CN106014683B - A kind of TBCC SERN structures of band supercharging flow control apparatus - Google Patents
A kind of TBCC SERN structures of band supercharging flow control apparatus Download PDFInfo
- Publication number
- CN106014683B CN106014683B CN201610378297.4A CN201610378297A CN106014683B CN 106014683 B CN106014683 B CN 106014683B CN 201610378297 A CN201610378297 A CN 201610378297A CN 106014683 B CN106014683 B CN 106014683B
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- Prior art keywords
- expansion
- unilateral
- shaped
- unicom pipeline
- sern
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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
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The present invention relates to a kind of TBCC SERN structures of band supercharging flow control apparatus, it includes the lower wall surface of single expansion ramp nozzle, the contraction section of monocline surface expansion pipe and the unilateral expansion arc of monocline surface expansion pipe；Also include the band supercharging flow device being arranged on the unilateral expansion arc of monocline surface expansion pipe；The booster that described band supercharging flow device includes U-shaped unicom pipeline and is arranged on U-shaped unicom pipeline, and, the front port of U-shaped unicom pipeline is placed in oblique shock wave and before the intersection point of the unilateral expansion arc of monocline surface expansion pipe, the rear port of U-shaped unicom pipeline is placed in after the intersection point of oblique shock wave and the unilateral expansion arc of monocline surface expansion pipe.Pass through the pressurization to flowing through intercommunicating device air-flow, it is extracted throughput more in shunting zone, then sprayed by front port with larger speed, so both Disengagement zone scope is caused to greatly reduce, even eliminate, cause shock-wave spot reach again, the static pressure distribution of main flow is changed, improved expansion work operating mode.
Description
Technical field
The present invention relates to aero-engine technology field, especially a kind of band applied to hypersonic aircraft flows control
The single expansion ramp nozzle structure of system, it can specifically realize that jet pipe crosses the recovery of expansion lower thrust coefficient and pitching moment control
Nozzle structure.
Background technology
At present, begun to appear in from the figure of the mankind on sky, the requirement to flight just increasingly increases.Especially step into
Since 21 century, the low cost of space loading is delivered, the rapid strike of overlength distance target and the high speed of global range is transported
Defeated, a variety of such targets all cause people increasingly to expand long-range, high-speed aircraft demand, are such as sent out with turboram
Motivation (TBCC) is the high-speed aircraft of power.This kind of hypersonic aircraft is the generation after propeller and jet plane
The third time revolution of appearance in boundary's aviation history, and the technology commanding elevation of this century aerospace field, carry out hypersonic
Aircraft studies forward-looking, strategic and drive property, military, economy and civilization of human society will be produced immeasurable
Profound influence.
Following supersonic speed/hypersonic aircraft is a propulsion plant and the highly integrated system of aircraft fuselage,
The influence of this important composition Components on Engine Performance of ejector exhaust pipe is must take into consideration in the integrated design of aircraft.Exhaust
Jet pipe is the main generating means of motor power, and in flight Mach number 6, thrust is up to engine gross thrust caused by it
70% or so, the quality of ejector exhaust pipe design directly influences the performance of whole engine.Due to supersonic speed/hypersonic flight
The broad flight envelope of device, in order to reach best jet pipe internal performance, it is desirable to the blow down ratio of jet pipe reaches hundreds of or even thousands of,
Expansion ratio reaches tens.There is the problems such as mechanical restriction and sealing mechanism of expanding noodles in traditional axisymmetric nozzle, this to spray
The maximum expansion ratio of pipe can not meet above-mentioned requirements.In order to solve this problem, gas extraction system is usually using the spray of single expansion inclined-plane
The form of (single Expansion Ramp Nozzle, abbreviation SERN) is managed, the distinctive advantages of SERN are：Body after aircraft
Lower surface can obtain very high expansion ratio as SERN outer expansion inclined-plane；SERN declined board is relatively short,
The integration of it and aircraft can greatly reduce the weight of propulsion system.In addition, SERN is easier to realize relative to traditional jet pipe
Thruster vector control and deboost, to improve the mobility of aircraft：SERN can also reduce noise, reduce infrared target
Characteristic, improve the survival ability of aircraft.Because SERN design Mach number and design expansion ratio are all very high, and working range
Very broad, under low flight Mach number and low blow down ratio (transonic speed stage), stream will be in expansion shape in jet pipe
State, the performance of jet pipe significantly deteriorate, and thrust coefficient is greatly reduced.How low pressure ratio under the conditions of big expansion ratio SERN property is improved
A urgent problem to be solved can be become.Numerous studies are carried out for this problem both at home and abroad, it is proposed that many solution party
Case, wherein most schemes need complicated Machinery Control System, but mechanical system can increase the weight of engine, make jet pipe
Moving component in high temperature environments increases, and aggravates cooling system burden, improves design cost, and can increase radar reflection face
Product, reduce the Stealth Fighter of aircraft.
