CN109356746A - Aero-engine integrates exhaust structure - Google Patents
Aero-engine integrates exhaust structure Download PDFInfo
- Publication number
- CN109356746A CN109356746A CN201811530655.4A CN201811530655A CN109356746A CN 109356746 A CN109356746 A CN 109356746A CN 201811530655 A CN201811530655 A CN 201811530655A CN 109356746 A CN109356746 A CN 109356746A
- Authority
- CN
- China
- Prior art keywords
- tail bone
- flat segments
- aero
- supporting plate
- exhaust structure
- 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
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
- F01D25/305—Exhaust heads, chambers, or the like with fluid, e.g. liquid injection
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Exhaust Silencers (AREA)
Abstract
This application provides a kind of aero-engines to integrate exhaust structure, including mounting flange side, flat segments, lobed mixer, tail bone, supporting plate and self-locking silk braid, the flat segments are connect with the mounting flange side and the lobed mixer respectively, the tail bone is connected in the flat segments by the supporting plate, and the self-locking silk braid is set to the junction of the tail bone Yu the supporting plate.
Description
Technical field
This application involves aero-engine technology fields, specifically provide a kind of integrated exhaust structure of aero-engine.
Background technique
The exhaust mode of traditional double duct aviation turbofan engines is separated exhaust and mixing exhaust, mixing exhaust aviation
Jet pipe, mixer and jet pipe collectively constitute gas deflation assembly in engine.Mixer uses flange in existing aero-engine
It is fixed on turbine rear casing outer ring casing rear flange side, tail bone equally uses flange to be fixed on turbine rear casing inner ring casing
It installs on side afterwards.Background proposed by the present invention is in mixing aviation turbofan engine, and aero-engine overall structure layout takes
Disappear in the case where turbine rear casing and axle center ventilation, the tail bone in gas deflation assembly is faced with the fixed situation of no stator casing.
Implementation in the prior art is mixer and tail bone in the mixing aviation turbofan engine containing turbine rear casing
The organization plan being connect with turbine rear casing independently.
Under the conditions of the application background that the present invention faces, prior art and the prior art related to the present invention are lacked
Point is: technical aspect, prior art and the prior art, for fixed tail bone, need volume under the background of no turbine rear casing
It is outer to increase non-master support case, and lobed mixer is also required to be fixed on non-master support case, i.e., non-master support case replaces
The function of the fixed gas deflation assembly of former turbine rear casing；In terms of cost, prior art and the prior art need additional increase by one
A non-master support case, adds additional cost；In terms of efficiency, prior art and the prior art are because adding additional zero group
Part reduces assembly, decomposition, maintenance efficiency.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of aero-engines to integrate exhaust structure,
Including mounting flange side, flat segments, lobed mixer, tail bone, supporting plate and self-locking silk braid, the flat segments respectively with the fixation
Flange is connected with the lobed mixer, and the tail bone is connected in the flat segments by the supporting plate, the self-locking silk
Set is set to the junction of the tail bone Yu the supporting plate.
According at least one embodiment of the application, in a tubular form, the mounting flange side is in a ring and even for the flat segments
It is connected to one end of the flat segments, the lobed mixer is connected to the other end of the flat segments.
According at least one embodiment of the application, the quantity of the supporting plate is multiple, one end company of multiple supporting plates
It is connected on the medial surface of the flat segments, the other end of multiple supporting plates is all connected on the tail bone.
According at least one embodiment of the application, the tail bone includes larger diameter end and tip, multiple supporting plates
The other end is all connected to the larger diameter end of the tail bone, and the lobed mixer is stretched out at the tip of the tail bone.
According at least one embodiment of the application, the supporting plate passes through the larger diameter end of the tail bone, in the supporting plate
The end for being pierced by the tail bone is provided with self-locking silk braid.
Aero-engine provided by the embodiments of the present application integrates exhaust structure, compared with prior art: solving aviation hair
Motivation does not have under the background of turbine rear casing, under the premise of not increasing independent function casing, the fixed problem of tail bone；Cancelling
Under the background of tail bone axle center ventilation, the configuration of the complete pointed cone of tail bone is realized, the reflection effect of gas deflation assembly is improved；Lobe is mixed
Clutch and tail bone integrated body structure are individual construction, and using increasing material manufacturing one-pass molding, the process-cycle is short, and reduces boat
Empty engine machine part quantity, weight and cost；Have good assembling and maintainability in aero-engine complete machine.
Detailed description of the invention
Fig. 1 is the structural schematic diagram that aero-engine provided by the embodiments of the present application integrates exhaust structure；
Fig. 2 is the partial enlarged view that aero-engine provided by the embodiments of the present application integrates exhaust structure.
