CN105298684B - A kind of aero-engine tail bone attachment structure - Google Patents
A kind of aero-engine tail bone attachment structure Download PDFInfo
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- CN105298684B CN105298684B CN201510594807.7A CN201510594807A CN105298684B CN 105298684 B CN105298684 B CN 105298684B CN 201510594807 A CN201510594807 A CN 201510594807A CN 105298684 B CN105298684 B CN 105298684B
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Abstract
A kind of aero-engine tail bone attachment structure, it is related to the tail bone attachment structure design field in aircaft configuration, for reducing aero-engine tail bone junction flow perturbation and vibration, the connection side of tail bone connecting bracket and mounting bracket are formed in one structure, connect on when being fixedly connected on the installation of engine turbine rear housing by the first bolt, mounting bracket is arranged at intervals with being connected on while in connection, and one end away from connection side in mounting bracket is provided with self-locking nut；Second bolt coordinates with self-locking nut is fixedly connected with tail bone with engine turbine rear housing, tightens after the second bolt, the head top surface of the second bolt and the water passage surface of tail bone are on the same face.The disturbance that the aero-engine tail bone connection knot that the present invention is provided is produced when reducing air-flow through tail bone, structure processing facility, assembly and disassembly process without interference, structure high temperature resistant, good rigidity, practicality be higher, can Reusability, device stability it is high, safe and reliable.
Description
Technical field
The present invention relates to the tail bone attachment structure design field in aircaft configuration, in particular to a kind of aviation
Engine tail bone attachment structure, for reducing aero-engine tail bone junction flow perturbation and vibration.
Background technology
The tail bone of aero-engine and jet pipe, blender composition engine exhaust functional unit.Between each part
It is sequentially connected, traditional tail bone is directly bolted on the engine turbine rear housing of front end, but after being due to tail bone
The approximate closing in end, therefore the bolt used in connection tail bone, must open several dead slots, with full in the circumference on the water passage surface of tail bone
Assembly space needed for sufficient fixing bolt.To adapt to assemble and the dead slot of additional processing on the water passage surface of tail bone, directly lead
Produce larger disturbance during the airflow passes tail bone for causing engine inner flow passage, flow perturbation so that cause the vibration of tail bone segment structure plus
Play, the improvement of influence complete machine oscillation, and vibration aggravation can cause the connector more fatiguability for fixing tail bone and be broken, and jeopardize and start
The operation safety of machine.Therefore, the technical problem of urgent need to resolve is how to design a kind of aero-engine to be connected with tail bone at this stage
Structure, to overcome the defect in aero-engine tail bone attachment structure in the prior art.
The content of the invention
It is an object of the invention to solve above-mentioned deficiency of the prior art to be connected with tail bone there is provided a kind of aero-engine
Structure.
The purpose of the present invention is achieved through the following technical solutions：A kind of aero-engine tail bone attachment structure, its feature
It is, including：
Tail bone connecting bracket, including connection side and mounting bracket, wherein, connection side and mounting bracket are formed in one knot
Structure, is connected on when being fixedly connected on the installation of engine turbine rear housing by the first bolt, the mounting bracket edge connection length of side
Spend direction to be arranged at intervals, the plate face of mounting bracket is parallel with the water passage surface of tail bone, one away from connection side in mounting bracket
End is provided with self-locking nut；Connecting bracket is integrated mechanism, is constituted by connecting side and mounting bracket, wherein connection side is fixed on hair
On the installation side of motivation turbine rear casing；Mounting bracket is to install the epitaxial structure on side, the plate face of mounting bracket and the stream of tail bone
Road face be arranged in parallel.
Second bolt, the water passage surface of tail bone is docked with the water passage surface smooth and seamless of engine turbine rear housing, in tail
Self-locking nut position corresponding position on the water passage surface of vertebra and mounting bracket offers bolt positioning groove, bolt positioning groove bottom surface
Offer bolt hole,
Tail bone is simultaneously fixedly connected by the second bolt passing through bolt hole with self-locking nut cooperation with engine turbine rear housing, is twisted
After tight second bolt, the head top surface of the second bolt and the water passage surface of tail bone are on the same face.
