CN109956044A - The nacelle of jet engine - Google Patents
The nacelle of jet engine Download PDFInfo
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- CN109956044A CN109956044A CN201811570506.0A CN201811570506A CN109956044A CN 109956044 A CN109956044 A CN 109956044A CN 201811570506 A CN201811570506 A CN 201811570506A CN 109956044 A CN109956044 A CN 109956044A
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- nacelle
- skin plate
- panel
- translation
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- 230000003068 static effect Effects 0.000 claims description 9
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 239000007921 spray Substances 0.000 claims description 2
- 239000000872 buffer Substances 0.000 description 7
- 230000007246 mechanism Effects 0.000 description 4
- 238000007599 discharging Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005662 electromechanics Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings or cowlings
- B64D29/02—Power-plant nacelles, fairings or cowlings associated with wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of nacelle of jet engine, the nacelle has the deboost device selectively operated, air-flow is led to leaf grating during deboost operates by deboost device again, nacelle include: translation rectification skin plate, translation rectification skin plate be configured to deboost operate during between collapsed state and unfolded state transverse movement with expose leaf grating with translation rectification skin plate be in unfolded state when transmitting deboost air-flow；At least one auto-translating panel, auto-translating panel is configured to be arranged to close with the leading edge slat of the aircraft wing of nacelle to be installed, auto-translating panel can rectify the movement synergistically transverse movement automatically of skin plate at least part motion range of translation rectification skin plate between collapsed state and unfolded state with translation, and the movement of auto-translating panel is less than the movement of translation rectification skin plate with the variable gap space when auto-translating panel changes between its collapsed state and unfolded state between offer auto-translating panel and leading edge slat.
Description
Technical field
The present invention relates to a kind of nacelles of jet engine with deboost device.
Background technique
It is known to be configured for being installed to carry-on jet aircraft engine under the wing including surrounding engine
Nacelle.Engine is connected to the downside of jet aircraft wing via pylon.One engine is placed in below wing
A known aspect is to keep clearance space between the leading edge slat of the nacelle and wing that surround jet engine.Leading edge slat
Such as it can move between different locations for example to influence the lift of aircraft and resistance.For example, leading edge slat can to
Lower section is moved upwardly toward the jet engine being located on the downside of wing to generate resistance during landing maneuver.
Other than leading edge slat moves during landing maneuver, jet engine itself can be grasped configured with deboost
Make, the exhaust of jet engine is made to be re-directed to jet hair via such as leaf grating from the aft exit part of engine whereby
The neighboring area of motivation.Leaf grating includes plurality of vanes, for by via the received air-flow of the entrance of jet engine from jet
The periphery of engine reboots outward, to slow down the propulsion of aircraft during landing.
One seed type of trhrust-reversal device is leaf grating reverser, the leaf grating reverser and the wind for being located at turbofan
The opening for fanning the radially arranged near the rear edge of radome fairing combines.The peace in each of one or more opening opening
Equipped with one group of cascade air-flow steering blade.Door and its associated actuating system is stopped to be oriented and neighbouring each opening
The inner wall of fan fairing flushes.These organize translation radome fairing covering (quilt of the outer surface by " cannula-like " of cascade blade
Referred to as translate radome fairing (transcowl)) covering.When enabling trhrust-reversal device during aircraft lands operate, electromechanics is caused
Dynamic system causes translation radome fairing to move backward, thus exposes leaf grating.Linking between translation radome fairing and blocking door makes to hinder
Gear door moves in bypass flow, thus blocks the normal route of the bypass flow of the rear portion of jet engine and makes
Bypass flow is turned to away by leaf grating.Air-flow can be re-directed to the forward direction side of aircraft by the air-flow steering blade of leaf grating
Upwards to help to slow down aircraft.
During aircraft operation, translation radome fairing should not contact the machine that jet engine is relatively closely positioned on
Any part of the wing.In fact, expect to have wing leading edge slat and translation radome fairing between minimum clearance (for example, a little English
It is very little) to avoid the risk of any contact.
