CN104712455A - Reverse thrust device of fanjet and reverse thrust blade grid applied to reverse thrust device - Google Patents
Reverse thrust device of fanjet and reverse thrust blade grid applied to reverse thrust device Download PDFInfo
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- CN104712455A CN104712455A CN201310680725.5A CN201310680725A CN104712455A CN 104712455 A CN104712455 A CN 104712455A CN 201310680725 A CN201310680725 A CN 201310680725A CN 104712455 A CN104712455 A CN 104712455A
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Abstract
The invention provides a blade grid array applied to a reverse thrust device of an aircraft fanjet. The blade grid array comprises multiple blade grids, wherein blade grid channels are formed between adjacent two blade grids; after the blade grids and the blade grid channels are configured to enable air flows in outer ducts to flow pass the blade grids, the blade grids can guide at least first part of the air flows to change the flowing direction so as to form the first reverse thrust, wherein the blade grids are formed as hollow blade grids to form blade grid inner runners extending in the longitudinal direction of the blade grids in the blade grids, and the air flows can flow through the blade grid inner runners; blade grid inner runner inlets are formed in one ends, near the outer ducts, of the blade grids, and blade grid inner runner outlet ends are formed at the opposite other end; and the second part of the air flows in the outer ducts enters the blade grid inner runners through the blade grid inner runner inlets, and is ejected out at the blade grid inner runner outlet ends along an airflow ejecting angle alpha to change the flowing direction so as to form the second reverse thrust.
Description
Technical field
The present invention relates to the thrust reverser of airplane engine, especially the thrust reverser of turbofan engine.To the invention further relates in thrust reverser counter pushes away leaf grating.
Background technique
First the implication of relevant technical terms is described.Thrust reverser: refer to engine air flow reverse, for providing the device of deboost when aircraft or landing.Instead push away efficiency: the ratio referring to deboost and forward thrust.
For shortening aircraft landing ground run distance, nearly all civil aircraft all adopts thrust reverser to slow down, and slow down relative to employing wheel brake device, THR REV can shorten aircraft landing Distance Shortened nearly 65%.The working principle of thrust reverser makes normal airflow flow direction in motor be greater than 90 ° turning back, thus produce thrust component on the direction contrary with normal thrust, thus reach the object making aircraft.In general, because turning back of air-flow can not reach 180 °, deboost is approximately about 30% of positive thrust.
Thrust reverser is broadly divided into cascade type thrust reverser, baffling gate-type thrust reverser and target formula thrust reverser according to the mechanism producing reaction thrust, these three kinds of thrust reversers respectively have pluses and minuses, its middle period target formula thrust reverser structure and motion simple, but weight is larger and pneumatic comparatively large with thermal force, generally adopts in turbojet engine or little Bypass Ratio Turbofan Engine; Baffling gate-type thrust reverser structural mechanism is relatively simple, but counter to push away efficiency relatively low; Cascade type thrust reverser is counter push away most effective, but structure relative complex, be at present large Bypass Ratio Turbofan Engine mainly adopt instead push away form.
CN102877382A provides a kind of newly counter to push away mobile cover design proposal for cascade type thrust reverser, when thrust reverser is in running order, the anti-mobile cover that pushes away is not to slide axially but radial development increases wind-exposuring area with this thus increases reaction thrust and instead push away efficiency.CN102753808A by designing an airway in the downstream of thrust reverser, thus reduces the overall sizes of thrust reverser and engine nacelle.CN102865156A provides and a kind ofly utilizes the variable area jet pipe of public actuator and the scheme of thrust reverser, utilize the actuating system of thrust reverser to complete adjustment to nozzle exit area, not only achieve the start of thrust reverser mechanism but also motor can be realized to nozzle exit area regulatory demand.US6434927B1 provides a kind of leaf grating portable thrust reverser scheme, when counter push away be in closed condition time, instead push away leaf grating standing part and moveable part is in same axial position, when counter push away open time, leaf grating moveable part moves with choked flow door backward, the program decreases the axial arranged space of leaf grating, makes motor compacter, is conducive to loss of weight.CN201245246Y provides that a kind of umbrella baffling door is counter pushes away scheme, and adopts nonmetallic material, reduces the weight of thrust reverser.
