CN106224016B - Turbine rotor, engine and the method for improving engine rotor centering reliability - Google Patents
Turbine rotor, engine and the method for improving engine rotor centering reliability Download PDFInfo
- Publication number
- CN106224016B CN106224016B CN201610788457.2A CN201610788457A CN106224016B CN 106224016 B CN106224016 B CN 106224016B CN 201610788457 A CN201610788457 A CN 201610788457A CN 106224016 B CN106224016 B CN 106224016B
- Authority
- CN
- China
- Prior art keywords
- level disk
- rotor
- turbine
- wheel shaft
- level
- 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.)
- Active
Links
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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
-
- 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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
- F01D1/20—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means traversed by the working-fluid substantially axially
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on shafts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of turbine rotor, engine and the method for improving engine rotor centering reliability, the turbine rotor includes turbine wheel shaft and the turbine disc assemblies being fixed together with turbine wheel shaft, turbine wheel shaft is hollow shaft, the internal spline that the external splines being designed with one end endoporus of turbine wheel shaft on the armature spindle with compressor rotor is meshed, close to internal spline turbine wheel shaft internal spline end face on be correspondingly arranged on it is relative with compressor rotor in centering mark.Turbine rotor, engine and the method for improving engine rotor centering reliability provided by the invention, when processing and checking compressor rotor and turbine rotor, increase corresponding centering mark, solve the unstable technical problem of the accuracy of alignment of calmed the anger during engine general assembly rotor and turbine rotor, improve the reliability of rotor centering.
Description
Technical field
The present invention relates to engine art, especially, is related to a kind of turbine rotor.A kind of moreover, it relates to bag
The method for including the engine of above-mentioned turbine rotor and improving engine rotor centering reliability.
Background technology
During engine general assembly, by the internal spline on the external splines and turbine wheel shaft on compressor rotor axle, compressor is turned
Son and turbine rotor are rigidly connected into turn over.But due to the interior flower on the external splines and turbine wheel shaft on compressor rotor axle
Key, in the presence of certain flute profile error, when external splines is engaged with different setting angles and internal spline, can be led in processing
Cause the accuracy of alignment of compressor rotor and turbine rotor inconsistent.When rotor Disalignment, can be produced at rotor connection spline
Raw additional moment of flexure and shearing force, and adjacent bearing bear radial forces, cause shaft strength to be worse off, generation is shaken
It is dynamic, so as to influence the safe handling of engine.
Therefore, the inconsistent caused vibration of the accuracy of alignment of turbine rotor and compressor rotor, is one urgently to be resolved hurrily
Technical problem.
The content of the invention
The invention provides a kind of turbine rotor, engine and the method for improving engine rotor centering reliability, with solution
The certainly technical problem of the inconsistent caused vibration of the accuracy of alignment of turbine rotor and compressor rotor.
The technical solution adopted by the present invention is as follows：
According to an aspect of the present invention, there is provided a kind of turbine rotor, including turbine wheel shaft and be fixedly connected on turbine wheel shaft
Turbine disc assemblies together, the axis part of turbine wheel shaft is cavity, is provided with cavity on the armature spindle with compressor rotor
The internal spline that external splines is meshed, it is correspondingly arranged on and compressor rotor phase on the internal spline end face of the turbine wheel shaft of internal spline
The centering mark of centering.
Further, centering mark be arranged on turbine wheel shaft internal spline end face it is corresponding with the circular runout low spot of internal spline
Angular position on.
Further, turbine disc assemblies include one-level disk component, two level disk component and the three-level disk group being sequentially axially connected
Part, one-level disk component include the one-level disk being connected with turbine wheel shaft and the grade blade being fixed on one-level disk, two level Pan Zujianbao
The two level disk being connected with one-level disk and two grade blades being fixed on two level disk are included, three-level disk component includes what is be connected with two level disk
Three-level disk and three grade blades being fixed on three-level disk.
Further, be provided with one-level disk one-level disk seal sternly comb tooth, be correspondingly arranged on two level disk it is tight with one-level disk seal
The two level disk seal of comb tooth connection is sternly combed tooth, and the three-level disk seal being connected with two level disk seal sternly comb tooth is correspondingly arranged on three-level disk and is sternly combed
Tooth.