In view of drawbacks described above, creator of the present invention obtains this creation finally by prolonged research and practice.
The content of the invention
In order to overcome the technical deficiency that hypersonic aircraft occurs in the transonic speed stage, realize superb in the range of whole envelope
Velocity of sound single expansion ramp nozzle (SERN) high performance operation, the invention provides a kind of list of band supercharging flow control apparatus
Inclined-plane expansion nozzle structure；The structure keep hypersonic aircraft highly fly/send out advantage integrated on the premise of, merge
Active Flow Control technology, it is real using simple pipeline and supercharging device on the premise of unobvious increase required control energy
The control of oblique shock wave position when now crossing swelling state, so improve pressure distribution of the jet pipe on monocline face and thrust performance with
And pitching performance, so as to which the high aeroperformance of high supersonic velocity aircraft exhaust system can be realized.
To achieve the above object, the present invention provides a kind of TBCC SERN structures of band supercharging flow control apparatus, and it is wrapped
Include the lower wall surface of single expansion ramp nozzle, the contraction section of single expansion ramp nozzle and the unilateral expansion arc of single expansion ramp nozzle；Also
Band including being arranged on the unilateral expansion arc of single expansion ramp nozzle is pressurized flow device；
The booster that described band supercharging flow device includes U-shaped unicom pipeline and is arranged on U-shaped unicom pipeline, and
And the front port of U-shaped unicom pipeline is placed in before the intersection point of oblique shock wave and the unilateral expansion arc of single expansion ramp nozzle, U-shaped UNICOM
The rear port of pipeline is placed in after the intersection point of oblique shock wave and the unilateral expansion arc of single expansion ramp nozzle.
Further, the position of described U-shaped unicom pipeline sets the intersection point for making shock wave and unilateral expansion arc to be in U-shaped
At circulation passage place-centric.
Further, the pressure ratio of described booster is 1.02-1.05, by the pressurization to flowing through intercommunicating device air-flow,
Throughput more in shunting zone is extracted, is then sprayed by front port with larger speed.
Compared with prior art, beneficial effects of the present invention are：The present invention is mainly based upon flow control technique, for changing
The kind hypersonic propulsion system of air suction type transonic speed thrust performance in itself and propose；Be intended to eliminate at this boundary-layer separation,
Improve flow field quality, cause boundary-layer flows about to change using the supercharging flow control apparatus of proposition.By to flowing through
The pressurization of intercommunicating device air-flow, throughput more in shunting zone is extracted, is then sprayed by front port with larger speed
Go out, so both Disengagement zone scope is greatly reduced, is even eliminated, cause shock-wave spot reach again, change the static pressure of main flow
Distribution, improved expansion work operating mode.When hypersonic aircraft is operated under other operating modes, closing supercharging device is
Can, now the pressure difference very little between communication passage front and back end portses, is not in the part refluence by rear port to front port, also not
The working characteristics of jet pipe can be had an impact.
Brief description of the drawings
Fig. 1 is TBCC SERN structures and the high-speed aircraft entirety structure with supercharging flow control apparatus of the present invention
Figure；
Fig. 2 is the partial enlarged drawing of the TBCC SERN structures with supercharging flow control apparatus of the present invention.
Embodiment
Below in conjunction with accompanying drawing, the forgoing and additional technical features and advantages are described in more detail.
Refer to shown in Fig. 1, it has the TBCC SERN structures and the high speed that are pressurized flow control apparatus for the present invention's
Aircraft entirety composition, it includes the lower wall surface 4 of single expansion ramp nozzle, the contraction section 6 of single expansion ramp nozzle and monocline face
The unilateral expansion arc 5 of expansion nozzle；Also include the band supercharging flow device being arranged on the unilateral expansion arc 5 of single expansion ramp nozzle.
Band supercharging flow device in the present embodiment includes U-shaped unicom pipeline 7 and the increasing being arranged on U-shaped unicom pipeline 7
Depressor 8, also, the front port of U-shaped unicom pipeline 7 be placed in oblique shock wave and the unilateral expansion arc 5 of single expansion ramp nozzle intersection point it
Before, the rear port of U-shaped unicom pipeline 7 is placed in after the intersection point of oblique shock wave and the unilateral expansion arc 5 of single expansion ramp nozzle.
