CN206627284U - A kind of testpieces of aero-engine jet pipe - Google Patents
A kind of testpieces of aero-engine jet pipe Download PDFInfo
- Publication number
- CN206627284U CN206627284U CN201621432822.8U CN201621432822U CN206627284U CN 206627284 U CN206627284 U CN 206627284U CN 201621432822 U CN201621432822 U CN 201621432822U CN 206627284 U CN206627284 U CN 206627284U
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- China
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- outer cover
- core nacelle
- testpieces
- tail bone
- leading portion
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Abstract
The utility model provides a kind of testpieces of aero-engine jet pipe, and the testpieces includes：The leading portion for the core nacelle outer cover being connected through a screw thread and the back segment of core nacelle outer cover；The leading portion for the tail bone being connected through a screw thread and the back segment of tail bone, wherein described tail bone is coaxial with the core nacelle outer cover inside the core nacelle outer cover, annular recess is distributed with along the inner surface circumferential direction of the core nacelle outer cover, annular recess is distributed with along the outer surface circumferential direction of the tail bone；And the support ring coaxial with the core nacelle outer cover, the support ring includes coaxial inner ring and outer rings, the outer shroud merges with the annular recess matching of core nacelle outer cover and pressed, and the inner ring merges with the annular recess matching of tail bone and pressed, and the inner ring is fixedly connected with the outer shroud.
Description
Technical field
It the utility model is related to aero-engine field, more particularly to a kind of testpieces of aero-engine jet pipe.
Background technology
Jet pipe is one of part of aero-engine, and main function is the product such as dioxy after aircraft fuel oil is burnt
Change carbon, sulfur dioxide, carbon monoxide, nitrogen oxides, imperfect combustion small molecule hydro carbons surge are gone out, during using spraying
Reaction force caused by air promotes aircraft, meanwhile, also function to the effect of waste air.
Jet pipe be gas internal energy is converted into kinetic energy so as to produce the important component of thrust, motor power and oil consumption rate by
The influence of ejector exhaust pipe performance is fairly obvious.Preferably to carry out nozzle performance research, aeroperformance test examination can be typically designed
Part is tested, result of the test and Numerical Simulation Results are contrasted, is Nozzle Design side so as to obtain the actual performance parameter of jet pipe
Case evaluates and optimizes offer support, the design work of finally and successfully propelling nozzle.
The situation of aeroperformance is verified for needing to test the jet pipe in multigroup different shaped face, if the design side according to routine
Each part of method, i.e. jet pipe is attached using the fastener such as bolt, then can cause big number of parts, buying or the process-cycle it is long,
The problems such as processing and management cost are high, dismounting is inconvenient.
Utility model content
The purpose of this utility model is to provide a kind of testpieces of the aero-engine jet pipe different from prior art, energy
Enough meet the needs of testpieces quick-replaceable and installation, reduce the number of parts that need to be processed, reduce processing cost.
According to above-mentioned purpose, the utility model provides a kind of testpieces of aero-engine jet pipe, and the testpieces includes：
The leading portion for the core nacelle outer cover being connected through a screw thread and the back segment of core nacelle outer cover；The leading portion and tail for the tail bone being connected through a screw thread
The back segment of vertebra, wherein the tail bone is coaxial with the core nacelle outer cover inside the core nacelle outer cover, along the core nacelle
Annular recess is distributed with the inner surface circumferential direction of outer cover, and it is recessed that ring-type is distributed with along the outer surface circumferential direction of the tail bone
Groove；And the support ring coaxial with the core nacelle outer cover, the support ring include coaxial inner ring and outer rings, the outer shroud with
The annular recess matching merging of core nacelle outer cover is pressed, and the inner ring merges with the annular recess matching of tail bone and pressed, described interior
Ring is fixedly connected with the outer shroud.
In one embodiment, the support ring is also included along the circumferentially distributed support plate of its outer ring inner surface, the support plate edge
Support ring length direction to be fixedly connected with outer shroud and inner ring.
In one embodiment, the number of the support plate is 4.
In one embodiment, the front end of the core nacelle outer cover is threadedly coupled with experimental bench.
