CN107882654A - The dual vector jet pipe of expansion segment pressure self-balancing and there is its aero-engine - Google Patents
The dual vector jet pipe of expansion segment pressure self-balancing and there is its aero-engine Download PDFInfo
- Publication number
- CN107882654A CN107882654A CN201711103242.3A CN201711103242A CN107882654A CN 107882654 A CN107882654 A CN 107882654A CN 201711103242 A CN201711103242 A CN 201711103242A CN 107882654 A CN107882654 A CN 107882654A
- Authority
- CN
- China
- Prior art keywords
- jet pipe
- expansion segment
- pressure
- adjustment sheet
- pressure adjustment
- 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
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The present invention relates to aero-engine jet pipe and exhaust technique field, specifically provide the dual vector jet pipe of expansion segment pressure self-balancing and there is its aero-engine, the vector spray installs pressure command pressure adjustment sheet in expansion segment, jet pipe wall inside and outside differential pressure is balanced by pressure adjustment sheet, reach the purpose to jet pipe component vibrationproof vibration damping, the external air flow for flowing through pressure adjustment sheet simultaneously also plays the effect for reducing jet pipe wall temperature, compared with conventional vector jet pipe, the jet pipe does not need the self-balancing of the i.e. achievable jet pipe wall face external and internal pressure of extra drive mechanism, the security reliability of vector spray significantly improves.
Description
Technical field
The present invention relates to aero-engine jet pipe and the binary in exhaust technique field, more particularly to expansion segment pressure self-balancing
Vector spray and there is its aero-engine.
Background technology
Traditional aero-engine dual vector jet pipe, large area than or the larger operating mode in deflection vector angle, spray
Pipe near wall occurs that air-flow separates, and thus brings the aerodynamic loading on flap uneven and with oscillation phenomenon
Appearance, this necessarily brings complexity to the design of vector spray structure, power transmission etc., while also the safety to jet pipe component makes
With bringing risk；In addition, separation area local temperature is very high, adjustment sheet hot-spot can be caused, impact vector jet pipe
Safe and reliable work.
The content of the invention
To overcome at least one defect existing for above-mentioned prior art, the invention provides the two of expansion segment pressure self-balancing
First vector spray, including：
One canned paragraph, it is fixed on engine afterbody；
Two converging portions, described converging portion one end are connected with the canned paragraph by revolute pair；
Two expansion segments, described expansion segment one end are connected by revolute pair with the other end of the corresponding converging portion, institute
State and multiple notches are provided with expansion segment, be ladder platform position limiting structure around the notch；
Multiple pressure adjustment sheets, it is connected to the expansion segment, the pressure adjustment sheet and the notch by revolute pair
Ladder platform position limiting structure coordinate, be bonded when closing the pressure adjustment sheet with the expansion segment, when the pressure adjustment sheet
When the ambient pressure at place is higher than nozzle wall pressure, the pressure adjustment sheet is inwardly opened, and external air flow enters jet pipe, balance spray
Tube wall face inside and outside differential pressure, vibrationproof vibration damping is carried out to jet pipe wall and reduces wall temperature, the ambient pressure at the pressure adjustment sheet
During less than nozzle wall pressure, the pressure adjustment sheet is closed；
Two side walls, the sidewall symmetry are fixed on the left and right sides of the canned paragraph, and with the converging portion and institute
State and seal between expansion segment.
Preferably, the canned paragraph turns square structure for circle；
The converging portion and the expansion segment are plate-like and be symmetricly set on the both sides up and down of the canned paragraph；
The side wall is plate-like；
The pressure adjustment sheet on the same expansion segment is distributed in matrix form.
Preferably, each expansion segment has 1~600 pressure adjustment sheet, wherein axially distributed have 1~20
Row, often arranging radially distributed has 1~30.
Preferably, each expansion segment has 12 pressure adjustment sheets, wherein axially distributed have 3 rows, often arranges
It is radially distributed to have 4.
Present invention also offers the aeroplane engine of the dual vector jet pipe with expansion segment pressure self-balancing as described above
Machine.
