CN102251879A - Differential adjustable unilateral expansion nozzle - Google Patents
Differential adjustable unilateral expansion nozzle Download PDFInfo
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- CN102251879A CN102251879A CN2011101544540A CN201110154454A CN102251879A CN 102251879 A CN102251879 A CN 102251879A CN 2011101544540 A CN2011101544540 A CN 2011101544540A CN 201110154454 A CN201110154454 A CN 201110154454A CN 102251879 A CN102251879 A CN 102251879A
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- adjustable
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Abstract
The invention provides a differential adjustable unilateral expansion nozzle. In the invention, a nozzle throat area is bilaterally adjustable and differential adjustment can be carried out to ensure that an engine flow variation requirement is satisfied in a whole flight envelope; an nozzle exit area is adjustable to ensure that a gas ideal complete expansion requirement can be satisfied in a certain flight Mach number range; and the upper web of a nozzle is divided into an adjustable upper web and a fixed upper web between which a certain gap exists and the after body of an aircraft can be directly utilized by the fixed upper web so that that the operating force of a movement mechanism can be reduced. A boundary layer discharged from a front fuselage can be injected into the fixed upper web through the gap under the flight conditions of transonic speed and low supersonic speed; and therefore, the wall static pressure of the fixed upper web is increased, the thrust loss caused by airflow overexpansion is decreased, meanwhile, the pitching moment of the aircraft is reduced and the nozzle is ensured to always achieve a higher thrust coefficient in the broad flight envelope, in addition, the cooling of the fixed upper web can be strengthened and the thermal load and the infrared signal characteristic of the nozzle are reduced.
Description
Technical field
The present invention relates to the adjustable monolateral expansion jet pipe of differential type.
Technical background
It is " revolution " for the third time on World Airways history after propeller cavitation and the jet airplane that hypersonic aircraft is described as, it also is the technology commanding height of 21st century aerospace field, carry out forward-looking, the strategic and drive property of hypersonic aircraft research, will produce immeasurable profound influence military affairs, economy and civilization of human society.
Can power plant be the main key technologies that realize hypersonic flight.In order to take into account the composite request of Security, Economy and fighting efficiency, adopting airbreathing motor is the very broad (height 0～40km or higher of flight envelope of the hypersonic aircraft of power, the aircraft Mach number from infrasound, stride sound, ultrasound velocity is to hypersonic), this requires aircraft/propulsion system/jet pipe to carry out integrated design.Monolateral expansion jet pipe (SERN) is because the back body lower surface that directly uses aircraft as outer expanding noodles, makes it have unique ability that satisfies big expansion ratio.And the non-symmetry structure of SERN, make it when non-design height flies, jet pipe has certain self adaptive-compensating characteristic.These advantages make monolateral expansion jet pipe become the most possible jet pipe type that adopts of following hypersonic aircraft.
In general, monolateral expansion jet pipe has following six big characteristics:
The jet pipe blow down ratio is very big, reaches three figure places;
Nozzle throat area (A
8) excursion is very big;
Nozzle exit area (A
9) and A
9/ A
8Excursion is very big;
Flow by jet pipe is big, and excursion is big;
The heat load height of jet pipe;
Require jet pipe in the flight envelope of broadness, to have higher thrust coefficient.
In fact, except this " four big two-supremes ", consider the actual installation and the use of jet pipe, also should be from intake duct, the coupling angle of motor and jet pipe and with aspect comprehensive study Design of Exhaust System such as body integrated design.
Summary of the invention
In order to satisfy jet pipe groundwork state and thrust performance requirement, the present invention proposes the solution of the adjustable monolateral expansion jet pipe of a kind of differential type.At design point exit area ratio A
9/ A
8Reach 8, blow down ratio is about 100, can satisfy the high blow down ratio requirement of big expansion ratio; Nozzle throat area (A
8) bilateral adjustable and can implement differential type and regulate, in whole flight envelope, all satisfy the requirement of motor changes in flow rate; Nozzle exit area (A
9) adjustable, in certain flight Mach number scope, can satisfy the desirable complete expansion requirement of combustion gas; The epiplastron of jet pipe is divided into adjustable epiplastron and fixing epiplastron, has certain clearance between the two, and wherein fixedly epiplastron directly utilizes body behind the aircraft, can reduce the steering force of motion like this.Transonic speed with under the low supersonic flight condition can inject to fixing epiplastron by the gap and letting out the boundary layer of removing from forebody, can improving fixedly like this, thereby the wall static pressure of epiplastron reduces the thrust loss that the air-flow overexpansion causes, reduce the pitch moment of aircraft simultaneously, guaranteed that jet pipe has higher thrust coefficient in the flight envelope of broadness; Can strengthen cooling in addition, reduce the heat load and the infrared signal feature of jet pipe holding part.
