CN214616797U - Gas turbine and aircraft - Google Patents
Gas turbine and aircraft Download PDFInfo
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- CN214616797U CN214616797U CN202120700847.6U CN202120700847U CN214616797U CN 214616797 U CN214616797 U CN 214616797U CN 202120700847 U CN202120700847 U CN 202120700847U CN 214616797 U CN214616797 U CN 214616797U
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- housing
- lock
- outer cover
- gas turbine
- lever
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Abstract
The utility model relates to a gas turbine and aircraft, gas turbine includes: an engine main body; the fixed outer cover is sleeved outside the engine main body and is fixed relative to the engine main body; the thrust reverser comprises a movable outer cover (1) which is sleeved outside the engine main body and is arranged with the fixed outer cover in the axial direction of the engine main body side by side, wherein the movable outer cover (1) is configured to move backwards relative to the fixed outer cover so as to form an outlet for spraying fluid forwards between the fixed outer cover and the movable outer cover; and a mobile housing lock (5) configured to limit the mobile housing (1) from moving backwards, wherein the mobile housing lock (5) is electrically controlled for electric unlocking and/or electric locking, and the problems of heavy weight, complex structure and high maintenance cost of a thrust reverser in the related art are solved.
Description
Technical Field
The utility model relates to an airborne vehicle field particularly, relates to a gas turbine and aircraft.
Background
The thrust reverser of an aircraft engine (gas turbine) is used for generating thrust when an aircraft lands and breaks take-off, and when the thrust reverser is unfolded, the movable outer cover moves backwards, and simultaneously, the bypass airflow is ejected in the reverse direction to generate the thrust reverser to realize the deceleration of the aircraft, and the thrust reverser does not allow the air unfolding. To prevent the thrust back mobile housing from uncommanded movement in the air, a mobile housing lock is required to lock the mobile housing. In the thrust reverser in active service at present, most all are hydraulic thrust reversals, and the removal dustcoat lock that uses for a lot adopts the actuator type, and the unblock of this lock not only needs the power still needs the hydraulic pressure source, and hydraulic use just need advance oil pipe and return oil pipe in the overall arrangement of hasp roof beam, causes thrust reversals to increase weight, and the structure is complicated, and the maintenance cost increases.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a gas turbine and aircraft to there are big, the structure complicacy of thrust reverser weight and the high problem of maintenance cost in improving the correlation technique.
According to an aspect of an embodiment of the present invention, there is provided a gas turbine, in some embodiments, comprising:
an engine main body;
the fixed outer cover is sleeved outside the engine main body and is fixed relative to the engine main body;
the thrust reverser comprises a movable outer cover which is sleeved outside the engine main body and is arranged side by side with the fixed outer cover in the axial direction of the engine main body, and the movable outer cover is configured to move backwards relative to the fixed outer cover so as to form an outlet for spraying fluid forwards between the fixed outer cover and the movable outer cover; and
the mobile housing lock is configured to limit the mobile housing to move backwards, and is an electrically-controlled lock capable of being unlocked and/or locked electrically.
In some embodiments, the mobile housing lock comprises:
a housing;
a latch configured to be movable relative to the housing to extend from or retract into the housing;
an electromagnetically attractive component configured to drive the locking pin to move relative to the housing.
In some embodiments, the electromagnetic attraction member is configured to drive the locking pin toward a retracted position within the housing to unblock the mobile housing lock from the mobile housing.
In some embodiments, the mobile housing lock further comprises a spring for biasing the locking pin, one of the spring and the electromagnetic attraction member being configured to drive the locking pin towards a position extended out of the housing and the other being configured to drive the locking pin towards a position retracted into the housing.
In some embodiments, the mobile housing lock further comprises a lever rotatably disposed within the housing, the electromagnetic attraction component being configured to drive the lever to rotate, the lever abutting or being coupled to the locking pin to move the locking pin relative to the housing.
In some embodiments of the present invention, the,
the center of rotation of the lever is located between the first and second ends of the lever,
the electromagnetic attraction member is configured to attract the first end of the lever to rotate the lever;
the second end of the lever abuts or is connected to the locking pin.
In some embodiments, the distance between the first end of the lever and the center of rotation is less than the distance between the second end of the lever and the center of rotation.
According to a further aspect of the invention, there is also provided an aircraft comprising a gas turbine as described above.
Use the technical scheme of the utility model, remove the automatically controlled lock that the dustcoat lock is electronic unblock and/or electronic shutting, consequently improved the thrust reverser weight that exists among the correlation technique big, the structure is complicated and the problem that maintenance cost is high.
Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments of the invention, which proceeds with reference to the accompanying drawings.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention or the related art, the drawings required to be used in the description of the embodiments or the related art will be briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive labor.
FIG. 1 illustrates a schematic view of an installation location of a mobile nacelle lock of a gas turbine according to an embodiment of the present invention;
FIG. 2 illustrates a schematic view of the internal structure of a mobile nacelle lock of a gas turbine in accordance with an embodiment of the present invention;
FIG. 3 is a schematic illustration of a mobile nacelle of a gas turbine engine in a locked position according to an embodiment of the present invention; and
fig. 4 shows a schematic structural diagram of a gas turbine engine in an unlocked state of the mobile cowl lock according to an embodiment of the present invention.
In the figure:
1. moving the housing; 2. a shackle beam; 3. a bolt; 4. a nut; 5. moving the housing lock; 6. a housing; 7. a lock pin; 8. a spring; 9. a lever; 10. an electromagnetic attraction member; 11. mounting a plate; 12. an electrical plug.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Referring to fig. 1, the gas turbine of the present embodiment includes an engine main body, a fixed outer cover sleeved outside the engine main body, and a thrust reverser.
The thrust reverser includes a movable housing 1 that is fitted around the engine main body and is arranged side by side with the fixed housing in the axial direction of the engine main body, and the movable housing 1 is configured to be movable rearward relative to the fixed housing to form an outlet for ejecting fluid forward between the fixed housing and the movable housing.
The thrust reverser further comprises a choke valve arranged on the inner side of the movable outer cover 1, and the choke valve is provided with a retracting position attached to the inner side of the movable outer cover 1 and a working position transversely arranged between the engine main body and the movable outer cover 1.
During normal movement of the gas turbine, the outlet between the mobile nacelle 1 and the fixed nacelle is closed, the choke is in the retracted position, the fluid of the bypass between the fixed nacelle and the engine body flows backwards through the passage between the mobile nacelle 1 and the engine body, so that the fluid is expelled through the rear of the gas turbine, thus bringing the gas turbine forward (arrow FWD for front and arrow a for rear).
When the airplane needs to be decelerated during landing or interrupted takeoff, the reverse thrust device works. The movable outer cover 1 of the thrust reverser moves backwards, the choke valve is switched to the working position, and fluid between the outer ducts between the fixed outer cover and the engine body flows forwards through an outlet between the movable outer cover and the fixed outer cover under the blocking action of the choke valve, so that the engine generates backward thrust.
The gas turbine of the present embodiment further includes a moving casing lock 5 for locking the moving casing 1 in a state of closing the outlet described above. The movable housing lock 5 is an electrically controlled lock which is electrically unlocked and/or locked, so that the problems of heavy weight, complex structure and high maintenance cost of a thrust reverser in the related art are solved.
As shown in fig. 2, the mobile housing lock 5 includes a housing 6, a lock pin 7, and an electromagnetic attraction member 10. The latch 7 is configured to be movable relative to the housing 6 to extend from or retract into the housing 6. The electromagnetic attraction part 10 is configured to drive the lock pin 7 to move relative to the housing 6.
In this embodiment, the moving casing lock 5 is fixed relative to the engine body, and the moving casing 1 is provided with a lock hole into which the lock pin 7 protrudes outside the casing 6 during normal operation of the gas turbine to restrict the moving casing from moving backward, as shown in fig. 3. When the gas turbine is in a reverse thrust state, the lock pin 7 is retracted from the lock hole into the housing 6, as shown in fig. 4, the moving cowl 1 is controlled to move backward, and the choke valve is switched to the operating position.
The electromagnetic attraction member 10 is configured to drive the lock pin 7 toward the position retracted into the housing 6 to release the moving-housing lock 5 from the limit of the moving housing 1.
The mobile housing lock 5 further comprises a spring 8 for urging the lock pin 7, one of the spring 8 and the electromagnetic attraction part 10 being configured to drive the lock pin 7 towards a position protruding out of the housing 9, and the other being configured to drive the lock pin 7 towards a position retracted into the housing 6.
The gas turbine further comprises a lever 9 rotatably arranged in the housing 6, the electromagnetic attraction part 10 being configured to drive the lever 9 to rotate, the lever 9 abutting or being connected with the locking pin 7 to move the locking pin 7 relative to the housing 6.
The center of rotation of the lever 9 is located between the first end and the second end of the lever 9, and the electromagnetic attraction member 10 is configured to attract the first end of the lever 9; the second end of the lever 9 abuts or is connected to the latch 7.
In the present embodiment, the distance between the first end of the lever 9 and the center of rotation is smaller than the distance between the second end of the lever 9 and the center of rotation.
The movable housing lock 5 mainly comprises a shell 6, an electromagnetic attraction part 10, a lever structure 9, a lock pin 7, a spring 8 and an electric plug 12.
The movable housing lock 5 is mounted on a lock catch beam 2 of an engine main body through a bolt 3, an electric plug 12 is used for connecting a power excitation cable, under the condition of no power excitation, the lock pin 7 is in a natural extending state, and at the moment, the lock pin 7 extends into a lock hole structure of the movable housing 1 to play a role in limiting the movable housing 1. The gas turbine further comprises a nut 4 adapted to the bolt 3.
The mobile housing lock 5 further comprises a mounting plate connected to the housing 6, and the mounting plate is provided with bolt holes matched with the bolts 3.
When the mobile housing lock 5 receives power excitation, the electromagnetic attraction part 10 attracts the first end of the lever 9, and the second end rotates to push the lock pin 7 due to the rotation of the lever 9, so that the lock pin 7 overcomes the elastic force of the spring 8, the spring 8 is further compressed, and the retraction of the lock pin 7 is realized. When the lock pin 7 retracts, the movable outer cover 1 is not limited any more.
When the power supply excitation on the movable housing lock 5 is removed, the electromagnetic attraction part 40 does not attract the lever 9 any more, and the lock pin 7 is ejected under the action of the elastic force of the spring 8, so that the lock pin 7 enters the lock hole of the movable housing 1 to lock the movable housing.
The movable outer cover lock 5 does not adopt a conventional actuator scheme, adopts a lever principle, can realize unlocking and locking of the movable outer cover lock only by introducing power excitation, does not need to introduce hydraulic pressure, relieves the problem of short layout space of a lock catch beam, and ensures that the layout is simpler and the weight is saved.
According to another aspect of the present invention, there is also provided an aircraft comprising the gas turbine as described above.
The above description is only exemplary embodiments of the present invention, and should not be construed as limiting the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A gas turbine engine, comprising:
an engine main body;
the fixed outer cover is sleeved outside the engine main body and is fixed relative to the engine main body;
the thrust reverser comprises a movable outer cover (1) which is sleeved outside the engine main body and is arranged with the fixed outer cover in the axial direction of the engine main body side by side, wherein the movable outer cover (1) is configured to move backwards relative to the fixed outer cover so as to form an outlet for spraying fluid forwards between the fixed outer cover and the movable outer cover; and
a mobile housing lock (5) configured to restrict the mobile housing (1) from moving backwards, the mobile housing lock (5) being an electrically controlled lock that is electrically unlocked and/or electrically locked.
2. Gas turbine according to claim 1, wherein said mobile nacelle lock (5) comprises:
a housing (6);
a latch (7) configured to be movable relative to the housing (6) to extend from or retract into the housing (6);
an electromagnetic attraction part (10) configured to drive the lock pin (7) to move relative to the housing (6).
3. Gas turbine according to claim 2, characterized in that said electromagnetic attraction part (10) is configured to drive said locking pin (7) towards a position retracted inside the casing (6) to free said mobile nacelle lock (5) from the limit of said mobile nacelle (1).
4. Gas turbine according to claim 2, wherein the mobile casing lock (5) further comprises a spring (8) for urging the locking pin (7), one of the spring (8) and the electromagnetic attraction part (10) being configured to drive the locking pin (7) towards a position protruding out of the casing (6) and the other being configured to drive the locking pin (7) towards a position retracted into the casing (6).
5. Gas turbine according to claim 2, wherein the mobile housing lock (5) further comprises a lever (9) rotatably arranged within the housing (6), the electromagnetic attraction part (10) being configured to drive the lever (9) in rotation, the lever (9) abutting or being connected with the locking pin (7) to move the locking pin (7) relative to the housing (6).
6. The gas turbine according to claim 5,
the centre of rotation of the lever (9) is located between the first and second ends of the lever (9),
the electromagnetic attraction part (10) is configured to attract a first end of the lever (9) to rotate the lever (9);
the second end of the lever (9) is abutted or connected with the lock pin (7).
7. Gas turbine according to claim 6, wherein the distance between the first end of the lever (9) and the centre of rotation is smaller than the distance between the second end of the lever (9) and the centre of rotation.
8. Gas turbine according to claim 2, wherein the locking pin (7) is configured to move in a straight line.
9. An aircraft, characterized in that it comprises a gas turbine according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120700847.6U CN214616797U (en) | 2021-04-07 | 2021-04-07 | Gas turbine and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120700847.6U CN214616797U (en) | 2021-04-07 | 2021-04-07 | Gas turbine and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214616797U true CN214616797U (en) | 2021-11-05 |
Family
ID=78400083
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120700847.6U Active CN214616797U (en) | 2021-04-07 | 2021-04-07 | Gas turbine and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214616797U (en) |
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2021
- 2021-04-07 CN CN202120700847.6U patent/CN214616797U/en active Active
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