The dual vector jet pipe of expansion segment pressure self-balancing provided by the invention and there is its aero-engine, have such as
Lower beneficial effect：
1st, jet pipe wall inside and outside differential pressure is balanced by pressure adjustment sheet, reaches the purpose to jet pipe component vibrationproof vibration damping；
2nd, the external air flow for flowing through pressure adjustment sheet also plays the effect for reducing jet pipe wall temperature；
3rd, do not need extra drive mechanism that the self-balancing of jet pipe wall face external and internal pressure, the safety of vector spray can be achieved
Reliability significantly improves.
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 shaft side figure of illustrative examples of the present invention；
Fig. 2 is a kind of shaft side figure of the expansion segment of illustrative examples of the present invention；
Fig. 3 is the sectional view that pressure adjustment sheet is closed in Fig. 1；
Fig. 4 is the sectional view that pressure adjustment sheet is in open mode in Fig. 1；
Fig. 5 is that partial pressure adjustment sheet open mode is cutd open when the dual vector jet pipe in Fig. 1 is in deflection vector state
View.
Reference：
10 canned paragraphs
20 converging portions
30 expansion segments
40 pressure adjustment sheets
50 side walls
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.
The invention provides the dual vector jet pipe of expansion segment pressure self-balancing, for balancing inside and outside nozzle divergence cone wall
Pressure difference, vibrationproof vibration damping simultaneously reduce wall temperature, are mainly used in the aero-engine with thrust vectoring function, are also applied for simultaneously
The aero-engine of similar functions or other kinds of airspace engine field.As shown in figure 1, the dual vector jet pipe includes one
The individual converging portion 20, two of canned paragraph 10, two expansion segment 30, multiple pressure adjustment sheets 40 and two side walls 50.
Supporting member of the canned paragraph 10 as dual vector jet pipe, it is fixed on engine afterbody.It is fixed in the present embodiment
Section 10 turns square structure for circle.The one end of converging portion 20 is connected by revolute pair with canned paragraph 10, realizes the regulation of nozzle throat area,
The other end is connected by revolute pair with corresponding expansion segment 30, and in the present embodiment, converging portion 20 and expansion segment 30 are plate-like and right
Claim the both sides up and down for being arranged on canned paragraph 10.Multiple notches are provided with expansion segment 30, are ladder platform position limiting structure around the notch,
Expansion segment 30 equally realizes the regulation of nozzle exit area, and ensures that engine jet pipe under different conditions is respectively provided with preferably property
Energy.Side wall 50 is symmetrically fixed on the left and right sides of canned paragraph 10, and is sealed between converging portion 20 and expansion segment 30, prevents gas
Body sprays from the both sides of the afterbody of canned paragraph 10.In the present embodiment, side wall 50 is plate-like.
As shown in Fig. 2 pressure adjustment sheet 40 is connected to expansion segment 30, the quantity and groove of pressure adjustment sheet 40 by revolute pair
Mouth quantity is identical, and the ladder platform position limiting structure of pressure adjustment sheet 40 and notch coordinates, and makes during the closing of pressure adjustment sheet 40 and expands
Section 30 is bonded, it is ensured that does not influence the aeroperformance of jet pipe while air-flow No leakage.In the present embodiment, on same expansion segment 30
Pressure adjustment sheet 40 is distributed in matrix form, and each expansion segment 30 has 1~600 pressure adjustment sheet 40, wherein axially distributed
There is 1~20 row, often arranging radially distributed has 1~30.In the present embodiment, each expansion segment 30 has 12 pressure adjustment sheets
40, wherein axially distributed have 3 rows, often arranging radially distributed has 4.
As shown in Figure 3 to Figure 4, when the ambient pressure at pressure adjustment sheet 40 is higher than nozzle wall pressure, pressure regulation
Piece 40 is inwardly opened, and external air flow enters jet pipe and flowed along inwall as shown by arrows in FIG., balances jet pipe wall inside and outside differential pressure,
The purpose of wall temperature is played to jet pipe wall vibrationproof vibration damping and reduced, ensure that jet pipe securely and reliably works, when pressure adjustment sheet 40
When the ambient pressure at place is less than nozzle wall pressure, pressure adjustment sheet 40 is closed, jet pipe now with no pressure adjustment sheet situation without
It is different.As shown in figure 5, when two expansion segments 30 carry out deflection vector to same direction, the pressure of two inwalls of expansion segment 30 is not
Together, therefore with the pressure adjustment sheet 40 on the expansion segment 30 of yawing moment homonymy open, the pressure on the expansion segment 30 of offside is adjusted
Nodal plate 40 is closed.