According to an aspect of the present invention, provide a kind of differential type adjustable monolateral expansion jet pipe, it is characterized in that comprising: rotating component fixedly casing, on/down convergence regulator plate, bottom web, adjustable epiplastron, fixedly epiplastron and a left side/right sideboard.
Description of drawings
Fig. 1 is the structure of the adjustable monolateral expansion jet pipe of differential type.
Fig. 2 is a jet pipe actuating system schematic representation.
Fig. 3 is rotating component fixedly casing structure and erection drawing.
Fig. 4 is last/following convergence regulator plate tectonic maps.
Fig. 5 is bottom web structure and erection drawing.
Fig. 6 is adjustable epiplastron tectonic maps.
Embodiment
Jet pipe conceptual scheme according to an embodiment of the invention is seen Fig. 1, install before its jet pipe comprises limit (1), circle torque changeover portion (2), back install limit (3), rotating component fixedly casing (4), on/restrain regulator plate (5), bottom web (6), adjustable epiplastron (7), fixedly epiplastron (8), a left side/right sideboard (9), supporting traverse (10) and stepper motor (11) etc. down.
Actuating system
As shown in Figure 2, actuating system according to an embodiment of the invention comprises stepper motor (11), multidiameter shaft (12), fitting seat (13), miniature bearing (14), fixedly conduit (15) and double end pull bar (16), wherein stepper motor (11) passes to multidiameter shaft (12) by the fitting seat (13) that is attached thereto with axial displacement, and multidiameter shaft (12) drives miniature bearing (14) in fixedly upward rolling of conduit (15) when axially moving.One end of double end pull bar (16) is connected with multidiameter shaft (12) by revolute, and the other end is connected by the 4th bearing pin (17) with suspension hook (18) in convergence regulator plate (5).Stepper motor (11) is when doing axial displacement, nozzle throat area (A
8) and nozzle exit area (A
9) change according to certain rules.
Rotating component is casing fixedly
According to one embodiment of present invention, as shown in Figure 3, rotating component fixedly casing (4) comprises/combination of lower frame (19) and a left side/right frame (20), is the important load parts of whole motion.As can be seen from Figure 3 rotating component fixedly casing (4) and a left side/right sideboard (9) and on/assembly relation of convergence regulator plate (5) down, on/down a left side/right double end the hanger (22) on the convergence regulator plate (5) by first bearing pin (21) and rotating component fixedly casing (4) be connected.
On/following convergence regulator plate
As shown in Figure 4, on according to an embodiment of the invention/convergence regulator plate (5) comprises base plate (23), a left side/right double end hanger (22), support hanger (24) and suspension hook (18) down.On/down convergence regulator plate (5) front end with a left side/right double end hanger (22) by first bearing pin (21) and rotating component fixedly casing (4) be connected, on/under restrain regulator plate (5) rear end and pass through second bearing pin (25) and be connected with bottom web (6) with adjustable epiplastron (7) respectively.When stepper motor (11) when axially moving forward, on/convergence regulator plate (5) is realized nozzle throat area (A around first bearing pin (21) rotation down
8) diminish; Work as A
8When becoming big, the aerodynamic force in the jet pipe is passed to multidiameter shaft (12) by regulator plate by double end pull bar (16), and the steering force by stepper motor (11) comes balance again.The minimum and maximum throat area ratio of jet pipe is about 3.
