Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
  • B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
  • B23P19/04—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
  • B23P19/042—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts specially adapted for combustion engines
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
  • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
  • B23P6/00—Restoring or reconditioning objects
  • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
  • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2230/00—Manufacture
  • F05D2230/60—Assembly methods
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2230/00—Manufacture
  • F05D2230/70—Disassembly methods
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2230/00—Manufacture
  • F05D2230/80—Repairing, retrofitting or upgrading methods
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/50—Bearings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/55—Seals
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49229—Prime mover or fluid pump making
  • Y10T29/49297—Seal or packing making
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49316—Impeller making
  • Y10T29/49318—Repairing or disassembling
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49718—Repairing
  • Y10T29/49721—Repairing with disassembling
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49718—Repairing
  • Y10T29/49721—Repairing with disassembling
  • Y10T29/4973—Replacing of defective part
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49815—Disassembling
  • Y10T29/49822—Disassembling by applying force
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/53—Means to assemble or disassemble

Definitions

• the invention relates to a method for changing a sealing plate and / or a bearing unit in an aircraft engine having the features of the preamble of claims 1, 2, 6, 7 and 9 and a corresponding device having the features of claim 10.
• Aircraft engines are subject in use a number of external influences that can lead to wear of components.
• Such wear may, for example, relate to the sealing plate, the so-called “front seal plate", which is provided in an aircraft engine for sealing a bearing unit, inter alia usually two or three waves are used.
• An example of a twin-shaft engine is the Pratt & Whitney 4000 engine model (PW4000).
• An inner Nl (low pressure) shaft serves to transmit power from the low-pressure turbine to the low-pressure compressor
• a second N2 (high-pressure) shaft coaxially surrounding the N1 shaft transmits the power from the high-pressure turbine to the high-pressure compressor.
• the N2 shaft is mounted at its front, the low-pressure compressor associated end via a bearing unit in the engine housing. If this bearing unit and / or the sealing plate arranged close to the bearing unit /, for example,
• the core engine 6, the “core engine”, is removed from the engine, and the core engine 6 also includes the bearing unit 2 to be replaced and the seal plate 12.
• the core engine 6 further includes the high-pressure compressor 30, the combustion chamber 31 and the high-pressure turbine as a rule 29th
• the sealing plate At the dismounted core engine 6, after dismantling further components, such as the sealing plate nut, the sealing plate to be repaired or to be replaced and the bearing unit 2 can be unscrewed or removed from the N2 shaft 4. After the repair or replacement of the building Parts are pressed or screwed onto the N2 shaft 4 again and the aircraft engine 1 is reassembled by an assembly process, which essentially corresponds to the reverse disassembly process.
• This known method is very complicated and expensive, in particular special because the engine must be removed to a high degree to replace the bearing unit and / or the sealing plate. In particular, it is not possible to replace a sealing plate on an on-wing engine still hanging on the aircraft wing.
• the invention has for its object to provide a method for changing a storage unit in an aircraft engine, in which the exchange of Lagerein unit with reduced effort is possible.
• the invention proposes a method for removing a sealing plate from an aircraft engine, comprising at least the following steps: a) disconnecting a sub-engine unit from the aircraft engine, wherein the sub-engine unit comprises the core engine and the low-pressure turbine of the aircraft engine
• a corresponding installation is furthermore proposed, ie a method for installing a sealing plate in an aircraft engine, wherein the method comprises at least the following steps: d) installation of the sealing plate in the sub-engine unit of an aircraft engine, wherein the sub-engine unit drives the nuclear engine and the low-pressure turbine of Aircraft engine includes
• a storage unit is removed or installed.
• Storage units must be repaired or renewed as described above, for example for reasons of wear. Initial tests have shown that the time saved by a change of the sealing plate and bearing unit according to the invention is about 290 employee hours, which is increasingly cost of materials resulted in a significant cost reduction.
• the bearing unit preferably comprises a ball bearing for a high-pressure shaft.
• the bearing unit preferably comprises a bevel gear.
