CN108252754A - Free power turbine - Google Patents
Free power turbine Download PDFInfo
- Publication number
- CN108252754A CN108252754A CN201710963236.9A CN201710963236A CN108252754A CN 108252754 A CN108252754 A CN 108252754A CN 201710963236 A CN201710963236 A CN 201710963236A CN 108252754 A CN108252754 A CN 108252754A
- Authority
- CN
- China
- Prior art keywords
- labyrinth
- ring
- air cavity
- axis
- roller bearing
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 claims abstract description 6
- 239000002245 particle Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
-
- 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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The present invention relates to a kind of free power turbines to include：Roller bearing and the air labyrinth sealing element with labyrinth ring and stator labyrinth flange.The roller bearing dividing bush of ring edge with radial direction nut orientation is between roller bearing inner ring and the cylindrical surface of axis, labyrinth ring forms the labyrinth seal with center annular air cavity together with stator flange, center annular air cavity is connected to the inside air cavity of axis in inlet, and it is connected to by one group of labyrinth teeth the air cavity of gas-turbine unit in exit, and the oil pocket of turbine is connected to by single labyrinth seal and by C-shaped fluting cavity, the C-shaped slots cylindrical part of the cavity by stator flange and the surrounding forepart by the labyrinth ring with inclined inner surface is formed.The stress in engine shaft is avoided to increase and by preventing oil from leaking into air cavity from oil pocket under all engine operation modes by by circumferentially Fix roller bearing retaining nut, to improve the reliability of gas-turbine unit.
Description
Technical field
The present invention relates to a kind of civilian and ground gas turbogenerators including free power turbine.
Background technology
Gas-turbine unit is known, wherein there are roller bearing stent, the inner ring peace of the roller bearing stent
(patent US 2008/0098717, IPC F02K3/02, date of publication on turbine wheel shaft：On May 1st, 2008).
The shortcomings that this design, is that its reliability is low, because roller bearing failure may lead to turbine due to its overheat
Axle fracture.
It is gas-turbine unit closest to claimed design, wherein the inner ring of roller bearing is mounted on engine shaft
Above and with nut locking in axial position, the nut is circumferentially locked in one with the holding plate in the axial notch of axis
It rises.Also there is the labyrinth ring for being installed to axis, the labyrinth ring collectively forms labyrinth seal (patent RU 2 250 with stator flange
386, IPC F02K3/06, date of publication：On April 20th, 2005).
The shortcomings that Known designs for being considered as prototype, is that its reliability is relatively low, because the axial notch of axis is stress liter
High device reduces the reliability of gas turbine due to potential axis failure.In addition, under the power condition of reduction, oil may
Air cavity is leaked into from oil pocket, so as to also reduce the reliability of engine.
The technological challenge solved by claimed invention is to rely on to keep spiral shell by circumferentially Fix roller bearing
Mother avoids the stress in engine shaft from increasing and by the way that oil is avoided to leak into gas from oil pocket in the case where engine reduces power
Chamber, to improve the reliability of gas-turbine unit.
Invention content
Technological achievement realizes that the free power turbine includes by free power turbine：Roller bearing, the Roller Shaft
The inner ring nut locking held is in axial position；And the air labyrinth sealing with labyrinth ring and labyrinth flange, and according to
The present invention, the free power turbine include：
The roller bearing dividing bush of ring edge with radial direction nut orientation is located at the circle of roller bearing inner ring and axis
Between cylindrical surface, and on the inside of the ring edge it is a series of flat and cylindrical surface, wherein bushing flat surfaces
The flat outer surface of engagement shaft, and be cylindrical on the outside of the annular ring, the axis for being manufactured with axis is accommodated thereon
To the axial edge for taking extrorse lock ring, the axial edge also has made of a series of flat and cylindrical surface
The flat outer surface of the flat surfaces engagement shaft of inside, wherein lock ring；
On dividing bush between roller bearing inner ring and lock ring, there are labyrinth ring, the labyrinth ring and stator flange
Labyrinth seal is formed together, and the labyrinth seal has center annular air cavity, and the center annular air cavity connects in inlet
It is connected to the inside air cavity of axis, and it is connected to by one group of labyrinth teeth the air cavity of gas-turbine unit, Yi Jitong in exit
It crosses single labyrinth seal and the oil pocket of turbine is connected to by C-shaped fluting cavity, the C-shaped slots cavity by stator flange
Cylindrical part is simultaneously formed by the surrounding forepart of the labyrinth ring with inclined inner surface.
Roller bearing dividing bush between the cylindrical surface of roller bearing inner ring and free vortex wheel shaft causes
Turbine wheel shaft can be avoided to damage in the case of roller bearing failure, so as to improve the reliability of gas turbine.
With prototype on the contrary, the invention enables the ring edge that radial direction nut orientation is manufactured on roller bearing dividing bush,
It has the inside as a series of flat and cylindrical surface, and the surface is contacted along the flat outer surface of axis, this makes
Obtaining can prevent bushing from being moved axially against axis, so as to prevent the imbalance of high speed free turbine rotor；In such case
Under, the stress concentration on axis surface is minimum.