Bottom web
As shown in Figure 5, bottom web according to an embodiment of the invention (6) comprises support hanger (24), base plate (26) and support (27).The as can be seen from Figure 5 assembly relation of bottom web (6) and chute (28) and a left side/right sideboard (9).Support (27) is installed in base plate (26) neutral position, and chute (28) is fixed on a left side/right sideboard (9), and the 3rd bearing pin (29) passes support (27) and cooperates with miniature bearing (30).Miniature bearing (30) rolled in chute (28) when bottom web (6) front end rotated around second bearing pin (25), and the effect of wherein cotter pin (31) is to prevent that miniature bearing (30) from coming off from the 3rd bearing pin (29).The established angle of chute (28) is to nozzle exit area (A
9) bigger influence arranged: when chute (28) when vertically placing, A in whole motion process
9Remain unchanged; When chute (28) horizontal positioned, A at this moment
9The excursion maximum.Take all factors into consideration A
9Excursion and the influence of jet pipe extrernal resistance, established angle is got 30 ° in a specific embodiment.
Adjustable epiplastron
As shown in Figure 6, adjustable epiplastron according to an embodiment of the invention (7) comprises support hanger (24), base plate (32) and slide block (33).When last convergence regulator plate (5) was done the folding and unfolding campaign of venturi, adjustable epiplastron (7) front end was done angular motion its rear end slide block (33) and is done and follow slip.Adjustable epiplastron (7) and fixedly have certain clearance between the epiplastron (8), as shown in Figure 1.Its size is along with throat area (A
8) diminish and diminish, reach minimum in design point state (throat area minimum) gap.The off-design point state particularly transonic speed with low supersonic flight condition under, the gap is bigger, can inject from forebody and let out the boundary layer of removing, can reduce the thrust loss that the air-flow overexpansion causes like this, reduce the pitch moment of aircraft simultaneously, can reduce the heat load of jet pipe in addition.
Fixing epiplastron
Fixedly epiplastron according to an embodiment of the invention (8) is the box-like structure that a section is similar to rectangle as shown in Figure 1, and its lower surface is as the outer expanding noodles of air-flow.In the middle of it is cavity, and longshore current is to having adopted many (as 3) strengthening rib to guarantee its rigidity.Fixedly epiplastron (8) as one independently cell cube directly connect and fix with a left side/right sideboard (9), simple and reliable for structure.
Left side plate and supporting traverse
Referring to Fig. 1.Because nozzle throat area (A
8) and discharge area (A
9) adjustable, a left side/right sideboard (9) with last/down convergence regulator plate (5), bottom web (6) and adjustable epiplastron (7) must the maintenance certain clearance; In a specific embodiment of the present invention, this gap is 1mm.Wherein a left side/right sideboard (9) and rotating component fixedly casing (4), fixedly epiplastron (8) is connected by set screw with supporting traverse (10).The configuration of a left side/right sideboard (9) has bigger influence to nozzle performance, and in a specific embodiment of the present invention, the shape of a left side/right sideboard (9) obtains by the CFD calculation optimization, and it has taken into account jet pipe weight and thrust performance demands.
Claims (10)
1. the adjustable monolateral expansion jet pipe of differential type is characterized in that comprising:
Rotating component is casing (4) fixedly;
On/following convergence regulator plate (5);
Bottom web (6);
Adjustable epiplastron (7);
Fixing epiplastron (8);
A left side/right sideboard (9).
2. according to the adjustable monolateral expansion jet pipe of the differential type of claim 1, it is characterized in that rotating component fixedly casing (4) comprising:
On/lower frame (19),
A left side/right frame (20),
Wherein go up/descend on the convergence regulator plate (5) a left side/right double end hanger (22) by first bearing pin (21) and rotating component fixedly casing (4) be connected.
3. according to the adjustable monolateral expansion jet pipe of the differential type of claim 2, it is characterized in that/descend that convergence regulator plate (5) comprising:
Base plate (23),
A described left side/right double end hanger (22),
Support hanger (24),
Suspension hook (18),
Wherein, on/down convergence regulator plate (5) front end with a left side/right double end hanger (22) by first bearing pin (21) and rotating component fixedly casing (4) be connected, on/under restrain regulator plate (5) rear end and pass through second bearing pin (25) and be connected with bottom web (6) with adjustable epiplastron (7) respectively.
