METHOD AND DEVICE FOR CHANGING A GASKET IN AN AIRCRAFT ENGINE

• US 20140130352A1
• Filed: 01/24/2012
• Published: 05/15/2014
• Est. Priority Date: 01/28/2011
• Status: Active Grant

• Current Assignee: Lufthansa Technik AG (Deutsche Lufthansa AG)
• Original Assignee: Lufthansa Technik AG (Deutsche Lufthansa AG)
• Inventors: Buldtmann, Markus, Hinz, Alexander, Roppelt, Eugen, Fitter, Jens
• Granted Patent: US 9,409,266 B2
• Time in Patent Office: Days
• US Class Current: 29/888.3
• CPC Class Codes: B23P 19/042 specially adapted for combustion engines shape of casings adapted to facilitate fitting or dismantling of engine parts for combustion engines F02F7/0046
• CPC Class Codes: B23P 6/002 Repairing turbine components, e.g. moving or stationary blades, rotors, B23P6/045 takes precedence
• CPC Class Codes: F01D 25/285 Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2230/70 Disassembly methods
• CPC Class Codes: F05D 2230/80 Repairing, retrofitting or upgrading methods
• CPC Class Codes: F05D 2240/50 Bearings
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: Y10T 29/49297 Seal or packing making
• CPC Class Codes: Y10T 29/49318 Repairing or disassembling
• CPC Class Codes: Y10T 29/49721 with disassembling
• CPC Class Codes: Y10T 29/4973 Replacing of defective part
• CPC Class Codes: Y10T 29/49822 by applying force
• CPC Class Codes: Y10T 29/53 Means to assemble or disassemble

Abstract

Method for removing a front seal plate (11) from an aircraft engine (1), the method comprising at least the following steps:

• • a) separating a part engine unit (5) from the aircraft engine (1), the part engine unit (5) comprising the core engine (6) and the low-pressure turbine (7) of the aircraft engine (1),
  • b) removing a front seal plate nut (10) from the part engine unit (5),
  • c) removing the front seal plate (11) from the part engine unit (5).

Claims

1. A method for removing a front seal plate from an aircraft engine, comprising at least the following steps:

a) separating a part engine unit from an aircraft engine, the part engine unit comprising a core engine and a low-pressure turbine of the aircraft engine,

b) removing a front seal plate nut from the part engine unit,

c) removing the front seal plate from the part engine unit.

3. The method according to claim 1, further comprising removing a bearing unit.

4. The method according to claim 3, wherein the bearing unit comprises a roller bearing for a high-pressure shaft.

5. The method according to claim 3, wherein the bearing unit is pushed onto a shaft to be mounted by a force application element.

9. The method according to claim 1, further comprising fitting the front seal plate or a second front seal plate into the aircraft engine, wherein fitting the front seal plate or the second front seal plate into the aircraft engine comprises:

d) fitting the front seal plate or the second front seal plate into the part engine unit of the aircraft engine,

e) fitting the front seal plate nut or a second front seal plate nut into the part engine unit

f) attaching the part engine unit to the aircraft engine.

11. The method according to claim 5, wherein the force application element is supported on a thread of the front seal plate nut.

12. The method according to claim 11, wherein the force application element is supported via a lengthening arrangement on a thread of the front seal plate nut, wherein the lengthening arrangement is supported on the thread of the front seal plate nut.

13. The method according to claim 3, further comprising:

fitting the bearing unit or a second bearing unit; and

fitting the front seal plate or a second front seal plate into the aircraft engine, wherein fitting the front seal plate or the second front seal plate into the aircraft engine comprises;

d) fitting the front seal plate or the second front seal plate into the part engine unit of the aircraft engine,

e) fitting the front seal plate nut or a second front seal plate nut into the part engine unit,

f) attaching the part engine unit to the aircraft engine.

2. A method for fitting a front seal plate into an aircraft engine, comprising at least the following steps:

d) fitting the front seal plate into the part engine unit of an aircraft engine, the part engine unit comprising the core engine and the low-pressure turbine of the aircraft engine,

e) fitting a front seal plate nut into the part engine unit,

f) attaching the part engine unit to the aircraft engine.

6. A method for removing a front seal plate from an aircraft engine, comprising at least the following steps:

g) removing the engine fan,

h) removing a coupling,

i) removing a support element,

j) removing a front seal plate nut,

k) removing the front seal plate.

8. The method according to claim 6, wherein the aircraft engine is mounted on the wing of an aircraft during the method.

14. The method according to claim 6, further comprising fitting the front seal plate or a second front seal plate into the aircraft engine, wherein fitting the front seal plate or the second front seal plate into the aircraft engine comprises:

l) fitting the front seal plate or the second front seal plate,

m) fitting the front seal plate nut or a second front seal plate nut,

n) fitting the support element,

o) fitting the coupling,

p) fitting the engine fan.

15. The method according to claim 6, further comprising removing a bearing unit.

16. The method according to claim 15, further comprising:

fitting the bearing unit or a second bearing unit; and

fitting the front seal plate or a second front seal plate into the aircraft engine, wherein fitting the front seal plate or the second front seal plate into the aircraft engine comprises;

l) fitting the front seal plate or the second front seal plate,

m) fitting the front seal plate nut or a second front seal plate nut,

n) fitting the support element,

o) fitting the coupling,

p) fitting the engine fan.

17. The method according to claim 15, wherein the aircraft engine is mounted on the wing of an aircraft during the method.

18. The method according to claim 16, wherein the aircraft engine is mounted on the wing of an aircraft during the method.

7. A method for fitting a front seal plate into an aircraft engine, comprising at least the following steps:

l) fitting the front seal plate,

m) fitting a front seal plate nut,

n) fitting a support element,

o) fitting a coupling,

p) fitting the engine fan.

10. A device for removing and/or fitting a front seal plate and/or a bearing unit in an aircraft engine, wherein the device is configured to:

a) separate a part engine unit from an aircraft engine, the part engine unit comprising a core engine and a low-pressure turbine of the aircraft engine,

b) remove a front seal plate nut from the part engine unit,

c) remove the front seal plate from the part engine unit.

19. The device according to claim 10, wherein the device is configured to:

d) fit the front seal plate or the second front seal plate into the part engine unit of the aircraft engine,

e) fit the front seal plate nut or a second front seal plate nut into the part engine unit,

f) attach the part engine unit to the aircraft engine.

20. The device according to claim 10, wherein the device is configured to remove a bearing unit.