CN104712455B - The thrust reverser of fanjet and push away leaf grating for the counter of the thrust reverser - Google Patents
The thrust reverser of fanjet and push away leaf grating for the counter of the thrust reverser Download PDFInfo
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- CN104712455B CN104712455B CN201310680725.5A CN201310680725A CN104712455B CN 104712455 B CN104712455 B CN 104712455B CN 201310680725 A CN201310680725 A CN 201310680725A CN 104712455 B CN104712455 B CN 104712455B
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Abstract
The present invention provides the cascade array in a kind of thrust reverser for airborne vehicle fanjet,Cascade array includes multiple leaf gratings,Two adjacent leaf gratings form leaf grating runner,Leaf grating and leaf grating runner are configured to make after the airflow passes leaf grating in by-pass air duct,Leaf grating can guide at least Part I air-flow therein to change flow direction,To form the first propulsive thrust,Wherein,Leaf grating is formed as hollow leaf grating,With being internally formed along the cascade internal flow road for allowing the flow to flow through of the Longitudinal extending of leaf grating in leaf grating,Leaf grating is forming cascade internal flow road import near one end of by-pass air duct,The cascade internal flow road port of export is formed in the opposite other end,The Part II of the air-flow in by-pass air duct enters the cascade internal flow road of leaf grating by the import of cascade internal flow road,Then sprayed along jet-impingement angle α by the cascade internal flow road port of export and Part II air-flow is changed flow direction,To form the second propulsive thrust.
Description
Technical field
The present invention relates to the thrust reverser of the thrust reverser of aircraft engine, especially fanjet.The present invention
Counter in further to thrust reverser pushes away leaf grating.
Background technology
The implication of relevant technical terms is illustrated first.Thrust reverser：Refer to by engine air flow reversely, be aircraft or
The device of deboost is provided during landing.It is counter to push away efficiency：Refer to the ratio of deboost and positive thrust.
To shorten aircraft landing ground run distance, almost all of civil aircraft is all slowed down using thrust reverser,
Slow down relative to using wheel brake device, THR REV can shorten aircraft landing Distance Shortened nearly 65%.Thrust reverser
Operation principle is that normal airflow flow direction occurs turning back more than 90 ° in making engine, so as to opposite with normal thrust
Thrust component is produced on direction, the purpose of aircraft is made so as to reach.In general, because turning back for air-flow can not possibly reach
180 °, deboost is about 30% of positive thrust or so.
Thrust reverser is broadly divided into cascade type thrust reverser according to the mechanism for producing propulsive thrust, baffling gate-type is counter pushes away
Power apparatus and target formula thrust reverser, these three thrust reversers respectively have advantage and disadvantage, its middle period target formula thrust reverser structure and
Motion is simple, but weight is larger and pneumatic and thermal force is larger, typically starts in turbojet engine or small bypass ratio turbofan
Used in machine；Baffling gate-type thrust reverser structural mechanism is relatively easy, but counter pushes away relatively inefficient；Cascade type propulsive thrust is filled
Put it is counter push away efficiency highest, but structure is relative complex, be at present big Bypass Ratio Turbofan Engine mainly use counter push away form.
CN102877382A provides a kind of new anti-passage dynamic cover design for cascade type thrust reverser, is pushed away when counter
When power apparatus are in running order, the anti-dynamic cover of passage be not to slide axially but radial development with this increase front face area so as to
Increase propulsive thrust and push away efficiency with counter.CN102753808A designs an airway by the downstream of thrust reverser, so that
Reduce the contour dimension of thrust reverser and engine nacelle.CN102865156A provides a kind of public actuator of utilization
Variable area jet pipe and the scheme of thrust reverser, the tune to nozzle exit area is completed using the actuating system of thrust reverser
Section, that is, realizing the start of thrust reverser mechanism can realize engine to nozzle exit area regulatory demand again.US6434927B1 is carried
For a kind of thrust reverser scheme of leaf grating packaged type, when it is counter push away be closed when, the anti-leaf grating fixed part and can of pushing away
Movable part is in same axial location, when it is counter push away opening when, leaf grating moveable part is moved backward with choked flow, and the program subtracts
The axial arranged space of leaf grating is lacked so that engine is compacter, is conducive to loss of weight.CN201245246Y provides a kind of umbrella
Shape baffling door is counter to push away scheme, and uses nonmetallic materials, reduces the weight of thrust reverser.