Fig. 6 is patent documentation
cN101104441Ain a side view that accompanying drawings that show an exemplary aircraft turbine fan gas turbine engine 10, it is installed on the upper surface of aircraft wing 12, and comprises trhrust-reversal device assembly 100.Core gas turbine engine 20 is encapsulated in the core cover 22 of annular, and fan gondola 24 is around a part for fan 16 and core-engine 20.Between the front portion of the core cover 22 around core gas turbine engine 20 and the afterbody internal surface by the isolated gondola 24 of this radially outward, define the bypass duct 26 of annular, i.e. by-pass air duct.Operationally, surrounding atmosphere 28 enters the entrance 30 of gas turbine assembly 10 and flows through fan 16.The first portion 32 of air-flow 28 is guided through core gas turbine engine 20, carry out compressing and and fuel mix, and by lighting a fire for generation of combustion gas 34, combustion gas 34 are discharged from the core nozzle 36 of core gas turbine engine 20.The second portion 38 of air-flow 28 is directed downstream through by-pass air duct 26.Trhrust-reversal device assembly 100 is arranged on the periphery of by-pass air duct 26.
Fig. 7 and 8 is patent documentation
cN101614164Ain accompanying drawing.As shown in Figure 7, leaf grating assembly 20 is disposed in discharge aperture 15.Leaf grating assembly 20 typically comprises the leaf grating section 28 of multiple circumferential arrangement.Fig. 8 shows typically for the some parts of the cascade type trhrust-reversal device 10 of turbofan aircraft motor.As shown in Figure 8, when launching trhrust-reversal device 10, moving translation sleeve 16 backward and making it away from the rear end of the fixing part 12 in cabin, between fixing part 12 and the front end of translation sleeve 16, providing discharge aperture 15 like this.In order to provide the deboost of the aircraft making landing, discharge aperture 15 allows fan stream to discharge from the ring-type fan pipe 13 (i.e. by-pass air duct) of motor.As shown in Figure 8, the multiple retardance doors 18 near the front end of launching translation sleeve 16, to be arrested in the flowing backward of the fan stream in ring-type fan pipe 13, and impel fan to flow through discharge aperture 15 to flow out motor.As shown in Figure 8, each leaf grating section 28 of circumference comprises multiple blade 25 be spaced along the longitudinal, and in order to provide deboost, blade 25 is configured to the direction of the fan stream of outflow to change into direction forward at least in part, to form plume.Blade 25 is typically supported between multiple longitudinal strut 26.
Generally, motor is with after thrust reverser, the significantly increase of weight can be caused, its weight accounts for about 30% of engine nacelle weight, this will inevitably increase the fuel consumption of motor and even whole aircraft, therefore ensure thrust reverser have enough counter push away efficiency while, keeping the weight of thrust reverser not increase or decreasing is the key of thrust reverser design.
Summary of the invention
The object of the invention is to solve above-mentioned defect of the prior art, namely improve the counter of thrust reverser when not increasing the weight of thrust reverser and push away efficiency.
For this reason, the invention provides a kind of for the leaf grating array in the thrust reverser of aircraft turbofan engine, described leaf grating array comprise along described turbofan engine axis longitudinal separation arrange, and be arranged on multiple leaf gratings of the periphery of the by-pass air duct of described turbofan engine, two adjacent leaf gratings form leaf grating runner, the two ends of leaf grating runner include notch portion and exit portion respectively, in intake section, the angle of air current flow direction opposite engine axis forms the tilt angle γ of intake section, in described exit portion, the angle of air current flow direction opposite engine axis forms the tilt angle δ of exit portion, after described leaf grating and described leaf grating runner are configured to make leaf grating described in the airflow passes in described by-pass air duct, described leaf grating can guide at least first portion air-flow wherein to change flow direction, to form the first reaction thrust, wherein, described leaf grating is formed as the leaf grating of hollow, to form the cascade internal flow road enabling air-flow flow through along the longitudinal extension of leaf grating in the inside of leaf grating, described leaf grating is forming the import of cascade internal flow road near one end of by-pass air duct, cascade internal flow road outlet end is formed at the contrary the other end, the second portion of the air-flow in described by-pass air duct enters the cascade internal flow road of described leaf grating by the import of cascade internal flow road, then spray along jet-impingement angle α through cascade internal flow road outlet end and make described second portion air-flow change flow direction, to form the second reaction thrust.