Further, one-level disk seal sternly comb tooth, which includes being separately positioned on the first of the both ends of the surface of one-level disk, obturages comb tooth and the
Two obturage comb tooth, and the 3rd of both ends of the surface of the two level disk seal sternly comb tooth including being separately positioned on two level disk, which obturage comb tooth and the 4th, obturages
Comb tooth, three-level disk seal sternly comb tooth includes being arranged on obturages comb tooth on three-level disk close to the 5th of two level disk, second obturage comb tooth with
3rd obturages comb tooth, and the 4th, which obturages comb tooth, obturages that comb tooth is relative to be connect with the 5th.
Further, turbine rotor includes axially penetrating through turbine wheel shaft, one-level disk and two level disk, for axial restraint one-level disk
With the short turnbuckle of two level disk.
Further, turbine rotor also includes axially penetrating through turbine wheel shaft, one-level disk, two level disk and three-level disk, for axial direction
The long turnbuckle of fixed one-level disk, two level disk and three-level disk.
Further, turbine rotor also includes being set on turbine wheel shaft and being arranged on the 6th of the front end of turbine wheel shaft obturaging comb
Tooth, turbine bearing and stop washer and locking nut, after the 6th obturages comb tooth via turbine bearing and stop washer, pass through locking
Nut is locked.
According to another aspect of the present invention, a kind of engine is also provided, including above-mentioned turbine rotor and compressor turn
Son.
According to another aspect of the present invention, a kind of method for improving engine rotor centering reliability, application are also provided
In above-mentioned engine, including step：
Bounce of all external spline teeths to rotor axis on the external splines of the armature spindle of compressor rotor is checked, and is being calmed the anger
The angular position that the external splines end face of machine rotor is corresponding with circular runout high point sets compressor rotor centering mark；
Bounce of all inner spline gears to turbine axis on the internal spline of the turbine wheel shaft of turbine rotor is checked, and is turned in turbine
The angular position that the internal spline end face of son is corresponding with circular runout low spot sets turbine rotor centering mark；
In engine general assembly, compressor rotor centering mark and turbine rotor centering mark are alignd.
The invention has the advantages that：
Turbine rotor provided by the invention, engine and the method for improving engine rotor centering reliability, in processing and
When checking compressor rotor and turbine rotor, increase corresponding centering mark, calmed the anger when solving engine general assembly rotor and whirlpool
The unstable technical problem of the accuracy of alignment of rotor is taken turns, improves the reliability of rotor centering.
In addition to objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to figure, the present invention is further detailed explanation.
Brief description of the drawings
The accompanying drawing for forming the part of the application is used for providing a further understanding of the present invention, schematic reality of the invention
Apply example and its illustrate to be used to explain the present invention, do not form inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the structural representation of turbine rotor preferred embodiment of the present invention；
Fig. 2 is the structural representation of turbine disc assemblies preferred embodiment in Fig. 1；
Fig. 3 is the structural representation of turbine wheel shaft preferred embodiment in Fig. 1；
Fig. 4 is the schematic flow sheet for the method preferred embodiment that the present invention improves engine rotor centering reliability.
Drawing reference numeral explanation：
10th, turbine wheel shaft；20th, turbine disc assemblies；11st, cavity；12nd, internal spline；21st, one-level disk component；22nd, two level disk group
Part；23rd, three-level disk component；211st, one-level disk；212nd, a grade blade；221st, two level disk；222nd, two grade blade；231st, three-level disk；
232nd, three grade blade；213rd, one-level disk seal is sternly combed tooth；223rd, two level disk seal is sternly combed tooth；233rd, three-level disk seal is sternly combed tooth；214th,
One obturages comb tooth；215th, second comb tooth is obturaged；224th, the 3rd comb tooth is obturaged；225th, the 4th comb tooth is obturaged；234th, the 5th comb is obturaged
Tooth；13rd, internal spline end face；30th, short turnbuckle；40th, long turnbuckle；50th, the 6th comb tooth is obturaged；60th, stop washer；70、
Locking nut；80th, turbine bearing.
Embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase
Mutually combination.Describe the present invention in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Referring to figs. 1 to Fig. 3, the preferred embodiments of the present invention provide a kind of turbine rotor, including turbine wheel shaft 10 and and turbine
The turbine disc assemblies 20 that axle 10 is fixed together, the axis part of turbine wheel shaft 10 is cavity 11, be provided with cavity 11 with
The internal spline 12 that external splines on the armature spindle of compressor rotor is meshed, close to the internal spline end of the turbine wheel shaft 10 of internal spline 12
Be correspondingly arranged on face 13 it is relative with compressor rotor in centering mark.Wherein, centering mark can be center line or mark
Lettering, for by turbine rotor and compressor rotor relatively in.
The turbine rotor that the present embodiment provides, be not in that vibration is big etc. different to ensure turbine rotor energy normal work
Chang Xianxiang, before general assembly, strict dynamic balancing inspection requirements need to be done to turbine rotor.As shown in figure 1, in parts machining and assembling
When, action balance inspection is entered to turbine wheel shaft 10, disks at different levels are ensured by the circle distribution for adjusting the blade in turbine disc assemblies 20
The static balance requirement of component, is finally combined carry out dynamic balancing measurement by turbine wheel shaft 10 and turbine disc assemblies 20.This implementation
Example is by when processing and checking turbine rotor, the increase centering mark corresponding with compressor rotor, it is total to solve engine
Calmed the anger during dress the unstable technical problem of accuracy of alignment of rotor and turbine rotor, improve the reliability of rotor centering.
Preferably, the turbine rotor provided referring to Fig. 3, the present embodiment, centering mark are arranged on the internal spline of turbine wheel shaft 10
In the angular position corresponding with the circular runout low spot of internal spline 12 of end face 13.Because the radial direction of internal spline 12 is jumped
Dynamic low spot represents the spline space width at this, during assembling, as the big spline tooth of transverse tooth thickness engages with the spline of space width, spline
It is uniform to engage backlash, the transmission stability of spline can be improved, ensures centering during spline connection rotor.
Preferably, as shown in figure 1, the turbine rotor that the present embodiment provides, turbine disc assemblies 20 include sequentially axially being connected
One-level disk component 21, two level disk component 22 and three-level disk component 23, one-level disk component 21 include be set on turbine wheel shaft 10
One-level disk 211 and the grade blade 212 being fixed on one-level disk 211, two level disk component 22 include being set on turbine wheel shaft 10
Two level disk 221 and two grade blades 222 being fixed on two level disk 221, three-level disk component 23 include being set on turbine wheel shaft 10
Three-level disk 231 and three grade blades 232 being fixed on three-level disk 231.The present embodiment in design, according to total enthalpy drop of turbine and
Level enthalpy drop ability, chooses suitable series, ensures that turbine both has high efficiency, has certain airload nargin and structure again
Strength margin.Wherein, the enthalpy drop of turbine refers to the acting ability of turbine, can send how much work(.
Alternatively, as shown in Fig. 2 the turbine rotor that the present embodiment provides, is provided with one-level disk seal on one-level disk 211 and sternly combs
The two level disk seal sternly comb tooth 223 being connected with one-level disk seal sternly comb tooth 213, three-level disk are correspondingly arranged on tooth 213, two level disk 221
The three-level disk seal sternly comb tooth 233 being connected with two level disk seal sternly comb tooth 223 is correspondingly arranged on 231.Specifically, one-level disk seal is sternly combed
The first of both ends of the surface of the tooth 213 including being separately positioned on one-level disk 211 obturages comb tooth 214 and second and obturages comb tooth 215, two level disk
Obturage comb tooth 223 and include being separately positioned on the 3rd of the both ends of the surface of two level disk 221 and obturage comb tooth 224 and the 4th and obturage comb tooth 225,
Three-level disk seal sternly comb tooth 233 includes being arranged on three-level disk 231 obturages comb tooth 234 close to the 5th of two level disk 221, and second obturages
Comb tooth 215 and the 3rd obturages comb tooth 224, and the 4th, which obturages comb tooth 225, obturages that comb tooth 234 is relative to be connect with the 5th.The present embodiment provides
Turbine rotor, high pressure gas after compressor reduces air loss after at different levels on the turbine disk obturage the decompression of comb tooth.
