CN107269396B - A kind of achievable bearing is total to the seal structure that chamber and bearing exocoel are pressed - Google Patents
A kind of achievable bearing is total to the seal structure that chamber and bearing exocoel are pressed Download PDFInfo
- Publication number
- CN107269396B CN107269396B CN201710706924.7A CN201710706924A CN107269396B CN 107269396 B CN107269396 B CN 107269396B CN 201710706924 A CN201710706924 A CN 201710706924A CN 107269396 B CN107269396 B CN 107269396B
- Authority
- CN
- China
- Prior art keywords
- bearing
- exocoel
- rear bearing
- pressure
- bearing block
- 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
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a kind of achievable bearings to be total to the seal structure that chamber and bearing exocoel are pressed, former and later two bearing pivots, one uses freely-supported support structure designs, another is designed using cantilevered support structure, to realize two adjacent bearing spaces apart from upper close, front and back bearings seat links together, and realizes the total chamber design between adjacent bearing, facilitates and adjust the intracavitary pressure of bearing.Respectively circumferentially arranged with several vent hole structures on front and back bearings seat, angular position, shape and the size of vent hole structure on two bearing blocks are adapted, and it corresponds, form the channel of two bearing exocoels of connection, pressure to realize former and later two bearing exocoels is balanced, air system flow path is simplified, reduces the design difficulty that air system obturages bearing bore, and operational reliability is high；The pressure of bearing exocoel is adjusted by adjusting its inlet and outlet castor backlash, is conducive to the foundation of the outer cavity pressure of bearing, and effect is obturaged in raising.
Description
Technical field
The present invention relates to ground gas turbine and aero-engine fields, and in particular to a kind of achievable bearing be total to chamber and
The seal structure that bearing exocoel is pressed realizes that engine bearing is total to outside chamber and bearing using new structure and layout principle
Cavity pressure is balanced, obturages effect so as to improve bearing bore, improves engine health.
Background technique
In ground gas turbine and aero-engine, bearing is one of essential critical component of engine, main
It to play a supportive role to engine other component, and bear certain axial force.In the process, be lubricated to bearing is to protect
Demonstrate,prove the most basic and most important link of the safe and reliable operation of bearing.Lubricating oil can reduce the friction and abrasion of bearing,
It takes away the heat as caused by rubbing surface and abrasion impurity and guarantees that bearing inner race can be adequately cooled, effectively reduce and often go out
The probability for hurting failure is rubbed on present high-speed bearing inner track.
In order to collect lubricating oil, and ensure lubricant effect, bearing is usually wrapped up by bearing bore.In engine operation process, axis
It holds and is filled with lubricating oil mist of oil and liquid lubricating oil in chamber always, in order to prevent the leakage of lubricating oil, lubricating oil consumption is reduced, to bearing bore
Effectively being obturaged is an important problem in engine.Although it is the best one kind side of obturaging of effect that contact, which is obturaged,
Formula, but the high-speed rotating state of rotatable parts determines that this obturage can not be able to satisfy long-lived demand in engine.It is non-to connect
Touch is obturaged as mainstream structure.Its cardinal principle is to guarantee that the pressure outside bearing bore is high by controlling the intracavitary external pressure of bearing
In the pressure in bearing bore, that is, it can ensure that the leakage that lubricating oil will not occur.And designer in industry it is generally acknowledged that
It is also more square for the design of engine if can guarantee the equilibrium of bearing bore inside and external pressure everywhere as far as possible
Just, can also guarantee bearing bore as much as possible obturages effect.In previous engine structure, although designer is not by
Same structure or design method is hardy realized the efficient balance to bearing bore external pressure and control, but is on the one hand limited to
Bearing arrangement, on the other hand since structure is excessively complicated, air system flow path is too long, leads to actual operating condition and pays no attention to
Think.In order to solve this problem, the performance of engine is further improved, it is necessary to seek new structure, simplify air system
System flow path realizes that effect is obturaged in the equilibrium for obturaging pressure of bearing bore, improvement, improves engine performance.