Preferably, this outlet end is made closed, described outlet end arranges the spray of at least one exhaust nozzle to spray the air-flow in cascade internal flow road along jet-impingement angle α.
Preferably, this outlet end is made closed, and described outlet end is formed at least one aperture, to spray the air-flow in cascade internal flow road along jet-impingement angle α.
Preferably, this outlet end is made unlimited, to spray the air-flow in cascade internal flow road along jet-impingement angle α.
Preferably, described cascade structure becomes to meet following formula:
0.9N
1≤N
2≤N
1－0.5
Wherein, N
1represent the outer thickness of leaf grating;
N
2represent thickness in leaf grating;
N
1and N
2unit be mm.
Preferably, the end face of cascade internal flow road import meets following formula relative to the angle beta of engine axis:
45°≤β≤90°
Preferably, the end face of cascade internal flow road import (5) offsets from the plane of the air-flow inflow direction perpendicular to the import of cascade internal flow road towards the direction making the windward side of described end face increase.
Preferably, the axis of exhaust nozzle and the angle of engine axis are formed as the airflow spray angle α of exhaust nozzle and meet following formula:
90°＜α≤135°
Preferably, in described leaf grating array, in the tilt angle δ of at least one pair of adjacent exit portion, the tilt angle of the exit portion of upstream end is less than the tilt angle of the exit portion of downstream part.
Preferably, in described leaf grating array, in the airflow spray angle α of at least one pair of adjacent cascade internal flow road outlet end, the airflow spray angle of the cascade internal flow road outlet end of upstream end is less than the airflow spray angle of the cascade internal flow road outlet end of downstream part.
Preferably, in described leaf grating array, the tilt angle δ of described exit portion is greater than 90 °, identical with the tilt angle δ of corresponding exit portion at the airflow spray angle α of inner flow passage outlet end of the leaf grating near described by-pass air duct downstream, close described by-pass air duct upstream the airflow spray angle α of inner flow passage outlet end of at least the first leaf grating of leaf grating be less than the tilt angle δ of corresponding exit portion.
Preferably, the number M of the exhaust nozzle of each leaf grating is not less than 3, but is not more than 10.
Preferably, exhaust nozzle is stretched on the described outlet end of leaf grating or to be placed in the outlet end of leaf grating inner and be not stretched on the outlet end of leaf grating, and meets following formula:
0.05L
1＜d＜N
1
Wherein, L
1represent the width of leaf grating
D represents the diameter of exhaust nozzle.
The present invention also provides a kind of thrust reverser comprising the aircraft turbofan engine of leaf grating array, and described thrust reverser is arranged on the by-pass air duct periphery of motor, and described thrust reverser comprises:
As above along the leaf grating array of the circumference at least partially of by-pass air duct periphery; Keep the leaf grating holder of described leaf grating array; Keep the front holder at described leaf grating holder two ends and rear holder respectively; At the anti-propelling mouth of the close described by-pass air duct of described leaf grating array, the air-flow in described by-pass air duct enters described leaf grating array from described anti-propelling mouth; Leaf grating array with the anti-release mouth instead advancing mouth relative, the air-flow in described leaf grating array is discharged from described anti-release mouth, thus formation reaction thrust.
Preferably, described front holder and rear holder are front fire-wall and rear fire-wall respectively.