In one embodiment, the cross section of the support plate is streamlined, and the fairshaped front end is towards air-flow incoming side
To.
In one embodiment, the contact surface of the back segment of the leading portion of the core nacelle outer cover and core nacelle outer cover is provided with mutually
The boss of cooperation, to determine the relative position of the back segment of the leading portion of core nacelle outer cover and core nacelle outer cover.
In one embodiment, the contact surface of the back segment of the leading portion of tail bone and tail bone is provided with the boss of mutual cooperation, with true
Determine the relative position of the leading portion of tail bone and the back segment of tail bone.
In one embodiment, the front end of core nacelle outer cover and the contact surface of testing stand are provided with the boss of mutual cooperation, with
Determine the relative position of core nacelle outer cover and testing stand.
In one embodiment, the leading portion and core that the annular recess of the outer shroud and core nacelle outer cover passes through core nacelle outer cover
The screw thread of the back segment covered out of my cabin presses.
In one embodiment, the annular recess of the inner ring and tail bone passes through the leading portion of tail bone and the screw thread of the back segment of tail bone
Press.
In one embodiment, the length of the support plate is less than the height of the outer shroud and the inner ring.
In one embodiment, the outer shroud and inner ring welding.
It is of the present utility model to use screw connection structure, while devise company of the support ring as core nacelle outer cover and tail bone
Fitting.
Technique effect of the present utility model includes：Design is connected through a screw thread, reduces the use of standard component, is added convenient
While work, reduce the quantity of part, reduce testpieces management and control cost；Before avoiding core nacelle outer cover leading portion and tail bone
The multiple workpieces of section, reduce processing cost；It is easy to Fast Installation and fast quick-detach, assembling and accessibility are good；By screw thread plus
Compact schemes ring, jet pipe and core engine room cover are connected, reduce the design and processing of frock, while preferably ensure that same
Axle degree；Support plate thickness design be easy to find connector accident is reversed, wrong, reduce installation error probability.
Brief description of the drawings
Fig. 1 shows the structural representation of the testpieces of the utility model jet pipe；
Fig. 2 a show the structural representation of the utility model support ring；
Fig. 2 b show the schematic diagram of the Section A-A in Fig. 2 a；
Fig. 2 c show the schematic diagram of the section B-B in Fig. 2 b；
Fig. 3 shows the enlarged drawing of threaded connection place.
For clarity, the brief description of reference given below：
10：Testpieces
101：Core nacelle outer cover
102：Tail bone
111：Core nacelle air inlet
1011：The leading portion of core nacelle outer cover
1012：The back segment of core nacelle outer cover
112、113：Screw thread
114、115：Annular recess
1021：The leading portion of tail bone
1022：The back segment of tail bone
103、20：Support ring
201、1032：The inner ring of support ring
202、1031：The outer shroud of support ring
203：Support plate
30：Threaded connection place
31、32：Boss
Embodiment
The processing of the testpieces of jet pipe is usually bolt connecting mode in the prior art, or directly integrally adds testpieces
Work is molded.
Technical solutions of the utility model are different from prior art, are connected through a screw thread the structure design with support ring, save
Number of parts caused by conventional bolt connection is big, buying or process-cycle are long, processing and management cost are high, dismounting inconvenience etc. is asked
Topic.The problem of experiment is required for testpieces overall processing every time is it also avoid, so as to reduce cost.
Fig. 1 is refer to, Fig. 1 shows the structural representation of the testpieces of the utility model jet pipe, and testpieces 10 includes core
The heart covers 101 and tail bone 102 out of my cabin, and tail bone 102 is coaxial with core nacelle outer cover 101 in the inside of core nacelle outer cover 101.
Air-flow enters testpieces from core nacelle air inlet 111, is then acted on inside core nacelle with tail bone 102, so that
Flow expansion is obtained to accelerate.
In actual applications, it can constantly change the structural form of core nacelle 101 and tail bone 102, and constantly be tested, be obtained
Go out result of the test, and contrasted with simulation result.