Recently, the jet engine with high bypass ratio engine has been developed, has been used to usually exist for example to increase
In the airflow bypass region of the bypass flow of the rear portion of jet engine.Increase airflow bypass regional diameter to be related to increasing spray
The diameter of gas engine blower and diameter around engine and the nacelle of fan.Larger-diameter nacelle means to lead
It causes the degree of approach between the leading edge slat and nacelle of wing to reduce, or alternatively needs to increase the height of undercarriage to keep
Previous gap.As best solution, due to the upper counterangle of wing, it should especially in the nacelle closer to aircraft fuselage
Interior string side on solve wing leading edge slat and translation radome fairing between gap tolerances.
The translational motion of translation radome fairing should be retained for the solution of the gap tolerances of nacelle.This movement allows
Leaf grating is covered during normal flight operations to retain aerodynamic performance, and allowed during landing maneuver via removable
Driving actuator mechanism make these leaf gratings expose.
U.S. Patent number 8,727,275,8,931,736,9,228,532 and 9,784,216 disclose it is known can be lateral
The radome fairing (or casing) of movement, these patents share shared specification.These patents, which disclose, to be configured to be attached to machine
Fixed interval (FI) space between the outlet radome fairing and the leading edge slat of wing of nacelle and nacelle on the downside of the wing.In order to realize
This fixed interval (FI) space, outlet radome fairing include the moveable part for being configured as external translation casing, and including being located at
Another fixed part near leading edge slat.This other fixed part is not moved when enabling deboost configuration, with
Just keep nacelle to the fixed interval (FI) space of leading edge slat.
U.S. Patent number 9,334,831 discloses a kind of nacelle of aircraft bypassed turbine Duct-Burning Turbofan, the nacelle packet
The downstream section with external structure is included, which has the radome fairing being movably mounted in fixing internal structure.
In the internal structure for the side that one first panel is mounted on nacelle, and a second panel is mounted on the other side of nacelle.
First panel is fixed and is arranged to the physical interference that radome fairing and aircraft wing element are limited during thrust reversing, and
At least one second panel is mounted in the opposite side at the top of nacelle, which can be mobile simultaneously relative to fixing internal structure
And it is arranged to for increasing the air discharged from nacelle during thrust reversing.
Summary of the invention
Need a kind of substitution nacelle, which optimizes the aerodynamic performance of the aircraft attached by it, while
Between the moveable part (such as moveable leading edge slat) of wing and the moveable part (such as translation radome fairing) of nacelle
Obtain gap tolerances.
For this purpose, disclosing a kind of nacelle of jet engine.
Detailed description of the invention
After the following detailed description is read in conjunction with the drawings, other feature and advantage of present disclosure are shown in which will be apparent from
It is existing, wherein similar element is specified by similar appended drawing reference, and wherein:
- Fig. 1 shows the jet engine below the wing for being mounted on aircraft, which includes according to this hair
Bright nacelle, what which had movably translates rectification skin plate when being switched on/off deboost and operating and puts down automatically
Move panel；
- Fig. 2A is the vertical view according to the nacelle of the jet engine of Fig. 1 of the first embodiment of nacelle according to the present invention
Figure, wherein translation rectification skin plate and auto-translating panel are in collapsed state；
- Fig. 2 B is the view similar with the view of Fig. 2A of the second embodiment according to nacelle according to the present invention, wherein
Translation rectification skin plate and auto-translating panel are in collapsed state；
- Fig. 2 C is the view similar with the view of Fig. 2A of the first embodiment according to nacelle according to the present invention, wherein
Translation radome fairing and auto-translating panel are in unfolded state；
- Fig. 2 D illustrates the substantially static frame of auto-translating panel, and show the auto-translating panel of Fig. 2A
Exemplary collapsed state；
It is similar to Fig. 2 D, Fig. 2 E illustrates the substantially static frame of auto-translating panel, and shows the automatic of Fig. 2 C
Translate the exemplary unfolded state of panel；
- Fig. 2 F, Fig. 2 G and Fig. 2 H show are for the guidance during flight and/or when enabling deboost operation
Period makes three different exemplary mechanisms that auto-translating panel is held in position on jet engine.
Specific embodiment
Referring to Fig.1, Fig. 2A and Fig. 2 C, aircraft (not shown) have the leading edge slat 104 for being partly shown as wing 102
Wing structure.Leading edge slat 104 can be moved forwardly and downwardly for example during landing maneuver, to generate resistance to assist flying
Row device slows down after contacting to earth.
