CN102251879B - Differential adjustable unilateral expansion nozzle - Google Patents
Differential adjustable unilateral expansion nozzle Download PDFInfo
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- CN102251879B CN102251879B CN2011101544540A CN201110154454A CN102251879B CN 102251879 B CN102251879 B CN 102251879B CN 2011101544540 A CN2011101544540 A CN 2011101544540A CN 201110154454 A CN201110154454 A CN 201110154454A CN 102251879 B CN102251879 B CN 102251879B
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- adjustable
- epiplastron
- nozzle
- bearing pin
- plate
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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 upperweb 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 differential adjustable unilateral expansion nozzle.
Technical background
It is for the third time " revolution " 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 hypersonic aircraft and study forward-looking, strategic and drive property, will produce immeasurable profound influence to 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.Unilateral expansion nozzle (SERN) is because the rear body lower surface that directly uses aircraft as outer expanding noodles, makes it have unique ability that satisfies large expansion ratio.And the non-symmetry structure of SERN, make it when non-design height flight, jet pipe has certain self adaptive-compensating characteristic.These advantages are so that unilateral expansion nozzle becomes the most possible jet pipe type that adopts of following hypersonic aircraft.
In general, unilateral expansion nozzle has following six large characteristics:
The jet pipe blow down ratio is very large, reaches three figure places;
Nozzle throat area (A
8) excursion is very large;
Nozzle exit area (A
9) and A
9/ A
8Excursion is very large;
Flow by jet pipe is large, and excursion is large;
The heat load of jet pipe is high;
Require jet pipe in the flight envelope of broadness, to have higher thrust coefficient.
In fact, except these " four large two height ", consider actual installation and the use of jet pipe, also should be from intake duct, the coupling angle of motor and jet pipe and with the design of the aspect comprehensive study vent systems 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 a kind of solution of differential adjustable unilateral expansion nozzle.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 large 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 gap between the two, and wherein fixedly epiplastron directly utilizes body behind the aircraft, can reduce like this steering force of motion.Transonic speed with under the low supersonic flying condition can inject to fixing epiplastron by the gap and letting out the boundary layer of removing from forebody, can improving so fixedly, thereby the wall static pressure of epiplastron reduces the thrust loss that the air-flow overexpansion causes, reduce simultaneously the pitch moment of aircraft, guaranteed that jet pipe has higher thrust coefficient in the flight envelope of broadness; Can strengthen in addition the cooling to holding part, reduce heat load and the infrared signal feature of jet pipe.
According to an aspect of the present invention, provide a kind of differential adjustable unilateral expansion nozzle, it is characterized in that comprising: rotating component is casing, up/down convergence regulator plate, bottom web, adjustable epiplastron, fixedly epiplastron and left/right side plate fixedly.
Description of drawings
Fig. 1 is the structure of differential adjustable unilateral expansion nozzle.
Fig. 2 is jet pipe actuating system schematic diagram.
Fig. 3 is fixedly casing structure and erection drawing of rotating component.
Fig. 4 is up/down 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, and its jet pipe comprises front mounting edge (1), circle torque changeover portion (2), rear mounting edge (3), rotating component, and fixedly casing (4), up/down restrain regulator plate (5), bottom web (6), adjustable epiplastron (7), fixedly epiplastron (8), left/right side plate (9), supporting traverse (10) and stepper motor (11) etc.
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 conduit (15) rolling 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 rule.
Rotating component is casing fixedly
According to one embodiment of present invention, as shown in Figure 3, rotating component fixedly casing (4) comprises and the combination of up/down frame (19) and left/right frame (20) is the important load parts of whole motion.The as can be seen from Figure 3 fixing assembly relation of casing (4) and left/right side plate (9) and up/down convergence regulator plate (5) of rotating component, the left/right double end hanger (22) on the up/down convergence regulator plate (5) by the first bearing pin (21) and rotating component fixedly casing (4) be connected.
Up/down convergence regulator plate
As shown in Figure 4, up/down convergence regulator plate according to an embodiment of the invention (5) comprises base plate (23), left/right double end hanger (22), supports hanger (24) and suspension hook (18).Up/down convergence regulator plate (5) front end with left/right double end hanger (22) by the first bearing pin (21) and rotating component fixedly casing (4) be connected, up/down restrains regulator plate (5) rear end and passes through the second bearing pin (25) and is connected 6 with adjustable epiplastron (7) with bottom web respectively) be connected.When stepper motor (11) when axially moving forward, up/down convergence regulator plate (5) is realized nozzle throat area (A around the first bearing pin (21) rotation
8) diminish; Work as A
8When becoming large, 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 left/right side plate (9).Support (27) is installed in base plate (26) neutral position, and chute (28) is fixed on the left/right side plate (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 the 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) larger impact arranged: when chute (28) when vertically placing, A in whole movement process
9Remain unchanged; When chute (28) horizontal positioned, A at this moment
9Excursion maximum.Consider A
9Excursion and the impact 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 upper 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 gap 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 is minimum) gap.The off-design point state particularly transonic speed with the low supersonic flying condition under, the gap is larger, 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 simultaneously the pitch moment of aircraft, can reduce in addition the heat load of jet pipe.
