CN108223429A - The fancase of the domain not fault wall - Google Patents
The fancase of the domain not fault wall Download PDFInfo
- Publication number
- CN108223429A CN108223429A CN201710924299.3A CN201710924299A CN108223429A CN 108223429 A CN108223429 A CN 108223429A CN 201710924299 A CN201710924299 A CN 201710924299A CN 108223429 A CN108223429 A CN 108223429A
- Authority
- CN
- China
- Prior art keywords
- blade
- stator blade
- outer shroud
- stator
- fancase
- 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
Classifications
-
- 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
- F04D29/263—Rotors specially for elastic fluids mounting fan or blower rotors on shafts
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- 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
- F04D29/002—Details, component parts, or accessories especially adapted for elastic fluid pumps
-
- 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
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/663—Sound attenuation
-
- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to aircraft casing technical fields, specifically provide the fancase of the domain not fault wall, stator blade is the structure type with installation side, supramarginal plate and blade, supramarginal plate is arranged on blade leading edge, casing interface is determined by stator blade installation side, realize that assembled safeguards seat, test bench on Vehicle Processing casing, sets shock-reducing rubber between stator blade and casing.
Description
Technical field
The present invention relates to aircraft casing technical field, the more particularly to fancase of the domain not fault wall.
Background technology
Fan propeller sub-assembly is the important component of aero-engine and gas turbine.For loss of weight, balance quality is improved, is turned
Full grade blisk scheme can be used in minor structure.It is the seam allowance matching allowance of guarantee rotor structure and dynamic balancing as a result, in skill
It needs to avoid assembly and disassembly disk body as possible in art state-maintenance, corresponding fancase need to use split form, ensure maintainability.
When fancase is Split Casing, can to avoid rotor structure decomposition, preserve dynamic balancing as a result, but machine can be weakened
Casket rigid circumference.It is proved through using, even if increasing casing wall thickness, increasing reinforcing rib, Split Casing still can be oval, causes：
1st, the angular casing matrix in part has touches mill risk with blade tip；
2nd, the angular casing matrix in part and tip clearance are excessive, influence aeroperformance, reduce fan aerodynamic stability；
3rd, it is horizontally mounted at side there are gas leakage situation, influences aeroperformance；
4th, aircraft is more demanding to the exterior contour of fancase, outer through passing through fan due to being horizontally mounted the presence on side
The problem of exterior contour that portion's pipeline faces transfinites；
5th, after fancase uses split scheme, entire stator structure (including fancase, stator blade and connector)
Weight can increase, and eventually lead to entire fan part loss of weight unobvious.
Invention content
To overcome above-mentioned at least one defect of the existing technology, the present invention provides the fan machines of the domain not fault wall
Casket including outer shroud, rotor blade, stator blade, inner ring and safeguards seat；
The rotor blade is blisk, and outside is mutually fixed with the outer shroud；
The stator blade and the rotor blade are alternately arranged in an axial direction, and the stator blade includes installation side, upper limb
Plate and blade, the installation side are arranged on the leading edge of the stator blade, and the interface between the outer shroud is according to the stator
The installation side location determination of blade, the stator blade outside are installed side by it and are mutually fixed with the outer shroud, and pass through its peace
Seam allowance on rim is felt relieved, and is mutually fixed with the inner ring on the inside of the stator blade, described quiet in non-pipes' analysis
The blade of blades has chamfering；
When the blade quantity A of the stator blade is odd number, the side of the stator blade axial direction includes B blade,
Opposite side includes A-B blade, and wherein B is the maximum integer less than A/2, when A is even number, the two of the stator blade axial direction
Side includes A/2 blade；
Described to safeguard that seat is fixed on by fastener on the outside of the outer shroud, the stator leaf is sunk in one end of the fastener
Inside the supramarginal plate of piece.
Preferably, it is coated with shock-reducing rubber between the supramarginal plate of each outer shroud and the stator blade positioned at the outer shroud front end.
Preferably, it is mutually fixed by welding manner with outer shroud positioned at the stator blade of runner tail end, positioned at runner tail end
Inner ring is domain inner ring.
The fancase of the domain provided by the invention not fault wall, has the advantages that：
1st, ensure under full grade blisk scheme, be not only avoided that the decomposition of rotor structure, preserved dynamic balancing as a result, but also can
Ensure that fancase uses domain scheme.
2nd, compared to opposite opened casing and traditional welding formula casing, when needing special vane, which can ensure
Measurement scheme measurement accuracy higher, aerodynamics influence smaller, repacking cost smaller, repacking period are shorter；
3rd, the program is adaptable to safeguarding seat and test bench, avoids conventionally employed Milling Machining boss or welded bands
Come process-cycle, welding stress the problems such as；
4th, the program allows the damping property of increase outer shroud but will not accelerate shock-reducing rubber due to oil leak, corrosion etc.