In such scheme preferably, the first bolt, the second bolt are high temperature resistant bolt, self-locking nut be high temperature resistant from
Split nut, when the first bolt, the second bolt self-locking nut reach the highest temperature in the junction of tail bone and engine turbine rear housing
Respective mechanical performance can still be kept.
In any of the above-described scheme preferably, the axial direction of the bolt positioning groove opened up on tail bone and the peace of tail bone connecting bracket
The plate face for filling support is vertical.Ensure that the space that tail bone is installed with engine turbine rear housing shared by the junction of side is minimum, it is to avoid right
The air-flow for flowing through pipes' analysis produces influence.
In any of the above-described scheme preferably, the head of the second bolt is the spiral shell opened up on cylindrical-shaped structure, the tail bone
The diameter of bolt locating slot is equal with the diameter on the head of the second bolt, the depth of the bolt positioning groove opened up on tail bone and the second spiral shell
The thickness on the head of bolt is equal.Ensure that the head of the second bolt is all embedded in the bolt positioning groove opened up on tail bone, reduction by the
Two bolts produce disturbing influence to the air-flow for flowing through tail bone pipes' analysis.
In any of the above-described scheme preferably, the first bolt is arranged between tail bone connecting bracket.Further preferably, first
Bolt is arranged at intervals at the mounting bracket of tail bone connecting bracket and is connected on side.
In any of the above-described scheme preferably, after the connection side of tail bone connecting bracket is by welding manner and engine turbine
The installation side of casing is fixedly connected.The connector connected between part can be reduced by the way of welding, space has been saved, reduced
To the structural damage of part, service life is extended.
In any of the above-described scheme preferably, after the connection side of tail bone connecting bracket is by riveting method and engine turbine
The installation side of casing is fixedly connected.The dismounting of tail bone connecting bracket can be facilitated by way of riveting, met with tail bone connecting bracket
Tail bone connecting bracket only need to be changed after to destruction, the overall constitutional detail without scrapping extends overall structure part
Service life.
Aero-engine provided by the present invention is with the beneficial effect of tail bone attachment structure, rational in infrastructure, and processing is just
Profit, assembly and disassembly process is without interference, and structure high temperature resistant, good rigidity, service life length, reliability are high, and practicality is higher, can
Reusability, simple in construction, easily manufactured, device stability is high, safe and reliable.
1st, eliminate because direct fixed tail bone, increase connecting bolt pull lemon space and on tail bone water passage surface working (finishing) area
Larger hole slot, the vibration for reducing runner flow perturbation and producing while tail bone connection safety is improved, is conducive to hair
The level of vibration control of motivation；
2nd, flow perturbation reduces, vibration values are reduced, and can further reduce the connector quantity used in fixed tail bone, Jin Erke
Optimize the structure that tail bone is fixed at engine turbine rear housing, be conducive to the structure optimization loss of weight and hair of engine turbine rear housing
The overall mass control of motivation；
3rd, tail bone connecting bracket component can be fixed on engine turbine rear housing, and assembling, which is decomposed, every time only need to buckle tail bone
, compare and traditional tail bone fixed structure form, the tail bone fixed form of this invention has more preferable assembling capacity；
4th, the producting process difficulty of this structure has been taken into full account, has made this structure that there is good productibility.
Brief description of the drawings
Fig. 1 is the structural representation of aero-engine one preferred embodiment of tail bone attachment structure according to the present invention；
Fig. 2 is to be assembled according to the aero-engine of the present invention with the embodiment illustrated in fig. 1 of tail bone attachment structure with tail bone
Cross-sectional view；
Fig. 3 is the partial enlarged drawing of the aero-engine embodiment illustrated in fig. 1 of tail bone attachment structure according to the present invention.