Aircraft includes pylon/installation part 106, which extends from wing 102 to support jet to start
Machine 108.Jet engine 108 includes nacelle 110, and the nacelle is for surrounding engine (not shown) and for enhancing aircraft
100 aerodynamic performance.Engine and nacelle 110 have the deboost device being selectively operated, the deboost device
Bypass flow is re-introduced to leaf grating 116 during deboost operation.
The translation rectification skin plate or translation radome fairing (transcowl) 120 of nacelle 110 were configured in the landing maneuver phase
Between under the action of driving actuator 126 can between " packing up " state (Fig. 2A) and " expansion " state (Fig. 1 and Fig. 2 C) laterally
It is movable.After translation rectification skin plate 120 is located at the static fan rectifying skin plate 114 for covering engine of inflow side
Side.In its collapsed state, translation rectification skin plate 120 close to fan rectifying skin plate 114, such as with fan rectifying skin plate
114 contacts.In its unfolded state, translation rectification skin plate 120 far from fan rectifying skin plate 114, so as to expose leaf grating 116 with
Emit deboost air-flow；And
According to the present invention, auto-translating panel (ATP) 208 be arranged at aircraft wing 102 leading edge slat 104 it is attached
Closely, nacelle install to/have it is to be installed to the aircraft wing.Therefore auto-translating panel is arranged in 110 top of nacelle, close to hang
Hanger 106.Auto-translating panel 208 is configured at least part motion range of translation rectification skin plate 120 and puts down
The movement synergistically transverse movement automatically of rectification skin plate 120 is moved, the movement of auto-translating panel is less than translation rectification skin plate
120 movement, to keep auto-translating panel when auto-translating panel 208 is converted between collapsed state and unfolded state
Variable gap space or nacelle gap area 124 between 208 and leading edge slat 104.Nacelle gap area 124 is for example landing
The gap of the interface of nacelle 110 and leading edge slat 104 is kept during operation.
As will be described, auto-translating panel 208 includes at least one spring, at least one spring is for compressing
Under make auto-translating panel 208 be biased to make the auto-translating panel to keep relative to translation rectification skin plate 120 in its figure
The collapsed state of 2A, being compressed in during deboost operates for spring are released when translation rectification skin plate 120 moves to draw
Auto-translating panel 208 is played to move.
As shown in Figure 2 A out, nacelle 110 includes the hinged access panel with part 210 and 216, each part tool
There are a plurality of hinges, these hinges are configured for keeping hinged access panel progress selective rotation movement logical to provide engine
Road.Hinged access panel part is tightened in position or is fixed to pylon 106 with other known technologies.
The part 120a and 120b of translation rectification skin plate 120 are configured to be placed to the opposite inflow side of jet engine
202 and outflow side 204 on, and shape is set to and is arranged to asymmetric relative to the central longitudinal axis 113 of nacelle.Note
Jet engine 108 and its nacelle 110 are divided into inflow side by meaning, in fig. 2, the transverse plane across longitudinal axis 113
202 and outflow side 204.
In the example of Fig. 2A, top view illustrates the inflow side 202 and right-hand side 204 or short that left-hand side is nacelle
The outflow side in cabin.The inflow side 202 of nacelle 110 is located closer to the fuselage (not shown) of aircraft, and the outflow of nacelle
Side 204 be located at nacelle 110 from the farther side of aircraft fuselage.
Auto-translating panel 208 is positioned in the nacelle gap area 124 of Fig. 1, only in jet in Fig. 2A and Fig. 2 C
On the inflow side 202 of engine.Leaf grating 116 (C referring to fig. 2) has and is arranged on the inflow side 202 of jet engine 108 in this way
The first leaf grating part 116a with first shape and be arranged on the outflow side 204 of jet engine 108 and have the
The shape of second leaf grating part 116b of two shapes, the first leaf grating part and the second leaf grating part is relative to jet engine 108
Central longitudinal axis 113 be asymmetrical, wherein the first leaf grating part 116a ratio for being arranged in inflow side 202 is arranged in outflow
Second leaf grating part 116b of side 204 is smaller.
In the collapsed state of translation rectification skin plate 120, leaf grating 116 is entirely surrounded by.