The leading portion 1011 of core nacelle outer cover 101 including core nacelle outer cover and the back segment 1012 of core nacelle outer cover, outside core nacelle
The leading portion 1011 of cover and the back segment 1012 of core nacelle outer cover are connected by screw thread 112, and screw thread 112 is around core nacelle outer cover
What the whole circumference of the front end face of the rear end face of leading portion 1011 and the back segment 1012 of core nacelle outer cover was set.
, only need to be by after the leading portion 1011 and core nacelle outer cover of core nacelle outer cover when changing different core nacelle outer covers 101
Section 1012 carries out simple turn-knob.
Covered out of my cabin with core 101 structure design it is similar, the leading portion 1021 of tail bone 102 including tail bone and the back segment of tail bone
1022, the leading portion 1021 of tail bone and the back segment 1022 of tail bone are connected by screw thread 113, and screw thread 113 is the leading portion around tail bone
What the whole circumference of the front end face of 1021 rear end face and the back segment 1022 of tail bone was set.
When changing different tail bones 102, only the back segment 1022 of the leading portion 1021 of tail bone and tail bone need to simply be revolved
Torsion.
In one embodiment, testpieces 10 also includes support ring 103, refer to Fig. 2 a, and Fig. 2 a show the utility model
The structural representation of support ring.
Support ring 20 includes coaxial inner ring 201 and outer shroud 202, and inner ring 201 is fixedly connected with outer shroud 202, also with regard to explanation
The position of inner ring 201 and outer shroud 202 is relatively fixed.
Continuing with reference to Fig. 1, annular recess 114 is distributed with along the inner surface circumferential direction of core nacelle outer cover 201, along
Annular recess 115 is distributed with the outer surface circumferential direction of tail bone 102.Wherein, the annular recess 114 and support ring of core nacelle outer cover
103 outer shroud 1031 is mutually matched, and outer shroud 1031 can just be caught in annular recess 114 so that core nacelle outer cover 102 and support
Position is relatively fixed ring 103 in the axial direction.
Likewise, the annular recess 115 of tail bone and the inner ring 1032 of support ring 103 are mutually matched, inner ring 1032 can be just
It is caught in well in annular recess 115 so that position is relatively fixed tail bone 102 in the axial direction with support ring 103.
Final purpose of the present utility model is so that the leading portion of core nacelle outer cover connects with back segment, the front end of tail bone and back segment
Connection.Then, core nacelle outer cover is fixedly connected with tail bone.
By described above, the leading portion and back segment of core nacelle outer cover have been connected through a screw thread, the leading portion and back segment of tail bone
It has been connected through a screw thread.Position of the outer shroud with core nacelle in the axial direction is relatively fixed, and inner ring and tail bone are in the axial direction
Position be relatively fixed.
So only need to fix outer shroud and inner ring, while cause outer shroud with core nacelle from circumferentially relative fortune
It is dynamic, and inner ring can not circumferentially relative motion with tail bone.
In one embodiment, the schematic diagram that Fig. 2 a and Fig. 2 b, Fig. 2 b show the Section A-A in Fig. 2 a is refer to, is supported
Ring 20 also includes along the circumferentially distributed support plate 203 of its outer ring inner surface, and support plate 203 is along support ring length direction and outer shroud 201
It is fixedly connected with inner ring 202.
In one embodiment, outer shroud 201 and inner ring 202 are welded.
In one embodiment, there are 4 support plates 203 along 20 outer ring inner surface of support ring is circumferentially distributed, between each two support plate
Angle be 90 degree.
In one embodiment, the length of support plate 203 is less than the height of inner ring and less than the height of outer shroud, can so save
Manufacture material, reduce cost.
Although in Fig. 1, the position of outer shroud 1031 and inner ring 1032 in the horizontal is alignment, it is to be understood that, outer shroud
1031 and the position of inner ring 1032 in the horizontal may not be alignment, the position of outer shroud 1031 in the horizontal can including
Before ring 1032, the position of inner ring 1032 in the horizontal can also be before outer shroud 1031.