Fig. 6 is patent documentCN101104441AIn an accompanying drawing, show an example aircraft turbofan
The side view of gas-turbine unit 10, its upper surface for being installed on aircraft wing 12, and including thrust reversing device assembly
100.Fan 20 is encapsulated in the core cowl 22 of annular, and fan nacelle 24 is sent out around fan 16 and core
A part for motivation 20.Radially outward it is spaced with by this in the front portion of the core cowl 22 around fan 20
Between the afterbody inner surface of the gondola 24 opened, the bypass duct 26 of annular, i.e. by-pass air duct are defined.Operationally, surrounding air
The 28 cocurrent passing through fan 16 of entrance 30 for entering gas turbine assembly 10.The Part I 32 of air-flow 28 is guided through core
Heart gas-turbine unit 20, it is compressed and mixes with fuel, and it is ignited and be used to produce burning gases 34, burn
Gas 34 is discharged from the core nozzle 36 of fan 20.The Part II 38 of air-flow 28 is guided to downstream and wears
Cross by-pass air duct 26.Thrust reversing device assembly 100 is arranged on the periphery of by-pass air duct 26.
Fig. 7 and 8 is patent documentCN101614164AIn accompanying drawing.As shown in Figure 7, the row of being disposed in of leaf grating component 20
Go out in opening 15.Leaf grating component 20 typically comprises the cascade segment 28 of multiple circumferential arrangements.Fig. 8 shows and is typically used for turbine
The some parts of the cascade-type thrust reverser 10 of turbofan aircraft engine.As shown in Figure 8, when expansion trhrust-reversal device 10
When, it is moved rearwards by translation sleeve 16 and makes it away from the rear end of the fixed part 12 of cabin, so covered in fixed part 12 and translation
Outlet opening 15 is provided between the front end of cylinder 16.Permit the deboost of the aircraft of landing, outlet opening 15 in order to provide
Perhaps fan stream is discharged from the ring-type fan pipe 13 (i.e. by-pass air duct) of engine.As shown in Figure 8, the front end for launching translation sleeve 16 is attached
Near multiple blocker doors 18, the flowing backward of the fan stream to be arrested in ring-type fan pipe 13, and promote fan stream by discharge
Flow out engine in opening 15.As shown in Figure 8, each cascade segment 28 of circumference includes multiple blades being spaced along the longitudinal
25, in order to provide deboost, side at least in part forward is changed into the direction that blade 25 is configured to the fan stream that will be flowed out
To form plume.Blade 25 is typically supported between multiple longitudinal struts 26.
Generally, engine can cause being significantly increased for weight with after thrust reverser, and it is short that its weight accounts for engine
30% or so of cabin weight, this will necessarily increase the fuel consumption of engine or even whole aircraft, therefore ensure propulsive thrust dress
Put with enough it is counter push away efficiency while, keep thrust reverser weight do not increase or decrease be thrust reverser design
Key.
The content of the invention
Present invention aim to address above-mentioned defect of the prior art, i.e., in the feelings of the weight for not increasing thrust reverser
The counter of thrust reverser is improved under condition and pushes away efficiency.
Therefore, the present invention provides the cascade array in a kind of thrust reverser for airborne vehicle fanjet, it is described
Cascade array includes that the axis along the fanjet is arranged and be arranged on the outer culvert of the fanjet longitudinally spacedly
Multiple leaf gratings of the periphery in road, two adjacent leaf gratings form leaf grating runner, and the two ends of leaf grating runner include intake section and go out respectively
Oral area point, the angle of air current flow direction opposite engine axis forms the inclination angle γ of intake section in intake section, described
The angle of air current flow direction opposite engine axis forms the inclination angle δ of exit portion, the leaf grating and institute in exit portion
State after leaf grating runner is configured to make leaf grating described in the airflow passes in the by-pass air duct, the leaf grating can guide it is therein extremely
Few Part I air-flow changes flow direction, to form the first propulsive thrust, wherein, the leaf grating is formed as hollow leaf grating, with
In being internally formed along the cascade internal flow road for allowing the flow to flow through of the Longitudinal extending of leaf grating for leaf grating, the leaf grating is near outer
One end of duct forms cascade internal flow road import, the cascade internal flow road port of export is formed in the opposite other end, in the by-pass air duct
Air-flow Part II by the import of cascade internal flow road enter the leaf grating cascade internal flow road, then by cascade internal flow road
The port of export sprays along jet-impingement angle α and the Part II air-flow is changed flow direction, to form the second propulsive thrust.