Auto-translating panel 208 is fastened to nacelle 110 in a manner of allowing movement thereof.Auto-translating panel 208 can be by
Be configured to include the hinge being attached to thereon, these hinges slideably with stationary orbit guide member engagement so that auto-translating
Panel 208 is along stationary guide rails translational motion, and when the aircraft is in flight and in auto-translating panel 208 from packing up
State motion is held in position in auto-translating panel 208 on nacelle 110 to (vice versa) during unfolded state.
With reference to Fig. 2 D to Fig. 2 F, the foundation structure (i.e. below nacelle) of jet engine 108 includes static flight device jet
Engine structure, the static flight device jet engine structure include forward frame 231 and rear frame 233 and multiple and different
Stationary orbit, such as primary track 232.Forward frame 231 and rear frame 233 are along the central longitudinal axis with nacelle
113 vertical planes extend.Secondary track 234 and three-level track 236 are fixedly mount to static flight device jet engine knot
Structure.Primary track, secondary track and three-level track extend each along the direction parallel with the central longitudinal axis 113 of nacelle,
It is fixed to multiple and different movable panel (that is, translation rectification skin plate 120 and auto-translating panel 208) such as
Several connecting elements of one or more hinges or sliding block etc are for guiding removable panel.
Particularly, auto-translating panel includes the connecting element of such as one or more hinges 244 or sliding block 238 etc,
For being somebody's turn to do certainly along stationary guide rails (the i.e. second level guide rail 234 and three-level guide rail 236) guidance for being located at 208 lower section of auto-translating panel
Dynamic translation panel movement.Hinge 244 and sliding block 238 include auto-translating panel 208 periphery and with stationary guide rails 234,
236 engagements.
In response to pushing translation rectification skin plate 120 in the forward direction, sliding block 238 is moved along second level guide rail 234.Note
Meaning, the movement of translation rectification skin plate 120 are in several feet of magnitude.
Auto-translating panel 208 includes pushing meanss 228, and driving actuator 126 is rectified by the pushing meanss and translation
The engagement of skin plate 120 is rearward to push up translation rectification skin plate expansion during deboost operates.Certainly, it pushes away
Dynamic device 228 can be located at any suitable location.Panel radial contact 230 may be embodied in along auto-translating panel 208
At certain positions with contact, allows and instruction (for example, flashing light or bright light) is provided when these contacts are closer to each other
To confirm that auto-translating panel 208 is in collapsed state.However, when auto-translating panel 208 rectifies skin plate in response to translation
120 movement and when Automatic-expanding, the relative proximities displacement of panel radial contact 230 with provide instruction (for example, stablize light or
Turn off the light) come indicate auto-translating panel 208 from its collapsed state be relocated towards and/or enter its unfolded state.
Other than multiple and different hinge 244 and sliding block 238, buffer (such as buffer 240) is comprised in automatically
It translates at the periphery of panel 208 and translation radome fairing panel 120 and around periphery, translation is rectified skin plate during flight
120 and auto-translating panel 208 be held in position in.Mechanical buffer unit is the known component that can protect from due to wink
Shi Li and cause the device excessively waved.Buffer 240 allows to move under tension and under compression and is occurring to impact thing
It can be enabled when part to become rigidity and be held in position in other removable panels.
The movement of translation rectification skin plate 120, which also releases, is located on or near the such as one or more of pushing meanss 228
The compression assembly parts of spiral compression spring 241 etc, movement of these compressed springs 241 in response to translation rectification skin plate 120
And automatic translational plane plate 208 is discharged, to allow the auto-translating panel to move limited distance (for example, 10 along stationary guide rails
Millimeter magnitude).This movement is performed by discharging compressed spring 241, these compressed springs will be for otherwise will
Auto-translating panel 208 is held in position in.
Because auto-translating panel 208 needs to remain fixed to jet engine 108 and due to once in its translation
Translation rectification skin plate 120 is rearward moving upwards and spring can made to decompress, and hinge 244 is also used in auto-translating panel
The auto-translating panel is held in position in during 208 movements.
Note that spring (such as spring 248) is the circumferential arrangement around auto-translating panel 208, and can be flat
It moves when rectification skin plate 120 moves and discharges to allow auto-translating panel to move forward.This movement can be by using all
It being controlled such as the hinge means of sliding block hinge 244 etc, these hinge means are included in the periphery of auto-translating panel 208, with
Stationary guide rails engagement positioned at 208 lower section of auto-translating panel.