Preferably, as shown in figure 1, the present embodiment provide turbine rotor, turbine rotor include axially penetrate through turbine wheel shaft 10,
One-level disk 211 and two level disk 221, for axial restraint one-level disk 211 and the short turnbuckle 30 of two level disk 221.Further,
Turbine rotor is also used for axial restraint one-level including axially penetrating through turbine wheel shaft 10, one-level disk 211, two level disk 221 and three-level disk 231
The long turnbuckle 40 of disk 211, two level disk 221 and three-level disk 231.The present embodiment passes through short turnbuckle 30 and long turnbuckle
40 connect the stability and turbine turn for axially position turbine disc assemblies 20, improving turbine disc assemblies 20 with the locking of turbine wheel shaft 10
The dynamic balance accuracy of son.
Preferably, as shown in figure 1, the turbine rotor that the present embodiment provides, turbine rotor also include being set in turbine wheel shaft 10
Go up and be arranged on the 6th of the front end of turbine wheel shaft 10 and obturage comb tooth 50, turbine bearing 80 and stop washer 60 and locking nut 70,
After 6th obturages comb tooth 50 via turbine bearing 80 and stop washer 60, locked by locking nut 70.The present embodiment carries
The turbine rotor of confession, high pressure gas after compressor are obturaged after comb tooth 50 is depressured through the 6th, the lubricating oil for lubricating turbine bearing 80 are entered
Row is obturaged, and prevents lubrication leakage into high-temperature fuel gas.
The present embodiment also provides a kind of engine, including above-mentioned turbine rotor and compressor rotor, will not be repeated here.
The present embodiment also provides a kind of method for improving engine rotor centering reliability, applied to above-mentioned engine
In, the method for the raising engine rotor centering reliability that the present embodiment proposes, including step：
Step S100, check that all external spline teeths are to the radial direction of rotor axis on the external splines of the armature spindle of compressor rotor
Bounce, and compressor rotor pair is set in the external splines end face of the compressor rotor angular position corresponding with circular runout high point
Middle mark.
When processing and checking compressor rotor, it is desirable to check all outer on the external splines of the armature spindle of compressor rotor
The profile error of spline tooth, circular runout of all external spline teeths of particular exam to rotor axis, and in outer spline end face and footpath
The angular position head-stamp " 0 " corresponding to bounce high point (representing that the distance at the point to center is maximum).Wherein, the radial direction of external splines
Bounce high point represents that the spline transverse tooth thickness at this is big.
Step S200, check that all inner spline gears are jumped to the radial direction of turbine axis on the internal spline of the turbine wheel shaft of turbine rotor
It is dynamic, and turbine rotor is set to acceptance of the bid in the internal spline end face of the turbine rotor angular position corresponding with circular runout low spot
Will.
When processing and checking turbine rotor, it is desirable to check all inner spline gears on the internal spline of the turbine wheel shaft of turbine rotor
Profile error, circular runout of all inner spline gears of particular exam to turbine axis, and in interior spline end face and circular runout
The corresponding angular position head-stamp " 0 " of low spot (representing that the distance at the point to center is maximum).Wherein, the circular runout of internal spline is low
Point represents the spline space width at this.
Step S300, in engine general assembly, compressor rotor centering mark and turbine rotor centering mark are alignd.
During engine assembly, during engine general assembly, it is desirable to " 0 " of compressor rotor end face and " 0 " of turbine rotor end face
Alignment, the tooth that the transverse tooth thickness of external splines is big engage with the groove of inner spline gear groove width, and the engagement backlash of spline is uniform, can improve spline
Transmission stability, so as to ensure the accuracy of alignment of compressor rotor and turbine rotor.
