CN109372638A - A kind of connection structure of aero-engine and accessory drive gearbox - Google Patents
A kind of connection structure of aero-engine and accessory drive gearbox Download PDFInfo
- Publication number
- CN109372638A CN109372638A CN201811538363.5A CN201811538363A CN109372638A CN 109372638 A CN109372638 A CN 109372638A CN 201811538363 A CN201811538363 A CN 201811538363A CN 109372638 A CN109372638 A CN 109372638A
- Authority
- CN
- China
- Prior art keywords
- engine
- accessory drive
- drive gearbox
- aero
- tie point
- 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.)
- Pending
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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
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
Abstract
The application belongs to Aeroengine Design technical field, and in particular to a kind of connection structure of aero-engine and accessory drive gearbox.Tie point at connection structure setting three provided by the present application, at triangle between tie point at three, triangular connection structure can guarantee that accessory drive gearbox is opposite with engine stable, and, two of them tie point is fixedly connected by pin shaft, and third is by assisting supporting plate to be fixedly connected；This connection type can either make the relative motion space for having certain between aero-engine and accessory drive gearbox, play the role of position compensation, and can guarantee stable connection, mitigate the inordinate wear of drive rod spline.
Description
Technical field
The application belongs to Aeroengine Design technical field, and in particular to a kind of company of aero-engine and accessory drive gearbox
Binding structure.
Background technique
The accessory drive gearbox of aero-engine is for installing engine accessory power rating and being allowed to obtain power from engine spindle
Device, accessory drive gearbox are typically mounted at the outside of engine.In general, accessory drive gearbox multi-pass crosses being hinged to be installed to and starting for both ends
On machine, but in certain h type engine h design process, due to by engine, aircraft structure size and installation space limited, casing
The contour dimensions such as width are smaller, shorter with the installation seam allowance of phase mate in the middle part of accessory drive gearbox, are completely new accessory drive gearboxes, former
There is mounting structure to cannot be guaranteed that installation is stablized.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
The purpose of the application is to provide the connection structure of a kind of aero-engine and accessory drive gearbox, to solve novel attachment machine
The firm problem of casket installation.Connection structure tie point at aero-engine and accessory drive gearbox setting three, and connected at three
At triangle between point, aero-engine and the accessory drive gearbox tie point at three pass through the first connecting elements, the second connection structure
Part is connected together with third connecting elements, can guarantee that accessory drive gearbox is firm.
The technical solution of the application is:
The first tie point, the second tie point and third tie point is arranged in the connection structure, at described three between tie point at
Triangle, the third tie point are located at installation seam allowance edge；
First connecting elements, first connecting elements are mounted on first tie point, and the first connecting elements includes upper
Shackle assembly and lower Shackle assembly, the first end of upper Shackle assembly are connect with accessory drive gearbox, are set in the second end of upper Shackle assembly
It is equipped with fixation hole；The first end of lower Shackle assembly is connect with aero-engine installation side, is arranged in the second end of lower Shackle assembly
There is a fixation hole, the fixation hole of the second end of the fixation hole of the second end of upper Shackle assembly and lower Shackle assembly passes through the fixed company of pin shaft
It connects, connection structure second connecting elements of tie point at second is identical as above-mentioned first connecting elements structure.Pin shaft connection
Mode enables to relatively stable between engine and accessory drive gearbox, while guaranteeing to generate between the two certain opposite
Movement, plays the role of position compensation
When installation, the first end of the upper Shackle assembly of the first connecting elements and the accessory drive gearbox are connected by bolt first
It connects；Secondly the first end of the lower Shackle assembly of the first connecting elements and aero-engine installation side are bolted；
Finally the second end of upper Shackle assembly is connected with the second end of lower Shackle assembly by pin shaft.
Optionally, the third connecting elements includes auxiliary supporting plate, and the first end of the auxiliary supporting plate passes through screw and institute
The auxiliary installation side connection of aero-engine Middle casing is stated, the second end of the auxiliary supporting plate passes through screw and the accessory drive gearbox
Auxiliary installation side connection.