Present invention also offers the aeroplane engine of the dual vector jet pipe with expansion segment pressure self-balancing as described above
Machine, the engine do not need the self-balancing of the i.e. achievable jet pipe wall face external and internal pressure of extra drive mechanism, the peace of vector spray
Full reliability significantly improves.
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 (5)
1. the dual vector jet pipe of expansion segment pressure self-balancing, it is characterised in that including：
One canned paragraph (10), it is fixed on engine afterbody；
Two converging portions (20), described converging portion (20) one end are connected with the canned paragraph (10) by revolute pair；
Two expansion segments (30), the other end of described expansion segment (30) one end by revolute pair with the corresponding converging portion (20)
Connection, multiple notches each are provided with the expansion segment (30), are ladder platform position limiting structure around the notch；
Multiple pressure adjustment sheets (40), it is connected to the expansion segment (30) by revolute pair, the pressure adjustment sheet (40) with
The ladder platform position limiting structure of the notch coordinates, and is bonded when closing the pressure adjustment sheet (40) with the expansion segment (30),
When the ambient pressure at pressure adjustment sheet (40) place is higher than nozzle wall pressure, the pressure adjustment sheet (40) is inwardly beaten
To open, external air flow enters jet pipe, balances jet pipe wall inside and outside differential pressure, and vibrationproof vibration damping is carried out to jet pipe wall and reduces wall temperature, when
When the ambient pressure at pressure adjustment sheet (40) place is less than nozzle wall pressure, the pressure adjustment sheet (40) is closed；
Two side walls (50), the side wall (50) are symmetrically fixed on the left and right sides of the canned paragraph (10), and with the convergence
Sealed between section (20) and the expansion segment (30).
2. dual vector jet pipe according to claim 1, it is characterised in that the canned paragraph (10) turns square structure for circle；
The converging portion (20) and the expansion segment (30) are plate-like and be symmetricly set on up and down the two of the canned paragraph (10)
Side；
The side wall (50) is plate-like；
The pressure adjustment sheet (40) on the same expansion segment (30) is distributed in matrix form.
3. dual vector jet pipe according to claim 2, it is characterised in that each expansion segment (30) has 1~600
The individual pressure adjustment sheet (40), wherein axially distributed have 1~20 row, often arranging radially distributed has 1~30.
4. dual vector jet pipe according to claim 3, it is characterised in that each expansion segment (30) has 12 institutes
Pressure adjustment sheet (40) is stated, wherein axially distributed there are 3 rows, often arranging radially distributed there are 4.