The present embodiment provide raising engine rotor centering reliability method, process and check compressor rotor and
During turbine rotor, increase corresponding centering mark in spline end face, calmed the anger when solving engine general assembly rotor and turbine turn
The unstable technical problem of sub accuracy of alignment, improve the reliability of rotor centering.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (9)
1. a kind of turbine rotor, it is characterised in that be fixed together including turbine wheel shaft (10) and with the turbine wheel shaft (10)
Turbine disc assemblies (20), the axis part of the turbine wheel shaft (10) is cavity (11), is provided with and presses on the cavity (11)
The internal spline (12) that external splines on the armature spindle of mechanism of qi rotor is meshed, close to the turbine wheel shaft of the internal spline (12)
(10) be correspondingly arranged on internal spline end face (13) it is relative with the compressor rotor in centering mark, the centering mark
It is arranged on the internal spline end face (13) of the turbine wheel shaft (10) angle corresponding with the circular runout low spot of the internal spline (12)
To on position.
2. turbine rotor according to claim 1, it is characterised in that
The turbine disc assemblies (20) include one-level disk component (21), two level disk component (22) and the three-level disk being sequentially axially connected
Component (23), the one-level disk component (21) include the one-level disk (211) being connected with turbine wheel shaft (10) and are fixed on the one-level
A grade blade (212) on disk (211), the two level disk component (22) include the two level disk (221) being connected with one-level disk (211)
With two grade blades (222) being fixed on the two level disk (221), the three-level disk component (23) includes and two level disk (221)
Connected three-level disk (231) and three grade blades (232) being fixed on the three-level disk (231).
3. turbine rotor according to claim 2, it is characterised in that
Be provided with the one-level disk (211) one-level disk seal sternly comb tooth (213), be correspondingly arranged on the two level disk (221) with
Sternly the comb two level disk seal of tooth (213) connection of the one-level disk seal is sternly combed tooth (223), is correspondingly arranged on the three-level disk (231)
Sternly combed tooth (233) with the two level disk seal three-level disk seal that tooth (223) is connected of sternly combing.
4. turbine rotor according to claim 3, it is characterised in that
What the one-level disk seal sternly combed that tooth (213) includes being separately positioned on the both ends of the surface of the one-level disk (211) first obturages comb
Tooth (214) and second obturages comb tooth (215), and the two level disk seal sternly combs tooth (223) including being separately positioned on the two level disk
(221) the 3rd of both ends of the surface obturages comb tooth (224) and the 4th obturages comb tooth (225), and the three-level disk seal is sternly combed tooth (233) bag
Include to be arranged on the three-level disk (231) and obturage comb tooth (234) close to the 5th of the two level disk (221), described second obturages
Comb tooth (215) and the described 3rd obturages comb tooth (224), and the described 4th, which obturages comb tooth (225) and the described 5th, obturages comb tooth (234)
It is relative to connect.
5. turbine rotor according to claim 2, it is characterised in that
The turbine rotor includes axially penetrating through the turbine wheel shaft (10), the one-level disk (211) and the two level disk (221),
For one-level disk (211) described in axial restraint and the short turnbuckle (30) of the two level disk (221).
6. turbine rotor according to claim 5, it is characterised in that
Also include axially penetrating through the turbine wheel shaft (10), the one-level disk (211), the two level disk (221) and the three-level disk
(231), spiral shell is tensed for one-level disk (211), the two level disk (221) and the long of the three-level disk (231) described in axial restraint
Bolt (40).
7. turbine rotor according to claim 5, it is characterised in that
Also include being set on the turbine wheel shaft (10) and being arranged on the 6th of the front end of the turbine wheel shaft (10) obturaging comb tooth
(50), turbine bearing (80) and stop washer (60) and locking nut (70), the described 6th obturages comb tooth (50) via turbine wheel shaft
After holding (80) and stop washer (60), locked by locking nut (70).
8. a kind of engine, it is characterised in that including the turbine rotor and compressor as any one of claim 1 to 7
Rotor.
