CN105781790B - A kind of curved two end number mixing exhaust systems of double S of segmentation reducing-pitch thread - Google Patents
A kind of curved two end number mixing exhaust systems of double S of segmentation reducing-pitch thread Download PDFInfo
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- CN105781790B CN105781790B CN201610008044.8A CN201610008044A CN105781790B CN 105781790 B CN105781790 B CN 105781790B CN 201610008044 A CN201610008044 A CN 201610008044A CN 105781790 B CN105781790 B CN 105781790B
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- 238000002156 mixing Methods 0.000 title claims abstract description 29
- 230000011218 segmentation Effects 0.000 title claims abstract description 15
- 230000008676 import Effects 0.000 claims abstract description 30
- 238000005452 bending Methods 0.000 claims abstract description 12
- 230000007704 transition Effects 0.000 claims description 10
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 238000000926 separation method Methods 0.000 abstract description 8
- 230000005855 radiation Effects 0.000 description 9
- 238000005516 engineering process Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000009826 distribution Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 230000003134 recirculating effect Effects 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000000977 initiatory effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000003595 spectral effect Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Exhaust Gas After Treatment (AREA)
- Investigating Or Analysing Materials By Optical Means (AREA)
Abstract
The invention discloses a kind of curved two end number mixing exhaust systems of the double S of segmentation reducing-pitch thread for fanjet infrared stealth, first axisymmetricly shape restrains its shape, it is in double S bending shapes convergences again, is made of sharp cone distal center cone, outer culvert axial symmetry converging portion, the outer curved binary converging portions of double S, intension axial symmetry converging portion and the curved converging portions of intension S contained.Sharp cone distal center cone connects to form intension wall surface with intension axial symmetry converging portion, can prevent intension path partially from expanding, and inhibits the flow separation on center cone wall surface.Outer culvert axial symmetry converging portion is connected to form outer culvert wall surface with the outer pair curved binary converging portions of S of containing, and can more efficiently be formed and be blocked to the high temperatures typicals component such as center cone and intension import section.The present invention can further suppress the infrared signature of exhaust system relative to existing double curved two end number mixing exhaust systems of S while improving exhaust system aeroperformance.
Description
Technical field
The present invention relates to aircraft fields, especially aircraft infrared signature suppression technology field.
Background technology
Infrared characteristic to aircraft research shows that：(1) exhaust of the main source of infrared radiation from aircraft of jet plane
System and fuselage skin；(2) in the case where flight Mach number is less than 1.5, the infrared spoke of exhaust system cavity and high-temperature component
It penetrates, 90% or more is reached to the contribution of aircraft medium-wave band infra-red radiation.Therefore, research aero-engine exhaust system is 3~5
The infrared signature of mu m waveband, the infrared suppressing technology for developing exhaust system are the key that promote aircraft battlefield survival skill
One of art.
Mainly there are following five aspects for the infrared suppressing measure of aero-engine exhaust system：(1) choosing of engine
It selects, that is, uses the fanjet of mixing exhaust, outer culvert cold airflow can be utilized to reduce exhaust system internal high temperature solid wall surface
Temperature, while inside and outside Gas Mixing in Cross flow of containing can reduce the temperature of tail jet, to inhibit the infra-red radiation of exhaust system special
Sign；(2) nozzle structure designs, i.e., using special-shaped jet pipe, nozzles with injector or using measures such as lobed mixers, for example, by using binary
Jet pipe, the blending of inside and outside culvert air-flow is strengthened using the strong three-dismensional effect of spray Bottomhole pressure, while increasing tail in nozzle exit
The heat exchange area of jet flow and outflow effectively reduces the infra-red radiation of jet flow；(3) change the transmitting of exhaust system solid components
Rate；(4) technology is blocked, for example, by using engine curved channel mounting technique, the nozzle contour of bending can be utilized to exhaust system
System internal high temperature component is blocked, to which the infrared signature of exhaust system be greatly reduced；(5) change jet flow infra-red radiation
Spectral characteristic.The characteristics of double curved two end number mixing exhaust systems of S then preferably combine special-shaped spray bar technology and block technology, gesture
There must be boundless application prospect on the following stealthy aircraft.
