CN107642504A - The fancase of Screw assembly - Google Patents
The fancase of Screw assembly Download PDFInfo
- Publication number
- CN107642504A CN107642504A CN201710924192.9A CN201710924192A CN107642504A CN 107642504 A CN107642504 A CN 107642504A CN 201710924192 A CN201710924192 A CN 201710924192A CN 107642504 A CN107642504 A CN 107642504A
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- CN
- China
- Prior art keywords
- outer shroud
- casing
- blade
- fancase
- stator
- Prior art date
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Abstract
The present invention relates to aero-engine technology field, specifically provide the fancase of Screw assembly, the domain stator blade that the processing scheme of casing and the welding of each stator blade is adjusted to the outer shroud of band second is screwed into the scheme of the first outer shroud in a screw connection manner, remove welding, Technology for Heating Processing, solve casing deformation, the dislocation of stator blade blade, turn the small initiation of stator axial gap the problems such as wear-resistant coating axial length is insufficient, big listrium small casing surplus, enhance casing antivibration kinetic force.
Description
Technical field
The present invention relates to the fancase of aero-engine technology field, more particularly to Screw assembly.
Background technology
Domain casing typically uses welded type at present：Irregularly-shaped hole, irregularly-shaped hole and stator supramarginal plate are milled out on Thin-Wall Outer Casing
Small―gap suture is welded after coordinating with electron beam, and structure is simplified.
Following defect be present in traditional welding formula fancase：
1st, due to each stator blade supramarginal plate being respectively welded, weld seam is more, easily weldering be present not at stator supramarginal plate
Saturating or excessive stress situation, easy crack initiation；
2nd, in the presence of offseting, casing is whole for the actual angular, axial location of blade and theoretical position after stator blade welding, heat treatment
Body, which shrinks to exist with stream data, to be offset, and influences aerodynamic stability, and deviation post is without statistics rule；
3rd, when the rotor blade of stator blade and next stage is axially in small distance, because casing rear flange side will be in upper limb
Beyond plate weld stressed zone, the wear-resistant coating axial length under-reserve above next stage rotor blade, rotator tip mill be present
To the risk of fancase matrix, if ensureing wear-resistant coating axial length, flange is in upper limb plate welding seams risk distance, easily
Crack initiation；
4th, it is necessary to which larger stator supramarginal plate, can cause casing milling when stator blade denseness is big, blade and blade shape changes greatly
Go out that the irregularly-shaped hole Later Zhou Dynasty, one of the Five Dynasties is smaller to surplus, the situation of margin of safety deficiency；
5th, needed due to safeguarding, axial region increase need to safeguard seat where stator blade, during using welding scheme, safeguarded
Seat weld seam relatively closely even intersects with supramarginal plate welding seam distance, easy crack initiation, is needed using assembling scheme outside Milling Machining casing
Surface, influence batch production speed of production.
The content of the invention
To overcome at least one defect existing for above-mentioned prior art, the invention provides the fancase of Screw assembly,
Including：
First outer shroud, its one end vertically have outside first flange side, and the other end has outside second flange
Side, the side on the close first flange side of the first outer shroud inwall is provided with wear-resistant coating, and first outer shroud has
Stop ledge, the stop ledge are located at the side for being axially distant from the first flange side of the wear-resistant coating, and described
The side on the close second flange side of one outer shroud inwall is provided with T-shaped screw thread, and through hole is provided with first outer shroud；
The second outer shroud obtained by machining mode, its one end are engaged with the stop ledge, second outer shroud
Outside is provided with the T-shaped screw thread being engaged with first outer shroud, and second outer shroud is consolidated by T-shaped screw thread and first outer shroud
It is fixed, through hole is provided with second outer shroud, it is corresponding with the through hole of first outer shroud；
The blade obtained by machining mode, it is integrally formed with second outer shroud；
Seat is safeguarded, it is fixed on the outside of first outer shroud by fastener, the position for safeguarding seat and described first
The through hole of outer shroud is corresponding, and one end of the fastener is sunken in second outer shroud.