Shock wave and the intersection point of unilateral expansion arc is set to be in U-shaped communication passage preferably, the position of U-shaped unicom pipeline 7 is set
At place-centric.
The supercharging device of the present embodiment, it is the compression device that pressure ratio is about 1.02-1.05, by flowing through intercommunicating device
The pressurization of air-flow, throughput more in shunting zone is extracted, is then sprayed by front port with larger speed.
Incorporated by reference to shown in Fig. 1, in embodiments of the present invention, the contraction section 6 and monocline surface expansion of single expansion ramp nozzle spray
Unilateral expansion arc is managed in the bottom of hypersonic aircraft covering 1；Hypersonic aircraft air intake duct 2 covers in hypersonic aircraft
The bottom of skin 1；Scramjet engine 3 be arranged on single expansion ramp nozzle lower wall surface 4 and hypersonic aircraft covering 1 it
Between.
In the present embodiment, start the booster 8 of the flow control apparatus with supercharging, flow field quality, lifting can be improved
Jet pipe aeroperformance, rear port of the fraction Jing Guo U-shaped communication passage 7 are flowed out (incorporated by reference to arrow side shown in Fig. 2 from preceding port
To), and then part reduces the size of Disengagement zone after shock wave, weakens the intensity of separation shock wave, and sprayed from U-shaped communication passage 7
The high-voltage high-speed airflow gone out will change the position of oblique shock wave, the intersection point of its expansion arc 5 unilateral with single expansion ramp nozzle is moved forward.
Incorporated by reference to shown in Fig. 2, when rear port of the air-flow Jing Guo U-shaped communication passage 7 flows out from preceding port, monocline surface expansion is sprayed
The static pressure of pipe main flow has been lifted, weakened expansion work adverse effect, so as to lifted the aeroperformance of monocline face jet pipe,
Weaken the influence of pitching moment.Can also be by regulating and controlling the pressure ratio of booster 8, to realize that single expansion ramp nozzle is different deep
The flow field spent under swelling state improves.In addition, if hypersonic aircraft departs from transonic operating condition, it is however generally that monocline face
Expansion nozzle also crosses expansion operating mode departing from serious, then booster 8 is now closed, due to the front and back end of communication passage 7
Mouth pressure difference is smaller, and the presence of the device can't produce obvious influence to single expansion ramp nozzle.
The operation principle of the embodiment of the present invention is as follows：
When hypersonic aircraft is operated in transonic operating condition, the blow down ratio of single expansion ramp nozzle is only 8-15, far
Less than the design blow down ratio (about 300 or so) of jet pipe, and serious expansion operating mode excessively is in, by single expansion ramp nozzle lower wall surface
The oblique shock wave stronger together that lip is sent intersects with the unilateral expansion arc of jet pipe, causes separation, the deterioration in flow field of boundary-layer,
Now in addition to it more obvious thrust loss be present, the pitching moment that also can not ignore jet pipe occurs.
It is contemplated that eliminate the boundary-layer separation at this, improve flow field quality, using the supercharging flowing control dress of proposition
Put so that boundary-layer flows about changes.
Because air-flow entered hydrostatic lifting after shock wave, the air-flow in boundary-layer Disengagement zone is high pressure low speed flow, in pressure difference
In the presence of power, the fraction in boundary-layer enters communication passage rear port and sprayed from front port, influences oblique shock wave and divides
From the form of shock wave, so as to change the released state of boundary-layer.However, simple is sharp to regulate and control by supercharging of the shock wave to air-flow
The effect of wave morphology does not protrude
Therefore supercharging device is added in U-shaped communication passage in the present embodiment, the device is that pressure ratio is about 1.02-1.05
Compression device, by the pressurization to flowing through intercommunicating device air-flow, be extracted throughput more in shunting zone, then pass through
Front port is sprayed with larger speed, is so both caused Disengagement zone scope to greatly reduce (as shown in Figure 2), even eliminate, is made again
Shock-wave spot reach is obtained, the static pressure distribution of main flow is changed, improved expansion work operating mode.Worked in hypersonic aircraft
When under other operating modes, close supercharging device, the now pressure difference very little between communication passage front and back end portses, be not in by
The part of rear port to front port is flow backwards, and also the working characteristics of jet pipe will not be had an impact.
Above-mentioned detailed description is illustrating for one of them possible embodiments of the present invention, and the embodiment is simultaneously not used to
The scope of the claims of the present invention is limited, all equivalence enforcements or change without departing from carried out by the present invention, is intended to be limited solely by the technology of the present invention
In the range of scheme.