Summary of the invention
For the disadvantages mentioned above and deficiency of the prior art, the present invention is intended to provide a kind of achievable bearing is total to outside chamber and bearing
The seal structure that chamber is pressed obturages effect for improving modern ground gas turbine and aeroplane engine inboard bearing chamber.Pass through
Using the novel seal structure and layout principle, it can be achieved that engine bearing is total to chamber and bearing bore external pressure is balanced, thus
Improve bearing bore and obturage effect, improves engine health, and then improve engine competitiveness.
To realize the target, the technical solution adopted by the present invention are as follows:
A kind of achievable bearing is total to the seal structure that chamber and bearing exocoel are pressed, including rear bearing block and front-end bearing pedestal, institute
It states and rear bearing is set in rear bearing block, fore bearing is set in the front-end bearing pedestal, the rear bearing is solid by cantilever support mode
It is scheduled in low-pressure turbine rotary shaft, the fore bearing is fixed in high-pressure turbine rotary shaft by freely-supported supporting way, described low
Pressure rotatable shaft is coaxially set in hollow high-pressure turbine rotary shaft, which is characterized in that
The rear bearing block is integrally cylindrical in shape structure, the whole disc-shaped structure of the front-end bearing pedestal, the rear bearing block
The mode that counterface is bolted or welds with counterface after the plate-like of the front-end bearing pedestal before ring-type is connected to
Together, two bearings are surrounded by the rear bearing block, front-end bearing pedestal, fore bearing, rear bearing, part low-pressure turbine rotary shaft jointly
Bearing bore；
It is common by the front end face for obturaging ring, preceding labyrinth seal ring and front-end bearing pedestal before being arranged on rear side of high-pressure turbine disk
Fore bearing exocoel is formed, by obturaging ring, the rear end face of rear bearing block, part low-pressure turbine after being arranged on front side of low-pressure turbine disk
Rotary shaft collectively constitutes rear bearing exocoel；
Circumferentially arranged with several vent hole structures on the front-end bearing pedestal, if on the rear bearing block circumferentially arranged with
Dry vent hole structure, angular position, shape and the size of the vent hole structure on two bearing blocks are adapted, and one is a pair of
It answers, the channel for being connected to the fore bearing exocoel and rear bearing exocoel is formed, to realize that the pressure of former and later two bearing exocoels is equal
Weighing apparatus.
In above-mentioned seal structure of the invention, former and later two bearings are two adjacent bearing pivots, one of to use
Freely-supported support structure designs, another is designed using cantilevered support structure, to realize two adjacent bearing spaces apart from upper
It is close.
More preferably, the forward and backward bearing block is by bolt or welding manner, directly or (centre passes through other indirectly
Engine part carries out connected) it links together, to realize the total chamber design between adjacent bearing, facilitate adjusting bearing intracavitary
Pressure.Be connected by screw bolts mode, can make engine assembly and later period maintenance decompose, part exchanging it is more convenient.
Using welding connecting mode, it is possible to reduce number of parts, and connect reliable, No leakage.It, should root using which kind of connection type
It is preferentially chosen according to the actual conditions of engine.
More preferably, the fore bearing passes through fore bearing clamp nut axial compression in the high-pressure turbine rotary shaft, institute
It states rear bearing and passes through rear bearing clamp nut axial compression in the low-pressure turbine rotary shaft.
More preferably, envelope is equipped on the counterface between adjacent bearing block or between other parts between the two
Tight slot can prevent mist of oil in bearing bore from letting out by the counterface between each part by arranging that O-ring seal is sealed
Leakage.
More preferably, two total chamber bearings similar in adjacent and space are laid out and share a set of lubricating oil oil return feeding system.
More preferably, the outer wall of the tubular rear bearing block is equipped with double fuel nozzle structures, can simultaneously forward latter two
Bearing provides lubricating oil.
More preferably, the angle and oil spout pore size of two nozzles of double fuel nozzle structures according to bearing arrangement with
And depending on needing.
More preferably, it in order to improve the clean-up performance of lubricating oil, prevents impurity from entering bearing, is equipped at jet expansion position removable
Unload filtering nozzle.
More preferably, the lubricating oil of oil system passed through on screw thread and the tubular rear bearing block outer wall for oil return lube pipe
Pipe mounting seat is connected.
More preferably, the leakage of lubricating oil in order to prevent, between the lubricating oil pipe mounting seat on oil pipe and the rear bearing block
Design has graphite annulus seal structure, carries out end face seal.