Reference：
1- engine turbines rear housing, 2- tail bones connecting bracket, 3- self-locking nuts, the bolts of 4- second, 5- tail bones, 6- first
Bolt.
Embodiment
In order to more fully understand the aero-engine tail bone attachment structure according to the present invention program, to make implementation of the present invention
Purpose, technical scheme and advantage it is clearer, below in conjunction with the accompanying drawing in the embodiment of the present invention, in the embodiment of the present invention
Technical scheme be further described in more detail.In the accompanying drawings, same or similar label represents same or like from beginning to end
Element or element with same or like function.Described embodiment is a part of embodiment of the invention, rather than entirely
The embodiment in portion.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to for explaining the present invention, and can not manage
Solve as limitation of the present invention.Based on the embodiment in the present invention, those of ordinary skill in the art are not making creative labor
The every other embodiment obtained under the premise of dynamic, belongs to the scope of protection of the invention.Below in conjunction with the accompanying drawings to the present invention's
Embodiment is described in detail.
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, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
As shown in Figure 1-Figure 3, the aero-engine tail bone attachment structure that the present invention is provided, including：Tail bone connecting bracket
2, including connection side and mounting bracket, wherein, connection side and mounting bracket are formed in one structure, and connection side passes through the first bolt
6 are fixedly connected on the installation side of engine turbine rear housing 1, and mounting bracket is arranged at intervals along connection edge lengths direction, is installed
The plate face of support is parallel with the water passage surface of tail bone 5, and one end away from connection side in mounting bracket is provided with self-locking nut 3；
It is pre-set in mounting bracket, directly tail bone 5 can be fixed on to the second bolt 4 from the outside of tail bone 5 using self-locking nut 3
On the installation side of engine turbine rear housing 1, it is to avoid the operation of installation bolt and nut simultaneously in installation process, zero is reduced
Complexity, the difficulty of the installation operation of part.
Second bolt 4, the water passage surface of tail bone 5 is docked with the water passage surface smooth and seamless of engine turbine rear housing 1,
The position corresponding position of self-locking nut 3 on the water passage surface of tail bone 5 and mounting bracket offers bolt positioning groove, bolt positioning groove
Bottom surface offers bolt hole, and the thickness of the pipes' analysis of tail bone 5 is spirally connected with the installation side of engine turbine rear housing 1, makes engine
Turbine rear casing 1 is on the same face after being docked with tail bone 5, it is to avoid produce interference to air-flow.
Second bolt 4 coordinates tail bone 5 and engine turbine rear housing 1 fix company through bolt hole and with self-locking nut 3
Connect, tighten after the second bolt 4, the head top surface of the second bolt 4 is on the same face with the water passage surface of tail bone 5.Second spiral shell
The head of bolt 4 is the diameter and the diameter phase on the head of the second bolt 4 of the bolt positioning groove opened up on cylindrical-shaped structure, tail bone 5
Deng the depth of the bolt positioning groove opened up on tail bone 5 is equal with the thickness on the head of second item bolt 4.
First bolt 6, the second bolt 4 are high temperature resistant bolt, and self-locking nut 3 is high temperature resistant self-locking nut, the first bolt
6th, the self-locking nut 3 of the second bolt 4 can still keep each when the junction of tail bone 5 and engine turbine rear housing 1 reaches the highest temperature
From mechanical performance.To tail bone 5 if the first bolt 6, the second bolt 4, self-locking nut 3 can be produced if deformation in hot environment
Attachment structure can produce influence, cause the connection of tail bone 5 and engine turbine rear housing 1 unstable, to integrally-built running
Cause damage.
The axial direction of the bolt positioning groove opened up on tail bone 5 is vertical with the plate face of the mounting bracket of tail bone connecting bracket 2.Using
The effect of this kind design is to ensure that the second bolt 4 in the bolt positioning groove on tail bone 5 is parallel, abundant with the plate face of mounting bracket
Laminating, reduces the influence to air-flow
First bolt 6 is arranged between tail bone connecting bracket 2.The connection side of tail bone connecting bracket 2 by welding manner with
Installation side after engine turbine rear housing 1 is fixedly connected.The connection side of tail bone connecting bracket 2 passes through riveting method and engine
Installation side after turbine rear casing 1 is fixedly connected.The bolt fixing hole of connecting bracket and mounting bracket are arranged at intervals, money is saved
Source, reduces the space shared by connecting bracket 2, improves operating efficiency.