Claims (3)
1. a kind of TBCC SERN structures of band supercharging flow control apparatus, it includes the lower wall surface of single expansion ramp nozzle, list
The contraction section and the unilateral expansion arc of monocline surface expansion pipe of inclined-plane expansion tube, it is characterised in that also include being arranged on monocline surface expansion
Manage the band supercharging flow device on unilateral expansion arc；
The booster that described band supercharging flow device includes U-shaped unicom pipeline and is arranged on U-shaped unicom pipeline, also, it is U-shaped
The front port of unicom pipeline is placed in before the intersection point of oblique shock wave and the unilateral expansion arc of monocline surface expansion pipe, after U-shaped unicom pipeline
Port is placed in after the intersection point of oblique shock wave and the unilateral expansion arc of monocline surface expansion pipe.
2. the TBCC SERN structures of band supercharging flow control apparatus according to claim 1, it is characterised in that described
The position of U-shaped unicom pipeline, which is set, makes shock wave and the intersection point of unilateral expansion arc be at U-shaped communication passage place-centric.
3. the TBCC SERN structures of band supercharging flow control apparatus according to claim 1 or 2, it is characterised in that institute
The pressure ratio for the booster stated is 1.02-1.05, by the pressurization to flowing through intercommunicating device air-flow, makes air-flow more in shunting zone
Amount is extracted, and is then sprayed by front port with larger speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610378297.4A CN106014683B (en) | 2016-05-30 | 2016-05-30 | A kind of TBCC SERN structures of band supercharging flow control apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610378297.4A CN106014683B (en) | 2016-05-30 | 2016-05-30 | A kind of TBCC SERN structures of band supercharging flow control apparatus |
Publications (2)
| Publication Number | Publication Date |
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| CN106014683A CN106014683A (en) | 2016-10-12 |
| CN106014683B true CN106014683B (en) | 2018-04-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610378297.4A Expired - Fee Related CN106014683B (en) | 2016-05-30 | 2016-05-30 | A kind of TBCC SERN structures of band supercharging flow control apparatus |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108678873A (en) * | 2018-03-08 | 2018-10-19 | 西北工业大学 | A kind of scramjet engine scheme of variable geometry combustor |
| CN109184952B (en) * | 2018-08-21 | 2019-06-18 | 西安理工大学 | A kind of hypersonic inlet not self-holding ability quantitative analysis method in starting state Disengagement zone |
| CN111594340B (en) * | 2020-04-30 | 2022-01-11 | 南京理工大学 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
| CN117227987B (en) * | 2023-11-14 | 2024-03-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Unilateral expansion tail spray groove integrally designed with control surface |
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| US6857600B1 (en) * | 2002-04-26 | 2005-02-22 | General Electric Company | Infrared suppressing two dimensional vectorable single expansion ramp nozzle |
| CN102251879A (en) * | 2011-06-09 | 2011-11-23 | 北京航空航天大学 | Differential adjustable unilateral expansion nozzle |
| FR2987081A1 (en) * | 2012-02-21 | 2013-08-23 | Snecma | Propulsion assembly for aerospace machine, has rocket engines forming ejectors to accelerate air flow in channel at supersonic speed, and conduit provided in interior wall downstream from output opening of channel |
| CN103899433A (en) * | 2014-03-31 | 2014-07-02 | 西北工业大学 | Novel thrust vectoring nozzle structure adopting shock vectoring controlling |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9009966B2 (en) * | 2013-03-15 | 2015-04-21 | Northrop Gurmman Systems Corporation | Internal/external single expansion ramp nozzle with integrated third stream |
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2016
- 2016-05-30 CN CN201610378297.4A patent/CN106014683B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6857600B1 (en) * | 2002-04-26 | 2005-02-22 | General Electric Company | Infrared suppressing two dimensional vectorable single expansion ramp nozzle |
| CN102251879A (en) * | 2011-06-09 | 2011-11-23 | 北京航空航天大学 | Differential adjustable unilateral expansion nozzle |
| FR2987081A1 (en) * | 2012-02-21 | 2013-08-23 | Snecma | Propulsion assembly for aerospace machine, has rocket engines forming ejectors to accelerate air flow in channel at supersonic speed, and conduit provided in interior wall downstream from output opening of channel |
| CN103899433A (en) * | 2014-03-31 | 2014-07-02 | 西北工业大学 | Novel thrust vectoring nozzle structure adopting shock vectoring controlling |
Non-Patent Citations (1)
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| 二次流喷射对喷管流场性能的影响;刘爱华，王占学;《二次流喷射对喷管流场性能的影响》;20070430;第28卷(第2期);144-147 * |
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| CN106014683A (en) | 2016-10-12 |
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