4. according to the adjustable monolateral expansion jet pipe of the differential type of claim 3, it is characterized in that further comprising actuating system, described actuating system comprises:
Stepper motor (11),
Multidiameter shaft (12),
Fitting seat (13),
Miniature bearing (14),
Fixing conduit (15),
Double end pull bar (16),
When stepper motor (11) when axially moving forward, on/convergence regulator plate (5) is realized nozzle throat area (A around first bearing pin (21) rotation down
8) diminish; Work as A
8When becoming big, the aerodynamic force in the jet pipe is passed to multidiameter shaft (12) by regulator plate by double end pull bar (16), and the steering force by stepper motor (11) comes balance again.
5. according to the adjustable monolateral expansion jet pipe of the differential type of claim 4, it is characterized in that the minimum and maximum throat area ratio of jet pipe is about 3.
6. according to the adjustable monolateral expansion jet pipe of the differential type of claim 5, it is characterized in that bottom web (6) comprising:
Support hanger (24),
Base plate (26),
Support (27), described support (27) are installed in base plate (26) neutral position,
Be fixed on the chute (28) on a left side/right sideboard (9),
Pass the 3rd bearing pin (29) of support (27),
The miniature bearing (30) that cooperates with the 3rd bearing pin (29),
Wherein
Miniature bearing (30) rolled in chute (28) when the front end of bottom web (6) rotated around second bearing pin (25), and cotter pin (31) is used to prevent that miniature bearing (30) from coming off from the 3rd bearing pin (29).
7. according to the adjustable monolateral expansion jet pipe of the differential type of claim 6, it is characterized in that
The established angle of chute (28) influences nozzle exit area (A
9), that is: when chute (28) when vertically placing, nozzle exit area (A in whole motion process
9) remain unchanged; When chute (28) horizontal positioned, nozzle exit area (A at this moment
9) the excursion maximum.
8. according to the adjustable monolateral expansion jet pipe of the differential type of claim 7, it is characterized in that adjustable epiplastron (7) comprising:
Support hanger (24),
Base plate (32), slide block (33),
Wherein,
When last convergence regulator plate (5) is done the folding and unfolding campaign of venturi, adjustable epiplastron (7) front end is done angular motion, the rear end slide block (33) of adjustable epiplastron (7) is done and is followed slip, adjustable epiplastron (7) and fixedly have certain clearance between the epiplastron (8), the size in this gap is along with throat area (A
8) reduce and diminish, be throat area (A at the design point state
8) the minimum time crack reaches minimum, the off-design point state particularly transonic speed with low supersonic flight condition under the gap bigger, can inject to the gap and let out the boundary layer of removing from forebody, thereby reduce the thrust loss that the air-flow overexpansion causes, reduce the pitch moment of aircraft, reduce the heat load of jet pipe.
9. the adjustable monolateral expansion jet pipe of differential type according to Claim 8, it is characterized in that fixing epiplastron (8) is similar to the box-like structure of rectangle for section, its lower surface is as the outer expanding noodles of air-flow, in the middle of it is cavity, longshore current is to having adopted many strengthening rib to guarantee its rigidity, and described fixedly epiplastron (8) directly connects with a left side/right sideboard (9) as a separate unit body to be fixed.