Preferably, when described air-flow sprays from the exhaust nozzle of the described outlet end being stretched on described leaf grating, following formula is met:
0.1L
2≤ L
3and L
3+ L
2< L
Wherein: L is the length of rear fire-wall;
L
2leaf grating horizontal projection length;
L
3the horizontal projection length of exhaust nozzle.
Accompanying drawing explanation
Fig. 1 a comprises the hollow anti-thrust reverser schematic diagram pushing away leaf grating according to civilian large Bypass Ratio Turbofan Engine of the present invention, and in figure, arrow represents the flow direction of the air-flow in by-pass air duct and the air-flow in thrust reverser;
Fig. 1 b is the anti-stereogram pushing away leaf grating of the part shown in Fig. 1 a;
Fig. 2 is the structural representation according to hollow leaf grating of the present invention, and it is the partial enlarged drawing of Fig. 1 a illustrated embodiment;
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 embodiment, it illustrates an embodiment of exhaust nozzle;
Fig. 5 is the schematic diagram of the exhaust nozzle structure of Fig. 1 a illustrated embodiment, it illustrates another embodiment of exhaust nozzle;
Fig. 6 is an embodiment of prior art, and it is the side view of aircraft turbine fan gas turbine engine, shows the position of trhrust-reversal device assembly on turbofan gas turbine engine;
Fig. 7 and 8 is an embodiment of another prior art, which respectively illustrates the total arrangement of the cascade type trhrust-reversal device of turbofan aircraft motor and makes the direction of fan stream change into the structure of the leaf grating in (plume) direction forward at least in part.
The description of reference numerals of the embodiment of the present invention:
1: the by-pass air duct of motor
2: instead release mouth
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: the leaf grating tie-beam keeping leaf grating
8: the rear holder (rear fire-wall) keeping leaf grating tie-beam
9: the core hood of motor
10:. contains jet pipe outward
11: the choked flow door stopping by-pass air duct air-flow
12: instead advance mouth
13: cascade internal flow road
14: the front holder (front fire-wall) keeping leaf grating tie-beam
Embodiment
The terminological interpretation hereinafter used:
Horizontal line refers to the straight line being parallel to motor longitudinal axis;
The outer thickness of leaf grating 6 is width and the leaf grating 6 wall thickness sum in the cascade internal flow road 13 of leaf grating 6;
In leaf grating 6, thickness is the width in cascade internal flow road 13;
The windward side of the end face of cascade internal flow road outlet end refers to the projection plane of this end face along by-pass air duct air current flow direction, relative with this air-flow.
As a preferred embodiment according to the present invention, push away efficiency to improve civilian large the counter of Bypass Ratio Turbofan Engine cascade type thrust reverser, reduce the weight of thrust reverser, the present invention devises a kind of hollow anti-organization plan pushing away leaf grating.By this structure, counter for the part air-flow that pushes away is discharged by the anti-leaf grating inner passage that pushes away, adds the flow of reaction thrust air-flow on the one hand, improve and instead push away efficiency, on the other hand, solid leaf grating is become hollow leaf grating, reduce the weight of thrust reverser, improve motor Economy.In addition, by changing the injection direction of leaf grating internal gas flow, adjusting anti-plug-flow field pattern, reducing the anti-amount pushing away air-flow and sucked again by intake duct, or avoiding the anti-air-flow that pushes away to be sucked again by intake duct, thus improve the stability of engine operation.
Specific embodiment relates to a kind of structure of hollow leaf grating of large Bypass Ratio Turbofan Engine thrust reverser in accordance with the principles of the present invention, is further described profit of the present invention below in conjunction with accompanying drawing and this embodiment.