More preferably, between former and later two static bearing blocks and corresponding rotatable parts, it is equipped with labyrinth seal structure,
Bearing bore is obturaged.
More preferably, the pressure of (defining castor tooth close to the side of bearing bore is inside) differs inside and outside castor tooth, bearing exocoel
Pressure is higher than the pressure of bearing bore, by adjusting the size of bearing intracavitary outer pressure difference and castor backlash, realizes to bearing bore
Obturage the adjustment of effect.
More preferably, between former and later two bearing exocoels and other regions of air system and bearing bore, pass through castor tooth knot
Structure is connected to.
More preferably, the incoming flow of upstream air system enters bearing exocoel by the castor backlash that castor tooth obturages ring.
More preferably, in the bearing exocoel on the outside of two castor tooth seal structures, in order to realize the pressure of two chambers, two
Design has the vent hole structure of two bearing exocoels of connection on a bearing block (including other components between bearing block).Pass through
This design can adjust the pressure in two bearing exocoels simultaneously, greatly reduce the design difficulty of engine air system,
The operational reliability for obturaging effect and engine is improved simultaneously.
More preferably, the cross sectional shape of the venthole on former and later two described bearing blocks can be designed as circle, ellipse, side
Shape or other shapes.
More preferably, the size and quantity of the venthole on former and later two described bearing blocks, according to the pressure of bearing exocoel
Size, and depending on obturaging uninterrupted.
More preferably, air leaks in order to prevent, causes the indoor pressure of former and later two bearing outer cavities uneven, along journey
Part counterface is equipped with and obturages slot, by arranging that O-ring seal is sealed.
More preferably, the air-flow in the downstream bearing exocoel continues flow further downstream by other castor backlashes, and complete
At the function of corresponding air system.
More preferably, the pressure in the isobaric bearing exocoel of two to be connected, the castor backlash of ring is obturaged by adjusting castor tooth
Size and the stream castor backlash size that goes out of downstream bearing bore are adjusted.
Selectively, according to the structure of two bearing blocks, different processing methods can be taken.When two bearing blocks design
When for two individual parts, it can be produced by way of machining；When two bearing blocks are designed as a part
When, it can be produced by the way of casting+machining.
The seal structure and placement scheme that chamber and bearing exocoel are pressed, phase are total to by using the above novel achievable bearing
Than traditional scheme, have the advantage that (1) by the layout designs to bearing pivot, realizes the total chamber of two adjacent bearings,
Facilitate the pressure of adjustment bearing bore；(2) using the novel bearing holder structure of included nozzle, reducing number of parts, structure is simple,
Reliability is improved, and facilitates adjusting oil flow；(3) by using novel bearing holder structure, two neighboring bearing is realized
The pressure of bearing exocoel is balanced, simplifies air system flow path, significantly reduces the design hardly possible that air system obturages bearing bore
Degree, and operational reliability is high；(4) pressure of bearing exocoel is adjusted by adjusting the inlet and outlet castor backlash of bearing exocoel
It is whole, be conducive to the foundation of the outer cavity pressure of bearing, effect is obturaged in raising.
Detailed description of the invention
Fig. 1 is that achievable bearing of the invention is total to the seal structure layout structure schematic diagram that chamber and bearing exocoel are pressed；
Fig. 2 is the schematic three dimensional views of rear bearing block structure of the invention.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention more comprehensible, right hereinafter, referring to the drawings and the embodiments,
The present invention is further described.
In engine operation process, need that high-speed rotating two bearings are lubricated and are cooled down, in the process,
Heat of the lubricating oil with bearing running, and the impurity that friction generates, and part lubricating oil becomes mist of oil state, therefore fills in bearing bore
Expire liquid lubricating oil and lubricating oil mist of oil, scavenge oil line road is flowed by the oil return hole on rear bearing block, realizes the receipts of lubricating oil
Collection and oil return.Lubrication leakage in bearing bore in order to prevent needs to obturage it.Although the effect that contact is obturaged is most
Good, but it is constrained to current technical level, it can not be widely applied within the engine.Therefore widespread practice still right and wrong
Contact seal.By adjusting the pressure difference between control bearing cavity and exocoel, achieve the effect that obturage.Start in previous
In machine, one side engine be limited to engine structure design, cannot achieve the total chamber of bearing, although another aspect engine through
Structure design is crossed, two adjacent bearings are total cavity configuration, but during being obturaged to bearing bore, due to air system
Flow path of uniting is complicated, causes the pressure of two bearing exocoels unbalanced, and control difficulty is big, in order to ensure sealing effect, often
There are very big nargin, largely leak into bearing bore so that obturaging air, increase the flow of air system, while
The recovery difficult of lubricating oil is increased, it is very unfavorable for engine performance.