Preferably, the port of export makes closing, the spray of at least one exhaust nozzle is set on the port of export with along gas
Air-flow in stream spray angle α injection cascade internal flows road.
Preferably, the port of export makes closing, at least one aperture is formed on the port of export, with along jet-impingement
Air-flow in angle [alpha] injection cascade internal flow road.
Preferably, the port of export make it is unlimited, with along the air-flow in jet-impingement angle α injections cascade internal flow road.
Preferably, the cascade structure is into meeting equation below：
0.9N1≤N2≤N1- 0.5
Wherein, N1Represent the outer thickness of leaf grating；
N2Represent thickness in leaf grating；
N1And N2Unit be mm.
Preferably, the end face of cascade internal flow road import meets equation below relative to the angle beta of engine axis：
45°≤β≤90°
Preferably, the import of cascade internal flow road（5）End face from the air-flow inflow direction perpendicular to the import of cascade internal flow road
Plane direction offsets the increased direction in the windward side of the end face.
Preferably, the airflow spray angle α that the axis of exhaust nozzle is formed as exhaust nozzle with the angle of engine axis is simultaneously
Meet equation below：
90 ° of ＜ α≤135 °
Preferably, in the cascade array, in the inclination angle δ of at least one pair of adjacent exit portion, upstream end
Inclination angle of the inclination angle of exit portion less than the exit portion at downstream.
Preferably, in the cascade array, in the airflow spray angle α of at least one pair of adjacent cascade internal flow road port of export
In, the jet-impingement of the airflow spray angle less than the cascade internal flow road port of export at downstream of the cascade internal flow road port of export of upstream end
Angle.
Preferably, in the cascade array, the inclination angle δ of the exit portion is more than 90 °, near the by-pass air duct
The airflow spray angle α of the inner flow passage port of export of the leaf grating in downstream is identical with the inclination angle δ of corresponding exit portion, near described
At least first airflow spray angle α of the inner flow passage port of export of leaf grating of the leaf grating of by-pass air duct upstream is less than corresponding exit portion
Inclination angle δ.
Preferably, the number M of the exhaust nozzle of each leaf grating is not less than 3, but no more than 10.
Preferably, exhaust nozzle is stretched on the port of export of leaf grating or is placed in inside the port of export of leaf grating without projection
In the port of export of leaf grating, and meet equation below：
0.05L1＜ d ＜ N1
Wherein, L1Represent the width of leaf grating
D represents the diameter of exhaust nozzle.
The present invention also provides a kind of thrust reverser of the airborne vehicle fanjet including cascade array, the propulsive thrust
Device is arranged on the by-pass air duct periphery of engine, and the thrust reverser includes：
The cascade array of at least a portion circumference along by-pass air duct periphery as described above；Keep the cascade array
Leaf grating keeper；The preceding holding seat and rear holding seat at the leaf grating keeper two ends are kept respectively；In the cascade array
Near the anti-propulsion mouthful of the by-pass air duct, the air-flow in the by-pass air duct enters the cascade array from the anti-propulsion mouth；
The anti-kick-off relative with anti-propulsion mouth of cascade array, the air-flow in the cascade array is discharged from the anti-kick-off, from
And form propulsive thrust.
Preferably, the preceding holding seat and rear holding seat are respectively preceding fire wall and rear fire wall.
Preferably, when the air-flow sprays from the exhaust nozzle of the port of export for being stretched on the leaf grating, meeting such as
Lower formula：
0.1L2≤L3And L3+ L2＜ L
Wherein：L is the length of rear fire wall；
L2Leaf grating floor projection length；
L3The floor projection length of exhaust nozzle.
Brief description of the drawings
Fig. 1 a are to include the hollow anti-propulsive thrust dress for pushing away leaf grating according to civilian big Bypass Ratio Turbofan Engine of the invention
Schematic diagram is put, arrow represents the flow direction of the air-flow in the air-flow and thrust reverser in by-pass air duct in figure；
Fig. 1 b are the anti-stereograms for pushing away leaf grating in part shown in Fig. 1 a；
Fig. 2 is the structural representation according to hollow leaf grating of the invention, and it is the partial enlarged drawing of Fig. 1 a illustrated embodiments；
Fig. 3 is the left view of the hollow cascade structure shown in Fig. 2；
Fig. 4 is the schematic diagram of the exhaust nozzle structure of Fig. 1 a illustrated embodiments, and it shows an implementation of exhaust nozzle
Example；
Fig. 5 is the schematic diagram of the exhaust nozzle structure of Fig. 1 a illustrated embodiments, and it shows another reality of exhaust nozzle
Apply example；
Fig. 6 is one embodiment of prior art, and it is the side view of aircraft turbine fan gas turbine engine, is shown
Position of the thrust reversing device assembly on turbofan gas turbine engine is gone out；
Fig. 7 and 8 is one embodiment of another prior art, and they respectively illustrate turbofan aircraft engine
The total arrangement of cascade-type thrust reverser and the direction of fan stream is set to change at least in part forward（Plume）The leaf in direction
The structure of grid.