Because the setting of support plate 203 is inside gas channel, in order to avoid the setting due to support plate is caused to air-flow
Influence, in one embodiment, the cross section of support plate 203 is streamlined, can specifically be shown referring to Fig. 2 c, Fig. 2 c in Fig. 2 b
The schematic diagram of section B-B, fairshaped front end can preferably avoid shadow of the support plate 203 to air-flow towards air-flow direction of flow
Ring.It is this to design the installation direction that also can be identified for that support ring when testpieces is installed, reduce installation error probability.
In a preferred embodiment, the enlarged drawing of threaded connection place 30 is as shown in figure 3, the leading portion and core of core nacelle outer cover
The contact surface of the back segment covered out of my cabin is provided with the boss 31 of mutual cooperation, to determine the leading portion of core nacelle outer cover and core nacelle outer cover
Back segment relative position.This boss is designed to cause the installation of threaded connection more accurately and fast.
More preferably, the contact surface of the back segment of the leading portion of tail bone and tail bone is provided with the boss 32 of mutual cooperation, to determine tail
The relative position of the leading portion of vertebra and the back segment of tail bone.The design of this boss also can be the installation being preferably threadedly coupled
Basis is provided.
In one embodiment, the leading portion of core nacelle outer cover is threadedly coupled with experimental bench.Testing stand can provide for testing stand
The air-flow of corresponding different parameters needed for test.
Identical with the purpose of design of foregoing boss, more preferably, the front end of core nacelle outer cover and the contact surface of testing stand are set
There is the boss of mutual cooperation, to determine the relative position of core nacelle outer cover and testing stand.
Generally, the leading portion 1011 of core nacelle outer cover, the front end 1021 of tail bone and support ring 103 need not all be changed.
When thering is new testpieces to need to be tested, by the back segment of the core nacelle outer cover of new testpieces and core nacelle outer cover
Front end is aligned, and by outer shroud as in the annular recess of core nacelle outer cover, back segment and the core nacelle outer cover of turn-knob core nacelle outer cover
Front end, so as to compress the annular recess of outer shroud and core nacelle outer cover.
Similarly, the back segment of the tail bone of new testpieces is aligned with tail bone front end, and inner ring is recessed as the ring-type of tail bone
In groove, back segment and the tail bone front end of turn-knob tail bone, so as to compress the annular recess of inner ring and tail bone.
Outer shroud and inner ring tightening by screw thread, respectively with the annular recess of core nacelle outer cover and the annular recess pressure of tail bone
Tightly.Due to the effect of stiction, the fixation of outer shroud and inner ring respectively with core nacelle outer cover and tail bone relative position is realized.
Thus core nacelle outer cover front end, core nacelle outer cover back segment, tail bone leading portion, tail bone back segment are all fixedly connected on
Together, and then can further be tested.
As described above, the testpieces of aero-engine jet pipe provided by the utility model, core nacelle is connected using screw thread
Leading portion and back segment, the leading portion and back segment of tail bone, are designed with support ring as core nacelle outer cover and the connector of tail bone.
By above-mentioned design, the technique effect that the utility model reaches includes：The use of the fasteners such as bolt is reduced, is reduced
Management and control cost；For the nozzle test part in multigroup different shaped face, reuse as far as possible, reduce the number of parts that need to be processed, drop
Low processing cost；It is easy to Fast Installation and dismounting.
Offer is for so that any person skilled in the art all can make or use this public affairs to being previously described for the disclosure
Open.Various modifications to the disclosure all will be apparent for a person skilled in the art, and as defined herein general
Suitable principle can be applied to spirit or scope of other variants without departing from the disclosure.Thus, the disclosure is not intended to be limited
Due to example described herein and design, but should be awarded and principle disclosed herein and novel features phase one
The widest scope of cause.