The fancase of Screw assembly provided by the invention, has the advantages that：
1st, the processing scheme of casing and the welding of each stator blade is adjusted to the domain stator spiral shell that machine adds threaded outer shroud
Line screws in the scheme of the first outer shroud, original machine is added, welded, is forged, Technology for Heating Processing is changed to pure machine and added, and weld seam quantity is by leaf
Piece number is kept to 0, avoid casing welding stress, add casing rigidity, reduce the equipment requirement to factory, without because
The long period that the processing of the special warfare such as welding, heat treatment, turnover are brought, shortens overall processing time and production cost, stator
Blade profile more meets design point；
2nd, casing deformation, the dislocation of stator blade blade are solved, turns the wear-resistant coating axial direction of the small initiation of stator axial gap
The problems such as curtailment, big listrium small casing surplus, reduce aerodynamic loss and touch the probability of mill matrix；
3rd, welding procedure is eliminated, casing welding stress is avoided, adds casing rigidity, due to cancelling welding procedure,
The material of first outer shroud and the second outer shroud can differ, and consider the demands such as loss of weight, vibration damping, stealthy, noise reduction, special work(can be used
Composite, the aluminum alloy materials of energy partly or entirely substitute titanium alloy material；
4th, compared to traditional welding formula casing, when needing special vane, the organization plan can ensure that measurement scheme measures
Accuracy is higher, aerodynamics influence is smaller, repacking cost is smaller, the repacking cycle is shorter；
5th, 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.
Brief description of the drawings
Embodiment below with reference to accompanying drawing description is exemplary, it is intended to for the explanation and illustration present invention, and can not be managed
Solve as the limitation to protection scope of the present invention.
Fig. 1 is a kind of elevation cross-sectional view of the fancase of illustrative examples of the present invention；
Fig. 2 is the elevational cross-sectional view for safeguarding seat in a kind of illustrative examples of the present invention.
Reference：
10 first outer shrouds
11 first flange sides
12 second flange sides
13 wear-resistant coatings
14 stop ledges
20 second outer shrouds
30 blades
40 safeguard seat
50 fasteners
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme 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 part of the embodiment of the present invention, rather than whole implementation
Example, in the case where not conflicting, the feature in embodiment and embodiment in the application can be mutually combined.Based in the present invention
Embodiment, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made,
Belong to the scope of protection of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of and describes the present invention and simplify description, rather than indicates 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 scope.
Herein, " schematic " expression " serving as example, example or explanation ", will should not be described herein as " showing
Any diagram, the embodiment of meaning property " are construed to a kind of preferred or more advantageous technical scheme.
Herein, " first ", " second " etc. are only used for mutual differentiation, rather than represent their significance level and order
Deng.
As shown in figure 1, the fancase of Screw assembly provided by the invention, including the first outer shroud 10, pass through machining side
The second outer shroud 20 that formula obtains, the blade 30 obtained by machining mode and safeguard seat 40.
The one end of first outer shroud 10 vertically has outside first flange side 11, and the other end has outside second flange
Side 12, the side on the close first flange side 11 of the inwall of the first outer shroud 10 is provided with wear-resistant coating 13, and the first outer shroud 10 has only
Dynamic boss 14, stop ledge 14 are located at the side for being axially distant from first flange side 11 of wear-resistant coating 13, in the first outer shroud 10
The side on the close second flange side 12 of wall is provided with T-shaped screw thread, and the region of T-shaped screw thread is the subregion of the second outer shroud 20, and
Not all region, through hole is provided with the first outer shroud 10.
The one end of second outer shroud 20 is engaged with stop ledge 14, and the outside of the second outer shroud 20 is provided with to be engaged with the first outer shroud 10
T-shaped screw thread, the second outer shroud 20 fixed by T-shaped screw thread and the first outer shroud 10, and through hole is provided with the second outer shroud 20, and it is with first
The through hole of outer shroud 10 is corresponding.
Blade 30 is integrally formed with the second outer shroud 20, and during assembling, the second outer shroud 20 is twisted from the place sidespin of second flange side 12
Enter the first outer shroud 10 and mutually fixed with it.