At least there are following advantageous effects in the application:
Connection structure provided by the present application can be applied to compact-sized, the lesser accessory drive gearbox of contour dimension and engine
Between connection, reduce the relative motion between engine and each engine accessory power rating and accessory drive gearbox, reduce engine abnormity vibration
A possibility that dynamic, realizes steady running of the engine under complex work situation.
Detailed description of the invention
Fig. 1 is the attachment structure schematic diagram of the aero-engine that application provides and accessory drive gearbox；
Fig. 2 is the link position schematic diagram of the aero-engine that application provides and accessory drive gearbox
Fig. 3 is connection structure each section label figure of the aero-engine that application provides and accessory drive gearbox.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 to Fig. 2 the application is described in further details with reference to the accompanying drawing.
As shown in figures 1 and 3, the connection structure of a kind of aero-engine and accessory drive gearbox provided by the present application, using three
The mode of place's connection realizes the installation of accessory drive gearbox on the engine, the connection structure of tie point formation triangle at three, three
Angular to have stable enabling capabilities, tie point mutually assists at three, is also able to maintain original state under the effect of larger power.
Tie point passes through the first connecting elements 1, the second connecting elements 2 and the connection boat of third connecting elements 3 respectively at three
Empty engine and accessory drive gearbox.
As shown in Figure 2, tie point passes through the first connecting elements 1 connection aero-engine and accessory drive gearbox at first,
The first end of the lower Shackle assembly 4 of first connecting elements 1 is installed side 7 with the aero-engine by bolt and is connect, institute
It states and is provided with fixation hole in the second end of lower Shackle assembly 4；The first end of Shackle assembly 5 passes through on first connecting elements 1
Bolt is connect with the accessory drive gearbox, is provided with fixation hole in the second end of the upper Shackle assembly 5；The lower Shackle assembly 4
The fixation hole of second end and the fixation hole of the second end of the upper Shackle assembly 5 be fixed together again by pin shaft, from
And complete the connection of the first tie point.
Tie point connects aero-engine and accessory drive gearbox, second connection by the second connecting elements 2 at second
Component 2 is identical with the first connecting elements structure.
Tie point connects aero-engine and accessory drive gearbox, the third connection by third connection structure 3 at third
Component 3, third connecting elements 3 can choose to assist supporting plate 9, and auxiliary 9 both ends of supporting plate pass through bolt and aeroplane engine
Machine and accessory drive gearbox.
First tie point and the second tie point provided by the present application are connected and fixed by pin shaft, can be made by pin shaft connection
Must be relatively stable between engine and accessory drive gearbox, while guaranteeing that certain relative motion can be generated between the two, it plays
The effect of position compensation；Third tie point is located at installation seam allowance edge, has between installation stop portion engine and accessory drive gearbox
Drive rod connection mitigates relative motion between engine and accessory drive gearbox to mitigate drive rod spline inordinate wear, and third connects
Contact passes through auxiliary supporting plate connection；While tie point can be further ensured that accessory drive gearbox and engine at triangle at three
It is relatively stable
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (3)
1. the connection structure of a kind of aero-engine and accessory drive gearbox is installed to aero-engine shell for accessory drive gearbox,
It is characterised by comprising:
The first tie point, the second tie point and third tie point is arranged in the connection structure, at triangle between tie point at described three
Shape, the third tie point are located at installation seam allowance edge；
First connecting elements (1), first connecting elements (1) are mounted on first tie point, first connecting elements
It (1) include lower Shackle assembly (4), the first end of the lower Shackle assembly (4) is connect with aero-engine installation side (7),
Fixation hole is provided in the second end of the lower Shackle assembly (4)；Upper Shackle assembly (5), the first of the upper Shackle assembly (5)
End is connect with the accessory drive gearbox, is provided with fixation hole in the second end of the upper Shackle assembly (5)；The lower Shackle assembly
(4) fixation hole of second end is fixedly connected with the fixation hole of the second end of the upper Shackle assembly (5) by pin shaft；
Second connecting elements (2) is in the second tie point connection empty engine and the accessory drive gearbox, the second connection structure
Part (2) is identical as the first connecting elements (1) structure；
Third connecting elements (3), third connection structure (3) the connection empty engine and the accessory drive gearbox.