• the ball bearing can be mounted on the bevel gear, which in turn sits on a shaft. This storage unit can be replaced by the inventive method with relatively little effort.
• the bearing unit is preferably pressed onto the shaft to be supported by a force application element, the force application element being supported on the thread of the seal plate nut directly or via an extension device.
• the force application element may be, for example, a hydraulic cylinder.
• the force application element transmits the generated force to the bearing unit via a push-on sleeve. It is advantageous if the force application element can be supported on the same shaft to which the bearing unit is pressed, for example, the N2 shaft. In a bearing change of the PW4000 according to the prior art, this can be done, for example, that a lock, a so-called.
• a corresponding installation is also proposed, that is to say a method for installing a sealing plate in an aircraft engine, the method comprising at least the following steps:
• the advantage of the methods g) to k) or 1) to p) is that the aircraft engine does not have to be dismantled from the wing of the aircraft in order to install or remove the sealing plate.
• the aircraft engine during the process is accordingly mounted on the wing of an aircraft. Due to such an "on-wing" change of the sealing plate, the required effort to repair or change a gasket plate can be significantly reduced. It not only saves the high transport costs of the engine to the workshop, but the engine is also much faster ready for use and thus more economical.
• One or more of the described methods may possibly also be used in stationary gas turbines.
• Fig. 1 Schematic representation of the structure of an aircraft engine
• Fig. 2 representation of the mounting state of an aircraft engine before the change of the sealing plate
• Fig. 3 cross section through the Nl and N2 shaft when loosening
• Fig. 4 cross section through the Nl and N2 shaft when loosening
• Fig. 5 Cross section through the Nl and N2 shaft when pressing a bearing unit on the N2 shaft.
• FIG. 1 shows a schematic representation of an aircraft engine 1. It is a twin-shaft engine, with the Nl shaft 3 coaxially surrounded by the N2 shaft 4.
• the NI shaft 3 transmits a rotational moment from the low-pressure turbine 7 to the engine fan 8, which is part of the low-pressure compressor.
• the N2 shaft 4 transmits Rotation torque from the high pressure turbine 29 to the high pressure compressor 30 and is mounted on its side associated with the low pressure compressor via a bearing unit 2 in the engine housing.
• a combustion chamber 31 is arranged, all three engine sections are part of a unit referred to as the core engine 6.
• the low-pressure turbine 7 forms, together with the core engine 6, the "core engine", a superordinate structural unit designated as a partial engine unit 5, which is also referred to as the "split engine".
• the coupling element 13 is the connection coupling between low-pressure compressor and low-pressure turbine
• the two support elements 9 in the PW4000 engine are referred to as "1.0 bearing support” and "1.5 bearing support”.
• FIG. 2 likewise shows an aircraft engine 1, in which FIG. 2, in addition to the bearing unit 2, also other components are shown, which are arranged on the N 2 shaft 4 next to the bearing unit 2.
• the bearing nut 12 is arranged to fix the bearing unit 2 in position on the N 2 shaft 4.
• the sealing plate 11 is arranged, which is fixed by a sealing plate nut 10 on the N2 shaft 4.
• FIG. 2 shows two assembly states of the aircraft engine 1, each of which shows an intermediate step of the method according to the invention. Above the dividing ne 15 the condition of the engine is clarified when it still hangs on the wing of an aircraft "on-wing.” According to the invention, one arrives at this state starting from an aircraft-mounted engine, in which, in a first step, the engine fan 8, the “fan module” is removed from the aircraft engine 1 and then in two more
• Steps the coupling element 13 and one or more support elements 9 are removed.
• the assembly state which is shown below the dividing plane 15, is achieved by separating the engine unit 5 from the rest of the engine, in which case the oil shaft 3 protrudes from the high-pressure compressor 30, since it remains in the engine unit 5 .
• the next step in both of the methods of the invention is to release the seal plate nut 10. This step is shown in FIG.