As shown in Fig. 2 safeguard that seat 40 is fixed on the outside of the first outer shroud 10 by fastener 50, the position of seat 40 and the is safeguarded
The through hole of one outer shroud 10 is corresponding, and one end of fastener 50 is sunken in the second outer shroud 20.When need carry out dynamic stress measurement or
In runner during stagnation temperature total pressure measurement, angularly the second outer shroud 20 can be carried out to add work cut-out that need to measure, increased in relevant position
The individual blade of specific function, positioned by the bolt of radial direction countersunk head form, ressemble what is be cut off after experiment
Blade.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can readily occur in, all should
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 (1)
1. the fancase of Screw assembly, it is characterised in that including：
First outer shroud (10), its one end vertically have outside first flange side (11), and the other end has outside second
Flange (12), the side of the close first flange side (11) of the first outer shroud (10) inwall are provided with wear-resistant coating
(13), and first outer shroud (10) has stop ledge (14), and the stop ledge (14) is located at the wear-resistant coating (13)
The side for being axially distant from the first flange side (11), the close second flange side of the first outer shroud (10) inwall
(12) side is provided with T-shaped screw thread, and through hole is provided with first outer shroud (10)；
The second outer shroud (20) obtained by machining mode, its one end are engaged with the stop ledge (14), and described second
The T-shaped screw thread being engaged with first outer shroud (10) is provided with the outside of outer shroud (20), second outer shroud (20) passes through T-shaped screw thread
It is fixed with first outer shroud (10), through hole is provided with second outer shroud (20), its through hole with first outer shroud (10)
It is corresponding；
The blade (30) obtained by machining mode, it is integrally formed with second outer shroud (20)；
Seat (40) is safeguarded, it is fixed on the outside of first outer shroud (10) by fastener (50), the position for safeguarding seat (40)
Put corresponding with the through hole of first outer shroud (10), one end of the fastener (50) is sunken in second outer shroud (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710924192.9A CN107642504B (en) | 2017-09-30 | 2017-09-30 | The fancase of Screw assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710924192.9A CN107642504B (en) | 2017-09-30 | 2017-09-30 | The fancase of Screw assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107642504A true CN107642504A (en) | 2018-01-30 |
| CN107642504B CN107642504B (en) | 2019-08-23 |
Family
ID=61123229
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710924192.9A Active CN107642504B (en) | 2017-09-30 | 2017-09-30 | The fancase of Screw assembly |
Country Status (1)
| Country | Link |
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| CN (1) | CN107642504B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3827680A1 (en) * | 1988-08-16 | 1990-02-22 | Mtu Muenchen Gmbh | Device for fixing a guiding grate, made of titanium, of an axial-flow compressor to a compressor housing made of a fibre-reinforced plastic |
| GB0210042D0 (en) * | 2002-05-02 | 2002-06-12 | Rolls Royce Plc | Casing section |
| US20020197157A1 (en) * | 2001-06-20 | 2002-12-26 | Dodd Alec G. | Tandem guide vanes |
| CN101497976A (en) * | 2007-12-27 | 2009-08-05 | 太空技术航空公司 | Method for manufacturing a turbomachine element and resulting device |
| CN104213947A (en) * | 2013-06-03 | 2014-12-17 | 航空技术空间股份有限公司 | Composite casing for axial turbomachine compressor with metal flange |
| CN104334855B (en) * | 2012-06-21 | 2016-12-14 | 川崎重工业株式会社 | The fan guard of aircraft engine |
-
2017
- 2017-09-30 CN CN201710924192.9A patent/CN107642504B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3827680A1 (en) * | 1988-08-16 | 1990-02-22 | Mtu Muenchen Gmbh | Device for fixing a guiding grate, made of titanium, of an axial-flow compressor to a compressor housing made of a fibre-reinforced plastic |
| US20020197157A1 (en) * | 2001-06-20 | 2002-12-26 | Dodd Alec G. | Tandem guide vanes |
| GB0210042D0 (en) * | 2002-05-02 | 2002-06-12 | Rolls Royce Plc | Casing section |
| CN101497976A (en) * | 2007-12-27 | 2009-08-05 | 太空技术航空公司 | Method for manufacturing a turbomachine element and resulting device |
| CN104334855B (en) * | 2012-06-21 | 2016-12-14 | 川崎重工业株式会社 | The fan guard of aircraft engine |
| CN104213947A (en) * | 2013-06-03 | 2014-12-17 | 航空技术空间股份有限公司 | Composite casing for axial turbomachine compressor with metal flange |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107642504B (en) | 2019-08-23 |
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