Classifications

• • 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
  • F01D17/00—Regulating or controlling by varying flow
  • F01D17/10—Final actuators
  • F01D17/12—Final actuators arranged in stator parts
  • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
  • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
  • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
• • 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
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
  • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
  • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
• • 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
  • F05D2220/00—Application
  • F05D2220/40—Application in turbochargers

Definitions

• the invention relates to the field of guide devices for turbomachines, in particular for turbines of turbochargers for supercharged internal combustion engines.
• It relates to a support ring of a guide device with adjustable guide vanes, guide devices with such a support ring, as well as flow machines with such guide devices with such a support ring.
• Exhaust gas turbochargers are used to increase the performance of internal combustion engines (reciprocating engines).
• An exhaust gas turbocharger consists of an exhaust gas turbine in the exhaust gas stream of the internal combustion engine and a compressor in the intake tract of the internal combustion engine.
• the turbine wheel of the exhaust gas turbine is set in rotation by the exhaust gas flow of the internal combustion engine and drives the impeller of the compressor via a shaft.
• the compressor increases the pressure in the intake tract of the internal combustion engine, so that when sucking a larger amount of air enters the combustion chambers.
• Exhaust gas turbines are also used as power turbines. In this case, they do not drive the compressor of an exhaust gas turbocharger via the shaft, but rather a generator or via a clutch another mechanical useful part.
• turbochargers with turbine and compressor components with fixed geometries have been used predominantly for large engines (fixed geometries). These geometries are for each individual motor designed and adapted. During the operation of the engine but they were unchanging.
• adjustable turbine geometries TMG that are adjustable in operation is increasingly being discussed. In this case, the opening of the guide vanes of the guide device of the exhaust gas turbine is varied by a rotation of the guide vanes.
• variable turbine geometries are well known in the art and particularly in the field of small engines, such as those used in passenger cars.
• variable turbine geometries are already being used today for gas engines which require precise regulation of the fuel / air ratio.
• widespread use of variable turbine geometries in large engines is to be expected.
• the guide In order to prevent the exhaust gases of the internal combustion engine in the bearing points of the guide vanes of the guide in exhaust gas turbochargers with variable turbine geometry and to exclude the leakage of exhaust gases into the environment, the guide must be supplied with air purge.
• the sealing air is guided in an inside of the cross-sectional profile of the bearing housing ring - hereinafter referred to as a support ring - the guide device arranged annular channel.
• a support ring - the guide device arranged annular channel.
• the cross section of the sealing air duct is relatively small due to the limited space inside the profile of the support ring. In order to achieve a uniform supply of sealing air, the air must therefore be supplied in several places. For this purpose, other special pipes are needed outside the guide.
• the object of the invention is to provide a cost-effective to manufacture support ring of a guide device of a turbomachine.
• this is achieved with a support ring, wherein the barrier air channel for preventing the ingress of gases from the flow channel into the bearing points of the guide vanes of the guide device as an outward opening and extending in the circumferential direction groove or channel is formed.
• the groove is embedded in an axial end face of the carrier ring.
• the groove is embedded in a radially outer side or inner side of the shell. If the barrier air duct designed as an open channel in the support ring, the support ring can thereby be poured without a core for the sealing air duct.
• the embedded in an axial end face or a shell side of the carrier ring sealing air channel is sealed according to the invention on its open side by the gas outlet housing and / or another housing part, such as the cover.
• the sealing air channel of the carrier ring formed according to the invention can have such a large cross-section that the entire sealing air can be supplied only at one point along the circumference. This makes it possible to save the distribution pipes and requires a smaller number of mechanical processing of the support ring.
• FIG. 1 shows an overall view of an exhaust gas turbocharger according to the prior art
• Fig. 3 shows a section through an exhaust gas turbine with an adjustable, axially flowed guide device with an inventively designed
• FIG. 4 is a view in the axial direction of a carrier ring according to the invention according to FIG. 3,
• FIG. 5 shows a guided along VV section through the support ring of FIG. 4
• Fig. 6 shows a section through a carrier ring according to the invention formed a radially flowed guide device.
• Fig. 1 shows a conventional exhaust gas turbocharger with exhaust gas turbine 20 and compressor 10, and disposed therebetween bearing housing 50.
• the exhaust gas turbine 20 includes a gas inlet housing 21, through which the hot exhaust gas flows to the turbine wheel and this drives before the exhaust gas through the gas outlet housing 22 of the exhaust system is supplied.
• the turbine wheel is arranged at one end of a shaft rotatable about the axis A, which is rotatably mounted in the bearing housing 50.
• the compressor wheel At the other end of the shaft is the compressor wheel, which compresses air drawn in through the air inlet housing 11, which air is subsequently collected in the air outlet housing 21 and fed to the combustion chambers of the internal combustion engine.