Design studies in relation to the curved two end number mixing exhaust systems of double S are actually rare.External Brunet etc. (Brunet E,
Seine N S,Daris T,et al.Exhaust assembly forming a horizontal propulsion gas
elbow in an aircraft:U.S.Patent 7784284B2 [P] .2010-08-31) devise a kind of curved binary sprays of double S
Pipe, intermediate position generate offset distance relative to turbine axis, so that combustion gas is deviateed central axis by first curved channel S, then pass through
Crossing second curved channel S makes combustion gas return in axial location, and then is carried out to high-temperature components such as turbo blade and center cones effective
It blocks, can not only reduce radar scattering feature, infrared signature can also be reduced.(Liu Changchun, the Ji Hong such as domestic Liu's normal spring
Lake, a kind of infrared signature numerically modeling [J] aviation power journals of double curved two-dimensional nozzles of S of the such as Huang Wei, 2013,28 (7):
1482-1488.) in order to reduce the infra-red radiation of axial symmetry exhaust system, a kind of curved two-dimensional nozzles of double S are devised, with axial symmetry
Jet pipe is compared can averagely reduce by 70% or more under the premise of thrust loss is not more than 3% by infra-red radiation.The design of the latter is deposited
In two point defects：(1) truncated cone shape center cone is used, there are apparent sudden expansion regions for center cone rear end, in addition intension curved wall
Influence, there are larger recirculating zones in intension channel, and the separation of center cone wall surface air-flow is serious, causes jet pipe to a certain extent
Aerodynamic loss；(2) double S bending nozzles initiating terminals are outer culvert diameter, to reach certain occlusion effect, need larger offset distance,
Lateral dimension is larger, to a certain extent so that nozzle structure size is larger, increases the weight of jet pipe.
Invention content
Goal of the invention：In order to overcome the deficiencies in the prior art, the present invention proposes a kind of segmentation reducing-pitch thread pair S curved two
First mixing exhaust system, for solving the skill that the curved two-dimensional nozzle center cone air-flow separation of existing double S is serious and jet pipe size is big
Art problem.
To realize that the above technical purpose, the present invention will take technical solution below：
A kind of curved two end number mixing exhaust systems of the double S of segmentation reducing-pitch thread, including the sharp cone distal center cone, interior that is distributed from inside to outside
Contain wall surface and outer culvert wall surface；The intension wall surface is by the intension axial symmetry converging portion of upstream and the curved converging portion light of the intension S in downstream
Slip is formed；It is smooth that the outer culvert wall surface contains the curved binary converging portions of double S by the outer culvert axial symmetry converging portion of upstream and outside downstream
Connection is formed；Above-mentioned sharp cone distal center cone, intension axial symmetry converging portion and the outer import section for containing axial symmetry converging portion three are
Perpendicular to engine axis approximately the same plane and three engine axis direction equal length；
The outer culvert axial symmetry converging portion is using engine axis as axial symmetry and along engine axis direction in gradually convergence
Shape, the outer culvert aisle spare at outlet is equal with the outer culvert aisle spare at its import section, and wall surface restrains molded line
Using Wei Duoxinsi base curves；
The intension axial symmetry converging portion is using engine axis as axial symmetry and along engine axis direction in gradually convergence
Shape, the intension aisle spare at outlet is equal with the intension aisle spare at its import section, to avoid intension logical
Road expansion causes that flow separation occurs on center cone wall surface, and wall surface restrains molded line and uses Wei Duoxinsi base curves；
The curved converging portions of intension S are gradually restrained along engine axis direction in S bendings shape, import section be it is round,
Outlet is hyperelliptic shape, and the transition section between its import section and its outlet is hyperelliptic shape；
The outer pair curved binary converging portions of S of containing gradually are restrained along engine axis direction in double S bendings shapes, import section
It is rectangle for round, outlet, and the transition section between its import section and its outlet is hyperelliptic shape；
Above-mentioned two transition section is consistent in the contour shape of the same axial positions of engine axis, to protect
Card intension exit flow is consistent with the outer culvert flow direction of exit flow and is evenly distributed, and intension high temperature gas flow is avoided externally to contain wall surface
It washes away, reduces interference of the outer culvert curved wall to intension air-flow.