Claims (12)
1. a kind of testpieces of aero-engine jet pipe, it is characterised in that the testpieces includes：
The leading portion for the core nacelle outer cover being connected through a screw thread and the back segment of core nacelle outer cover；
The leading portion for the tail bone being connected through a screw thread and the back segment of tail bone, wherein the tail bone is inside the core nacelle outer cover and institute
State that core nacelle outer cover is coaxial, annular recess is distributed with along the inner surface circumferential direction of the core nacelle outer cover, along the tail
Annular recess is distributed with the outer surface circumferential direction of vertebra；And
The coaxial support ring with the core nacelle outer cover, the support ring include coaxial inner ring and outer rings, the outer shroud and core
The annular recess matching merging that the heart covers out of my cabin is pressed, and the inner ring merges with the annular recess matching of tail bone and pressed, the inner ring
It is fixedly connected with the outer shroud.
2. testpieces as claimed in claim 1, it is characterised in that the support ring also includes circumferentially dividing along its outer ring inner surface
The support plate of cloth, the support plate are fixedly connected along support ring length direction with outer shroud and inner ring.
3. testpieces as claimed in claim 2, it is characterised in that the number of the support plate is 4.
4. testpieces as claimed in claim 1, it is characterised in that the front end of the core nacelle outer cover connects with experimental bench screw thread
Connect.
5. testpieces as claimed in claim 2, it is characterised in that the cross section of the support plate is streamlined, described streamlined
Front end towards air-flow direction of flow.
6. testpieces as claimed in claim 1, it is characterised in that after the leading portion and core nacelle outer cover of the core nacelle outer cover
The contact surface of section is provided with the boss of mutual cooperation, to determine the relative of the back segment of the leading portion of core nacelle outer cover and core nacelle outer cover
Position.
7. testpieces as claimed in claim 1, it is characterised in that the contact surface of the leading portion of tail bone and the back segment of tail bone is provided with
The boss of mutual cooperation, to determine the relative position of the back segment of the leading portion of tail bone and tail bone.
8. testpieces as claimed in claim 1, it is characterised in that the front end of core nacelle outer cover and the contact surface of testing stand are set
There is the boss of mutual cooperation, to determine the relative position of core nacelle outer cover and testing stand.
9. testpieces as claimed in claim 1, it is characterised in that the annular recess of the outer shroud and core nacelle outer cover passes through core
The leading portion and the screw thread of the back segment of core nacelle outer cover that the heart covers out of my cabin press.
10. testpieces as claimed in claim 1, it is characterised in that the annular recess of the inner ring and tail bone passes through tail bone
The screw thread of the back segment of leading portion and tail bone presses.
11. testpieces as claimed in claim 2, it is characterised in that the length of the support plate is less than the outer shroud and described interior
The height of ring.
12. testpieces as claimed in claim 2, it is characterised in that the outer shroud and inner ring welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621432822.8U CN206627284U (en) | 2016-12-23 | 2016-12-23 | A kind of testpieces of aero-engine jet pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621432822.8U CN206627284U (en) | 2016-12-23 | 2016-12-23 | A kind of testpieces of aero-engine jet pipe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206627284U true CN206627284U (en) | 2017-11-10 |
Family
ID=60212861
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621432822.8U Active CN206627284U (en) | 2016-12-23 | 2016-12-23 | A kind of testpieces of aero-engine jet pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206627284U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109406153A (en) * | 2018-12-14 | 2019-03-01 | 中国航发沈阳发动机研究所 | Aero-engine support device, experimental rig |
| CN111610027A (en) * | 2019-02-22 | 2020-09-01 | 中国航发商用航空发动机有限责任公司 | Aircraft engine fault simulation system and simulation method |
| CN113124739A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Plug type axisymmetric nozzle outlet section measuring device and measuring method |
-
2016
- 2016-12-23 CN CN201621432822.8U patent/CN206627284U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109406153A (en) * | 2018-12-14 | 2019-03-01 | 中国航发沈阳发动机研究所 | Aero-engine support device, experimental rig |
| CN111610027A (en) * | 2019-02-22 | 2020-09-01 | 中国航发商用航空发动机有限责任公司 | Aircraft engine fault simulation system and simulation method |
| CN113124739A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Plug type axisymmetric nozzle outlet section measuring device and measuring method |
| CN113124739B (en) * | 2019-12-31 | 2023-02-24 | 中国航发商用航空发动机有限责任公司 | Plug type axisymmetric nozzle outlet cross section measuring device and measuring method |
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