• FIG. 3 shows a cross section through the N1 and N2 shafts (3, 4) when the sealing plate nut 10 is loosened, a cross-sectional view and an outside view being combined in FIG. 3 and in FIGS. 4 and 5 described below.
• the N2 shaft 4 can be seen, on which the bearing unit 2, the bearing nut 12 and the seal plate 11 and the seal plate nut 10 sit.
• the N2 shaft 4 surrounds the Nl shaft 3, which protrudes from the N2 shaft 4.
• a spacer ring 17 is arranged, which remains during the removal and installation of the seal plate 11 and possibly the bearing unit 2 between the waves.
• the Nl wave lock the. on the low-pressure turbine side of the Nl shaft 3 for fixing the Nl shaft third can be provided.
• a sleeve-like N2 shaft extension 18 is placed, and about this N2 shaft extension 18 a Dichtungsplattenmutterverinrung 19.
• N2 shaft extension 18 By N2 shaft extension 18, the Nl shaft 4 is shielded and avoided so that when removing components, the Nl shaft 3 can be damaged ,
• the gasket plate nut extension 19 is radially fixed in position. Via a torque wrench 20, a rotational torque is transmitted to the Dichtungsplattenmutterverinrung 19, which in turn transmits the rotational moment on the sealing plate nut 10, whereby the sealing plate nut 10 can be unscrewed. Subsequently, the sealing plate 11 is removed, so that on the thread 21 (see Figure 4) no more components are available. The sealing plate 11 can now be repaired or replaced by a new sealing plate 11.
• FIGS. 4 and 5 show how, in addition to a replacement or repair of the sealing plate 11, the bearing unit 2 can also be repaired or replaced.
• FIG. A bearing nut extension 22 a torque is transmitted from a torque wrench 20 for releasing the bearing nut 12, so that the bearing nut . 12 can be unscrewed.
• the bearing unit 2 can be removed from the N2 shaft 4 become.
• This can be done for example by a stripping, in which, for example, a hydraulic cylinder provides a tensile force with which the bearing unit 2 can be deducted from the N2 shaft 4.
• this device engages behind the bevel gear 28, which is part of the bearing unit 2, and pulls with the bevel gear 28 and the bearing, which is designed here as a ball bearing 27, with from.
• FIG. 5 shows how a new or repaired bearing unit 2 is pressed onto the N 2 shaft 4.
• connection sleeve 25 is provided, which here is part of the extension device 24, and via which the force application element 23 can be supported on the thread 21 (cf., FIG. 4) of the seal plate nut 10.
• the connection sleeve 25 is part of the extension device 24, and via which the force application element 23 can be supported on the thread 21 (cf., FIG. 4) of the seal plate nut 10.
• the connecting sleeve 25 has two internal threads, wherein the first internal thread 14 is provided for screwing onto the thread 21 of the sealing plate nut 10 and the second provided for connection to the extension device 24 Subsequent to the repair or change of the storage unit 2, the aircraft engine 1 is reassembled, essentially the assembly is preferably carried out in the reverse order as the disassembly.
• the inventive method and its variations can save a lot of time and money, in particular by less work and less material costs, and in addition completely new possibilities, such as an "on-wing" change the sealing plate 11 is opened, so that sometimes not even a reserve engine in the exchange of a sealing plate 11 must be provided.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Mounting Of Bearings Or Others (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (1)

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• 2011
  • 2011-01-28 DE DE102011009770.8A patent/DE102011009770B4/de not_active Expired - Fee Related
• 2012
  • 2012-01-24 KR KR1020137020750A patent/KR101528585B1/ko not_active Expired - Fee Related
  • 2012-01-24 WO PCT/EP2012/000297 patent/WO2012100933A1/de not_active Ceased
  • 2012-01-24 CN CN201280006555.6A patent/CN103328773B/zh not_active Expired - Fee Related
  • 2012-01-24 US US13/982,445 patent/US9409266B2/en active Active
  • 2012-01-24 EP EP12708657.7A patent/EP2668373A1/de not_active Withdrawn

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