Due to being formed into cylinder on the outside of the radial ringed edge of dividing bush, the axial direction of lock ring is installed thereon
Cylindrical edge, it is possible to meet the proper alignment of lock ring and high-speed turbine axis, so as to prevent rotor in engine operating range
Interior is unbalance.
Manufacture has the lock ring of the axial orientation ring edge of axis, is a series of flat and round on the inside of the ring edge
The flat outer surface on the surface of cylindricality, wherein bushing flat surfaces engagement shaft so that the circumferential direction that can prevent lock ring against axis is moved
It is dynamic, so that it is guaranteed that bearing inner ring retaining nut is circumferentially fixed to appropriate location.
Labyrinth ring is installed on dividing bush between roller bearing inner ring and lock ring so that can be in labyrinth seal quilt
Overheat and the failure of turbine wheel shaft are prevented in the case of obstruction, this improves the reliability of gas-turbine unit.
Due to having the labyrinth seal of the oil pocket for roller bearing, wherein center annular air cavity is connected in inlet
The inside air cavity of turbine wheel shaft, and in exit, the air cavity of gas-turbine unit is connected to by one group of labyrinth teeth, Yi Jitong
It crosses single labyrinth seal and the oil pocket of roller bearing stent is connected to by C-shaped fluting air cavity, the C-shaped fluting air cavity is by fixed
The cylindrical part of sub- flange is simultaneously formed by the surrounding forepart of the labyrinth ring with inclined inner surface, it is possible to ensure that labyrinth is close
Reliable operation of the sealing under engine operating range (including transient mode), so as to improve the reliable of gas-turbine unit
Property.
Description of the drawings
Fig. 1 is the longitudinal profile of free power turbine；
Fig. 2 is the enlarged view of the section I in Fig. 1；
Fig. 3 is the A-A sections in Fig. 2；
Fig. 4 is the B-B sections in Fig. 2；
Fig. 5 is the enlarged view of the section II in Fig. 2.
Specific embodiment
Free power turbine component 1 includes the rear roller bearing 2 with inner ring 3, and the inner ring 3 is mounted on dividing bush 4
On, the dividing bush 4 is arranged on again at the exterior cylindrical surfaces 5 of the axis 6 of the rotor 7 of turbine 1.
Dividing bush 4, labyrinth ring 8 and lock ring 9 nut being mounted on axis 6 coupled with inner ring 3 mounted thereto
10 carry out axial restraint, and nut 10 and the after-poppet 11 of lock ring 9 circumferentially lock together.
Dividing bush 4 is manufactured with the radial ringed edge 12 of the orientation of lock ring 9, the interior table at the radial ringed edge
Face 13 is formed into a series of flat surfaces 14 and cylindrical surface 15, the cooperation flat outer surface 16 of the surface engagement shaft 6.
Radial clearance 18 is located between the cylindrical surface 15 of the ring edge 12 of dividing bush 4 and the cooperation cylindrical surface 17 of axis.
The outer surface 19 at radial ringed edge 12 is formed into cylinder, and the ring shaped axial edge 20 of wherein lock ring 9 is pacified
Mounted in thereon.
Lock ring 9 is also manufactured with ring edge 22, and the ring edge is oriented in the axis of the axis 6 in turbine 1
On 21, and the inner surface 23 of ring edge 22 is also formed as a series of flat surfaces 24 and cylindrical surface 25, the surface
The cooperation flat outer surface 26 of engagement shaft 6.Radial clearance 28 is located at the cylindrical surface 27 of ring edge 22 and the cooperation circle of axis 6
Between cylindrical surface 25.
Labyrinth ring 8 collectively forms labyrinth seal 30 with stator labyrinth flange 29, thus by air cavity 31 and free power whirlpool
The isolation sealing of oil pocket 32 in wheel 1.Labyrinth seal 30 includes center annular air cavity 33, and the center annular air cavity is in inlet
The inside air cavity 37 of axis 6 is connected to by radial passage 34,35 and 36, and in exit：It is connected by one group of labyrinth teeth 38
The oil pocket 32 of turbine 1, the C-shaped fluting gas are connected to air cavity 31 and by single tooth 39 and by C-shaped fluting air cavity 40
The surrounding forepart of cylindrical part 41 of the chamber by stator flange 29 and the labyrinth ring 8 with inclined inner surface 43 and 44 is formed.
Component operation is as follows.
In free power turbine 1 with during the power operation of reduction, labyrinth seal 30 is by being applied to C-shaped fluting air cavity
The centrifugal force of oil particles in 40 and effectively seal against oil pocket 32 because oil particles are discharged into oil pocket by inclined surface 43,44
In 32.When gas-turbine unit power increases, cooling air under an increased pressure is delivered from the inside air cavity 37 of axis 6
To labyrinth seal, this causes labyrinth seal 30 more effectively to work.Stator flange 29 is contacted in labyrinth seal 8 and is confused
In the case that palace sealing element 8 heats, axis 6 will be protected to exempt from against axis 6 and the circumferentially fixed dividing bush 4 together of flat surfaces 14
It is damaged.