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.Be cavity in the middle of it, adopted many (such as 3) strengthening rib to guarantee its rigidity along flowing to.Fixedly epiplastron (8) as one independently cell cube directly connect with left/right side plate (9) and fix, 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, the gap that left/right side plate (9) is certain with up/down convergence regulator plate (5), bottom web (6) and the necessary maintenance of adjustable epiplastron (7); In a specific embodiment of the present invention, this gap is 1mm.Wherein left/right side plate (9) and rotating component fixedly casing (4), fixedly epiplastron (8) is connected 10 with supporting traverse) be connected by set screw.The configuration of left/right side plate (9) has larger impact to nozzle performance, and in a specific embodiment of the present invention, the shape of left/right side plate (9) obtains by the CFD calculation optimization, and it has taken into account the requirement of jet pipe weight and thrust performance.
Claims (7)
1. differential adjustable unilateral expansion nozzle is characterized in that comprising:
Rotating component is casing (4) fixedly;
Up/down convergence regulator plate (5);
Bottom web (6);
Adjustable epiplastron (7);
Fixing epiplastron (8);
Left/right side plate (9),
Actuating system,
Wherein rotating component fixedly casing (4) comprising:
Up/down frame (19),
Left/right frame (20),
Wherein the left/right double end hanger (22) on the up/down convergence regulator plate (5) by the first bearing pin (21) and rotating component fixedly casing (4) be connected,
Up/down convergence regulator plate (5) comprising:
Base plate (23),
Described left/right double end hanger (22),
Support hanger (24),
Suspension hook (18),
Wherein, up/down convergence regulator plate (5) front end with left/right double end hanger (22) by the first bearing pin (21) and rotating component fixedly casing (4) be connected, up/down convergence regulator plate (5) rear end is connected 6 with adjustable epiplastron (7) with bottom web respectively by the second bearing pin (25)) be connected
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, up/down convergence regulator plate (5) is realized the nozzle throat area A around the first bearing pin (21) rotation
8Diminish; Work as A
8When becoming large, 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.
2. according to claim 1 differential adjustable unilateral expansion nozzle is characterized in that
The minimum and maximum throat area ratio of jet pipe is 3.
3. according to claim 2 differential adjustable unilateral expansion nozzle 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 the left/right side plate (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 the second bearing pin (25), and cotter pin (31) is used for preventing that miniature bearing (30) from coming off from the 3rd bearing pin (29).
4. according to claim 3 differential adjustable unilateral expansion nozzle is characterized in that
The established angle of chute (28) affects nozzle exit area A
9, that is: when chute (28) when vertically placing, nozzle exit area A in whole movement process
9Remain unchanged; When chute (28) horizontal positioned, nozzle exit area A at this moment
9Excursion maximum.
5. according to claim 4 differential adjustable unilateral expansion nozzle is characterized in that adjustable epiplastron (7) comprising:
Support hanger (24),
Base plate (32), slide block (33),
Wherein,
When up/down 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 gap between the epiplastron (8), the size in this gap is along with throat area A
8Reduce and diminish, be throat area A at the design point state
8It is minimum that the minimum time gap reaches, transonic speed with the low supersonic flying condition under the gap larger, 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.
6. according to claim 5 differential adjustable unilateral expansion nozzle, 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, cavity in the middle of it, has adopted many strengthening rib to guarantee its rigidity along flowing to, described fixedly epiplastron (8) directly connects with left/right side plate (9) as a separate unit body to be fixed.
7. according to claim 6 differential adjustable unilateral expansion nozzle is characterized in that
Keep certain gap between left/right side plate (9) and up/down convergence regulator plate (5), bottom web (6) and the adjustable epiplastron (7),
Left/right side plate (9) and rotating component fixedly casing (4), fixedly epiplastron (8) is fixedly connected with supporting traverse (10),
The shape of left/right side plate (9) has been taken into account the requirement of jet pipe weight and thrust performance.
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 CN102251879A (en) | 2011-11-23 |
| CN102251879B true 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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| CN102760193B (en) * | 2012-07-26 | 2014-09-17 | 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 |
| CN103334849B (en) * | 2013-06-26 | 2015-08-19 | 中国航空工业集团公司沈阳发动机设计研究所 | The two sliding-beam type binary of a kind of single actuating system is received and is expanded jet pipe control mechanism |
| CN104033283B (en) * | 2014-06-05 | 2016-05-04 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of Novel Dual unilateral expansion nozzle |
| CN104033280B (en) * | 2014-06-06 | 2016-06-08 | 中国航空工业集团公司沈阳发动机设计研究所 | The curved binary vector spray blocking function of a kind of S of realization |
| CN104033281B (en) * | 2014-06-09 | 2017-01-25 | 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 |
| 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 |
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| CN114152403B (en) * | 2022-02-08 | 2022-09-06 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-precision pitching moment measuring device based on mechanical bearing |
| 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 |
| CN114673605B (en) * | 2022-04-14 | 2023-10-10 | 中国航发沈阳发动机研究所 | Single-side expansion spray pipe with light weight and high stealth capacity |
| 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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