Further, in the present invention, the diameter of the outlet of intension axial symmetry converging portionIts
In, D1For the diameter in the import section of sharp cone distal center cone, D3For the diameter in the import section of intension axial symmetry converging portion.
Further, in the present invention, the diameter of the outer outlet for containing axial symmetry converging portion
Wherein, D2、D3The respectively diameter of the diameter of the outlet of intension axial symmetry converging portion and import section, D5For outer culvert axis pair
Claim the diameter in the import section of converging portion.
Advantageous effect：
The present invention is segmented the curved two end number mixing exhaust systems of the double S of reducing-pitch thread, and first axisymmetricly shape gradually restrains exhaust system,
It is in that double S bending shapes are gradually restrained again, can effectively improve the infrared stealth performance of fanjet.Specifically include following several sides
Face：
(1) sharp cone distal center cone is used, first axisymmetricly shape restrains intension wall surface, then is restrained in S bending shapes, so sets
Meter avoids the expansion of intension path partially, it is suppressed that air-flow effectively reduces intension bending in the separation of center cone near wall
The influence that wall surface flows intension air-flow improves the aeroperformance of the curved two end number mixing exhaust systems of double S；
(2) contain wall surface first axisymmetricly shape convergence outside, then in double S bending shapes convergences, the initiating terminal of double curved converging portions of S is
Outer culvert axial symmetry converging portion outlet diameter, it is only necessary to smaller offset distance, so that it may to reach better occlusion effect, lateral dimension compared with
It is small, the size and weight of the curved two end number mixing exhaust systems of entire double S can be mitigated to a certain extent.
Description of the drawings
Fig. 1 is curved 1/2 physical models of two end number mixing exhaust system of the double S of segmentation reducing-pitch thread designed by the present invention；
Fig. 2 is the schematic diagram of the curved two end number mixing exhaust system planes of symmetry of the double S of segmentation reducing-pitch thread designed by the present invention；
Fig. 3 is the Section A-A figure of Fig. 2；
Fig. 4 is the double curved two end number mixing exhaust system planes of symmetry of S of segmentation reducing-pitch thread and the air flow path designed by the present invention
Schematic diagram；
Fig. 5 is (Liu Changchun, lucky Honghu, a kind of infrared signature numbers of double curved two-dimensional nozzles of S of the such as Huang Wei such as Liu Changchun
Value research [J] aviation power journals, 2013,28 (7):Double S curved two with truncated cone shape center cone designed by 1482-1488.)
Velocity vector distribution on first exhaust system plane of symmetry；
Fig. 6 is by (Liu Changchun, lucky Honghu, a kind of infrared signatures of double curved two-dimensional nozzles of S of the such as Huang Wei such as Liu Changchun
Numerically modeling [J] aviation power journals, 2013,28 (7):The band sharp cone distal center cone of design method design 1482-1488.)
Double S curved two end number mixing exhaust system plane of symmetry velocity vector distributions；
Fig. 7 is the velocity vector on the curved two end number mixing exhaust system planes of symmetry of the double S of segmentation reducing-pitch thread designed by the present invention
Distribution；
Fig. 8 is in Fig. 6, Fig. 7 under two kinds of design schemes, center cone projected area profiles versus in exhaust system Caudad and
Exhaust system radiation intensity compares.
Specific implementation mode
The present invention is further described below in conjunction with the accompanying drawings.