10. according to the adjustable monolateral expansion jet pipe of the differential type of claim 9, it is characterized in that keeping certain clearance between a left side/right sideboard (9) and last/following convergence regulator plate (5), bottom web (6) and the adjustable epiplastron (7),
A left side/right sideboard (9) and rotating component fixedly casing (4), fixedly epiplastron (8) is fixedlyed connected with supporting traverse (10),
The shape of a left side/right sideboard (9) has been taken into account jet pipe weight and thrust performance demands.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101544540A CN102251879B (en) | 2011-06-09 | 2011-06-09 | Differential adjustable unilateral expansion nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101544540A CN102251879B (en) | 2011-06-09 | 2011-06-09 | Differential adjustable unilateral expansion nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102251879A true CN102251879A (en) | 2011-11-23 |
| CN102251879B CN102251879B (en) | 2013-10-16 |
Family
ID=44979384
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011101544540A Expired - Fee Related CN102251879B (en) | 2011-06-09 | 2011-06-09 | Differential adjustable unilateral expansion nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102251879B (en) |
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| CN102760193A (en) * | 2012-07-26 | 2012-10-31 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for adjusting and designing outlet area of engine jet pipe based on installation performance |
| CN103334849A (en) * | 2013-06-26 | 2013-10-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Double-sliding beam type two-dimensional convergent-divergent nozzle control mechanism for single actuator systems |
| CN104033280A (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 | Binary vector spraying pipe capable of realizing S-bent shading function |
| 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 |
| CN104033283A (en) * | 2014-06-05 | 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 single-side expansion nozzle |
| CN106014683A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Pressurization flow control device-containing SERN structure for TBCC |
| CN106014684A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Combined flow control method and structure for improving SERN for TBCC |
| CN106050469A (en) * | 2016-07-01 | 2016-10-26 | 南京航空航天大学 | Nozzle structure for realizing throat area adjustment and thrust vector and adjusting method |
| CN109356747A (en) * | 2018-12-13 | 2019-02-19 | 西安航天动力研究所 | A kind of adjustable punching engine jet pipe of larynx diameter |
| CN110159454A (en) * | 2019-06-17 | 2019-08-23 | 西安航空学院 | Ducted rocket adjustable jet |
| CN112211749A (en) * | 2020-09-18 | 2021-01-12 | 西北工业大学 | Small solid rocket engine |
| CN112229640A (en) * | 2020-10-16 | 2021-01-15 | 中国航发四川燃气涡轮研究院 | Rigidity test device and measurement method for aircraft engine tail nozzle adjusting mechanism |
| CN113494385A (en) * | 2021-06-25 | 2021-10-12 | 北京理工大学 | Key structure parameter optimization method for reliable movement of engine tail nozzle |
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| CN113915026A (en) * | 2021-11-05 | 2022-01-11 | 沈阳飞机设计研究所扬州协同创新研究院有限公司 | Unilateral expansion spray pipe with vector adjustment capability |
| CN113944565A (en) * | 2021-10-19 | 2022-01-18 | 中国科学院工程热物理研究所 | Tail nozzle structure for improving vibration characteristic |
| CN114109644A (en) * | 2021-10-09 | 2022-03-01 | 中国航发贵阳发动机设计研究所 | Method for adjusting area of exit throat of special-shaped fixed spray pipe of aircraft engine |
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| CN114673605A (en) * | 2022-04-14 | 2022-06-28 | 中国航发沈阳发动机研究所 | Light high stealthy unilateral expansion spray tube of ability |
| CN114790954A (en) * | 2022-04-14 | 2022-07-26 | 中国航发沈阳发动机研究所 | High-efficiency throat-adjustable invisible low-tail-resistance unilateral expansion nozzle |
| CN115614179A (en) * | 2022-08-31 | 2023-01-17 | 中国航发四川燃气涡轮研究院 | Adjusting mechanism for throat area |
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| CN106014684A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Combined flow control method and structure for improving SERN for TBCC |
| CN106014683B (en) * | 2016-05-30 | 2018-04-06 | 西北工业大学 | A kind of TBCC SERN structures of band supercharging flow control apparatus |
| CN106050469A (en) * | 2016-07-01 | 2016-10-26 | 南京航空航天大学 | Nozzle structure for realizing throat area adjustment and thrust vector and adjusting method |
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| CN110159454B (en) * | 2019-06-17 | 2023-11-24 | 西安航空学院 | Adjustable jet pipe of solid flushing engine |
| CN110159454A (en) * | 2019-06-17 | 2019-08-23 | 西安航空学院 | Ducted rocket adjustable jet |
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| CN113944565B (en) * | 2021-10-19 | 2022-06-28 | 中国科学院工程热物理研究所 | Tail nozzle structure for improving vibration characteristic |
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| CN114790954B (en) * | 2022-04-14 | 2024-06-18 | 中国航发沈阳发动机研究所 | High-efficiency throat-adjustable high-stealth low-tail-resistance unilateral expansion spray pipe |
| CN115614179A (en) * | 2022-08-31 | 2023-01-17 | 中国航发四川燃气涡轮研究院 | Adjusting mechanism for throat area |
| CN115614179B (en) * | 2022-08-31 | 2024-04-05 | 中国航发四川燃气涡轮研究院 | Throat area adjusting mechanism |
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