During specific use, in engine assembly, it can first use several corner bolts of high temperature resistant 12, i.e.,
Tail bone connecting bracket 2 is fixed on the installation side of engine turbine rear housing 1 by one bolt 6, and this support assembling is preferable, and one
After secondary installation, follow-up assembling, decomposition reduce engine assembly, the workload decomposed, are beneficial to without split connecting bracket 2 again
Engine unitization is managed.One resistant to elevated temperatures self-locking nut is installed on every plate rack that tail bone connecting bracket 2 is extended
3, used for fixing tail bone 5, advantageously reduce assembly difficulty using self-locking nut and reduce and assemble time-consuming.In the runner of tail bone 5
Surface, it is only necessary to open several and meet the corner bolt of high temperature resistant 12, be i.e. the bolt hole that the second bolt 4 sedimentation is installed is (more straight than bolt head
The big 5mm in footpath), the angle of the bolt hole on tail bone 5 and position are conducive to the assembling and decomposition of tail bone, when assembling every time, only need
Tail bone is buckled in connecting bracket 2, then the-the second bolt of corner bolt 4 of high temperature resistant 12 is screwed into resistant to elevated temperatures self-locking nut 3
.
Aero-engine above in association with the present invention is described in detail with tail bone attachment structure specific embodiment, but not
It is limitation of the present invention, every technical spirit according to the present invention is belonged to any simple modification made for any of the above embodiments
The technical scope of the present invention, in addition it is also necessary to explanation, according to the aero-engine tail bone attachment structure technical scheme of the present invention
Category include each part mentioned above between any combination.
Claims (7)
1. a kind of aero-engine tail bone attachment structure, it is characterised in that including：
Tail bone connecting bracket (2), including connection side and mounting bracket, wherein, connection side and mounting bracket are formed in one structure,
Connect on when being fixedly connected on the installation of engine turbine rear housing (1) by the first bolt (6), mounting bracket edge connection side
Length direction is arranged at intervals, and the plate face of mounting bracket is parallel with the water passage surface of tail bone (5), away from connection side in mounting bracket
One end be provided with self-locking nut (3)；
Second bolt (4), the water passage surface of tail bone (5) is docked with the water passage surface smooth and seamless of engine turbine rear housing (1),
Self-locking nut (3) position corresponding position on water passage surface and mounting bracket in tail bone (5) offers bolt positioning groove, bolt
Positioning groove bottom offers bolt hole,
Second bolt (4) through bolt hole and coordinates that tail bone (5) and engine turbine rear housing (1) is solid with self-locking nut (3)
Fixed connection, is tightened after the second bolt (4), the head top surface of the second bolt (4) is in the same face with the water passage surface of tail bone (5)
On.
2. aero-engine as claimed in claim 1 tail bone attachment structure, it is characterised in that：First bolt (6), the second spiral shell
Bolt (4) is high temperature resistant bolt, and self-locking nut (3) is high temperature resistant self-locking nut, the first bolt (6), the second bolt (4), self-locking
Nut (3) can still keep respective mechanicalness when the junction of tail bone (5) and engine turbine rear housing (1) reaches the highest temperature
Energy.
3. aero-engine as claimed in claim 1 tail bone attachment structure, it is characterised in that：The spiral shell opened up on tail bone (5)
The axial direction of bolt locating slot is vertical with the plate face of the mounting bracket of tail bone connecting bracket (2).