In order to solve this problem, improve bearing bore and obturage effect, the present invention provides a kind of achievable bearings to be total to chamber and axis
The novel seal structure that exocoel is pressed is held, as shown in Figure 1.
Achievable bearing of the invention is total to the novel seal structure that chamber and bearing exocoel are pressed, including rear bearing block 1, front axle
Seat 2 is held, 1 entirety of rear bearing block is cylindrical in shape structure, the whole disc-shaped structure of front-end bearing pedestal 2, and the counterface of the two passes through bolt
Mode is attached, and is facilitated the assembly of engine and the detachable maintaining in later period, is leaked in order to prevent, in rear bearing block 1 with before
Design has sealing structure 1003 on the counterface of bearing block 2, and seal groove is processed on bearing block, is carried out by O-shaped rubber ring
It obturages；It can also be attached using welding manner, two bearing blocks are structure as a whole at this time, and sealing effect is good, do not need to set
Count additional sealing structure.Designer should select according to actual needs.
3 be labyrinth seal；4 be fore bearing, using freely-supported support construction；5 be fore bearing clamp nut, and main function is
Fore bearing 4, high-pressure rotary component etc. are subjected to axial compression；7 be rear bearing, using cantilevered support structure；6 compress for rear bearing
Nut, main function are by 7 axial compression of rear bearing；8 be low-pressure turbine rotary shaft；Rear bearing 7 compresses spiral shell by rear bearing
Mother 6 is simultaneously fixed in low-pressure turbine rotary shaft 8 by the way of cantilever support, and fore bearing 4 passes through fore bearing clamp nut 5 and adopts
It is fixed in high-pressure turbine rotary shaft with the mode that freely-supported supports, low-pressure turbine rotary shaft 8 is coaxially set in hollow high pressure
In rotatable shaft.
By rear bearing block 1, front-end bearing pedestal 2, fore bearing 4, fore bearing clamp nut 5, rear bearing clamp nut 6, rear bearing
7, rotary shaft 8 surrounds the bearing bore 9 of two bearings jointly.Since two bearing blocks 1,2 are connected, and centre is set without other parts
Meter, it is achieved that the total chamber design of two bearings 4,7, while two bearings share a set of oil system.In bearing block inner wall
Upper design has double oil spout mouth structures 1002, can carry out oil spout to two bearings 4,7 simultaneously.The spray angle of lubricating oil can pass through
The atomizer angle for adjusting double oil spout mouth structures 1002 is adjusted, and the size of oil flow can be by adjusting double atomizer knots
The oil spout pore size of structure 1002 is adjusted, and is designed using the structure of the bis- atomizer one of this bearing block-, it is possible to reduce part
Number, while improving fuel feeding reliability.In addition, impurity enters bearing in order to prevent, it can be exported in atomizer and increase filter structure.
10 be before obturage ring, by preceding obturaging ring 10, labyrinth seal ring 3 and front-end bearing pedestal 2, collectively constitute outside fore bearing
Chamber 18；11 be high-pressure turbine disk；12 be bolt, and two bearing blocks 1,2 are connected by the bolt 12；13 be supporting plate casing, 14
Rear bearing block 1 is connected with supporting plate casing 13 by the bolt 14 for bolt；15 be after obturage ring, obturaged after ring 15, after
Bearing block 1, rotary shaft 8 collectively constitute rear bearing exocoel 19；16 be oil pipe, the cunning being threadably secured on rear bearing block 1
In oil pipe mounting base 1001.High pressure lubricating oil is leaked from lubricating oil pipe mounting seat 1001 in order to prevent, in oil pipe 16 and oil pipe
Design has graphite seal ring 17 between mounting base 1001, can be effectively prevented lubrication leakage.