The description of reference numerals of the embodiment of the present invention：
1：The by-pass air duct of engine
2：Anti- kick-off
3：Leaf grating runner
3a：Leaf grating runner intake section
3b:Cascade flow road exit portion
4：Exhaust nozzle
5：The import of cascade internal flow road
6：Leaf grating
7：Keep the leaf grating tie-beam of leaf grating
8：Keep the rear holding seat of leaf grating tie-beam（Fire wall afterwards）
9：The core hood of engine
10：It is outer to contain jet pipe
11：Stop the choked flow door of by-pass air duct air-flow
12：Anti- propulsion mouth
13：Cascade internal flow road
14：Keep the preceding holding seat of leaf grating tie-beam（Preceding fire wall）
Specific embodiment
The term for hereinafter using is explained：
Horizontal line refers to the straight line parallel to engine longitudinal axis；
The outer thickness of leaf grating 6 is the width and the wall thickness sum of leaf grating 6 in the cascade internal flow road 13 of leaf grating 6；
Thickness is the width in cascade internal flow road 13 in leaf grating 6；
The windward side of the end face of the cascade internal flow road port of export refers to perspective plane of the end face along by-pass air duct air current flow direction, with
The air-flow is relative.
It is anti-in order to improve civilian big Bypass Ratio Turbofan Engine cascade type as a preferred embodiment of the invention
The anti-weight for pushing away efficiency, reducing thrust reverser of thrust device, the present invention devises a kind of hollow anti-structure side for pushing away leaf grating
Case.By the structure, a part of reverse thrusting airflow is discharged by the anti-leaf grating inner passage that pushes away, on the one hand increased propulsive thrust air-flow
Flow, improve it is counter push away efficiency, on the other hand, solid leaf grating is changed into hollow leaf grating, reduce the weight of thrust reverser,
Improve engine economy.Additionally, the injection direction by changing leaf grating internal gas flow, adjusts anti-plug-flow field distribution, reduce
The amount that reverse thrusting airflow is sucked again by air intake duct, or avoid reverse thrusting airflow from being sucked again by air intake duct, so as to improve engine work
Stability.
A specific embodiment in accordance with the principles of the present invention is related to a kind of big Bypass Ratio Turbofan Engine thrust reverser
The structure of hollow leaf grating, is further described with the embodiment to profit of the present invention below in conjunction with the accompanying drawings.
As seen in figure la and lb, it illustrates the structural representation using the hollow anti-thrust reverser for pushing away leaf grating.In figure
Show the core hood 9 of covering engine, the air-flow outflow in the by-pass air duct 1, prevention by-pass air duct 1 of the outside of core hood 9
The choked flow door 11 and the thrust reverser of airflow passes of by-pass air duct 1.After airflow passes thrust reverser in by-pass air duct 1, extremely
Few a part of air-flow therein is formed and the reverse air-flow of the air-flow of by-pass air duct 1.Thrust reverser includes preceding holding seat 14 and rear guarantor
Hold seat 8, along the circumferentially distributed multiple cascade arrays of at least a portion of the periphery of by-pass air duct 1, be provided with cascade array its two
End keeps seat 14 and the rear leaf grating tie-beam 7 kept on seat 8 before being separately mounted to.Wherein, each cascade array includes multiple edges
Multiple leaf gratings 6 of longitudinally spaced distributions, it is preferred that for each cascade array provides two leaf grating tie-beams 7, they are respectively provided with
In two ends of each leaf grating 6.Leaf grating tie-beam can also use other structures, such as platy structure.Thrust reverser is also
Including anti-propulsion mouth 12 and anti-kick-off 2, the air-flow in by-pass air duct 1 enters thrust reverser, Ran Houtong by anti-propulsion mouth 12
Cross anti-kick-off 2 and leave thrust reverser, so as to form propulsive thrust.