Fig. 1 is the curved 1/2 physical model schematic diagrames of two end number mixing exhaust system of the double S of segmentation reducing-pitch thread designed by the present invention,
Along X-axis line direction it is engine axis in coordinate system, exhaust system is first using engine axis as axial symmetry and along engine
Axis direction is in that double S bendings shapes gradually restrain (in figure B sections) in gradually convergence shape (in figure A sections), then along engine axis direction,
By outer culvert axial symmetry converging portion 1, intension axial symmetry converging portion 2, sharp cone distal center cone 3, the curved converging portions 4 of intension S and the double S of outer culvert
Curved binary converging portion 5 forms, and the curved converging portion of intension axial symmetry converging portion 2 and intension S 4 is connected to form the intension wall of exhaust system
Face 6, outer culvert axial symmetry converging portion 1 are connected to form the outer culvert wall surface 7 of exhaust system with the outer curved binary converging portions of double S 5 of containing.
It can be obtained by Fig. 2：
Outer 1 import diameter of section of culvert axial symmetry converging portion is D5, exit diameter D4, outer culvert axial symmetry converging portion 1 goes out
Outer culvert aisle spare at mouth section is equal with the outer culvert aisle spare at import section, and wall surface restrains molded line and uses Wei Duoxinsi
Base curves, the equal length of length and sharp cone distal center cone 3 are L1。
2 import diameter of section of intension axial symmetry converging portion is D3, exit diameter D2, intension axial symmetry converging portion 2 goes out
Intension aisle spare at mouth section is equal with the intension aisle spare at import section, and wall surface restrains molded line and uses Wei Duoxinsi
Base curves, the equal length of length and sharp cone distal center cone 3 are L1。
Sharp cone distal center cone 3, inlet diameter D1, length L1。
The import section of the curved converging portions of intension S 4 is circle, a diameter of D2, outlet is hyperelliptic shape, length L2, into
Transition section between mouthful section and outlet is hyperelliptic shape, and the contour shape of transition section always with same axial position
The transition section contour shape of the curved binary converging portions of the double S in the place of setting 5 is consistent.
The outer import section for containing the curved binary converging portions of double S 5 is circle, a diameter of D5, outlet is rectangle, length L4,
Transition section between import section and outlet is hyperelliptic shape, and the outer maximum for containing the curved binary converging portion center lines of double S is partially
Away from for S；
Fig. 4 is the double curved two end number mixing exhaust system planes of symmetry of S of segmentation reducing-pitch thread and the air flow path designed by the present invention
Schematic diagram, A sections in figure, B sections of identical to those shown in Fig. 1, respectively (intension, outer culvert) axial symmetry converging portions and outer to contain double S curved
Converging portion, C sections are the curved converging portions of intension S in figure.Intension combustion gas (filled arrows in figure) in intension channel can and be contained outside
Outer culvert cold air (hollow arrow in figure) in channel first passes through mixing, together arranges to air.
Fig. 5 is (Liu Changchun, lucky Honghu, a kind of infrared signature numbers of double curved two-dimensional nozzles of S of the such as Huang Wei such as Liu Changchun
Value research [J] aviation power journals, 2013,28 (7):1482-1488.) the curved binary of double S with truncated cone shape center cone designed
Mixing exhaust symmetry system having symmetry face velocity vector is distributed.Since using truncated cone shape center cone, center cone rear end exists apparent
Sudden expansion region, there are larger recirculating zone (arrow locations in figure) in intension channel, and the separation of center cone wall surface air-flow is serious, centainly
The aerodynamic loss of exhaust system can be caused in degree.
Fig. 6 is the curved two end number mixing exhaust systems of double S with sharp cone distal center cone designed by the design method of Liu Changchun etc.
Plane of symmetry velocity vector is distributed.Equally, there are apparent sudden expansion regions in intension channel, in addition the shadow of intension curved wall
It rings, there are larger recirculating zone (arrow locations in figure) in intension channel, the wall surface air-flow separation of center cone lower section is serious.
Fig. 7 is the curved two end number mixing exhaust systems pair of the double S of segmentation reducing-pitch thread with sharp cone distal center cone designed by the present invention
Velocity vector distribution on title face.As it can be seen that intension channel, without local sudden expansion region, air-flow is also not present in center cone near wall
The case where separation.