Pressure in fore bearing exocoel 18 and rear bearing exocoel 19 is higher than the pressure in bearing bore 9, in order to reduce bearing envelope
Effect is obturaged in the design difficulty of tight component, raising, and design has vent hole structure 2001 on front-end bearing pedestal 2, on rear bearing block 1
Design has vent hole structure 1004, angular position, shape and the complete phase of size of the vent hole structure on two bearing blocks 1,2
Together, it corresponds, forms the channel of two bearing exocoels 18,19 of connection.Simultaneously when designing vent hole structure, it shall be noted that keep away
Allow lube pipe.This design can greatly shorten the flow path of air system between two bearing exocoels, simplify air system knot
Structure realizes that the pressure of two bearing exocoels 18,19 is balanced.Thus the flow path of air system as illustrated by the arrows in fig. 1, comes from sky
The air-flow of gas system upstream enters turbine chamber 20 by the airflow channel on high-pressure turbine disk 11.There are two go out for the turbine chamber 20
Mouthful, respectively the castor tooth on high-pressure turbine disk 11 with before obturage ring 10 composition castor toothing 1101 and labyrinth seal ring 3 on
Castor tooth with before obturage ring 10 composition castor toothing 3002, by adjust two castor toothings castor backlash, can distinguish
Control enters the assignment of traffic of two outlets.Enter fore bearing exocoel 18 by the air-flow of castor toothing 3002, is sealed by castor tooth
Tight structure 3001, completion are obturaged to what is exported before bearing bore 9；Most of air-flow in the fore bearing exocoel 18 passes through on bearing block
Through-hole 2001 and 1004, into rear bearing exocoel 19.The air-flow in venthole is from the abutting end between part in order to prevent
Face leakage, the pressure influenced in bearing exocoel are established, and design has O-ring seal close on the counterface of two bearing blocks 1,2
Seal structure 1003.
Air-flow in rear bearing exocoel 19, the castor tooth that a part passes through castor tooth and the formation of rear bearing block 1 in rotary shaft 8
Seal structure 8001 obturages the rear outlet of bearing bore 9, and another part is downstream flowed by the continuation of castor toothing 8002
It is dynamic.Since two bearing exocoels 18,19 are connected to, by castor toothing as inlet and outlet, and the same bearing bore is carried out
It obturages, therefore is very easy to establish stable pressure difference, it is ensured that obturage effect.
In order to which more clearly the structure of expression rear bearing block 1, Fig. 2 are the three dimensional structure diagram of rear bearing block.In figure
1001 be lubricating oil pipe mounting seat, and 1002 be double fuel nozzle structures, and 1003 be O-shaped rubber ring seal groove, and 1004 be venthole.
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 (7)
1. a kind of achievable bearing is total to the seal structure that chamber and bearing exocoel are pressed, including rear bearing block and front-end bearing pedestal, described
Rear bearing is set in rear bearing block, fore bearing is set in the front-end bearing pedestal, the rear bearing is fixed by cantilever support mode
In low-pressure turbine rotary shaft, the fore bearing is fixed in high-pressure turbine rotary shaft by freely-supported supporting way, the low pressure
Rotatable shaft is coaxially set in hollow high-pressure turbine rotary shaft, which is characterized in that
The rear bearing block is integrally cylindrical in shape structure, the whole disc-shaped structure of the front-end bearing pedestal, the ring-type of the rear bearing block
The mode that preceding counterface is bolted or welds with counterface after the plate-like of the front-end bearing pedestal links together,
Surround the axis of two bearings jointly by the rear bearing block, front-end bearing pedestal, fore bearing, rear bearing, part low-pressure turbine rotary shaft
Hold chamber；
Front end face by obturaging ring, preceding labyrinth seal ring and front-end bearing pedestal before being arranged on rear side of high-pressure turbine disk collectively constitutes
Fore bearing exocoel is rotated by obturaging ring, the rear end face of rear bearing block, part low-pressure turbine after being arranged on front side of low-pressure turbine disk
Axis collectively constitutes rear bearing exocoel；
Circumferentially arranged with several vent hole structures on the front-end bearing pedestal, circumferentially arranged with several logical on the rear bearing block
Air hole structure, angular position, shape and the size of the vent hole structure on two bearing blocks are adapted, and are corresponded, shape
At the channel of the fore bearing exocoel and rear bearing exocoel is connected to, to realize that the pressure of former and later two bearing exocoels is balanced.