9. a kind of method for improving engine rotor centering reliability, applied in engine as claimed in claim 8, it is special
Sign is, including step：
Check that all external spline teeths are to rotor shaft run-out on the external splines of the armature spindle of compressor rotor, and in compressor
The angular position that the external splines end face of rotor is corresponding with circular runout high point sets compressor rotor centering mark；
Check that all inner spline gears are to turbine shaft run-out on the internal spline of the turbine wheel shaft of turbine rotor, and in turbine rotor
The internal spline end face angular position corresponding with circular runout low spot turbine rotor centering mark is set；
In engine general assembly, the compressor rotor centering mark and the turbine rotor centering mark are alignd.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610788457.2A CN106224016B (en) | 2016-08-31 | 2016-08-31 | Turbine rotor, engine and the method for improving engine rotor centering reliability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610788457.2A CN106224016B (en) | 2016-08-31 | 2016-08-31 | Turbine rotor, engine and the method for improving engine rotor centering reliability |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106224016A CN106224016A (en) | 2016-12-14 |
| CN106224016B true CN106224016B (en) | 2018-01-12 |
Family
ID=58073710
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610788457.2A Active CN106224016B (en) | 2016-08-31 | 2016-08-31 | Turbine rotor, engine and the method for improving engine rotor centering reliability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106224016B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110509052B (en) * | 2019-07-31 | 2020-09-11 | 中国航发南方工业有限公司 | Engine turbine rotor assembly vehicle and turbine rotor assembly method |
| CN114201879B (en) * | 2021-12-14 | 2024-04-09 | 中国航发燃气轮机有限公司 | Angular fixed butt joint combination method for compressor turbine rotor of gas turbine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6340285B1 (en) * | 2000-06-08 | 2002-01-22 | General Electric Company | End rail cooling for combined high and low pressure turbine shroud |
| CN101498573A (en) * | 2009-02-20 | 2009-08-05 | 中冶实久建设有限公司南京分公司 | Aligning method for turbine shaft and generator shaft |
| EP2415966A1 (en) * | 2010-08-05 | 2012-02-08 | Siemens Aktiengesellschaft | Power train for a gas turbine |
| US9249676B2 (en) * | 2012-06-05 | 2016-02-02 | United Technologies Corporation | Turbine rotor cover plate lock |
| 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 |
-
2016
- 2016-08-31 CN CN201610788457.2A patent/CN106224016B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106224016A (en) | 2016-12-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20210222588A1 (en) | Containment system for gas turbine engine | |
| CN106224016B (en) | Turbine rotor, engine and the method for improving engine rotor centering reliability | |
| CN104081025B (en) | The gear-box of turbogenerator | |
| CN1854485B (en) | Turbine module for gas turbine starter | |
| EP2635781B1 (en) | Exhaust gas turbocharger with means for axially securing the shaft in the event of a compressor wheel burst | |
| CN103867650B (en) | Double helical tooth planetary transmission device | |
| CN106801625A (en) | The turbine vane with exit passageway in shield | |
| US20190128126A1 (en) | Turbine blisk and method of manufacturing thereof | |
| US20190186598A1 (en) | Apparatus and system for thin rim planet gear for aircraft engine power gearbox | |
| CN110199090A (en) | Heat insulation structural for revolving wormgear frame | |
| CA2708467C (en) | Method and apparatus for providing rotor discs | |
| CN107366735A (en) | A kind of helical gear and preparation method thereof | |
| Nam et al. | The effects of non‐torque loads on a three‐point suspension gearbox for wind turbines | |
| CN204312136U (en) | The wheel disc seam position structure of gas turbine rotor and gas turbine rotor | |
| CN107131282B (en) | Merge the high speed roller gear dynamic mesh stiffness calculation method of back of tooth contacting mechanism | |
| CN105570187A (en) | Control method for dimensions of rotor tips of gas compressor | |
| US20120023747A1 (en) | Methods for cluster gear timing and manufacturing | |
| US20200300161A1 (en) | Position securement of an exhaust gas turbocharger housing | |
| CN108708958B (en) | Gear with reduced roller element stress and method of making such gear | |
| CN107709754A (en) | The little gear starter transmission device of gear geometry with amendment | |
| CN2936520Y (en) | Indexing unit for processing large integral key shaft | |
| CN110645097A (en) | Gas turbine generating set rotor subassembly and gas turbine generating set | |
| CN108204896A (en) | A kind of simplification connection structure suitable for the experiment of circular arc end gear disc spins | |
| Moslem et al. | Loaded and unloaded tooth contact analysis of spiral bevel gears in consideration of misalignments | |
| EP3058180B1 (en) | Fan rotor with integrated platform attachment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
|
| CP01 | Change in the name or title of a patent holder |