One or more buffers 246 may be located on the position around auto-translating panel 208, in the normal operating phase
Between assist for the auto-translating panel being held in position in, and discharge and allow automatically flat during deboost operation
Panel 208 is moved to move.
These buffers 246 ought be put down automatically for assisting being held in position in auto-translating panel 208
It moves when panel 208 is displaced to the degree of its Support Position and assists the auto-translating panel stop motion.
Spring or buffer (not shown) can also be positioned in the periphery of auto-translating panel 208 to resist retainer,
The retainer is used to limit its movement when auto-translating panel and/or translation rectification skin plate 120 are in unfolded state.
For making auto-translating panel 208 be held in position in and also allow in forward direction side on nacelle 110
In the alternate embodiment of the slide block mechanism of upward limiting translation, with reference to Fig. 2 G, sliding block arrangement includes sliding block assembly parts, the sliding block
Assembly parts are attached to auto-translating panel 208 to engage with stationary guide rails, which is attached to jet engine 108 to draw
Auto-translating panel 208 is led to move relative to translation rectification skin plate 120.More specifically, as being used for auto-translating panel
208 are connected to the alternative solution (or additional aspects) of the hinge arrangement of jet engine 108, and auto-translating panel 208 includes sliding
Block 254, the sliding block are engaged with guide rail 256, and sliding block is at least one pressure for being held in position in auto-translating panel 208
Contracting spring 241 translates after discharging along the guide rail, and the guide rail 256 prolongs along the direction parallel with central longitudinal axis 113
The fixed structure of the upper beam 106B for stretching, and being fixed to such as jet engine pylon 106 etc.
At least one the sliding block assembly parts for being attached to auto-translating panel 208 are engaged with stationary guide rails, and the stationary guide rails are attached
Jet engine is connected to guide auto-translating panel 208 hinged relative to what is remain stationary during auto-translating panel movement
Access panel movement, and guide auto-translating panel 208 relative to translation radome fairing movement.Note that F and Fig. 2 G according to fig. 2
Two embodiments, translation rectification skin plate 120 and auto-translating panel 208 are configured to be placed to jet engine 108
The part of opposite inflow side and outflow side is asymmetricly arranged relative to the central longitudinal axis 113 of nacelle.
For auto-translating panel 208 being held in position in and also being allowed the slide block mechanism of its translational motion
Another alternate embodiment in, with reference to Fig. 2 H, integrated slider assembly parts 258 are formed on auto-translating panel 208
The first side downside, and the guide rail including being expressed as cylindrical guiding channel 260.Translation rectification skin plate 120 includes collection
At sliding block assembly parts 262, which is formed on the downside of translation rectification skin plate 120 to draw with static
Lead 260 engagements.The assembly parts can be formed as the male connector engaged with cylindrical channel 260.
In the other side of auto-translating panel 208, integrated slider assembly parts 264 are formed on auto-translating panel
208 downside, the guide rail including being expressed as cylindrical guiding channel 268.It is attached to the upper beam of jet engine pylon 106
The sliding block assembly parts 266 of 106B are engaged with static guiding piece 268.The assembly parts can be formed as engaging with cylindrical channel 268
Male connector.
Two guide-rail channels 260 and 264 extend along the direction parallel with central longitudinal axis 113.
As described herein, it is noted that in the embodiment of Fig. 2A and Fig. 2 C, auto-translating panel 208 exists only in jet hair
The inflow side 202 of motivation 108, to solve the leading edge slat 104 of aircraft wing 102 about jet engine inflow side
Clearance issues.In an alternative embodiment, about Fig. 2 B, the mirrored portion 208,222 of auto-translating panel is configured to be placed to
The opposite inflow side 202 and outflow side 204 of jet engine, and it is symmetrical relative to the central longitudinal axis of nacelle 110 113
Ground arrangement.According to this alternate embodiment, the part 120a and 120b of translation rectification skin plate 120 are configured to be placed to jet
The opposite inflow side 202 and outflow side 204 of engine, and shape is set to and is arranged to vertical relative to the center of nacelle
It is symmetrical to axis 113.
