ring is set at the rear end face of the oil scraper ring.
17. connection structure according to claim 16, which is characterized in that the final stage turbine rotor wheel disc extendes back axle journal
On also set up a graphite annulus runway, be arranged one between the rear end face of the graphite annulus runway and the stick roller bearing inner ring front end face
Adjusting pad II, the adjusting pad II are opposite between the stick roller bearing runway and rolling element under hot working condition to adjust
Axial position.
18. connection structure according to claim 17, which is characterized in that also set up at the front end face of the graphite annulus runway
The one labyrinth seal ring abutted with it.
19. connection structure according to claim 1, which is characterized in that the import of the first order compressor rotor wheel disc
Side surface and/or the outlet side surface of final stage turbine rotor wheel disc are equipped with continuously in a circumferential or intermittent balance boss, for adjusting
The computing ballance correction of turn over sub-component.
20. connection structure according to claim 1, which is characterized in that the extension of the first order compressor rotor wheel disc
The diameter of axle journal is adjusted according to the DN value design result of bearing, and the length for the axis that protracts according to the layout of bearing bore and is obturaged
Mode is adjusted；Journal diameter parameter interconnected is dynamic according to the rotor of rotor component construction between other compressor stages and grade
Mechanical characteristic is adjusted.
21. connection structure according to claim 1, which is characterized in that the front end of the center pull rod and the first order
A support baffle ring is also set up between the centre bore of compressor rotor wheel disc, and the support baffle ring and the first order compressor turn
Sealing ring is equipped between the centre bore of sub- wheel disc.
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| CN201811289987.8A CN109209641B (en) | 2018-10-31 | 2018-10-31 | A kind of connection structure of engine rotor assemblies |
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| CN201811289987.8A CN109209641B (en) | 2018-10-31 | 2018-10-31 | A kind of connection structure of engine rotor assemblies |
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| CN109209641B true CN109209641B (en) | 2019-09-24 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110173353B (en) * | 2019-05-31 | 2021-01-22 | 中国航发湖南动力机械研究所 | Engine rotor system |
| CN110374697B (en) * | 2019-07-19 | 2021-09-03 | 中国航发沈阳发动机研究所 | Adjusting device for controlling axial distance between rotor and stator of engine |
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| CN111810511A (en) * | 2020-07-24 | 2020-10-23 | 中国科学院工程热物理研究所 | Engine wheel disc rear end nut locking structure |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3042095B2 (en) * | 1991-10-16 | 2000-05-15 | 石川島播磨重工業株式会社 | Gas turbine fastening device |
| JP3733573B2 (en) * | 1995-03-03 | 2006-01-11 | 石川島播磨重工業株式会社 | Gas turbine and its assembly method |
| DE102008015688A1 (en) * | 2008-03-26 | 2009-10-01 | Man Turbo Ag | Turbine rotor for a gas turbine |
| IT1399904B1 (en) * | 2010-04-21 | 2013-05-09 | Nuovo Pignone Spa | STACKED ROTOR WITH TIE AND BOLTED FLANGE AND METHOD |
| CN105290833B (en) * | 2015-11-20 | 2017-05-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Device locking reverse hook press plate through lever mechanism |
| CN107091156B (en) * | 2017-06-30 | 2018-12-28 | 西安中工动力能源有限公司 | A kind of micro-gas-turbine machine rotor and assembly method |
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