• the turbine is an axial flowed axial turbine.
• the exhaust gas could be directed onto the turbine wheel in a direction which is strictly radial or slightly inclined to the radial direction, in which case a radial or mixed-flow turbine is used.
• Fig. 2 shows a section of an axial turbine of a conventional exhaust gas turbocharger.
• the turbine wheel 25 is arranged on the shaft 30 which is rotatable about the axis A in the bearing housing 50.
• the turbine wheel 25 includes a plurality of blades 26, which are distributed along the circumference of the radially outer edge of the turbine wheel.
• the exhaust gas flow in the flow channel from the gas inlet housing 21 to the gas outlet housing 22 is indicated in the figures in each case by arrows.
• the blades of the turbine wheel are flowed in the axial direction.
• an adjustable guide upstream of the rotor blades 26 of the exhaust turbine, an adjustable guide (adjustable turbine geometry) is arranged.
• This adjustable guide device comprises a plurality of guide vanes 41, which each have a shaft 42.
• Each of the guide vanes 41 is mounted in each case with its shaft 42 about the axis B rotatably in the housing.
• the housing of the guide device comprises a support ring 40, which encloses the flow channel in an annular manner. Towards the flow channel, the support ring 40 can still enclose a cover ring 45.
• the shafts 42 of the guide vanes 41 are arranged in the support ring 40 in holes provided and stored. These bearings run, as the shafts 42 of the vanes 41, substantially in the radial direction.
• the support ring 40 is usually fastened with fastening means on the gas outlet housing 22 and / or on the gas inlet housing 21. As fasteners bolts, screws or tabs are used.
• the adjustable guide device further comprises an adjusting ring 43 and per guide vane an adjusting lever 44, which are guided through openings 49 in the support ring to the shaft 42.
• the adjustment levers 44 transmit the rotational movement to the shafts 42 of the vanes.
• a barrier air channel 46 is arranged in the support ring 40. The sealing air is fed at one or more points in the annular inside the profile carrier ring 40 extending sealing air channel 46 and flows through the openings for the shafts of the vanes in the flow channel.
• the openings 48 for receiving and supporting the shafts 42 of the guide vanes 41 are in turn supplied via a sealing air channel 46 with sealing air in the case of the axially flow-through guide device with the carrier ring according to FIG.
• the sealing air channel 46 is sealed with sealing elements 47, so that no blocking air can escape in this direction along the shank of the guide vanes.
• the sealing air channel 46 is designed as a groove let into the axial end face of the carrier ring 40, as can also be seen from the schematic representations of the axially flow-through guide device according to FIGS. 4 and 5.
• the sealing air channel 46 When installed, the sealing air channel 46 is bounded by the adjacent to the axial end face housing part 22. Thus arises for as a groove in the
• Housing side be admitted in the axial direction opening groove 23.
• the sealing air channel is composed of the carrier ring-side sealing air channel 46 and the housing-side groove 23.
• the contact surfaces between the carrier ring and the adjacent housing parts may be flat, inclined or stepped in the region of the sealing air channel.
• the groove 23 widening the sealing air channel can extend on the side of the housing into the region of the cover ring 45. As a result, the cross section can be further enlarged.
• the sealing air channel can be sealed by sealing elements 47 arranged radially inside and / or outside the sealing air channel. This makes it possible to prevent the sealing air fed into the barrier air channel 46 with excess pressure from escaping through the connection between the gas outlet housing 22 and the carrier ring 40.
• the groove which forms the sealing air channel 46 can also be embedded on the end face of the carrier ring 40 facing the gas inlet housing 21.
• the grooves forming the sealing air channel in the carrier ring and / or in the adjacent housing may be formed as annular groove segments, that is to say they may be divided along the circumference into a plurality of sections. Each barrier air duct segment can be supplied individually with external air from the outside.
• Fig. 6 shows a section through the support ring of a radially flowed guide device, such as those used in radial or mixed flow turbines.
• the sealing air channel 46 is formed according to the invention by a radially outwardly or radially inwardly opening groove in the support ring.
• Barrier air duct 46 forming groove is thus embedded in a lateral surface of the carrier ring 40.
• the limitation of the groove to the annular cavity is effected by an adjacent housing part, in the case of an exhaust gas turbine, this would be about
• Gas inlet housing 21 Again, a circumferential groove 23 can be inserted to expand the sealing air channel 46 in the adjacent housing part.
• FIG. 4 the adjusting lever for adjusting the guide vanes is not shown.
• the embodiments described in detail show the guide device with the carrier ring according to the invention designed as an adjustable guide device of an exhaust gas turbine.
• all features should also apply to the general application in any turbomachine, in particular a compressor, validity. LIST OF REFERENCE NUMBERS

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Supercharger (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Control Of Turbines (AREA)

Priority Applications (3)

Applications Claiming Priority (2)

Publications (1)

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Citations (3)

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• 2008
  • 2008-04-23 EP EP20080154983 patent/EP2112332B1/de active Active
• 2009
  • 2009-04-23 KR KR1020107022843A patent/KR101244956B1/ko active IP Right Grant
  • 2009-04-23 CN CN200980115076.6A patent/CN102016237B/zh active Active
  • 2009-04-23 JP JP2011505504A patent/JP5021846B2/ja active Active
  • 2009-04-23 WO PCT/EP2009/054857 patent/WO2009130262A1/de active Application Filing

Patent Citations (3)

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