2. seal structure according to claim 1, which is characterized in that former and later two adjacent bearings, one of them is
Freely-supported support construction, another is cantilevered support structure, so that two bearing spaces are close, the bearing block of two bearings uses spiral shell
Bolt or the mode of welding connect together, so that two bearings realize chamber altogether, when being attached using bolt, adjacent
Design has seal groove between part counterface, is obturaged using O-shaped rubber ring.
3. seal structure according to claim 2, which is characterized in that former and later two described bearings share a set of lubricating oil and supply
Oil return system is equipped with double oil spout mouth structures on the outer wall of the rear bearing block, realizes the common oil spout of latter two bearing forward.
4. seal structure according to claim 3, which is characterized in that two atomizers of double oil spout mouth structures
Spray angle and nozzle opening size are individually adjusted design.
5. seal structure according to claim 4, which is characterized in that be equipped with filter structure in the outlet of atomizer, mention
The cleannes of high lubricating oil.
6. seal structure according to claim 3, which is characterized in that oil system passes through screw thread for oil return oil pipe
It is fixed in the lubricating oil pipe mounting seat of the rear bearing block, graphite seal ring knot is equipped between oil pipe and lubricating oil pipe mounting seat
Structure.
7. seal structure according to claim 1, which is characterized in that the rear bearing block and front-end bearing pedestal are added using mechanical
Work or casting combine the mode of machining to be produced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710706924.7A CN107269396B (en) | 2017-08-17 | 2017-08-17 | A kind of achievable bearing is total to the seal structure that chamber and bearing exocoel are pressed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710706924.7A CN107269396B (en) | 2017-08-17 | 2017-08-17 | A kind of achievable bearing is total to the seal structure that chamber and bearing exocoel are pressed |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107269396A CN107269396A (en) | 2017-10-20 |
| CN107269396B true CN107269396B (en) | 2019-02-15 |
Family
ID=60080420
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710706924.7A Active CN107269396B (en) | 2017-08-17 | 2017-08-17 | A kind of achievable bearing is total to the seal structure that chamber and bearing exocoel are pressed |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107269396B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109707515B (en) * | 2018-12-04 | 2020-04-21 | 中国科学院工程热物理研究所 | Impeller type wheel disc structure for gas turbine lubricating oil way system |
| CN110056430B (en) * | 2019-04-24 | 2020-04-07 | 中国航发湖南动力机械研究所 | Bearing common-cavity lubricating and shaft-to-shaft sealing device and birotor aero-engine |
| CN110500141B (en) * | 2019-07-31 | 2021-11-30 | 中国航发南方工业有限公司 | Sealing and ventilating structure |
| CN111764969B (en) * | 2020-07-27 | 2022-08-30 | 中国航发沈阳发动机研究所 | Aeroengine sealing structure |
| CN113309616B (en) * | 2021-05-27 | 2022-09-16 | 中国航发南方工业有限公司 | Sealing structure for bearing of compressor |
| CN114542205B (en) * | 2022-02-11 | 2022-11-22 | 中国航发沈阳发动机研究所 | High-temperature-resistant and high-pressure-resistant bearing cavity structure of high-mach aircraft engine |
| CN114593155B (en) * | 2022-03-18 | 2023-06-23 | 中国科学院工程热物理研究所 | Variable-rigidity aeroengine dynamic pressure bearing mounting structure |
| CN114738120B (en) * | 2022-04-18 | 2024-01-30 | 中国航发沈阳发动机研究所 | Aeroengine bearing cavity sealing air-entraining structure |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1270959A (en) * | 1968-09-27 | 1972-04-19 | Bennes Marrel | Means for cooling or regulating the temperature of a gas turbine engine |
| DE102009054007A1 (en) * | 2009-11-19 | 2011-05-26 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine i.e. flight gas turbine, for engine of e.g. jet, has circular seal element including outer ring at axial side and thread at opposite axial side, where thread of circular seal element is screwed on thread of high pressure shaft |