Therefore, cause can for embodiment of the present invention as characterized above and the known features of claimed invention
The stress in engine shaft is avoided to increase and by preventing oil from existing by circumferentially Fix roller bearing retaining nut to rely on
Air cavity is leaked into from oil pocket under all engine operation modes, to improve the reliability of gas turbine.
Claims (1)
1. a kind of free power turbine, including：
Roller bearing, inner ring nut locking in axial position and
Air labyrinth sealing element with labyrinth ring and stator labyrinth flange,
It is characterized in that：
With radial direction nut orientation ring edge roller bearing dividing bush between inner ring and the cylindrical surface of axis,
It is a series of flat and cylindrical surface on the inside of ring edge, wherein bushing flat surfaces contact the flat of the axis
Outer surface,
Cylinder is made on the outside of annular ring, accommodates the axial edge of lock ring thereon,
Lock ring is manufactured with the axes orientation edge of axis, and edge, which also has, is formed into a series of flat and cylindrical table
The inside in face, wherein lock ring flat surfaces contact the flat outer surface of the axis；
There are labyrinth ring on dividing bush between roller bearing inner ring and lock ring, labyrinth ring forms tool together with stator flange
There is the labyrinth seal of center annular air cavity,
Center annular air cavity is connected to the inside air cavity of axis in inlet, and in exit, it is connected to by one group of labyrinth teeth
The air cavity of gas-turbine unit and the oil pocket that turbine is connected to by single labyrinth seal and by C-shaped fluting air cavity,
Fluting cylindrical part of the air cavity by stator flange and the surrounding forepart by the labyrinth ring with inclined inner surface formed.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2016152410A RU2659694C2 (en) | 2016-12-28 | 2016-12-28 | Free power turbine |
| RURU2016152410 | 2016-12-28 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108252754A true CN108252754A (en) | 2018-07-06 |
| CN108252754B CN108252754B (en) | 2021-05-04 |
Family
ID=62722253
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710963236.9A Active CN108252754B (en) | 2016-12-28 | 2017-10-17 | Free power turbine |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN108252754B (en) |
| RU (1) | RU2659694C2 (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070044307A1 (en) * | 2005-08-26 | 2007-03-01 | Snecma | Method of assembling a turbomachine |
| US20070177936A1 (en) * | 2006-01-30 | 2007-08-02 | Snecma | System for connecting an engine shaft with a retractable nut |
| CN101769203A (en) * | 2008-12-30 | 2010-07-07 | 通用电气公司 | Methods, systems and/or apparatus relating to inducers for turbine engines |
| US20110247345A1 (en) * | 2010-04-12 | 2011-10-13 | Laurello Vincent P | Cooling fluid pre-swirl assembly for a gas turbine engine |
| CN204140138U (en) * | 2014-09-25 | 2015-02-04 | 中航商用航空发动机有限责任公司 | A kind of engine rotor supporting structure and aeroengine |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2151885C1 (en) * | 1997-12-16 | 2000-06-27 | Открытое акционерное общество "Авиадвигатель" | Gas turbine engine sealing device |
| RU2250386C2 (en) * | 2003-05-08 | 2005-04-20 | Открытое акционерное общество "Авиадвигатель" | Two-shaft gas-turbine engine |
| RU2269006C1 (en) * | 2004-04-05 | 2006-01-27 | Открытое акционерное общество "Авиадвигатель" | Gas-turbine power plant |
| US7921634B2 (en) * | 2006-10-31 | 2011-04-12 | General Electric Company | Turbofan engine assembly and method of assembling same |
-
2016
- 2016-12-28 RU RU2016152410A patent/RU2659694C2/en active
-
2017
- 2017-10-17 CN CN201710963236.9A patent/CN108252754B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070044307A1 (en) * | 2005-08-26 | 2007-03-01 | Snecma | Method of assembling a turbomachine |
| US20070177936A1 (en) * | 2006-01-30 | 2007-08-02 | Snecma | System for connecting an engine shaft with a retractable nut |
| CN101769203A (en) * | 2008-12-30 | 2010-07-07 | 通用电气公司 | Methods, systems and/or apparatus relating to inducers for turbine engines |
| US20110247345A1 (en) * | 2010-04-12 | 2011-10-13 | Laurello Vincent P | Cooling fluid pre-swirl assembly for a gas turbine engine |
| CN204140138U (en) * | 2014-09-25 | 2015-02-04 | 中航商用航空发动机有限责任公司 | A kind of engine rotor supporting structure and aeroengine |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2016152410A (en) | 2018-06-28 |
| RU2659694C2 (en) | 2018-07-03 |
| CN108252754B (en) | 2021-05-04 |
| RU2016152410A3 (en) | 2018-06-28 |
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