In the embodiment shown in Fig. 1 a and 1b, leaf grating 6 is designed to hollow.It is hollow as shown in Fig. 1 a and 1b and 2
Empty part forms cascade internal flow road 13 to leaf grating 6 wherein, and is formed and each leaf grating tie-beam 7 between each leaf grating 6
Leaf grating runner 3.Leaf grating 6 forms cascade internal flow road import 5 near one end of anti-propulsion mouth 12, and leaf grating 6 is close to the one of anti-kick-off 2
The formation cascade internal flow road port of export at end（It is unmarked）If the port of export makes closing, set on the port of export to
Few exhaust nozzle spray 4 is with jet-stream wind.
Two adjacent leaf grating 6 forms leaf grating runner 3, and the two ends of leaf grating runner 3 are respectively intake section 3a and exit portion 3b.
The inclination angle γ that the angle of air current flow direction relative level line is formed in intake section 3a is less than 90 °, and in exit portion 3b
The inclination angle δ that the angle of middle air current flow direction relative level line is formed is more than 90 °, as shown in Figure 2.So, in by-pass air duct 1
By there is a deflection after leaf grating 6, the angle of the deflection depends on the inclination angle of the exit portion 3b of leaf grating runner 3 to air-flow
δ。
As seen in figure la and lb, the air-flow for flowing through by-pass air duct (1) enters thrust reverser by anti-propulsion mouth 12, and respectively
Discharged outside engine by anti-kick-off 2 through leaf grating runner 3 and cascade internal flow road 13.Wherein by-pass air duct-leaf grating runner is by core
Hood 9, choked flow 11, anti-propulsion mouth 12, leaf grating 6, leaf grating tie-beam 7, preceding holding seat 14, rear holding 2 groups of seat 8 and anti-kick-off
Into；By-pass air duct-cascade internal flow road advances mouth 12, cascade internal flow road import 5, leaf grating 6, exhaust nozzle 4 and anti-kick-off 2 by counter
Composition.The inclination angle δ of the exit portion 3b of leaf grating runner 3 is depended on from the direction of the air-flow of by-pass air duct-leaf grating runner outflow,
And the direction of the air-flow from by-pass air duct-cascade internal flow road outflow depends on the air-flow spray of the port of export of cascade internal flow road 13 of leaf grating 6
Penetrate angle [alpha] of the direction relative to horizontal axis, i.e. jet-impingement angle 3b.
Fig. 2 and 3 shows a preferred embodiment of the invention.Where due to preceding holding seat 14, rear holding seat 8
Position is high temperature position, and preceding holding seat 14 and rear holding seat 8 are made into preceding fire wall 14 and rear fire wall 8 respectively.Fire wall 8 afterwards
Length less than or equal to preceding fire wall 14 length and be set to L, the width perpendicular to drawing shown in Fig. 1 a and 1b of leaf grating 6 is
L1, the floor projection length of leaf grating 6 is L2, the floor projection length of exhaust nozzle 4 is L3, the outer thickness of leaf grating 6 is N1, in leaf grating 6
Thickness is N2, a diameter of d of exhaust nozzle 4, exhaust nozzle axis is α, the import 5 in cascade internal flow road 13 with horizontal angle
End face and horizontal angle be β, the number of exhaust nozzle 4 is M.
Following setting is made in a preferred embodiment of the invention：
（1）It is counter to push away thickness N in leaf grating for the air-flow for enabling by-pass air duct as much as possible 1 enters cascade internal flow road 132Should
Thickness N outer not less than leaf grating10.9 times, and with N2=0.9N1For optimal, meanwhile, in order to ensure that leaf grating 6 has certain intensity,
N1With N2Difference should be not less than 0.5mm.
Formula 1：0.9N1≤N2≤N1- 0.5
Wherein unit is mm
（2）To ensure that cascade internal flow road 13 can capture more by-pass air duct air-flows, the end face and water of cascade internal flow road import 5
The angle β of horizontal line should be not less than 45 °, but to reduce the influence to the runner at cascade internal flow road import 5, β should be not more than 90 °.
Formula 2：45°≤β≤90°
（3）For the air-flow for ensureing cascade internal flow road 13 can provide bigger propulsive thrust, the axis and level of exhaust nozzle 4
The angle α of line should be greater than 90 °, but to reduce the amount that reverse thrusting airflow is sucked again by engine inlets, α should be not more than 135 °.It is right
In first leaf grating near preceding fire wall 14, its α is optimal with 120 °.In a preferred embodiment, in upstream
The leaf grating of preceding fire wall 14 is located proximate to, the exhaust angle δs of the spray angle α less than leaf grating runner 3 of its exhaust nozzle 4.