| CN104847500A (en) * | 2015-04-30 | 2015-08-19 | 中国科学院工程热物理研究所 | Lubricating oil passage system, bearing co-chamber structure and gas turbine engine |
| CN204878738U (en) * | 2015-06-18 | 2015-12-16 | 中国南方航空工业(集团)有限公司 | Structure of obturaging |
| CN105386794A (en) * | 2015-12-10 | 2016-03-09 | 西安航天动力研究所 | Turbine disc rigidity self-reinforcement turbine structure |
| CN105387210A (en) * | 2015-12-12 | 2016-03-09 | 中国南方航空工业(集团)有限公司 | Lubricating oil sealing structure |
| CN106948873A (en) * | 2017-04-07 | 2017-07-14 | 中国航发沈阳发动机研究所 | Seal structure between stators part |
-
2017
- 2017-08-17 CN CN201710706924.7A patent/CN107269396B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1270959A (en) * | 1968-09-27 | 1972-04-19 | Bennes Marrel | Means for cooling or regulating the temperature of a gas turbine engine |
| DE102009054007A1 (en) * | 2009-11-19 | 2011-05-26 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine i.e. flight gas turbine, for engine of e.g. jet, has circular seal element including outer ring at axial side and thread at opposite axial side, where thread of circular seal element is screwed on thread of high pressure shaft |
| CN104847500A (en) * | 2015-04-30 | 2015-08-19 | 中国科学院工程热物理研究所 | Lubricating oil passage system, bearing co-chamber structure and gas turbine engine |
| CN204878738U (en) * | 2015-06-18 | 2015-12-16 | 中国南方航空工业(集团)有限公司 | Structure of obturaging |
| CN105386794A (en) * | 2015-12-10 | 2016-03-09 | 西安航天动力研究所 | Turbine disc rigidity self-reinforcement turbine structure |
| CN105387210A (en) * | 2015-12-12 | 2016-03-09 | 中国南方航空工业(集团)有限公司 | Lubricating oil sealing structure |
| CN106948873A (en) * | 2017-04-07 | 2017-07-14 | 中国航发沈阳发动机研究所 | Seal structure between stators part |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107269396A (en) | 2017-10-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107269396B (en) | A kind of achievable bearing is total to the seal structure that chamber and bearing exocoel are pressed | |
| CN106150699B (en) | Fuel nozzle, gas turbine and the method for gas turbine middle (center) bearing fuel feeding | |
| CN101036007B (en) | Transmission arrangement | |
| US20190186297A1 (en) | Fan drive gear system manifold radial tube filters | |
| CN107044480A (en) | Bearing with drainage loop and press-filming damping device | |
| CN105465371A (en) | Bidirectional-rotation self-pumping fluid dynamic pressure type mechanical seal | |
| WO2020100251A1 (en) | Centrifugal compressor and turbocharger equipped with centrifugal compressor | |
| CN107893765A (en) | A kind of single screw rod water-lubricated compressor | |
| CN105042085A (en) | Low-speed box penetrating shaft gas sealing device for high-low temperature box | |
| CN102852798A (en) | Roots vacuum pump cooling system | |
| CN112253776A (en) | Valve with filtering function | |
| CN106678186A (en) | Bidirectional thrust bearing | |
| CN106678187A (en) | Bearing | |
| CN108457865B (en) | High temperature resistant pump and cooling structure thereof | |
| KR101382309B1 (en) | Bearing of turbo-charger | |
| CN104929779A (en) | Turbine disk connecting structure and gas turbine engine with same | |
| CN110513484A (en) | A kind of combined type pass damping seal with flanging damping type hole | |
| CN109372792A (en) | Horizontal pump is lubricated from medium | |
| CN206647433U (en) | A kind of bearing | |
| CN209354420U (en) | Horizontal pump is lubricated from medium | |
| CN106763238A (en) | A kind of hydrogenerator with efficient oil cooling bearing | |
| CN203783874U (en) | Radial plunger pump | |
| CN109854629A (en) | A kind of heat-proof device of Micro Turbine Jet Engine bearing | |
| CN211117608U (en) | Combined hole type damping seal with edgefold damping holes | |
| CN208845370U (en) | A kind of centrifugal pump with water-cooled pump cover and sealing gland |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | 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 |