2. the connection structure of aero-engine and the accessory drive gearbox described in a kind of aviation according to claim 1, special
Sign is, the first end of the lower Shackle assembly (4) and aero-engine installation side (7) are bolted, it is described on
The first end of Shackle assembly (5) is bolted with the accessory drive gearbox.
3. the connection structure of aero-engine and the accessory drive gearbox described in a kind of aviation according to claim 1, special
Sign is that the third connecting elements (3) includes auxiliary supporting plate (9), and the first end of auxiliary supporting plate (9) and the aviation are sent out
Motivation Middle casing auxiliary installation side (10) connection, the second end and accessory drive gearbox auxiliary of auxiliary supporting plate (9) are installed
While being bolted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811538363.5A CN109372638A (en) | 2018-12-16 | 2018-12-16 | A kind of connection structure of aero-engine and accessory drive gearbox |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811538363.5A CN109372638A (en) | 2018-12-16 | 2018-12-16 | A kind of connection structure of aero-engine and accessory drive gearbox |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109372638A true CN109372638A (en) | 2019-02-22 |
Family
ID=65373988
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811538363.5A Pending CN109372638A (en) | 2018-12-16 | 2018-12-16 | A kind of connection structure of aero-engine and accessory drive gearbox |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109372638A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110745250A (en) * | 2019-11-22 | 2020-02-04 | 中国航发沈阳黎明航空发动机有限责任公司 | Assembly type mounting structure and mounting method for ignition accessory of aero-engine |
| CN113137466A (en) * | 2021-04-29 | 2021-07-20 | 中国航发沈阳发动机研究所 | Hanging device for gear box of aircraft engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1691056A1 (en) * | 2005-01-20 | 2006-08-16 | Snecma | Bypass turbofan engine with means to drive the gearbox |
| US20100327588A1 (en) * | 2009-06-29 | 2010-12-30 | Enzo Macchia | Gas turbine with magnetic shaft forming part of a generator/motor assembly |
| CN108145382A (en) * | 2017-12-18 | 2018-06-12 | 中国航发贵州黎阳航空动力有限公司 | A kind of quick positioning and processing method of accessory drive gearbox |
| CN207642339U (en) * | 2017-12-04 | 2018-07-24 | 成都航利电气有限公司 | A kind of special punching device of engine accessory power rating wheel chamber casing |
| CN208070047U (en) * | 2018-03-23 | 2018-11-09 | 中国航发哈尔滨东安发动机有限公司 | A kind of fixed structure of aircraft accessory casing |
-
2018
- 2018-12-16 CN CN201811538363.5A patent/CN109372638A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1691056A1 (en) * | 2005-01-20 | 2006-08-16 | Snecma | Bypass turbofan engine with means to drive the gearbox |
| US20100327588A1 (en) * | 2009-06-29 | 2010-12-30 | Enzo Macchia | Gas turbine with magnetic shaft forming part of a generator/motor assembly |
| CN207642339U (en) * | 2017-12-04 | 2018-07-24 | 成都航利电气有限公司 | A kind of special punching device of engine accessory power rating wheel chamber casing |
| CN108145382A (en) * | 2017-12-18 | 2018-06-12 | 中国航发贵州黎阳航空动力有限公司 | A kind of quick positioning and processing method of accessory drive gearbox |
| CN208070047U (en) * | 2018-03-23 | 2018-11-09 | 中国航发哈尔滨东安发动机有限公司 | A kind of fixed structure of aircraft accessory casing |
Non-Patent Citations (1)
| Title |
|---|
| 吴有元等: ""某型发动机附件机匣固定问题探讨"", 《航空维修与工程》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110745250A (en) * | 2019-11-22 | 2020-02-04 | 中国航发沈阳黎明航空发动机有限责任公司 | Assembly type mounting structure and mounting method for ignition accessory of aero-engine |
| CN113137466A (en) * | 2021-04-29 | 2021-07-20 | 中国航发沈阳发动机研究所 | Hanging device for gear box of aircraft engine |
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| PB01 | Publication | ||
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Application publication date: 20190222 |