Fig. 8 is that have two kinds of exhaust systems of identical structure size (shown in Fig. 6 and Fig. 7) center cone in exhaust system Caudad
The comparison of the comparison and exhaust system infrared radiation intensity of projected area., it is apparent that with the design side by Liu Changchun etc.
The curved two end number mixing exhaust systems of double S with sharp cone distal center cone of method design are compared, and the present invention blocks internal high-temperature component
Effect is more preferable, and infrared suppressing is better, and center cone only has the former half or so, spoke in the projected area of exhaust system Caudad
It is even more to decline 50% or more to penetrate feature.
The above is only a preferred embodiment of the present invention, it should be pointed out that：For the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (3)
1. a kind of curved two end number mixing exhaust systems of the double S of segmentation reducing-pitch thread, it is characterised in that：Including the sharp cone distal being distributed from inside to outside
Center cone (3), intension wall surface (6) and outer culvert wall surface (7)；The intension wall surface (6) by upstream intension axial symmetry converging portion (2)
It is smoothly connected to be formed with the curved converging portions of intension S (4) in downstream；It is described it is outer contain wall surface (7) by upstream outer culvert axial symmetry converging portion
(1) it is smoothly connected to be formed with the double curved binary converging portions (5) of S of the outer culvert in downstream；Above-mentioned sharp cone distal center cone (3), intension axial symmetry
Converging portion (2) and it is outer contain axial symmetry converging portion (1) three import section be perpendicular to engine axis approximately the same plane and
Equal length of the three in engine axis direction；
The outer culvert axial symmetry converging portion (1) is using engine axis as axial symmetry and along engine axis direction in gradually convergence
Shape, the outer culvert aisle spare at outlet is equal with the outer culvert aisle spare at its import section, and wall surface restrains molded line
Using Wei Duoxinsi base curves；
The intension axial symmetry converging portion (2) is using engine axis as axial symmetry and along engine axis direction in gradually convergence
Shape, the intension aisle spare at outlet is equal with the intension aisle spare at its import section, and wall surface restrains molded line
Using Wei Duoxinsi base curves；
The curved converging portions of intension S (4) are gradually restrained along engine axis direction in S bendings shape, and import section is round, goes out
Mouth section is hyperelliptic shape, and the transition section between its import section and its outlet is hyperelliptic shape；
The double curved binary converging portions (5) of S of outer culvert are in that double S bendings shapes are gradually restrained along engine axis direction, import section
It is rectangle for round, outlet, and the transition section between its import section and its outlet is hyperelliptic shape；
Above-mentioned two transition section is consistent in the contour shape of the same axial positions of engine axis.
2. the curved two end number mixing exhaust systems of the double S of segmentation reducing-pitch thread as described in claim 1, it is characterised in that：Intension axial symmetry
The diameter of the outlet of converging portion (2)Wherein, D1For sharp cone distal center cone (3) import section it is straight
Diameter, D3For the diameter in the import section of intension axial symmetry converging portion (2).
3. the curved two end number mixing exhaust systems of the double S of segmentation reducing-pitch thread as described in claim 1, it is characterised in that：Outer culvert axial symmetry
The diameter of the outlet of converging portion (1)Wherein, D2、D3Respectively intension axial symmetry converging portion (2)
Outlet diameter and import section diameter, D5For the diameter in the import section of outer culvert axial symmetry converging portion (1).
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107229798A (en) * | 2017-06-02 | 2017-10-03 | 南京航空航天大学 | A kind of pair of S bending nozzle design method |
| CN108104973A (en) * | 2017-11-28 | 2018-06-01 | 中国航发沈阳发动机研究所 | A kind of two-dimensional nozzle |
| CN110566363B (en) * | 2019-09-03 | 2021-08-17 | 中国航空工业集团公司西安飞机设计研究所 | Engine exhaust system |
| CN115341959B (en) * | 2022-07-26 | 2023-07-21 | 南京航空航天大学 | Combined blade |
| CN115614176B (en) * | 2022-08-29 | 2024-04-19 | 中国航发四川燃气涡轮研究院 | Infrared and radar comprehensive stealth device based on internal and external culvert structure integration |
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