Formula 3：90 ° of ＜ α≤135 °
（4）To ensure that air-flow has enough speed and good directionality from after the ejection of exhaust nozzle 4, exhaust nozzle 4
Floor projection length L3Leaf grating floor projection length L should be not less than20.1 times, but to ensure to reduce weight and recurring structure is dry
Relate to, the floor projection length L of exhaust nozzle 43With the floor projection length L of leaf grating 62Sum should be less than the length L of rear fire wall 8, with
L2=0.2L3For optimal.That is the floor projection length L of exhaust nozzle 43, leaf grating floor projection length L2, rear fire wall 8 length L
Between meet following condition：
Formula 4：0.1L2≤L3And L3+ L2＜ L
（5）To ensure the uniform of anti-plug-flow, and there can be enough air-flows to be discharged from cascade internal flow road 13, exhaust nozzle 4
It is uniformly distributed along the width of leaf grating 6, the number M of the exhaust nozzle 4 of each leaf grating is not less than 3, but in view of arrangement space
And weight factor, M is not more than 10.
Formula 5：3≤M≤10
（6）To ensure that the reliable of exhaust nozzle 4 is installed and exhaust capacity, exhaust nozzle diameter d should be less than the outer thickness of leaf grating
N1, but should be greater than cascade-wide L10.05 times.
Formula 5：0.05L1＜ d ＜ N1
As shown in Figures 4 and 5, two embodiments of exhaust nozzle 4 are respectively illustrated.In the embodiment shown in fig. 4, it is vented
The exhaust nozzle 4 being configured similarly to shown in Fig. 2 of nozzle 4, exhaust nozzle 4 is stretched on the end of leaf grating 6.And shown in Fig. 5
In embodiment, exhaust nozzle 4 is placed in the inner end portion of leaf grating 6 without being stretched on the end of leaf grating 6, so both ensure that air-flow
From the speed that the nozzle of leaf grating 6 sprays, influence of the nozzle to anti-plug-flow is reduced again.One embodiment not shown in figure
In, the cascade internal flow road port of export of leaf grating 6 makes unlimited, the then air-flow directly outflow from the port of export.Not shown in figure
Another embodiment in, the cascade internal flow road port of export of leaf grating 6 makes closing, and some apertures are set in the blind end,
Then air-flow directly flows out from these apertures.
In as mentioned in the embodiment of figure 2, the end face of cascade internal flow road import 5 is from perpendicular to the import of cascade internal flow road（5）
The plane direction of air-flow inflow direction offsets the increased direction in the windward side of the end face.
By the description of exemplary embodiment as described above of the invention, it can be realized that the present invention made as
Under improvement：
（1）When aircraft landing, abort etc. and to need thrust reverser to work in the case of, in accordance with the invention it is possible to make
Contain air-flow outside most of engine and enter leaf grating runner and from the discharge of anti-kick-off from anti-propulsion mouth, a part of air-flow is advanced from anti-
Mouth enters leaf grating inner flow passage, and exports discharge from leaf grating inner flow passage, is most discharged outside engine through anti-kick-off afterwards, is increased with this
Plus counter push away the counter of leaf grating and push away efficiency.
（2）To ensure speed of the air-flow from after the ejection of leaf grating inner flow passage with needed for, and ensure that its injection direction meets
The anti-demand for pushing away design, exhaust nozzle is set in leaf grating inner flow passage exit.
（3）For the leaf grating in upstream position, the spray angle of its exhaust nozzle is less than the exhaust angle of leaf grating runner,
To reduce sucking again for reverse thrusting airflow.
（4）To enable that leaf grating captures more air-flows, the import of leaf grating inner flow passage uses spade structure.
The implementation of above-mentioned example is illustrated the implementation in the technical scheme for solving the technical problem to be solved in the present invention
Example.Under the example of above-described embodiment, other equivalent and similar means for meeting the principle of the invention belong to protection of the present invention
Scope in.Inventive principle of the invention be the leaf grating of thrust reverser is made it is hollow, to form cascade internal flow road, from
And cascade internal flow road also counter is pushed away effect improving for forming deboost.