As shown in figures i a andb, it illustrates the hollow anti-structural representation pushing away the thrust reverser of leaf grating of employing.There is shown the core hood 9 of covering engine, the by-pass air duct 1 outside core hood 9, the air-flow outflow choked flow door 11 of by-pass air duct 1 in prevention by-pass air duct 1 and the thrust reverser of airflow passes.After airflow passes thrust reverser in by-pass air duct 1, a part of air-flow at least wherein forms the air-flow reverse with by-pass air duct 1 air-flow.Thrust reverser comprises front holder 14 and rear holder 8, the leaf grating tie-beam 7 be arranged on respectively along multiple leaf grating arrays of the distribution of circumference at least partially of the periphery of by-pass air duct 1, its two ends of being provided with leaf grating array in front holder 14 and rear holder 8.Wherein, each leaf grating array comprises multiple multiple leaf gratings 6 longitudinally spaced apart, and preferably, for each leaf grating array provides two leaf grating tie-beams 7, they are separately positioned on two ends of each leaf grating 6.Leaf grating tie-beam also can adopt other structure, such as platy structure.Thrust reverser also comprises the anti-mouth 12 that advances and releases mouth 2 with anti-, and the air-flow in by-pass air duct 1 enters thrust reverser by anti-propelling mouth 12, then leaves thrust reverser by anti-mouth 2 of releasing, thus forms reaction thrust.
In the embodiment shown in Fig. 1 a and b, leaf grating 6 is designed to hollow.As shown in Fig. 1 a and b and 2, the leaf grating 6 empty part formation cascade internal flow road 13 wherein of hollow, and leaf grating runner 3 is formed between each leaf grating 6 and between each leaf grating tie-beam 7.Leaf grating 6 forms cascade internal flow road import 5 near the anti-one end of mouth 12 that advances, leaf grating 6 is near anti-formation cascade internal flow road outlet end (unmarked) releasing one end of mouth 2, if this outlet end is made closed, then the spray 4 of at least one exhaust nozzle is set on this outlet end with jet-stream wind.
Two adjacent leaf gratings 6 form leaf grating runner 3, and the two ends of leaf grating runner 3 are respectively intake section 3a and exit portion 3b.The tilt angle γ that in intake section 3a, the angle of air current flow direction relative level line is formed is less than 90 °, and the tilt angle δ that the angle of air current flow direction relative level line is formed in exit portion 3b is greater than 90 °, as shown in Figure 2.Like this, the air-flow in by-pass air duct 1 has had a deflection after leaf grating 6, and the angle of this deflection depends on the tilt angle δ of the exit portion 3b of leaf grating runner 3.
As shown in figures i a andb, the air-flow flowing through by-pass air duct (1) enters thrust reverser by the anti-mouth 12 that advances, and is discharged outside motor by anti-mouth 2 of releasing through leaf grating runner 3 and cascade internal flow road 13 respectively.Wherein by-pass air duct-leaf grating runner is made up of core hood 9, choked flow door 11, anti-mouth 12, leaf grating 6, leaf grating tie-beam 7, front holder 14, rear holder 8 and the anti-mouth 2 of releasing of advancing; By-pass air duct-cascade internal flow road is made up of anti-mouth 12, cascade internal flow road import 5, leaf grating 6, exhaust nozzle 4 and the anti-mouth 2 of releasing of advancing.The tilt 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 angle [alpha] of jet-impingement direction relative to horizontal axis of cascade internal flow road 13 outlet end of leaf grating 6, i.e. jet-impingement angle 3b are depended in the direction of the air-flow flowed out from by-pass air duct-cascade internal flow road.
Fig. 2 and 3 shows according to a preferred embodiment of the present invention.Because the position at front holder 14, rear holder 8 place is high temperature position, front holder 14 and rear holder 8 are made front fire-wall 14 and rear fire-wall 8 respectively.The length of rear fire-wall 8 is less than or equal to the length of front fire-wall 14 and is decided to be L, and the width perpendicular to drawing shown in Fig. 1 a and b of leaf grating 6 is L
1, the horizontal projection length of leaf grating 6 is L
2, the horizontal projection length of exhaust nozzle 4 is L
3, the outer thickness of leaf grating 6 is N
1, in leaf grating 6, thickness is N
2, the diameter of exhaust nozzle 4 is d, and exhaust nozzle axis and horizontal angle are α, and the end face of the import 5 in cascade internal flow road 13 and horizontal angle are β, and the number of exhaust nozzle 4 is M.