Claims (8)
1. a kind of nacelle (110) of jet engine (108), the nacelle has the deboost device being selectively operated, institute
It states deboost device to be re-introduced to air-flow leaf grating (116) during deboost operation, the nacelle (110) includes:
Fan rectifying skin plate (114), the fan rectifying skin plate are configured as the static office of the jet engine (108)
Portion's covering；
Translation rectification skin plate (120), the translation rectification skin plate are configured to during deboost operates described flat
It moves rectification skin plate (120) and rectifies skin plate close to the collapsed state of the fan rectifying skin plate (114) and the translation
(120) transverse movement between the unfolded state far from the fan rectifying skin plate (114), to expose the leaf grating (116)
To emit deboost air-flow；And
The nacelle (110) is characterized in that the nacelle includes at least one auto-translating panel (208), described automatic flat
Moving panel is configured to be arranged to and have the leading edge slat (104) of the aircraft wing of the nacelle (110) to be installed close, institute
Stating auto-translating panel can be in collapsed state and exhibition at least part motion range of translation rectification skin plate (120)
The movement synergistically transverse movement automatically of skin plate (120), the auto-translating panel are rectified between open state with the translation
(208) movement is less than the movement of translation rectification skin plate (208), so as to when the auto-translating panel (120) is at it
It is provided between the auto-translating panel (208) and the leading edge slat (104) when changing between collapsed state and unfolded state
Variable clearance space (124).
2. nacelle (110) as described in claim 1, which is characterized in that the auto-translating panel (208) includes at least one
Compressed spring (241), at least one described compressed spring for making the auto-translating panel (208) be biased to make under compression
The auto-translating panel (208) keeps being in collapsed state relative to translation rectification skin plate (120), the spring
It is released during being compressed in deboost operation when translation rectification skin plate (120) moves to cause the auto-translating
Panel (208) movement.
3. nacelle (110) as claimed in claim 1 or 2, which is characterized in that the auto-translating panel (208) includes radial
When contact (230), the radial contact are used to indicate the auto-translating panel (208) in collapsed state and/or described
When auto-translating panel (208) is in unfolded state.
4. nacelle (110) according to any one of claims 1 to 3, the nacelle includes stationary guide rails (234,236),
These stationary guide rails extend along the direction parallel with central longitudinal axis (113) of the jet engine (108), feature
It is, the auto-translating panel (208) includes connecting element (238,244), these connecting elements are described automatic for guiding
Panel is translated to move along the stationary guide rails being located at below the auto-translating panel (208), the connecting element (238,
244) it is arranged at the periphery of the auto-translating panel (208) and is engaged with the stationary guide rails (234,236).
5. nacelle (110) according to any one of claims 1 to 4, which is characterized in that the auto-translating panel
It (208) include spring (248), the spring is arranged around the periphery of the auto-translating panel (208), and described
It is discharged when translation rectification skin plate (120) movement to allow the auto-translating panel (108) to move.
6. nacelle (110) according to any one of claims 1 to 5, which is characterized in that the nacelle (110) includes two
A auto-translating panel (208), center longitudinal axis of described two auto-translating panels relative to the jet engine (108)
Line (113) is respectively placed in two opposite sides of the jet engine (108), and the panel (208) is relative to the jet
The central longitudinal axis (113) of engine (108) symmetrically arranges.
7. nacelle (110) according to claim 6, which is characterized in that the leaf grating (116), which has, is arranged in the jet
The first leaf grating part (116a) with first shape on the first side (202) of engine (108) and it is arranged in the spray
The second leaf grating part (116b) with the second shape in second side (204) of gas engine (108), first leaf grating portion
Divide central longitudinal axis of the shape of (116a) and second leaf grating part (116b) relative to the jet engine (108)
It (113) is asymmetrical.
8. nacelle (110) according to any one of claims 1 to 5, which is characterized in that the nacelle (110) only includes
One auto-translating panel (208).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201762609697P | 2017-12-22 | 2017-12-22 | |
| US62/609,697 | 2017-12-22 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109956044A true CN109956044A (en) | 2019-07-02 |
| CN109956044B CN109956044B (en) | 2022-03-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811570506.0A Active CN109956044B (en) | 2017-12-22 | 2018-12-21 | Nacelle for a jet engine |
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