Claims (16)
1. a kind of cascade array in thrust reverser for airborne vehicle fanjet, the cascade array is included along described
The axis of fanjet arrange longitudinally spacedly and be arranged on the fanjet by-pass air duct periphery multiple leaves
Grid, two adjacent leaf gratings form leaf grating runner (3), and the two ends of leaf grating runner (3) include intake section (3a) and exit portion respectively
(3b), the angle of air current flow direction opposite engine axis forms the inclination angle of intake section (3a) in intake section (3a)
γ, the angle of air current flow direction opposite engine axis forms the inclination angle of exit portion (3b) in the exit portion (3b)
δ, the leaf grating (6) and the leaf grating runner (3) are configured to make after leaf grating described in the airflow passes in the by-pass air duct, described
Leaf grating can guide at least Part I air-flow therein to change flow direction, to form the first propulsive thrust, it is characterised in that
The leaf grating (6) is formed as hollow leaf grating, and making along the Longitudinal extending of leaf grating (6) is internally formed with leaf grating (6)
The cascade internal flow road (13) that air-flow can flow through, the leaf grating (6) is forming cascade internal flow road import near one end of by-pass air duct
(5) the cascade internal flow road port of export, is formed in the opposite other end, the Part II of the air-flow in the by-pass air duct is by leaf grating
Tunnel inlets (5) enter the cascade internal flow road (13) of the leaf grating (6), then by the cascade internal flow road port of export along jet-impingement
Angle [alpha] sprays and the Part II air-flow is changed flow direction, to form the second propulsive thrust.
2. cascade array as claimed in claim 1, it is characterised in that the port of export makes closing, on the port of export
At least one exhaust nozzle (4) is set with along the air-flow in jet-impingement angle α injections cascade internal flow road (13).
3. cascade array as claimed in claim 1, it is characterised in that the port of export makes closing, on the port of export
At least one aperture is formed, with along the air-flow in jet-impingement angle α injections cascade internal flow road (13).
4. cascade array as claimed in claim 1, it is characterised in that the port of export make it is unlimited, with along airflow spray angle
Degree α sprays the air-flow in cascade internal flow road (13).
5. cascade array as claimed in claim 1, it is characterised in that the cascade structure is into meeting equation below：
0.9N1≤N2≤N1- 0.5
Wherein, N1Represent the outer thickness of leaf grating；
N2Represent thickness in leaf grating；
N1And N2Unit be mm.
6. cascade array as claimed in claim 1, it is characterised in that the end face of cascade internal flow road import (5) is relative to starting
The angle beta of arbor line meets equation below：
45°≤β≤90°。
7. cascade array as claimed in claim 6, it is characterised in that the end face of cascade internal flow road import (5) is from perpendicular to leaf
The plane direction of the air-flow inflow direction of grid inner flow passage import (5) offsets the increased direction in the windward side of the end face.
8. such as the described cascade array in claim 2, it is characterised in that the axis and engine axis of exhaust nozzle (4)
Angle be formed as the airflow spray angle α of exhaust nozzle (4) and meet equation below：
90 ° of ＜ α≤135 °.
9. the cascade array as described in any one in claim 1-8, it is characterised in that in the cascade array,
In the inclination angle δ of at least one pair of adjacent exit portion (3b), the inclination angle of the exit portion (3b) of upstream end is less than at downstream
Exit portion (3b) inclination angle.
10. the cascade array as described in any one in claim 1-8, it is characterised in that in the cascade array,
In the airflow spray angle α of at least one pair of adjacent cascade internal flow road port of export, the air-flow of the cascade internal flow road port of export of upstream end
Airflow spray angle of the jet angle less than the cascade internal flow road port of export at downstream.
11. cascade array as described in any one in power claim 1-8, it is characterised in that in the cascade array
In, the inclination angle δ of the exit portion (3b) is more than 90 °, in the inner flow passage outlet of the leaf grating (6) near the by-pass air duct downstream
The airflow spray angle α at end is identical with the inclination angle δ of corresponding exit portion (3b), in the leaf grating near the by-pass air duct upstream
(6) inclinations angle of at least first airflow spray angle α of the inner flow passage port of export of leaf grating (6) less than corresponding exit portion (3b)
δ。
12. cascade arrays as claimed in claim 8, it is characterised in that the number M of the exhaust nozzle (4) of each leaf grating is not small
In 3, but no more than 10.