5. aero-engine, it is characterised in that：Include the expansion segment pressure as described in any claim in Claims 1-4
The dual vector jet pipe of self-balancing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711103242.3A CN107882654A (en) | 2017-11-10 | 2017-11-10 | The dual vector jet pipe of expansion segment pressure self-balancing and there is its aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711103242.3A CN107882654A (en) | 2017-11-10 | 2017-11-10 | The dual vector jet pipe of expansion segment pressure self-balancing and there is its aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107882654A true CN107882654A (en) | 2018-04-06 |
Family
ID=61779897
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711103242.3A Pending CN107882654A (en) | 2017-11-10 | 2017-11-10 | The dual vector jet pipe of expansion segment pressure self-balancing and there is its aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107882654A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151228A (en) * | 2022-02-09 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Method for dividing binary vector spray pipe regulating sheet into discrete cold air areas |
| CN114856857A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Integrated type round-square casing with multiple channels |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103437911A (en) * | 2013-09-04 | 2013-12-11 | 北京航空航天大学 | Partition-bearing fluid control binary vector nozzle tube and vector thrust generation and control method thereof |
| CN103696875A (en) * | 2013-12-05 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Sawtooth angle-adjustable two-dimensional vectoring nozzle |
| CN104033279A (en) * | 2014-06-06 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Novel two-dimensional vector nozzle |
| CN104033281A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary vectoring nozzle with unilateral expansion function |
| CN204113490U (en) * | 2014-08-29 | 2015-01-21 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of sphere vector spray ball face sealing structure |
| US20150027102A1 (en) * | 2013-03-16 | 2015-01-29 | Patrick R.E. Bahn | Tri-propellant rocket engine for space launch applications |
| CN106194496A (en) * | 2016-08-04 | 2016-12-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of governor valve |
-
2017
- 2017-11-10 CN CN201711103242.3A patent/CN107882654A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150027102A1 (en) * | 2013-03-16 | 2015-01-29 | Patrick R.E. Bahn | Tri-propellant rocket engine for space launch applications |
| CN103437911A (en) * | 2013-09-04 | 2013-12-11 | 北京航空航天大学 | Partition-bearing fluid control binary vector nozzle tube and vector thrust generation and control method thereof |
| CN103696875A (en) * | 2013-12-05 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Sawtooth angle-adjustable two-dimensional vectoring nozzle |
| CN104033279A (en) * | 2014-06-06 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Novel two-dimensional vector nozzle |
| CN104033281A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary vectoring nozzle with unilateral expansion function |
| CN204113490U (en) * | 2014-08-29 | 2015-01-21 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of sphere vector spray ball face sealing structure |
| CN106194496A (en) * | 2016-08-04 | 2016-12-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of governor valve |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151228A (en) * | 2022-02-09 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Method for dividing binary vector spray pipe regulating sheet into discrete cold air areas |
| CN114856857A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Integrated type round-square casing with multiple channels |
| CN114856857B (en) * | 2022-05-12 | 2023-06-13 | 中国航发四川燃气涡轮研究院 | Multi-channel integrated round-square casing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107401956A (en) | Amphibious cruise missile and its attitude control method based on venturi offset fluidic vectoring nozzle | |
| CN107882654A (en) | The dual vector jet pipe of expansion segment pressure self-balancing and there is its aero-engine | |
| CN104760703B (en) | A kind of punching engine cooling body | |
| CN106184719B (en) | A kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle | |
| ITTO20110122A1 (en) | AIRCRAFT CONFIGURATION TO IMPROVED AERODYNAMIC PERFORMANCES. | |
| EP3147210B1 (en) | Unmanned helicopter | |
| CN103057694A (en) | Open type control surface for Coanda effect aircraft | |
| US11254437B2 (en) | Aircraft engine assembly | |
| CN113247279B (en) | Scheme for realizing separation of hypersonic air inlet duct fairing by utilizing gap flow | |
| US20120112011A1 (en) | Casing for a lifting aid | |
| CN105083565B (en) | Propulsion assembly and aircraft for aircraft | |
| JP2006056364A (en) | Vertical take-off/landing aircraft | |
| CN107882653A (en) | Expansion segment pressure self-balancing axisymmetric vectoring exhaust nozzle and there is its aero-engine | |
| CN106014684A (en) | Combined flow control method and structure for improving SERN for TBCC | |
| CN103381883A (en) | Overpressure door for aircraft | |
| CN103101625B (en) | Noise suppression device of high frequency pulse jet weapon cabin | |
| CN206141808U (en) | Horn subassembly and aircraft of aircraft | |
| CN106194496A (en) | A kind of governor valve | |
| CN107618661A (en) | Short distance vertically taking off and landing flyer based on venturi offset fluidic vectoring nozzle | |
| EP2995552A1 (en) | Chamber in an airfoil | |
| CN105464838B (en) | Method and apparatus for being deflected by dynamicthrust guiding and plume | |
| CN103600844B (en) | Produce the combination aircraft of greater lift | |
| CN109723571B (en) | Throat offset type pneumatic thrust vectoring nozzle with trapezoidal section and aircraft equipped with same | |
| CN114087087B (en) | Multi-principle multi-mode pneumatic thrust vectoring nozzle and control method | |
| CN113247276B (en) | Two-stage pneumatic separation type hypersonic air inlet duct fairing |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180406 |