Following setting is done in a preferred embodiment according to the present invention:
(1) for enabling the air-flow of by-pass air duct 1 as much as possible enter cascade internal flow road 13, anti-thickness N in leaf grating is pushed away
2the outer thickness N of leaf grating should be not less than
10.9 times, and with N
2=0.9N
1for the best, meanwhile, in order to ensure that leaf grating 6 has certain intensity, N
1with N
2difference should be not less than 0.5mm.
Formula 1:0.9N
1≤ N
2≤ N
1-0.5
Wherein unit is mm
(2) for ensureing that more by-pass air duct air-flows can be caught in cascade internal flow road 13, end face and the horizontal angle β of cascade internal flow road import 5 should be not less than 45 °, but for reducing the impact on the runner at cascade internal flow road import 5 place, β should be not more than 90 °.
Formula 2:45 °≤β≤90 °
(3) for ensureing that the air-flow in cascade internal flow road 13 can provide larger reaction thrust, axis and the horizontal angle α of exhaust nozzle 4 should be greater than 90 °, but for reducing the anti-amount pushing away air-flow and sucked by engine inlets again, α should be not more than 135 °.For first leaf grating near front fire-wall 14, its α is best with 120 °.In a preferred embodiment, for being in the leaf grating of upstream position near front fire-wall 14, the spray angle α of its exhaust nozzle 4 is less than the exhaust angle δ of leaf grating runner 3.
Formula 3:90 ° of < α≤135 °
(4) for ensureing that air-flow has enough speed and good directivity, the horizontal projection length L of exhaust nozzle 4 after exhaust nozzle 4 sprays
3leaf grating horizontal projection length L should be not less than
20.1 times, but for ensure reduce weight and not recurring structure interference, the horizontal projection length L of exhaust nozzle 4
3with leaf grating 6 horizontal projection length L
2sum should be less than the length L of rear fire-wall 8, with L
2=0.2L
3for the best.The i.e. horizontal projection length L of exhaust nozzle 4
3, leaf grating horizontal projection length L
2, rear fire-wall 8 length L between meet following condition:
Formula 4:0.1L
2≤ L
3and L
3+ L
2< L
(5) for ensureing the even of anti-plug-flow field, and enough air-flows can be had to discharge from cascade internal flow road 13, exhaust nozzle 4 is uniformly distributed along the width direction of leaf grating 6, and the number M of the exhaust nozzle 4 of each leaf grating is not less than 3, but consider arrangement space and weight factor, M is not more than 10.
Formula 5:3≤M≤10
(6) for ensureing reliable installation and the venting capacity of exhaust nozzle 4, exhaust nozzle diameter d should be less than the outer thickness N of leaf grating
1, but cascade-wide L should be greater than
10.05 times.
Formula 5:0.05L
1< d < N
1
As shown in Figures 4 and 5, two embodiments of exhaust nozzle 4 are respectively illustrated.In the embodiment shown in fig. 4, the structure of exhaust nozzle 4 is similar to the exhaust nozzle 4 shown in Fig. 2, and exhaust nozzle 4 is stretched on the end of leaf grating 6.And in the embodiment shown in fig. 5, exhaust nozzle 4 is placed in the inner end portion of leaf grating 6 and is not stretched on the end of leaf grating 6, so both ensure that the speed that air-flow sprays from leaf grating 6 nozzle, again reduces the impact of nozzle on anti-plug-flow field.In a unshowned in the drawings embodiment, the cascade internal flow road outlet end of leaf grating 6 is made unlimited, then air-flow directly flows out from this outlet end.In another embodiment unshowned in the drawings, the cascade internal flow road outlet end of leaf grating 6 is made closed, and in this closed end, arrange some apertures, 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 the plane perpendicular to cascade internal flow road import (5) air-flow inflow direction towards the direction skew making the windward side of described end face increase.
By the description of exemplary embodiment as above according to the present invention, can recognize that the present invention has made following improvement:
(1) when aircraft landing, abort etc. needs thrust reverser work, according to the present invention, most of motor can be made to contain air-flow outward advance mouth to enter leaf grating runner from anti-and discharge from anti-mouth of releasing, part air-flow enters leaf grating inner flow passage from the anti-mouth that advances, and discharge from the outlet of leaf grating inner flow passage, discharge outside motor finally by anti-mouth of releasing, increase with this and instead push away the counter of leaf grating and push away efficiency.
(2) for ensureing that air-flow has required speed after the ejection of leaf grating inner flow passage, and ensure that its injection direction meets the anti-demand pushing away design, exhaust nozzle is set in leaf grating inner flow passage outlet port.
(3) for the leaf grating being in upstream position, the spray angle of its exhaust nozzle is less than the exhaust angle of leaf grating runner, instead pushes away sucking again of air-flow to reduce.
(4) for making leaf grating can catch more air-flow, the import of leaf grating inner flow passage adopts spade structure.
Above-mentioned exemplary embodiment shows the embodiment in the technological scheme solving the technical problem to be solved in the present invention.Under the example of above-described embodiment, other meets the equivalence of the principle of the invention and similar means all belong in the scope of protection of the invention.Inventive principle of the present invention is, makes hollow by the leaf grating of thrust reverser, to form cascade internal flow road, thus makes cascade internal flow road also be used for forming deboost, improves and instead push away effect.
Claims (16)
1. one kind for the leaf grating array in the thrust reverser of aircraft turbofan engine, described leaf grating array comprise along described turbofan engine axis longitudinal separation arrange, and be arranged on multiple leaf gratings of the periphery of the by-pass air duct of described turbofan engine, two adjacent leaf gratings form leaf grating runner (3), the two ends of leaf grating runner (3) include notch portion (3a) and exit portion (3b) respectively, in intake section (3a), the angle of air current flow direction opposite engine axis forms the tilt angle γ of intake section (3a), in described exit portion (3b), the angle of air current flow direction opposite engine axis forms the tilt angle δ of exit portion (3b), after described leaf grating (6) and described leaf grating runner (3) are configured to make leaf grating described in the airflow passes in described by-pass air duct, described leaf grating can guide at least first portion air-flow wherein to change flow direction, to form the first reaction thrust, it is characterized in that,
Described leaf grating (6) is formed as the leaf grating of hollow, to form the cascade internal flow road (13) enabling air-flow flow through along the longitudinal extension of leaf grating (6) in the inside of leaf grating (6), described leaf grating (6) is forming cascade internal flow road import (5) near one end of by-pass air duct, cascade internal flow road outlet end is formed at the contrary the other end, the second portion of the air-flow in described by-pass air duct enters the cascade internal flow road (13) of described leaf grating (6) by cascade internal flow road import (5), then spray along jet-impingement angle α through cascade internal flow road outlet end and make described second portion air-flow change flow direction, to form the second reaction thrust.
2. leaf grating array as claimed in claim 1, it is characterized in that, this outlet end is made closed, described outlet end arranges at least one exhaust nozzle spray (4) to spray the air-flow in cascade internal flow road (13) along jet-impingement angle α.
3. leaf grating array as claimed in claim 1, it is characterized in that, this outlet end is made closed, and described outlet end is formed at least one aperture, to spray the air-flow in cascade internal flow road (13) along jet-impingement angle α.
4. leaf grating array as claimed in claim 1, it is characterized in that, this outlet end is made unlimited, to spray the air-flow in cascade internal flow road (13) along jet-impingement angle α.
5. leaf grating array as claimed in claim 1, is characterized in that, described cascade structure becomes to meet following formula:
0.9N
1≤N
2≤N
1－0.5
Wherein, N
1represent the outer thickness of leaf grating;
N
2represent thickness in leaf grating;
N
1and N
2unit be mm.
6. leaf grating array as claimed in claim 1, it is characterized in that, the end face of cascade internal flow road import (5) meets following formula relative to the angle beta of engine axis:
45°≤β≤90°。
7. leaf grating array as claimed in claim 6, is characterized in that, the end face of cascade internal flow road import (5) offsets from the plane of the air-flow inflow direction perpendicular to cascade internal flow road import (5) towards the direction making the windward side of described end face increase.
8., as the leaf grating array as described in claim 2, it is characterized in that, the axis of exhaust nozzle (4) and the angle of engine axis are formed as the airflow spray angle α of exhaust nozzle (4) and meet following formula:
90°＜α≤135°。
9. the leaf grating array as described in any one in claim 1-8, it is characterized in that, in described leaf grating array, in the tilt angle δ of at least one pair of adjacent exit portion (3b), the tilt angle of the exit portion (3b) of upstream end is less than the tilt angle of the exit portion (3b) of downstream part.
10. the leaf grating array as described in any one in claim 1-8, it is characterized in that, in described leaf grating array, in the airflow spray angle α of at least one pair of adjacent cascade internal flow road outlet end, the airflow spray angle of the cascade internal flow road outlet end of upstream end is less than the airflow spray angle of the cascade internal flow road outlet end of downstream part.
11. as weighed the leaf grating array as described in any one in claim 1-8, it is characterized in that, in described leaf grating array, the tilt angle δ of described exit portion (3b) is greater than 90 °, identical with the tilt angle δ of corresponding exit portion (3b) at the airflow spray angle α of inner flow passage outlet end of the leaf grating (6) near described by-pass air duct downstream, close described by-pass air duct upstream the airflow spray angle α of inner flow passage outlet end of at least the first leaf grating (6) of leaf grating (6) be less than the tilt angle δ of corresponding exit portion (3b).
12. leaf grating arrays as claimed in claim 8, is characterized in that, the number M of the exhaust nozzle (4) of each leaf grating is not less than 3, but is not more than 10.
13. leaf grating array as claimed in claim 8, is characterized in that, exhaust nozzle (4) is stretched on the described outlet end of leaf grating (6) or to be placed in the outlet end of leaf grating (6) inner and be not stretched on the outlet end of leaf grating (6), and meets following formula:
0.05L
1＜d＜N
1
Wherein, L
1represent the width of leaf grating (6)
D represents the diameter of exhaust nozzle (4).
14. 1 kinds of thrust reversers comprising the aircraft turbofan engine of leaf grating array, described thrust reverser is arranged on the by-pass air duct periphery of motor, and described thrust reverser comprises:
The leaf grating array of the circumference at least partially along by-pass air duct periphery as described in any one in claim 1-13;
Keep the leaf grating holder (7) of described leaf grating array;
Keep front holder (14) and the rear holder (8) at described leaf grating holder (7) two ends respectively;
The anti-propelling mouth (12) of the close described by-pass air duct of described leaf grating array, the air-flow in described by-pass air duct enters described leaf grating array from described anti-propelling mouth (12);
Leaf grating array with the anti-anti-release mouth (2) advancing mouth (12) relative, the air-flow in described leaf grating array is discharged from described anti-release mouth (2), thus forms reaction thrust.
15. thrust reversers as claimed in claim 14, is characterized in that, described front holder (14) and rear holder (8) are front fire-wall and rear fire-wall respectively.
16. thrust reversers as claimed in claim 15, is characterized in that, when described air-flow sprays from the exhaust nozzle (4) of the described outlet end being stretched on described leaf grating (6), meet following formula:
0.1L
2≤ L
3and L
3+ L
2< L
Wherein: L is the length of rear fire-wall;
L
2leaf grating horizontal projection length;
L
3the horizontal projection length of exhaust nozzle.
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| 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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| 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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| Publication Number | Publication Date |
|---|---|
| CN104712455A true CN104712455A (en) | 2015-06-17 |
| CN104712455B CN104712455B (en) | 2017-07-04 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
| CN112796882A (en) * | 2020-12-30 | 2021-05-14 | 长江大学 | Reverse thrust system of turboprop engine |
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| 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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| 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 |
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| CN112796882A (en) * | 2020-12-30 | 2021-05-14 | 长江大学 | Reverse thrust system of turboprop engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104712455B (en) | 2017-07-04 |
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