13. cascade arrays as claimed in claim 8, it is characterised in that exhaust nozzle (4) be stretched on leaf grating (6) it is described go out
Mouth end is placed in inside the port of export of leaf grating (6) without being stretched on the port of export of leaf grating (6), and meets equation below：
0.05L1＜ d ＜ N1
Wherein, L1Represent the width of leaf grating (6)；
D represents the diameter of exhaust nozzle (4)；
N1Represent the outer thickness of leaf grating.
A kind of 14. thrust reversers of airborne vehicle fanjet, the thrust reverser is arranged on outside the by-pass air duct of engine
Zhou Shang, the thrust reverser includes：
Cascade array as described in any one in claim 1-13, the cascade array along the engine outer culvert
At least a portion circumference of road periphery；
Keep the leaf grating keeper (7) of the cascade array；
Preceding holding seat (14) at leaf grating keeper (7) two ends and rear holding seat (8) are kept respectively；
In the anti-propulsion mouthful (12) of the close described by-pass air duct of the cascade array, air-flow in the by-pass air duct counter is pushed away from described
Import (12) enters the cascade array；
In the relative anti-kick-off (2) of cascade array and anti-propulsion mouth (12), air-flow in the cascade array is from described anti-
Kick-off (2) is discharged, so as to form propulsive thrust.
15. thrust reversers as claimed in claim 14, it is characterised in that seat (14) and rear holding seat (8) are kept before described
It is respectively preceding fire wall and rear fire wall.
16. thrust reversers as claimed in claim 15, it is characterised in that when the air-flow is from being stretched on the leaf grating (6)
The port of export exhaust nozzle (4) spray when, meet equation below：
0.1L2≤L3And L3+L2＜ L
Wherein：L is the length of rear fire wall；
L2Leaf grating floor projection length；
L3The floor projection length of exhaust nozzle.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310680725.5A CN104712455B (en) | 2013-12-12 | 2013-12-12 | The thrust reverser of fanjet and push away leaf grating for the counter of the thrust reverser |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310680725.5A CN104712455B (en) | 2013-12-12 | 2013-12-12 | The thrust reverser of fanjet and push away leaf grating for the counter of the thrust reverser |
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| CN104712455A CN104712455A (en) | 2015-06-17 |
| CN104712455B true CN104712455B (en) | 2017-07-04 |
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| CN110530595A (en) * | 2019-07-19 | 2019-12-03 | 南京航空航天大学 | A kind of plane cascade test platform test section inlet system of the adjustable angle of attack |
| CN112796882B (en) * | 2020-12-30 | 2022-03-15 | 长江大学 | Reverse thrust system of turboprop engine |
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|---|---|---|---|---|
| CN101104441A (en) * | 2006-07-11 | 2008-01-16 | 通用电气公司 | Gas turbine engine and method of operating same |
| CN101614164A (en) * | 2008-06-23 | 2009-12-30 | 罗尔股份有限公司 | Trhrust-reversal device leaf grating assembly and posterior lobe grating ring with flow deflector portion |
| CN102933829A (en) * | 2010-06-08 | 2013-02-13 | 埃尔塞乐公司 | Self-mounted cascade for a thrust reverser |
| FR2981989A1 (en) * | 2011-10-31 | 2013-05-03 | Aircelle Sa | MOBILE SCREW REVERSE INVERTER AND MONOBLOC MOBILE HOOD |
| CN103184935A (en) * | 2011-12-28 | 2013-07-03 | 中航商用航空发动机有限责任公司 | Hot-air anti-icer for engine inlet |
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2013
- 2013-12-12 CN CN201310680725.5A patent/CN104712455B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101104441A (en) * | 2006-07-11 | 2008-01-16 | 通用电气公司 | Gas turbine engine and method of operating same |
| CN101614164A (en) * | 2008-06-23 | 2009-12-30 | 罗尔股份有限公司 | Trhrust-reversal device leaf grating assembly and posterior lobe grating ring with flow deflector portion |
| CN102933829A (en) * | 2010-06-08 | 2013-02-13 | 埃尔塞乐公司 | Self-mounted cascade for a thrust reverser |
| FR2981989A1 (en) * | 2011-10-31 | 2013-05-03 | Aircelle Sa | MOBILE SCREW REVERSE INVERTER AND MONOBLOC MOBILE HOOD |
| CN103184935A (en) * | 2011-12-28 | 2013-07-03 | 中航商用航空发动机有限责任公司 | Hot-air anti-icer for engine inlet |
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|---|---|
| CN104712455A (en) | 2015-06-17 |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201108 Shanghai city Minhang District Lotus Road No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |