1. In a hinge having a bracket, a shank having an engagement portion adapted to securely engage with a screen of a laptop computer and an extending portion extending from a free end of the engagement portion and through the bracket, a first sleeve securely engaged with the bracket and a second sleeve pivotally engaged with the first sleeve, wherein
the first sleeve has an arcuate step formed on a peripheral edge thereof, a neck extending from an inner periphery of the arcuate step, at least one indentation defined in the arcuate step and a first right angle defined at an intersection between the arcuate step and the peripheral edge; and
the second sleeve has at least one projection formed on a peripheral edge thereof to correspond to and be selectively received in the at least one indentation of the first sleeve so as to provide a positioning effect to the second sleeve when the at least one projection is received in the at least one indentation and a second right angle defined in the peripheral edge of the second sleeve to correspond to the first right angle such that a wall defining the first right angle abutting a wall defining the second right angle is able to prevent excessive pivotal movement of the second sleeve relative to the first sleeve.
2. The hinge as claimed in claim 1, wherein the at least one indentation includes a first indentation defined in the peripheral edge of the first sleeve and a second indentation also defined in the peripheral edge of the first sleeve to be opposite to the first indentation.
3. The hinge as claimed in claim 2, wherein the at least one projection includes a first projection formed on the peripheral edge of the second sleeve and a second projection also formed on the peripheral edge of the second sleeve so that the first projection and the second projection are able to slidably engage with the peripheral edge of the first sleeve and the first projection and the second projection of the second sleeve are able to be selectively received in the first indentation and the second indentation of the first sleeve.
4. The hinge as claimed in claim 3, wherein the first sleeve further has a third indentation defined in a peripheral edge of the arcuate step to be adjacent to the first right angle, the second sleeve further has a third projection adjacent to the second right angle and defined in the peripheral edge of the second sleeve, the third projection having a height the same as a depth of the arcuate step so as to correspond to and be selectively received in the third indentation of the first sleeve.
5. The hinge as claimed in claim 4, wherein the first sleeve has a first arcuate face bridging the first indentation to the peripheral edge of the first sleeve, a second arcuate face bridging the second indentation to the peripheral edge of the first sleeve and a third arcuate face bridging the third indentation to the first right angle, the second sleeve has a first arcuate bridging face bridging the first projection to the peripheral edge of the second sleeve, a second arcuate bridging face bridging the second projection to the peripheral edge of the second sleeve and a third arcuate bridging face bridging the third projection to the peripheral edge of the second projection.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A sealing system for a turbomachine having a flow-restricting wall and at least one series of rotor blades including a plurality of rotor blades, the flow-restricting wall and the at least one series of rotor blades defining an annular space therebetween having a flow direction, the sealing system comprising:
a first seal and a second seal disposed in the annular space between the flow-restricting wall and the at least one series of rotor blades;
wherein the first seal includes
a first sealing fin that is disposed on an end of a rotor blade facing the flow-restricting wall, the rotor blade being from the at least one series of rotor blades, and
a first abradable lining that is disposed on an inside of the flow-restricting wall and is opposite the first sealing fin; and
wherein the second seal is disposed following the first seal in the flow direction and includes
a second abradable lining that is disposed on the end of the rotor blade facing the flow-restricting wall, and
a second sealing fin that is disposed on the inside of the flow-restricting wall and is opposite the second abradable lining.
2. A sealing system in accordance with claim 1, wherein the first sealing fin and the second abradable lining are disposed on a shroud of the rotor blade.
3. A sealing system in accordance with claim 2, wherein the shroud has at least one chamfer in a rearward region in the flow direction.
4. A sealing system in accordance with claim 3, wherein the chamfer is at an angle a in the range between 10\xb0 and 65\xb0 relative to a longitudinal axis of the turbomachine.
5. A sealing system in accordance with claim 4, wherein the chamfer is at an angle a in the range between 20\xb0 and 45\xb0 relative to a longitudinal axis of the turbomachine.
6. Sealing system according to claim 2, characterized in that the first sealing fin is integrated into the shroud.
7. A sealing system in accordance with claim 1, wherein the second abradable lining has at least one chamfer in a rearward region in the flow direction.
8. A sealing system in accordance with claim 7, wherein the chamfer is at an angle a in the range between 10\xb0 and 65\xb0 relative to a longitudinal axis of the turbomachine.
9. A sealing system in accordance with claim 8, wherein the chamfer is at an angle a in the range between 20\xb0 and 45\xb0 relative to a longitudinal axis of the turbomachine.
10. A sealing system in accordance with claim 1, wherein at least one of the first sealing fin or the second sealing fin is tilted opposite the flow direction.
11. A sealing system in accordance with claim 1, wherein the second sealing fin is integrated into the flow-restricting wall.
12. A sealing system in accordance with claim 1, wherein the sealing system is provided in the form of a stepped labyrinth.
13. A gas turbine aircraft engine comprising:
a casing wall;
at least one series of rotor blades including a plurality of rotor blades, the casing wall and the at least one series of rotor blades defining an annular space therebetween having a flow direction;
a first seal disposed in the annular space between the casing wall and the at least one series of rotor blades;
the first seal including a first sealing fin that is disposed on an end of a rotor blade facing the casing wall, the rotor blade being from the at least one series of rotor blades, and
a first abradable lining that is disposed on an inside of the casing wall and is opposite the first sealing fin; and
a second seal disposed in the annular space following the first seal in the flow direction and including
a second abradable lining that is disposed on the end of the rotor blade facing the casing wall, and
a second sealing fin that is disposed on the inside of the casing wall and is opposite the second abradable lining.
14. A gas turbine aircraft engine in accordance with claim 13, wherein the first sealing fin and the second abradable lining are disposed on a shroud of the rotor blade.
15. A gas turbine aircraft engine in accordance with claim 14, wherein the first sealing fin is integrated into the shroud.
16. A gas turbine aircraft engine in accordance with claim 13, wherein at least one of the first sealing fin or the second sealing fin is tilted opposite the flow direction.
17. A gas turbine aircraft engine in accordance with claim 13, wherein the second sealing fin is integrated into the casing wall.