4. aero-engine as claimed in claim 1 tail bone attachment structure, it is characterised in that：Second bolt (4)
Head is cylindrical-shaped structure, the diameter on the diameter of the bolt positioning groove opened up on the tail bone (5) and the head of the second bolt (4)
Equal, the depth of the bolt positioning groove opened up on tail bone (5) is equal with the thickness on the head of the second bolt (4).
5. aero-engine as claimed in claim 1 tail bone attachment structure, it is characterised in that：First bolt (6) is arranged at
Between the tail bone connecting bracket (2).
6. aero-engine as claimed in claim 1 tail bone attachment structure, it is characterised in that：The tail bone connecting bracket
(2) connection is fixedly connected while by welding manner with the installation after engine turbine rear housing (1).
7. aero-engine as claimed in claim 1 tail bone attachment structure, it is characterised in that：The tail bone connecting bracket
(2) connection is fixedly connected while by riveting method with the installation after engine turbine rear housing (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510594807.7A CN105298684B (en) | 2015-09-18 | 2015-09-18 | A kind of aero-engine tail bone attachment structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510594807.7A CN105298684B (en) | 2015-09-18 | 2015-09-18 | A kind of aero-engine tail bone attachment structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105298684A CN105298684A (en) | 2016-02-03 |
| CN105298684B true CN105298684B (en) | 2017-11-03 |
Family
ID=55196369
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510594807.7A Active CN105298684B (en) | 2015-09-18 | 2015-09-18 | A kind of aero-engine tail bone attachment structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110566364B (en) * | 2019-09-10 | 2022-05-06 | 中国航空工业集团公司西安飞机设计研究所 | Flexible compensation connecting structure of asymmetric spray pipe and engine |
| CN112355610B (en) * | 2020-10-28 | 2021-06-29 | 上海尚实能源科技有限公司 | Splicing equipment for assembling gas turbine engine |
| CN112282963B (en) * | 2020-10-28 | 2021-05-04 | 上海尚实能源科技有限公司 | Gas turbine engine tail cone connecting piece |
| CN112318090B (en) * | 2020-10-28 | 2021-06-15 | 上海尚实能源科技有限公司 | Gas turbine engine centerbody assembly system |
| CN112196838B (en) * | 2020-12-09 | 2021-02-19 | 中国航发上海商用航空发动机制造有限责任公司 | Aeroengine impeller machine and aeroengine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4907743A (en) * | 1987-11-12 | 1990-03-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Assembly of two bodies having distinctly different coefficients of expansion |
| GB2238027A (en) * | 1989-11-17 | 1991-05-22 | Gen Electric | Aerodynamic shield for structural joint |
| EP1265034A1 (en) * | 2001-06-06 | 2002-12-11 | Snecma Moteurs | Mounting of a turbine ceramic matrix composite combustion chamber with brazed mounting lungs |
| CN103717870A (en) * | 2011-08-12 | 2014-04-09 | 埃尔塞乐公司 | Exhaust cone for aircraft turbojet engine |
| CN103764985A (en) * | 2011-08-12 | 2014-04-30 | 埃尔塞乐公司 | Exhaust plug for an aircraft turbojet engine |
-
2015
- 2015-09-18 CN CN201510594807.7A patent/CN105298684B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4907743A (en) * | 1987-11-12 | 1990-03-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Assembly of two bodies having distinctly different coefficients of expansion |
| GB2238027A (en) * | 1989-11-17 | 1991-05-22 | Gen Electric | Aerodynamic shield for structural joint |
| EP1265034A1 (en) * | 2001-06-06 | 2002-12-11 | Snecma Moteurs | Mounting of a turbine ceramic matrix composite combustion chamber with brazed mounting lungs |
| CN103717870A (en) * | 2011-08-12 | 2014-04-09 | 埃尔塞乐公司 | Exhaust cone for aircraft turbojet engine |
| CN103764985A (en) * | 2011-08-12 | 2014-04-30 | 埃尔塞乐公司 | Exhaust plug for an aircraft turbojet engine |
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| Publication number | Publication date |
|---|---|
| CN105298684A (en) | 2016-02-03 |
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