Wherein:
Specific embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining related application, rather than the restriction to this application.It also should be noted that in order to
Convenient for description, part relevant to the application is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
It should be noted that in the description of the present application, term " center ", "upper", "lower", "left", "right", "vertical",
The direction of the instructions such as "horizontal", "inner", "outside" or the term of positional relationship are direction based on the figure or positional relationship, this
It is intended merely to facilitate description, rather than indication or suggestion described device or element must have a particular orientation, with specific
Orientation construction and operation, therefore should not be understood as the limitation to the application.
In addition it is also necessary to explanation, in the description of the present application unless specifically defined or limited otherwise, term " peace
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, be also possible to be electrically connected；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.To those skilled in the art, it can understand that above-mentioned term exists as the case may be
Concrete meaning in the application.
Fig. 1 is the structural schematic diagram that aero-engine provided by the embodiments of the present application integrates exhaust structure, as shown in Figure 1,
Aero-engine integrates exhaust structure, including mounting flange side 1, flat segments 2, lobed mixer 3, tail bone 4, supporting plate 5 and self-locking
Silk braid 6.
Wherein, flat segments 2 are connect with mounting flange side 1 and lobed mixer 3 respectively, and tail bone 4 is connected to flat by supporting plate 5
On straight section 2, self-locking silk braid 6 is set to the junction of tail bone 4 Yu supporting plate 5.
Optionally, in a tubular form, in a ring, mounting flange side 1 is connected to the one of flat segments 2 to flat segments 2 on mounting flange side 1
End, lobed mixer 3 are connected to the other end of flat segments 2.
Wherein, the diameter of 2 one end of flat segments is identical as the diameter on mounting flange side 1, the diameter of lobed mixer 3 with it is straight
The diameter of the other end of section 2 is identical.
Optionally, the quantity of supporting plate 5 is multiple, and one end of multiple supporting plates 5 is connected on the medial surface of flat segments 2, multiple
The other end of supporting plate 5 is all connected on tail bone 4.
Wherein, multiple supporting plates 5 can be evenly arranged on the inner sidewall of flat segments 2, can also be unevenly arranged in
On the inner sidewall of flat segments 2.
Further, tail bone 4 includes larger diameter end and tip, and the other end of multiple supporting plates 5 is all connected to the big straight of tail bone 4
Lobed mixer 3 is stretched out at the tip at diameter end, tail bone 4.
The larger diameter end of tail bone 4 does not stretch out flange installation when 1 either installs with flange 1 in same plane.
Further, supporting plate 5 passes through the larger diameter end of tail bone 4, and the end that supporting plate 5 is pierced by tail bone 4 is provided with self-locking silk
Set 6, the connection for fixed supported slab 5 and tail bone 4.
The above, the only specific embodiment of the application, it is apparent to those skilled in the art that,
For convenience of description and succinctly, the system, module of foregoing description and the specific work process of unit can refer to preceding method
Corresponding process in embodiment, details are not described herein.It should be understood that the protection scope of the application is not limited thereto, it is any to be familiar with
Those skilled in the art within the technical scope of the present application, can readily occur in various equivalent modifications or substitutions,
These modifications or substitutions should all cover within the scope of protection of this application.
So far, it has been combined preferred embodiment shown in the drawings and describes the technical solution of the application, still, this field
Technical staff is it is easily understood that the protection scope of the application is expressly not limited to these specific embodiments.Without departing from this
Under the premise of the principle of application, those skilled in the art can make equivalent change or replacement to the relevant technologies feature, these
Technical solution after change or replacement is fallen within the protection scope of the application.
Claims (5)
1. a kind of aero-engine integrates exhaust structure, which is characterized in that including mounting flange side (1), flat segments (2), lobe
Mixer (3), tail bone (4), supporting plate (5) and self-locking silk braid (6),
The flat segments (2) connect with the mounting flange side (1) and the lobed mixer (3) respectively, and the tail bone (4) is logical
It crosses the supporting plate (5) to be connected on the flat segments (2), the self-locking silk braid (6) is set to the tail bone (4) and the supporting plate
(5) junction.
2. aero-engine according to claim 1 integrates exhaust structure, which is characterized in that the flat segments (2) are in pipe
Shape, the mounting flange side (1) in a ring and are connected to one end of the flat segments (2), and the lobed mixer (3) is connected to
The other end of the flat segments (2).
3. aero-engine according to claim 2 integrates exhaust structure, which is characterized in that the quantity of the supporting plate (5)
To be multiple, one end of multiple supporting plates (5) is connected on the medial surface of the flat segments (2), multiple supporting plates (5) it is another
One end is all connected on the tail bone (4).
4. aero-engine according to claim 3 integrates exhaust structure, which is characterized in that the tail bone (4) includes big
The other end at diameter end and tip, multiple supporting plates (5) is all connected to the larger diameter end of the tail bone (4), the tail
The lobed mixer (3) is stretched out at the tip of vertebra (4).
5. aero-engine according to claim 4 integrates exhaust structure, which is characterized in that the supporting plate (5) passes through institute
The larger diameter end for stating tail bone (4) is provided with self-locking silk braid (6) in the end that the supporting plate (5) is pierced by the tail bone (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811530655.4A CN109356746A (en) | 2018-12-14 | 2018-12-14 | Aero-engine integrates exhaust structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811530655.4A CN109356746A (en) | 2018-12-14 | 2018-12-14 | Aero-engine integrates exhaust structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109356746A true CN109356746A (en) | 2019-02-19 |
Family
ID=65329614
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811530655.4A Pending CN109356746A (en) | 2018-12-14 | 2018-12-14 | Aero-engine integrates exhaust structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109356746A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110939530A (en) * | 2019-11-14 | 2020-03-31 | 西安航天动力研究所 | Mixed flame stabilizing device |
| CN111981510A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Lobe mixer capable of generating swirling jet flow |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454234A (en) * | 2014-12-10 | 2015-03-25 | 南京航空航天大学 | Structure for increasing thrust by outflow from turbofan central cone |
| CN106801649A (en) * | 2017-01-23 | 2017-06-06 | 中国航发沈阳发动机研究所 | A kind of plug axisymmetric nozzle |
| CN106870200A (en) * | 2017-02-16 | 2017-06-20 | 中国航发沈阳发动机研究所 | A kind of axial symmetry plug nozzle of subregion cooling |
| CN108757216A (en) * | 2018-07-10 | 2018-11-06 | 西北工业大学 | A kind of petal-shaped noise reduction D-shaped vector spray |
-
2018
- 2018-12-14 CN CN201811530655.4A patent/CN109356746A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454234A (en) * | 2014-12-10 | 2015-03-25 | 南京航空航天大学 | Structure for increasing thrust by outflow from turbofan central cone |
| CN106801649A (en) * | 2017-01-23 | 2017-06-06 | 中国航发沈阳发动机研究所 | A kind of plug axisymmetric nozzle |
| CN106870200A (en) * | 2017-02-16 | 2017-06-20 | 中国航发沈阳发动机研究所 | A kind of axial symmetry plug nozzle of subregion cooling |
| CN108757216A (en) * | 2018-07-10 | 2018-11-06 | 西北工业大学 | A kind of petal-shaped noise reduction D-shaped vector spray |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110939530A (en) * | 2019-11-14 | 2020-03-31 | 西安航天动力研究所 | Mixed flame stabilizing device |
| CN111981510A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Lobe mixer capable of generating swirling jet flow |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109356746A (en) | Aero-engine integrates exhaust structure | |
| CN103635658B (en) | The rectifying device of gas-turbine structural member | |
| CN103620165B (en) | Turbine set blower-casting | |
| US9481470B2 (en) | Intermediate structure for independently de-mountable propulsion components | |
| CN101522524B (en) | Bypass turbojet engine nacelle | |
| EP3009649B1 (en) | Integrated outer flowpath ducting and front frame system for use in a turbofan engine and method for making same | |
| WO2005100765A1 (en) | Dual inlet turboprop | |
| CA2910055A1 (en) | Composite material inlet plenum and gas turbine engine system comprising said plenum | |
| US20170175640A1 (en) | High pressure exhaust muffling device with multiple sources | |
| EP2878796B1 (en) | Engine duct and aircraft engine | |
| GB2312251A (en) | Ducted fan gas turbine engine mounting | |
| EP3574197A1 (en) | Asymmetric inlet particle separator system | |
| US20200140110A1 (en) | Fuel Oxygen Conversion Unit | |
| CN106812626B (en) | Contain casing outside a kind of engine | |
| US10184401B2 (en) | Turbojet engine suspension using a double rear support | |
| CN103080563A (en) | Flow straightener device for turbomachine | |
| US9092029B2 (en) | Vehicle monitoring system | |
| CA2565216A1 (en) | Eductor swirl buster | |
| US8240979B2 (en) | Gas turbine engine systems involving integrated fluid conduits | |
| CN102971217A (en) | Airflow-straightening structure for the nacelle of an aircraft engine | |
| EP3608230A1 (en) | Genset and method of producing a genset | |
| CN115614177A (en) | Full-shielding mixing integrated casing | |
| CN107021139B (en) | Instrument panel assembly and vehicle with it | |
| CN209129680U (en) | Turborotor divides chamber feeder | |
| RU2523729C1 (en) | Fuel supply system of unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190219 |
|
| RJ01 | Rejection of invention patent application after publication |