Aging does not influence aeroperformance；
5th, it is welded to connect since subseries casing and blade eliminate, the material of casing and fan-shaped stator blade can not
It is identical, consider loss of weight, vibration damping, the demands such as stealthy, noise reduction, can be used the composite material of specific function, aluminum alloy materials part or
Replacing whole titanium alloy material.
Description of the drawings
It is exemplary below with reference to the embodiment of attached drawing description, it is intended to for the explanation and illustration present invention, and cannot manage
It solves as the limitation to protection scope of the present invention.
Fig. 1 is a kind of front view of illustrative examples of the present invention；
Fig. 2 is the assembling schematic diagram for safeguarding seat in a kind of illustrative examples of the present invention.
Reference numeral：
10 outer shrouds
20 rotor blades
30 stator blades
40 inner ring
50 safeguard seat
60 fasteners
70 shock-reducing rubbers
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.
It should be noted that：In the accompanying drawings, from beginning to end same or similar label represent same or similar element or
Element with same or like function.Described embodiment is the implementation of part of the embodiment of the present invention rather than whole
Example, in the absence of conflict, the feature in embodiment and embodiment in the application can be combined with each other.Based in the present invention
Embodiment, those of ordinary skill in the art's all other embodiments obtained without creative efforts,
It shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description rather than instruction or imply meaning
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention be protected
Protect the limitation of range.
Herein, " schematic " expression " serving as example, example or explanation " should not will be described herein as " showing
Any diagram, the embodiment of meaning property " are construed to a kind of preferred or more advantageous technical solution.
As shown in Figure 1, the fancase of the domain provided by the invention not fault wall, including outer shroud 10, rotor blade 20, stator
Blade 30, inner ring 40 and safeguard seat 50.
Rotor blade 20 is blisk, and outside is fixed with 10 phase of outer shroud.
Stator blade 30 and rotor blade 20 are alternately arranged in an axial direction, and stator blade 30 includes installation side, supramarginal plate and leaf
Body, installation side are arranged on the leading edge of stator blade 30, and the interface between outer shroud 10 is according to the installation side position of stator blade 30
It determining, 30 outside of stator blade is installed side by it and is fixed with 10 phase of outer shroud, and installs the seam allowance on side by it and feel relieved,
30 inside of stator blade is fixed with 40 phase of inner ring, and in the present embodiment, stator blade 30 and outer shroud 10 positioned at runner tail end pass through
Welding manner is mutually fixed, and the inner ring 40 positioned at runner tail end is domain inner ring, and each outer shroud 10 and positioned at 10 front end of outer shroud
Stator blade 30 supramarginal plate between be coated with shock-reducing rubber 70.The blade of stator blade 30 in non-pipes' analysis has
Angle.
When the blade quantity A of stator blade 30 is odd number, the axial side of stator blade 30 includes B blade, another
Side includes A-B blade, and wherein B is the maximum integer less than A/2, when A is even number, the axial both sides Jun Bao of stator blade 30
Containing A/2 blade.
As shown in Fig. 2, safeguarding that seat 50 is fixed on 10 outside of outer shroud by fastener 60, stator is sunk in one end of fastener 60
It, can be to avoid the flow field in the presence and influence pipes' analysis of threaded hole inside the supramarginal plate of blade 30.
As shown in Figure 1, during assembling, three-level rotor blade 20 is connected first, and outer shroud 10 is promoted from rear side；
After level-one stator blade 30 and level-one inner ring 40 are assembled, using turning gap between stator, from upper and lower sides assembling, solid
It is fixed, the level-one outer shroud 10 of shock-reducing rubber 70 has then been coated from rear side propulsion again, has been screwed into fastener 60, seat 50 is safeguarded in assembling；Two level
After stator blade 30 and two level inner ring 40 are assembled, using turning gap between stator, from upper and lower sides assembling, fixed, finally from rear side
Two level outer shroud 10 is promoted, is screwed into fastener 60, seat 50 is safeguarded in assembling；Finally from rear side assembling three-level stator blade 30.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all should by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (3)
1. the fancase of the domain not fault wall, it is characterised in that：Including outer shroud (10), rotor blade (20), stator blade (30),
Inner ring (40) and safeguard seat (50)；
The rotor blade (20) is blisk, and outside is mutually fixed with the outer shroud (10)；
The stator blade (30) and the rotor blade (20) are alternately arranged in an axial direction, and the stator blade (30) includes installation
Side, supramarginal plate and blade, the installation side are arranged on the leading edges of the stator blade (30), the boundary between the outer shroud (10)
Face according to the installation side location determination of the stator blade (30), on the outside of the stator blade (30) by its install side with it is described
Outer shroud (10) is mutually fixed, and is installed the seam allowance on side by it and felt relieved, stator blade (30) inside and the inner ring
(40) it mutually fixes, the blade of the stator blade (30) in non-pipes' analysis has chamfering；
When the blade quantity A of the stator blade (30) is odd number, the side of stator blade (30) axial direction includes B leaf
Body, opposite side include A-B blade, and wherein B is the maximum integer less than A/2, when A is even number, the stator blade (30)
Axial both sides include A/2 blade；
Described to safeguard that seat (50) is fixed on by fastener (60) on the outside of the outer shroud (10), one end of the fastener (60) sinks
Inside the supramarginal plate for entering the stator blade (30).
2. the fancase of the domain according to claim 1 not fault wall, it is characterised in that：Each outer shroud (10) and positioned at this
Shock-reducing rubber (70) is coated between the supramarginal plate of the stator blade (30) of outer shroud (10) front end.
3. the fancase of the domain according to claim 1 not fault wall, it is characterised in that：Positioned at the stator leaf of runner tail end
Piece (30) is mutually fixed with outer shroud (10) by welding manner, and the inner ring (40) positioned at runner tail end is domain inner ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710924299.3A CN108223429B (en) | 2017-09-30 | 2017-09-30 | Whole ring fan casing without breaking disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710924299.3A CN108223429B (en) | 2017-09-30 | 2017-09-30 | Whole ring fan casing without breaking disc |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108223429A true CN108223429A (en) | 2018-06-29 |
| CN108223429B CN108223429B (en) | 2021-03-30 |
Family
ID=62655425
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710924299.3A Active CN108223429B (en) | 2017-09-30 | 2017-09-30 | Whole ring fan casing without breaking disc |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108223429B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111664124A (en) * | 2020-06-05 | 2020-09-15 | 中国航发沈阳发动机研究所 | Stator structure, rotor and stator assembly structure with same and assembly method of rotor and stator assembly structure |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3823553A (en) * | 1972-12-26 | 1974-07-16 | Gen Electric | Gas turbine with removable self contained power turbine module |
| US4037473A (en) * | 1971-09-16 | 1977-07-26 | International Harvester Company | Radiation pyrometers with purging fluid |
| CN102091757A (en) * | 2010-12-30 | 2011-06-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Integral precision casting method for large thin-wall casing part |
| CN203051237U (en) * | 2013-01-15 | 2013-07-10 | 哈尔滨东安发动机（集团）有限公司 | Surge-preventing structure for aero-engine compressor |
| CN203548348U (en) * | 2013-09-27 | 2014-04-16 | 沈阳黎明航空发动机(集团)有限责任公司 | Low-pressure compressor structure for aircraft-derived gas turbine |
| CN106939832A (en) * | 2017-04-27 | 2017-07-11 | 中国科学院工程热物理研究所 | A kind of axle wander about as a refugee the heart blisk formula combination compressibility |
| CN107061314A (en) * | 2017-03-28 | 2017-08-18 | 沈阳冠能燃气轮机科技有限公司 | The low-pressure compressor changed a social system using retired engine |
-
2017
- 2017-09-30 CN CN201710924299.3A patent/CN108223429B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4037473A (en) * | 1971-09-16 | 1977-07-26 | International Harvester Company | Radiation pyrometers with purging fluid |
| US3823553A (en) * | 1972-12-26 | 1974-07-16 | Gen Electric | Gas turbine with removable self contained power turbine module |
| CN102091757A (en) * | 2010-12-30 | 2011-06-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Integral precision casting method for large thin-wall casing part |
| CN203051237U (en) * | 2013-01-15 | 2013-07-10 | 哈尔滨东安发动机（集团）有限公司 | Surge-preventing structure for aero-engine compressor |
| CN203548348U (en) * | 2013-09-27 | 2014-04-16 | 沈阳黎明航空发动机(集团)有限责任公司 | Low-pressure compressor structure for aircraft-derived gas turbine |
| CN107061314A (en) * | 2017-03-28 | 2017-08-18 | 沈阳冠能燃气轮机科技有限公司 | The low-pressure compressor changed a social system using retired engine |
| CN106939832A (en) * | 2017-04-27 | 2017-07-11 | 中国科学院工程热物理研究所 | A kind of axle wander about as a refugee the heart blisk formula combination compressibility |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111664124A (en) * | 2020-06-05 | 2020-09-15 | 中国航发沈阳发动机研究所 | Stator structure, rotor and stator assembly structure with same and assembly method of rotor and stator assembly structure |
| CN111664124B (en) * | 2020-06-05 | 2022-07-26 | 中国航发沈阳发动机研究所 | Stator structure, rotor and stator assembly structure with same and assembly method of rotor and stator assembly structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108223429B (en) | 2021-03-30 |
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